CH680395A5 - Absolute measurement of earth movement - using vectorial addition of measured velocity vectors for movement of earth, sun and galaxy - Google Patents

Abstract

The absolute measurement of the earth's movement uses vectorial addition of the velocity rectors for the earth's spin, the rotation of the earth about the sun and the rotation of the sun about the centre of the galaxy and the movement of the galaxy in space. A defined equation is used expressed in terms of the actual propagation time of electromagnetic waves between a transmitter and a spaced receiver, the angle between the transmission path and the direction of the absolute movement of the earth, the scaler size of the velocity vector for the absolute movement and the propagation velocity of the electromagnetic waves. The actual propagation times for 2 opposing transmission paths of equal length are compared. ADVANTAGE - High percentage accuracy.

Description

       

  
 



  The invention relates to a device for performing a method for measuring the size and direction of the resulting from the vectorial addition of the speed vectors of the rotation of the earth around the earth's axis, the orbit of the earth around the sun, the orbit of the sun around the center of our Milky Way system forming galaxy and the motion vector of our galaxy in space, the velocity vector of the absolute movement of the earth in space.



  Contrary to the previous assumption that the speed of the absolute movement of the earth in space is not measurable, theoretical studies of the Doppler effect with electromagnetic waves necessarily lead to the conclusion that the speed of the absolute movement of the earth in space must be measurable.

  This conclusion ultimately results from the irrefutable fact that electromagnetic waves propagate in a vacuum around the location of their origin spherically or more specifically spherically in the form of a propagation velocity c of electromagnetic waves, and that the origin of the electromagnetic waves for a moving transmitter of electromagnetic waves progresses over time shifted in the direction of movement of the transmitter, so that the spherical shells of different diameters representing the temporally successive waves are pressed together in the direction of movement of the transmitter and pulled apart in the opposite direction in the manner characteristic of the Doppler effect from the transmitter or from the center of the innermost spherical shell.



  This effect of compressing the spherical jackets or the waves represented by them in the direction of movement of the transmitter and pulling them apart in the opposite direction, as well as the wavelength reduction or frequency increase resulting from the compression and the resulting wavelength increase or frequency reduction resulting from the pulling apart radiated waves must occur in a moving transmitter because of the previously discussed shift of the origin of the waves in the direction of movement of the transmitter, i.e. also within one and the same moving inertial system with the transmitter stationed in the same and only moving with it and not only in relation to the inertial system provided with the transmitter moved other inertial systems.



  In practice, this means that the Doppler effect of electromagnetic waves must also occur within a moving inertial system with a fixed transmitter, which is, however, contrary to the experience that such a Doppler effect cannot be measured within a moving inertial system with a fixed transmitter or more correctly, it doesn't seem measurable. However, this apparent contradiction is relatively easy to clarify:



  The transmitter moves along with the inertial system in which it is stationed, while emitting a full sine wave from its position at the initial zero crossing of the sine wave on a straight line on which it moves together with the inertial system by a distance v. To forward, which corresponds to the product of the speed of movement v of the inertial system in the direction of the straight line and the oscillation period To = 1 / fo of the sine wave, which is inversely proportional to the transmission frequency fo. During the same time, the sine wave emitted by the transmitter moves forward at the propagation speed c of electromagnetic waves on the straight line, so that the initial zero crossing of the emitted sine wave after the period of oscillation To ends by the distance c. To moved forward on the straight.

  After the oscillation period To, the distance between the transmitter and the initial zero crossing of the radiated sine wave under consideration is the same (cTo - vTo), and because after the oscillation period To, beginning with an initial zero crossing, the transmitter begins to emit the next sine wave , the distance between the initial zero crossings of two successive radiated sine waves corresponding to the wavelength lambda is thus the same
 
EMI3.1
 and thus the frequency f of the sine wave emitted by the transmitter in the direction of movement is the same
 
EMI3.2
  so by the factor
EMI3.3
  higher than the transmitter frequency fo. This initially proves that the Doppler effect also occurs with a moving transmitter if the transmitter is stationed in an inertial system and only the inertial system moves together with the transmitter.



  The apparent contradiction is that, on the one hand, the Doppler effect actually occurs with the electromagnetic waves emitted by a transmitter stationed in a moving inertial system, as previously demonstrated, but on the other hand it is not measurable within this moving inertial system (or more precisely, it cannot be measured) appears to be), is explained in principle by the fact that the Doppler effect on a receiver that is stationed in the moving inertial system is completely eliminated.

  This is because a receiver located on the aforementioned straight line at a fixed distance from the transmitter in front of the same, which, like the transmitter, is stationed in the moving inertial system and moves together with the moving inertial system in the direction of the straight line, moves from the time of arrival the initial zero crossing of the above-mentioned sine wave emitted by the transmitter during reception of the full sine wave by the distance v. To forwards and runs away from the end of the incoming sine wave, so to speak, so that the wavelength lambda e of the received sine wave deviates from the wavelength ambda = cTo - vTo of the sine waves to be moved towards the receiver by v.

  To to lambda e = lambda + vTo = (cTo - vTo) + vTo = cTo increased and thus the frequency fe of the received sine wave again the same
 
EMI4.1
 is equal to the transmitter frequency fo.



   The whole thing can be explained very simply using the example of a moving locomotive with a steam whistle on the driver's cab and a first observer standing on the rails at a greater distance in front of the locomotive and a second observer sitting on the chimney of the locomotive: the first observer hears the frequency the whistle of the steam whistle increased frequency of the wave emitted by the steam whistle in the direction of travel of the locomotive because it does not run away from the incoming waves.

  The second observer gets exactly the same wave with its increased frequency, but since the second observer sits on the locomotive and therefore runs away from the incoming waves at the locomotive's speed, so to speak, the wavelength of the waves picked up by the second observer's ear is extended, the second observer hears not the increased frequency, but the frequency of the whistle of the steam pipe. The same effect would also occur for the first observer if he instead ran along the rails at the same speed as that of the locomotive.



  But while one could start with sound waves from the idea that the Doppler effect there would be caused by the "headwind" of the moving transmitter compared to the standing air forming the transmission medium for the sound waves, a corresponding idea with electromagnetic waves comes up with a kind of " Ether wind "as the cause of the Doppler effect of electromagnetic waves because of mental difficulties, because the actual transmission medium of electromagnetic waves is the absolute vacuum and an absolute vacuum is generally regarded as an absolute nothing, which has all properties and, of course, a function as one Excludes kind of "ether wind" from the outset.

  However, the question of the existence of a "material ether", which was much discussed in the context of the turn of the century and finally answered in a negative sense, was not precise enough, because if one considers the term "material" by the more precise term "for the transfer" in this question and storage of electromagnetic energy having suitable properties ", this question should of course have been answered in the affirmative, because the vacuum forming the" ether "has the two properties of a dielectric constant proportional to the absolute dielectric constant epsilon o and one of the absolute permeability constant mu o proportional permeability and thus has the two properties necessary for the transmission and storage of electromagnetic energy, as well as gases such as

  Air and all other liquid and solid substances (hence the term "material ether") have the properties necessary for the transmission and storage of sound energy.



  Nevertheless, the results of the Michelson experiment seemed to support the representatives of the theory of the absence of a "material ether", because with the astronomical knowledge available around the turn of the century, i.e. without knowledge of the Hubble effect of the red shift of the spectrum of distant galaxies, which was only discovered in 1929 , the results of the Michelson experiment seemed to be interpretable only in the sense of the absence of a "material ether" and the ultimately resulting impossibility of measuring the speed of the absolute movement of the earth in space, but as follows in the context of an explanation of the theoretical basis of the present Measurement method will still be shown, with today's knowledge,

   in particular with the evidence provided by the Hubble effect of the occurrence of the Doppler effect even in the case of electromagnetic waves, the results of the Michelson experiment that could only be explained at the time only by replacing the Galilei transformation with the Torentz transformation, even without the introduction of the Lorentz transformation, so that the conclusion drawn at the time from the results of the Michelson experiment of an impossibility of measuring the speed of the absolute movement of the earth in space, looking back, lacked the necessary basis.



  Strictly speaking, this conclusion was already lacking the necessary basis around the turn of the century, because the fact that the Doppler effect also occurs with electromagnetic waves was not only finally proven in 1929 by the discovery of the Hubble effect, but Doppler himself had it in the middle of the previous one Century by observing double star systems revolving around a common center of gravity based on the color differences between the light of the star moving towards us and the light of the star moving away from us, the occurrence of the Doppler effect was also demonstrated in light and thus according to Maxwell in electromagnetic waves,

   only this knowledge had been lost around the turn of the century due to the ignorance of school science, which at the time denied the Doppler effect, and therefore had not been taken into account when interpreting the results of the Michelson experiment, which then resulted in the unnecessary introduction of the Lorentz transformation the results of the Michelson experiment could not be explained without taking into account the (already proven) Doppler effect of electromagnetic waves based on the Galilei transformation.



  The invention was based on the object, using the Doppler effect which also occurs within a moving inertial system with a fixed transmitter, to create a device of the type mentioned at the beginning with which the speed of the absolute movement of the earth in space is at least of the order of magnitude accuracy can be determined by percentages.



  According to the invention, this is achieved in a device of the type mentioned at the outset in that means are provided to measure the speed vector of the absolute movement of the earth in space by measuring a quantity dependent on a real propagation time of electromagnetic waves in at least three spatial directions and which do not fall in the same spatial plane mathematical determination of the scalar size and direction of the speed vector of the absolute earth movement from the measured values and to determine this determination using the relationship
 
EMI7.1
 between the real transit time tL of electromagnetic waves over a transmission path from a transmitter of electromagnetic waves to a receiver of electromagnetic waves located at a distance from the transmitter, the angle alpha between the transmission path and the direction of the absolute movement of the earth,

   the scalar quantity v of the velocity vector of the absolute earth movement and the propagation velocity c of electromagnetic waves takes place, the quantity dependent on the real transit time belonging to a group that includes the real transit time tL itself and the difference
EMI7.2
  between the real transit time tL and the fictitious transit time resulting from the determination of the transit time by phase shift measurement
EMI7.3
 as well as the difference
 
EMI7.4
 between real terms
 
EMI7.5
 on two oppositely directed transmission links of the same length a,

   and that for measuring a real transit time tL the time between the emission of the wave front of an electromagnetic wave from the transmitter and the arrival of this wave front at the receiver and for measuring a transit time difference DELTA t between two real transit times
EMI7.6
  the time difference between the arrival times of the wave fronts of an electromagnetic wave emitted by a transmitter is determined at the receivers arranged at the ends of two equally long, oppositely directed transmission links.



  The decisive advantage of the present device is the direct measurement of the times determining the measurement result, because in contrast to this, in all other relevant methods, in particular in the interferometric measuring method according to Michelson, but also in measuring methods in radio-based range finders such as the so-called one-way range finders ( e.g.

  Global Positioning System), which should also be suitable for speed measurement in the case of a known measuring section, not the time, but a phase shift measured directly and then indirectly the desired variable from the measured phase shift, i.e. the sought movement speed v in the Michelson method and in the case of radio-based range finders the desired measuring section or

   If the measuring path is known, the running tent sought is determined, and since the phase shift of a wave compared to a comparison wave can only be measured when a number of waves corresponding to the transit time from the transmitter to the receiver has arrived in the receiver, and - as already briefly explained at the beginning - the when transmitting from a stationary transmitter to a stationary receiver in a moving inertial system, the Doppler effect in the receiver during the period of arrival of a wave as a result of the movement of the receiver (which takes place together with the moving inertial system) in this period of time is completely canceled out and thus also the frequency change caused by the Doppler effect and dependent on the movement speed v of the inertial system (from fo in the example discussed at the beginning)
EMI8.1
 )
 undone again,

   is the measurement result when measuring a phase shift and determining the propagation time of the wave from the transmitter to the receiver from the phase shift measured in the receiver at the movement speed v of the inertial system (in the example discussed above, therefore, at the transmitter frequency fo, the transmission frequency resulting from the Doppler effect
EMI8.2
  and the reception frequency fo resulting after the reversal of the Doppler effect) is the same as for the movement speed 0 of the inertial system (in the example discussed at the beginning, therefore, for the transmitter frequency fo, the transmission frequency
 
EMI8.3
  and the reception frequency fo), so that the speed of the absolute movement of the earth in space cannot be determined using measurement methods which are based in principle on phase shift measurement.

  In contrast, when measuring the time directly (in the example discussed at the outset, the time from the radiation of the aforementioned initial zero crossing of the considered sine wave to the arrival of this initial zero crossing of the considered sine wave at the receiver), there is no cancellation of the Doppler effect (because the receiver detects the Doppler - Effect only reverses during the period of arrival of the sine wave and accordingly has not yet been reversed at the beginning of this period, so that the distance a between the transmitter and receiver (in the example discussed at the beginning, therefore, is one x times the Distance (cTo - vTo) between the transmitter and the initial zero crossing of the sine wave under consideration after a period of oscillation To amount to a = x.

   (cTo - vTo)) and the measured transit time from the transmitter to the receiver (in the example discussed above, the transit time tL = x. To corresponding to x times the oscillation period To of the initial zero crossing of the considered sine wave from the transmitter to the receiver) the movement speed v des Inertial systems can be determined (in the example discussed at the beginning with
 
EMI9.1
 or with the help of an additional measurement in the direction opposite to the direction of the speed v with the result
 
EMI9.2
 by forming the difference between the two measured times
 
EMI9.3
 with the difference
 
EMI9.4
 



  The present device can advantageously be designed in such a way that a stationary transmitter of electromagnetic waves above the earth with a transmission frequency above 100 MHz, which lies in a plane from which the earth's axis has a constant distance over its entire length, at least over the period of time from approximately half a revolution of the earth at predetermined times, at regular intervals in succession, in each case simultaneously emitting an electromagnetic wave in all directions of the plane, and that from a preferably at least 8 even numbered even number of stationary receivers, also located above the earth, lying on the plane mentioned a circle with the radius R is evenly distributed around the transmitter at equal angular intervals,

   the exact time of arrival of the wave front of the electromagnetic wave emitted by the transmitter at one of the predetermined times is determined and recorded, and that for each electromagnetic wave emitted by the transmitter at one of the predetermined times for each pair of diagonally opposite one another at an angular distance of 180 ° The time difference DELTA t of the registered arrival times of the wave front or the transit times of the wave front between the transmitter and the receiver is formed for recipients of the said even-numbered plurality of receivers and that the largest of all time differences DELTA t which are formed from the arrival times determined during half a revolution of the earth are formed from the largest. the scalar size of the velocity vector of the absolute movement of the earth in space or

   their relationship
EMI10.1
  too close to the propagation speed c of electromagnetic waves
 
EMI10.2
 is determined and the direction of this speed vector approximately corresponds to the direction in which a vector points from the transmitter to the receiver with the larger of the two arrival times at the time the two arrival times with the named greatest time difference DELTA t are determined.



  In the present device, the transmitter and receiver can advantageously be arranged in the vicinity of the equator in a plane substantially parallel to the earth's surface, preferably over an uninhabited lowland area with low air humidity and relatively low ground reflection. Such an arrangement has the advantage that all the receivers, including the associated mast, to the top of which the receiver is attached, can be of the same design, while in the case of an arrangement of transmitters and receivers in moderate widths, the plane in which the transmitter and receiver are to be arranged , yes, not parallel, but sloping to the surface of the earth, which would inevitably result in different mast heights for the receivers, which would also be less advantageous with regard to possible interference from reflection on the masts.



  In order to achieve the desired measurement accuracy in the order of percent, it is further advantageous with the present device to emit an electromagnetic wave from the transmitter in the same time intervals between 1 and 60 minutes, preferably every 4 minutes (corresponding to an angular degree of the earth's rotation) allow. For the same purpose, 24 (corresponding to 15 angular degrees in said plane) receivers are also advantageously used.



  In the present device, the receivers can advantageously be arranged at a distance from the transmitter of between 1 km and 30 km, preferably 3 km. The lower limit of the limits of this preferred distance range is due to the fact that atomic clocks are currently able to measure units of time of approx. 0.05 ns at best, and that at a speed v APPROX corresponding to the orbital speed of the sun around the galaxy center, the absolute speed Movement of the earth resulting time difference DELTA t at a distance of R = 1 km approx. 5 ns or approx.

   Would be 100 counting units and thus a measurement inaccuracy of 1% would already exist, while with higher distances better measurement accuracy can be achieved in this respect, but on the other hand the disturbing influences on the transmission path increase with the distance, until at distances of more than 30 km these interferences caused measurement inaccuracies are no longer negligible.



  In the case of the present device, the rising edge on the wave front of the electromagnetic wave should also be made so steep that the threshold value of the response sensitivity of the receiver is exceeded within less than 1 ns, preferably less than 0.1 ns. This is also important in order to achieve the desired measurement accuracy, but it can be done without great difficulty e.g. Realizable with a laser pulse source, since a pulse duration of less than 1 ns can already be achieved with laser pulse sources specially designed for short-term pulses and the duration of the rising edge is generally less than 0.1 ns for a total pulse duration of less than 1 ns.

  Because of the resultant expediency of using a laser pulse source to generate the electromagnetic waves, the transmitter in the present device should advantageously have an electromagnetic wave in the frequency range of 10 <1> <3> Hz to 1.5. 10th <1> Radiate <5> Hz, preferably visible or ultraviolet light.



  In a preferred embodiment of the present device, atomic clocks are used to measure the time, in particular the arrival times of the wavefront of the electromagnetic wave at the receivers, and the atomic clocks are synchronized at the same time and at the same location before the first measurement, preferably in the form that in the atomic clocks counters provided for counting the half-waves of the natural vibrations of the atoms are simultaneously set to zero at the same location before the measuring device provided for carrying out the method is set up.



  An advantageous embodiment of the present device is characterized by a transmitter which has a laser beam source perpendicular to the plane in which the transmitter and receiver are located, a conical mirror coaxial with the laser beam axis with a cone opening angle of 90 ° and the conical mirror coaxial with the laser beam axis annular surrounding, of two truncated cone-shaped reflection-free boundary surfaces with a cone opening angle, the at least at a transmitter height h above the ground and a distance R of the receiver from the transmitter
 
EMI12.1
 is formed, comprises beam limiting means, a number of receivers of at least 8,

   Each of which has a photocell and an atomic clock with a counter intended for counting the half or full waves of the natural vibrations of the atoms, and means for determining the count of the same at the moment the wave front of the electromagnetic wave emitted by the transmitter arrives at the photocell of the receiver and for registration of the determined counter reading includes a control and evaluation center, the control means for controlling the times of the radiation of electromagnetic waves from the transmitter and for activating the receiver shortly before and for deactivating the same shortly after the radiation and computing means for the approximate determination of the amount and direction the speed vector of the absolute movement of the earth in space from the registered counter readings,

   the angular position of said plane in space at the first emission of an electromagnetic wave from the transmitter and the time difference between the first and that radiation at which there is the greatest difference between the registered counter readings of a pair of mutually opposite receivers, and data transmission means for transmission the registered meter readings from the receivers to the control and evaluation center and for the transmission of control signals from the control and evaluation center to the transmitter and the receivers.



   With particular advantage, this advantageous embodiment of the present device can be further developed in order to achieve a measurement accuracy with less than 1% error in amount such that 24 receivers are provided and the control means are designed such that they run every 4 minutes after passing through an angular degree of rotation Earth around the earth's axis cause the emission of an electromagnetic wave from the transmitter and that the computing means are designed such that after each emission of an electromagnetic wave from the transmitter from each of the 12 pairs of opposing receivers, the difference DELTA z = z1 - z2 between the in form the first receiver of the pair registered count z1 and the count z2 registered in the second receiver of the pair,

   the amounts <SEP> DELTA e.g. Compare <SEP> of the 12 differences formed and at least the differences DELTA z = z1 - z2 from the recipient pair with the highest amount <SEP> DELTA e.g. <SEP> and of two adjacent pairs of receivers on both sides together with a parameter n indicating the degrees of rotation of the earth since the start of the measurement, corresponding to the number of emits of electromagnetic waves from the transmitter, and from the values resulting during half a revolution of the earth, the 180 highest amounts assigned to 180 individual emissions <SEP> DELTA e.g. <SEP> the maximum amount <SEP> DELTA e.g. Find <SEP> max and out <SEP> DELTA e.g. <SEP> max, the propagation speed c of electromagnetic waves,

   the transmitter-receiver distance R and the time period Tz per counting unit of the counters provided in the atomic clocks of the receivers according to the relationship v APPROX <SEP> DELTA e.g. <SEP> max. Tz. c <2> / 2R determine the magnitude of the speed of the absolute movement of the earth in space and furthermore from the angular position of the plane mentioned in space with the first radiation of an electromagnetic wave from the transmitter, the rotation of the plane in space up to the radiation at yourself <SEP> DELTA e.g. <SEP> max and the assigned parameter nz results in (nz - 1) angular degrees around an axis falling in the plane, running through the transmitter, parallel to the earth's axis and the direction in the plane from the transmitter to the named first receiver with positive DELTA z or 

   to said second receiver in the case of a negative DELTA z by interpolation at least between the DELTA z values stored under the parameter nz, preferably with further inclusion of those under the parameters (nz + 1), (nz + 2) etc.  as well as (nz - 1), (nz - 2) etc.  stored DELTA z values, determine the direction of the speed vector of the absolute movement of the earth in space.  



  Based on the figures below, the invention is explained in more detail below in terms of its theoretical basis and in an exemplary embodiment.  Show it
 
   Fig.  1 The transmission of an electromagnetic wave from a transmitter S to a receiver E in a stationary reference system in which no Doppler effect occurs,
   Fig.  1a to 1i the transmission of an electromagnetic wave from a transmitter S to a receiver E in an inertial system moved with v = c / 2 at intervals of one oscillation period To of the oscillation generated in the transmitter over the time period from 0 to 8To and the resultant Doppler effect,
   Fig.  2a to 2e which are shown in FIGS. 

   1a to 1i shown transmission in the form of Doppler diagrams of the electromagnetic waves emitted by the transmitter S and at intervals of 4To over the period from 0 to 16To and the movement of the inertial system carrying the transmitter S and the receivers E and E * (dashed rectangle) During this period, the spherical propagation of the electromagnetic waves around their place of origin, the significantly lower propagation speed of the electromagnetic waves in the direction of movement of the inertial system than in the opposite direction (Fig.  2c) and the reason for the impossibility of determining the different propagation velocities by means of phase shift measurement (Fig.  2e + 2c),
   Fig. 

   3 shows a Doppler diagram for determining the wavelength lambda of an electromagnetic wave from the period of oscillation To of the oscillation generated in the transmitter, the speed v of the moving inertial system carrying the transmitter and the angle alpha between the direction of movement of the inertial system and the direction of radiation of the transmitter,
   Fig.  4 shows a Doppler diagram to show the directional difference in the direction of propagation of the electromagnetic waves emanating from a transmitter S in a moving inertial system carrying the transmitter and the direction of propagation of these electromagnetic waves in the moving inertial system.
   Fig. 

   5 shows a diagram for determining the propagation speed va and the transit time tL of an electromagnetic wave in an inertial system which moves at the speed v and carries the transmitter of the electromagnetic wave on a transmission path of length a which is at an angle alpha to the direction of movement of the inertial system,
   Fig.  6 shows a schematically illustrated exemplary embodiment of a device for carrying out the present measuring method with a transmitter S and 24 receivers E in a side view in its arrangement in the equatorial region 1 of the earth 2 rotating about the earth axis 4 and also dashed another exemplary embodiment provided as a test device with a transmitter S and 2 receivers E arranged in a north-south direction at an angle of 54.74 ° to the earth's axis 4,
   Fig.  7 that in Fig. 

   6 shows an exemplary embodiment of a device for carrying out the present measurement method with a transmitter S and 24 receivers E in a top view,
   Fig.  8 is a block diagram of the internal structure of a central transmitter 5 and two in opposite directions at the same distance R or  a pair of receivers 6 and 7, arranged by the central transmitter 5, of a device for carrying out the present measurement method as in FIGS.  6 and 7 (with 12 such transmission link pairs) or in Fig.  6 shown in dashed lines (with such a transmission link pair),
   Fig.  9 and Fig.  9a to 9i the transmission of a pulse of an electromagnetic wave from a transmitter S to a receiver E in a stationary reference system (Fig.  9) and an inertial system moved with v = c / 2 (Fig.  9a to 9i) at the same time intervals as in FIGS. 

   1a to 1i to demonstrate the same speed of the wave front of a pulse (Fig.  9a to 9i) as the wavefront of a sustained wave (Fig.  1a to 1i).  
 



  As a theoretical basis for the present measurement method, it must first of all be demonstrated that the reasons previously raised against the measurability of the speed of the absolute movement of the earth in space can be refuted.  



  The main reason for the assumption that the speed of the absolute movement of the earth in space cannot be measured is likely to be the result of the Michelson test: Because despite repeated repetitions with increasingly refined measuring devices and correspondingly higher measuring accuracy, the result of the Michelson test was in any case a speed v = 0 of the absolute movement of the earth in space, a result that could not have been applicable under any circumstances because of the orbit of the earth around the sun. 

  To explain this measurement result, which does not match experience, approx.  10 years after the first implementation of the Michelson experiment by Lorentz, the Galileo transformation, on the basis of which the Michelson experiment was calculated and after which the result of the Michelson experiment was approximately
EMI17. 1
 proportional phase shift between interfering light beams would have to be replaced by the so-called Lorentz transformation, with which the calculation of the Michelson test leads to the result of a phase shift zero between the interfering light beams at any velocities v that matches the measurement result, but at the same time, of course, also a determination is excluded from v by means of this phase shift (which is zero at any v).  



  To explain the measurement result of the Michelson experiment, however, it would not have been necessary to introduce the Lorentz transformation if the Doppler effect had been taken into account when calculating the Michelson experiment on the basis of the Galilei transformation.  In the following, this is initially based on FIG.  1, 1a to 1i and 2a to 2e clearly demonstrated using an example and then generally for the movement of an inertial system with a fixed transmitter and receiver in a direction perpendicular to the connecting straight line between transmitter and receiver and radiation from the transmitter in the direction of the connecting straight line a mathematical derivation based on the Galilei transformation is shown:



  In a stationary reference system, the phase shift of an electromagnetic wave occurring over a transmission path from a transmitter permanently stationed in the stationary system with the movement speed v = 0 to a receiver likewise stationarily stationed in the stationary system with the movement speed v = 0 is proportional to that of the distance between transmitter and receiver corresponding length of the transmission path or more precisely to the running distance s of the wave from the transmitter to the receiver corresponding to the length of the transmission path in the stationary system. 

  If fo is the frequency, To = 1 / fo is the period of oscillation and lambda o = c / fo is the wavelength of the electromagnetic oscillation generated by the transmitter, then according to the relationship f.   lambda = c in the stationary system (in which there is no Doppler effect and the frequency f of the electromagnetic wave on the transmission link is therefore equal to the oscillation frequency fo of the transmitter), the wavelength lambda of the electromagnetic wave on the transmission link is equal to lambda = c / fo = lambda o and thus the phase shift DELTA @ of the electromagnetic wave on the transmission path is the same
 
EMI18. 1
 Fig.  1 shows as an example for comparison with the following with reference to FIG. 

   1a to 1i to be discussed transmission in a moving inertial system an electromagnetic wave in a stationary reference system on a transmission path from the transmitter S to the receiver E of a length of 8 lambda o = 8c / fo = 8cTo at the time t = to + 8To, at which the Wavefront from the transmitter S with the frequency
 
EMI18. 2nd
  and the phase @ = 2f.  (t-to) = 2fo.  (t-to) = omega o (t-to) radiated sine wave A.  sin omega o (t-to) has just reached the receiver E.  Since the running distance s of the wave from the transmitter to the receiver corresponds to the length of the transmission path in the stationary system, the phase shift DELTA @ over the transmission path in FIG.  1 as well as directly from FIG.  1 can be seen immediately
EMI18. 3rd
 



  Using the Fig.  1a to 1i will now be clearly demonstrated that the phase shift DELTA @ over the transmission path assuming the same distance s = c (t-to) of the waves from the transmitter S to the receiver E in the stationary system due to the Doppler effect regardless of the speed of movement v of sender and receiver equal to the phase shift
 
EMI18. 4th
  at v = 0, using the example of one in a stationary system (marked in Figs.  1a to 1i through the two outer delimitation lines of the running path s of the waves in the stationary system) with the speed v = c / 2 in the direction of the connecting straight line from the transmitter S to the receiver E with the inertial system moving at a distance
 
EMI19. 1
 Transmitter S and receiver E stationed fixed to one another (marked in FIGS. 

   1a to 1i by the two position lines indicating the positions of the transmitter and the receiver) and one from the transmitter S as in FIG.  1 generated sine wave A.  sin omega o (t-to) with the frequency fo, the oscillation period To = 1 / fo and the wavelength lambda o = c / fo = cTo.  



  The development of the transmission of an electromagnetic wave in the inertial system moved with v = c / 2 from time t = to or  t-to = 0To, to which the transmitter S as shown in Fig.  1a can be seen at the beginning of the running path s of the waves (left outer boundary line of the stationary system) and just with the radiation of the sine wave A.  sin omega o (t-to) begins at intervals of one oscillation period To up to the time t = to + 8To or  t-to = 8To at which the wave front of the electromagnetic wave emitted by the transmitter S just reaches the receiver E. 

   After an oscillation period To at the time t-to = 1To, the wave front of the wave emitted by the transmitter S, which propagates with the propagation speed c of electromagnetic waves, has as shown in FIG.  1b can be seen from the location of their emission (position of the transmitter S in FIG.  1a) moved forward by cTo = c / fo = lambda o towards the receiver.  In the same period, the transmitter S has turned in the same direction
EMI19. 2nd
 
 moved forward and emitted a full sine wave.  The wavelength lambda of this emitted full sine wave corresponds to the distance between the wave front and the transmitter S at the time t-to = 1To and is therefore as shown in FIG.  1b can be seen immediately as lambda = cTo - vTo = cTo (1-v / c) = lambda o (1-v / c) = lambda o / 2. 

  This radiated full sine wave with the wavelength lambda = cTo (1-v / c) = lambda o / 2 and the frequency
 
EMI19. 3rd
 now moves with the speed of propagation c of electromagnetic waves towards the receiver E, and at the same time the transmitter S radiates another full sine wave with the same wavelength lambda o / 2 and the same during the next oscillation period To up to the time t-to = 2To Frequency 2fo and moves as in Fig.  1c can be seen to advance a further lambda o / 2, and the whole is then repeated with each further period of oscillation To, as in the FIGS. 

   1d to 1i can be seen until the wave front of the sine waves emitted by the transmitter S at the point in time t-to = 8To, like the transmitter S, is stationed in the moving inertial system and has therefore reached receiver E moving together with the transmitter S, and thus at the same time at the end of the running distance s of the waves (right outer boundary line of the stationary system).  



  From the successive Fig.  1a to 1i it is now clearly evident that the wave front (and thus also the waves following the wave front), due to their progress with the propagation speed c of electromagnetic waves within the transmission time 8To, the same travel distance s = 8cTo = 8 lambda o as in the one shown in FIG . 

   1 passes through the dormant system shown, but only the transmission path in the inertial system moved with v = c / 2
 
EMI20. 1
 from the transmitter S stationed in the moving inertial system to the receiver E stationed in the moving inertial system at a distance a from the transmitter S and therefore moves only within the moving inertial system at the rate of propagation
 
EMI20. 2nd
  moved forward, although the wavefront and the subsequent waves proceed even with the propagation speed c of electromagnetic waves.  



  As from Fig.  1i can also be seen, the phase shift is DELTA @ over the transmission path a in the inertial system moved with v = c / 2 in the final state reached at the time t-to = 8To, in which the wavefront just at the end of the transmission path at the receiver E and at the same time at the end the running distance s of the waves has arrived, 8 full wavelengths or  8th .  2 and is therefore just as large as with v = 0 in the 

   1 shown at rest system with the same distance s = 8cTo of the waves, so that this example can already be seen that the phase shift DELTA @ with the same length s of the waves from the transmitter S to the receiver E regardless of the movement speed v of the transmitter and The recipient is what has to be basically

   because the waves propagate at the propagation speed c of electromagnetic waves and therefore the transmission time must be the same for the same distance s of the waves from the transmitter to the receiver and the transmitter emits the same number of waves in the same transmission time and thus over the transmission path regardless of the speed of movement v the same number of waves must be located between the transmitter and receiver, which necessarily results in the same phase shift over the transmission link.  



  The Fig.  1i therefore already immediately shows what has happened to FIGS.  1a to 1i in comparison to Fig.  1 should be clearly demonstrated, namely that the phase shift
EMI21. 1
 over the transmission path a = s (1-v / c) in the inertial system moving with the speed v because of the shortened wavelength due to the Doppler effect lambda = cTo (1-v / c) = lambda o (1-v / c) der electromagnetic wave on the transmission line equal
EMI21. 2nd
  and thus with the same distance s of the waves from the transmitter S to the receiver E regardless of the speed of movement v of the transmitter and receiver equal to the phase shift
EMI21. 3rd
 
 at v = 0 and consequently the movement speed v of a moving inertial system in a stationary system cannot be measured by means of a phase shift,

   whereas, in the case of a predetermined transmission distance a, the determination of v = c - va = c - a / tL (= c - 4cTo / 8To = c - c / 2 = c / 2 in Fig.  1i shown) by measuring the transmission time tL is in principle easily possible (provided that suitable technical equipment is available for measuring the usually very short transmission times).  



  The fact that the speed of movement of a moving inertial system in a stationary system can be determined by measuring the transmission time of an electromagnetic wave from a transmitter stationed in the moving inertial system to a receiver also stationed in the moving inertial system must be shown particularly clearly in FIG.  2a to 2e, in which the same development of the transmission of an electromagnetic wave in the inertial system moved with v = c / 2 as in FIGS.  1a to 1i in the form of the spread of the waves emitted by the transmitter S, taking into account the Doppler effect, is shown around the transmitter S, but no longer here at time intervals of one oscillation period To of the transmitter S as in FIGS. 

   1a to 1i, but only at intervals of 4To, but not only for the period from 0 to 8To, until the wave front arrives at the receiver E, as shown in FIGS.  1a to 1i, but for the double period of 0 to 16 tons, until all the waves on the transmission path at the time of arrival of the wave front arrive at the receiver E. 

   The dashed rectangle in the Fig.  2a to 2e symbolize the inertial system moving with the movement speed v = c / 2 with the sinusoidal oscillation A fixedly located therein.  sin omega o (t-to) generating transmitter S and the receiver E fixed at a distance a = 4cTo in front of the transmitter S in the moving inertial system and an additional receiver E * fixed at a distance 3a = 12 cTo behind the transmitter S in the moving inertial system , in each case in the positions of the moving inertial system to the next to the Fig.  2a to 2e specified times (t-to) = 0To, 4To, 8To, 12To and 16To, and the individual circles in these figures represent the geometric locations of the transmitter S at the start of the transmission at the time t-to = 0To in the in Fig. 

   2a shown position emitted wavefront (solid circles), of the transmitter S at the time t-to = 4To in the in Fig.  2b shown position emitted zero crossing between the fourth and fifth wave (dashed circles), that of the transmitter S at the time t-to = 8To in the in Fig.  2c shown position emitted zero crossing between the eighth and ninth wave (dash-dotted circles) and that of the transmitter S at the time t-to = 12To in the in Fig.  2d shown position radiated zero crossing between the twelfth and thirteenth wave (dotted circle) each at the times indicated next to the figures.  



  The figure which shows the development of the transmission at the time the wavefront arrives at the receiver E  2c, one can immediately see that the wavefront (shown by the solid circle) due to the Doppler effect at the same time t-to = 8To arrives at the additional receiver E * three times as far as the receiver E from the transmitter S and consequently already at Time t-to = 8To / 3 would arrive at the additional receiver if it were not arranged at a distance 3a, but at the same distance a from the transmitter S as the receiver E, and accordingly between the arrival of the wavefront at the distance a in front of the transmitter S arranged receiver E and an additional receiver arranged at the same distance a behind the transmitter S, a time difference DELTA t - 8To- 8To / 3 = 16To / 3 occurs,

   from which the movement speed v of the moving inertial system carrying the transmitter and the two receivers according to the following in connection with FIG.  5 still in detail derived on the basis of the Galilei transformation
EMI23. 1
 can be easily determined (in the present case with DELTA t = 16To / 3 and a = 4cTo
EMI23. 2nd
 



  If one wanted to contest the occurrence of such a time difference and claim that even with a moving transmitter, the wavefront of an electromagnetic wave emitted by the transmitter would arrive at the same point in time with two receivers arranged at the same distance in front of and behind the transmitter and moving with the transmitter, then In principle, the assertion is made that there is no Doppler effect in the case of electromagnetic waves emitted by a moving transmitter, but that the electromagnetic waves emitted by the transmitter with the propagation speed c of electromagnetic waves are in the form of concentric spherical coats with the transmitter as the center around the transmitter would spread out and the concentric spherical coats would be taken away by the moving transmitter, and such an assertion would be tantamount to asserting

   that the electromagnetic waves emitted by the transmitter in its direction of movement would propagate at a speed (c + v) corresponding to the sum of the speed of light c and the speed of movement v of the transmitter, an assertion that already arises because of the propagation that is mandatory according to Maxwell's field theory electromagnetic waves at the rate of propagation
EMI24. 1
 prohibited from the outset.  The occurrence of the above-mentioned time difference DELTA t and the possibility of determining the speed of movement v thus given is not only readily apparent from FIG.  2c recognizable, but also indisputable.  



  The representation of the transmission of electromagnetic waves in the form of a sequence of Doppler diagrams as in the Fig.  2a to 2e, however, shows something else essential: namely, while the usual representation of the Doppler effect in the form of only one similar to that in FIG.  2e-looking diagram often gives the viewer the impression that the waves surrounding the transmitter, represented as circles, are being carried along by the moving transmitter, and such an impression (which for the reasons mentioned above contradicts Maxwell's field theory and is therefore incorrect) still from the Fig.  2a to 2e were conveyed if all the circles in these figures had been drawn through, the 

   2a to 2e shown representation of the Doppler diagrams in the form of dotted, dash-dotted, dashed and solid (better still differently colored) circles immediately clearly that each wave propagates circularly (or more correctly spherically shaped) around the location of its origin with the propagation speed of electromagnetic waves (which when looking at e.g. B. 

   all solid circles or all dashed circles in the sequence of figures from top to bottom is directly visible) and that the phase shift occurring in the receiver E or E * when receiving the waves on the transmission path from the arrival of the beginning of the first wave (wave front) to Arrival of the end of the last wave occurs, firstly it can be read directly from the Doppler diagrams and secondly regardless of v the exact distance between transmitter S and receiver E or  E * corresponds.  Because the waves propagate at the propagation speed c of electromagnetic waves, the distance between the receiver E or 

  E * and the wavefront (solid circle) to the (in Fig.  2e) time of arrival of said end of the last wave at the receiver of the time difference multiplied by the propagation speed c of electromagnetic waves between the arrival of the start of the first and the end of the last wave at the receiver (in FIG.  2e at the receiver E, therefore, distance 4cTo and thus time difference 4To and at the receiver E * distance 12cTo and thus time difference 12To), and since in the same inertial system (dashed rectangle) as the transmitter S, the receiver E is permanently stationed or  E * the Doppler effect occurring on the transmission link, as already mentioned at the beginning, is completely canceled when the transmitted waves are received in the receiver and the oscillation caused by the received waves in the receiver E or 

   E * therefore has the same frequency fo and oscillation period To = 1 / fo as the oscillation generated by the transmitter, corresponds to that in the receiver E or  E * phase shift occurring during said time difference, the ratio of this time difference to the oscillation period To multiplied by 2 (in FIG.  2e at receiver E, i.e. time difference 4To and thus phase shift 2.  4To: To = 4.  2 and at the receiver E * time difference 12To and thus phase shift 2.  12To: To = 12.  2), or in short is shown in Fig.  2e the distance between the receiver and the wavefront at receiver E is 4cTo = 4 lambda o 0 4.  2 and at the receiver E * equal to 12cTo = 12 lambda o = 12.  2 and thus corresponds as in FIGS.  2a and 2c can be seen exactly the distance a = 4cTo between transmitter S and receiver E or  the distance 3a = 12cTo between the transmitter S and the receiver E *, so that those in the receiver E or 

  E * occurring phase shift firstly directly from the Doppler diagram in Fig.  2e can be read and, secondly, regardless of the movement speed v of the moving inertial system carrying the transmitter and receiver E and E *, the exact distance between transmitter S and receiver E or  E * corresponds.  



  The representation of the transmission of electromagnetic waves in the form of a sequence of Doppler diagrams in the Fig.  2a to 2e therefore shows, so to speak, at first glance the solution to the problem that arose with the unexpected result of the Michelson experiment: When measuring the length of a transmission link in a moving inertial system by means of a phase shift, the measurement result corresponds exactly to the length of the transmission link, regardless of the movement speed v of the inertial system and is therefore exactly the same as the measurement result that would result at v = 0, so that the attempt made in the Michelson experiment to determine a path difference, which enables the determination of v, between two transmission paths of the same length in the moving inertial system, 

   a phase shift corresponding to the path difference between the two light beams coming from the transmitter to the receiver and interfering there on these different paths had to lead to the result of a path difference zero and thus a phase shift zero between the interfering light beams, which according to the calculation of the Doppler effect not taking into account the Michelson experiment the speed of movement v = 0 of the inertial system could be assigned.  



  In principle, it has already been proven that the result of the Michelson experiment already at the time of the first experiment in 1881, taking into account the Doppler effect in light (or  according to Maxwell's field theory for electromagnetic waves published around 1870) would have been predictable and therefore the introduction of the Lorentz transformation in 1892 to explain the result of the Michelson experiment was superfluous.  



  However, in order to dispel any doubts about the predictability of the result of the Michelson experiment in this regard and also to counter the possible objection from the outset that the Fig.  2a to 2e do not represent any generally valid proof, but would only show a single example with two transmission paths of different lengths at an angle of 180 ° to one another, while in contrast to this, in the Michelson test, the two transmission paths are at an angle of 90 ° to one another and have the same length are generally demonstrated here for any movement speeds v of the inertial system and any angle alpha between the transmission path from the transmitter to the receiver and the direction of movement of the moving inertial system carrying the transmitter and receiver,

   that the phase shift of the vibration caused by the received waves in the receiver, regardless of the speed of movement v of the inertial system and regardless of the angle alpha between the transmission path and the direction of movement of the inertial system, corresponds exactly to the length of the transmission path in the moving inertial system and thus exactly the distance a between the transmitter and receiver and Accordingly, in the Michelson experiment, the change in the angle alpha between the transmission path and the direction of movement of the inertial system caused by the rotation of the test arrangement by 90 ° for each of the two equally long transmission paths at an angle of 90 ° did not change the phase shifts of those arriving at the receiver via the two transmission paths Light rays in the receiver image and therefore no change in the difference between them

   Could result in phase shifts and therefore the shift of the interference fringes in the receiver image expected with the rotation of the test arrangement had to fail to occur.  



  To determine the phase shift of the vibration caused by the received waves in the receiver, frequency f and wavelength lambda of the wave emitted by the transmitter onto the transmission link to the receiver at an angle alpha between the transmission link and the direction of movement of the transmitter and receiver, with the movement speed v to determine the moving inertial system.  The transmitter likes a vibration A.  sin omega o (t-to) with the oscillation period To, the frequency fo = 1 / To or  the angular frequency omega o = 2fo and the phase position @o = - omega oto at time t = 0 and at time t = to or  t-to = 0 at the point Po in Fig.  3 are located and begin to emit an electromagnetic wave at this time. 

  Then the geometric location is that of the transmitter at time t = to or  t-to = 0 wave front of the electromagnetic wave emitted from the location point Po after an oscillation period To at the time t = to + To or  t-to = To the in Fig.  3 represented circle (or  correct the spherical cladding shown in section) around the point Po with the radius cTo = c / fo = lambda o from a wavelength lambda o of the oscillation generated by the transmitter resulting from the propagation speed c of the wavefront and the time period To since the radiation .  During the period from t-to = 0 to t-to = To, the transmitter has changed as shown in Fig.  3 can be seen moving from the point Po in the direction of movement of the inertial system carrying it by the distance vTo and thereby emitting a full wave. 

   The wavelength lambda of the emitted full wave in the direction of the transmission path at an angle alpha to the direction of movement must be equal to the distance that the wavefront in the time from t-to = 0 to t-to = To from the transmitter in the moving inertial system along the Has covered the transmission path, and this path is equal to the distance between the position of the transmitter at the time t-to = To and the intersection P1 of the transmission path emanating from the transmitter with the circle in FIG.  3 (or  more correctly the intersection point P1 of the transmission path through the geometrical location of the wavefront at that time, in FIG.  3 spherical jacket shown in section). 

  Hence, it follows from Fig.  3 for the wavelength lambda of the waves radiated from the transmitter onto the transmission link to the receiver depending on the angle alpha between the transmission link and the direction of movement of the transmitter or  of the inertial system that supports it
EMI28. 1
 



  and for the resulting frequency f of the electromagnetic waves on the transmission link
EMI29. 1
 



  Checking this for lambda and f depending on
EMI29. 2nd
  and alpha apply formulas for an angle alpha = 0 between the transmission path and the direction of movement of the transmitter
EMI29. 3rd
 
 



  Correspondence with the relationships already derived at the beginning for wavelength lambda and frequency f of the wave emitted by the transmitter in the direction of movement
 
EMI29. 4th
 and thus represents the correctness of the above general formulas for lambda and f as a function of
EMI29. 5
  and alpha proven.  



  Using these formulas for the wavelength lambda and the frequency f, the transmitter moving at an velocity that generates an electromagnetic oscillation with the oscillation period To, the frequency fo = 1 / To and the wavelength lambda o = c / fo = cTo Electromagnetic waves emanating from the transmitter and at an angle alpha to the direction of movement of the transmitter and emitted with the transmitter along the transmission path can now be transmitted within a moving inertial system from a transmitter stationed in the inertial system via the transmission link to a receiver stationed in the inertial system mathematically represent their individual phases as follows:



  Electromagnetic vibration generated by the transmitter: (with @o = - omega oto) F (t) = Asin (omega ot + @o) = Asin omega o (t-to) = Asin2fo (t-to)



  Electromagnetic wave emitted by the transmitter onto the transmission path with a factor due to the Doppler effect in the radiation
EMI29. 6
  frequency changed from fo to f at the location of the transmitter
EMI29. 7
 



  Electromagnetic wave radiated by the transmitter onto the transmission link after passing through the transmission link with a phase shift corresponding to the length a of the transmission link
EMI30. 1
  at the location of the receiver stationed at the end of the transmission path at a distance a from the transmitter
EMI30. 2nd
 



  In the receiver, the electromagnetic wave caused by the received electromagnetic wave, due to the cancellation of the Doppler effect when receiving, by a factor
 
EMI30. 3rd
 frequency changed from f to fo
 
EMI30. 4th
 



  For the phase shift DELTA @e of the vibration caused in the receiver by the received waves
EMI30. 5
 compared to the vibration Asin2fo (t-to) generated by the transmitter
EMI30. 6
 



  and as can be seen, this phase shift is exactly the same as the phase shift regardless of the movement speed v of the inertial system carrying the transmitter and receiver and regardless of the angle alpha between the transmission path from the transmitter to the receiver and the direction of movement of the inertial system
EMI30. 7
  which would result at v = 0 with the wavelength lambda o over the transmission path a, and thus corresponds exactly to the distance a between the transmitter and the receiver, and thus the generally valid proof is provided that if the Doppler effect had been taken into account, it would have been predictable from the start that the rotation of the test arrangement by 90 ° during the Michelson experiment could not lead to the expected shift of the interference fringes in the receiver image.  



  If one applies this general proof specifically to the experimental setup during the Michelson experiment (or more precisely to the description of the basic structure of the Michelson experimental setup used in the literature) and designates the semitransparent mirror with G in the experimental setup (according to the common names in the literature), the mirror at the end of the test arrangement (or  of the inertial system carrying the experimental arrangement) with S1 and the mirror at the end of the transmission path perpendicular to the direction of movement of the experimental arrangement (or  of the inertial system carrying the experimental arrangement) with S2 and further with
 a = length of the transmission path in the experimental setup (i.e. H. 

   in the moving inertial system)
 
EMI31. 1
 = Ratio of the speed of movement v of the test arrangement (or  of the inertial system carrying the experimental set-up) for the propagation speed c of electromagnetic waves
  alpha = angle between the transmission path and the direction of movement of the test arrangement
 fo = frequency of vibration in the transmitter
 f = frequency of the waves on the transmission link
 fe = frequency of the vibration in the receiver caused by the received waves
  lambda o =
EMI31. 2nd
 Wavelength (or more correctly the oscillation period multiplied by the propagation speed c of electromagnetic waves) of the oscillation in the transmitter
  lambda = wavelength of the waves on the transmission link
  lambda e = wavelength (or more correctly multiplied by the propagation speed c of electromagnetic waves) the oscillation time in the receiver of the

   received waves caused vibration
  DELTA @ = phase shift over the transmission link
  DELTA @e = phase shift of the vibration caused in the receiver compared to the vibration in the transmitter
 s = path of the waves from the transmitter to the receiver calculated by Michelson
 The following general representation of the various phases of a transmission from a fixed transmitter to a fixed receiver in one and the same moving inertial system results in the following frequencies, wavelengths and phase shifts on the individual transmission links of the Michelson test arrangement:

   


 1.  Transmission path 1 from G to S1, transmitter G, receiver S1
 
EMI32. 1
 


 2nd  Transmission path 2 from S1 to G, transmitter S1, receiver G
 
EMI32. 2nd
 


 3rd  Transmission path 3 from G to S2, transmitter G, receiver S2
 
EMI33. 1
 


 4th  Transmission path 4 from S2 to G, transmitter S2, receiver G
 
EMI33. 2nd
 



  The above list of frequencies, wavelengths and phase shifts on the individual transmission links of the Michelson test arrangement shows that the phase shifts over the pure transmission links also take into account the Doppler effect
 
EMI33. 3rd
 exactly the path of the waves calculated by Michelson
 
EMI33. 4th
  correspond on these transmission links. 

  Of course, this must also be the case because the waves between the transmitter and receiver propagate at the propagation speed c of electromagnetic waves and the path of the waves from the transmitter to the receiver (apart from their dependence on the distance a of the receiver from the transmitter and on the speed of movement v des Transmitter and receiver carrying inertial system and the angle alpha between the direction of movement of the inertial system and the transmission path from the transmitter to the receiver) thus only depends on the propagation speed c of electromagnetic waves, but not on the frequency of the waves and therefore also the change in the frequency of the waves as a result of Doppler effect on the running distance of the waves can have no influence. 

  The error in the calculation of the Michelson experiment was therefore not in the running distances calculated by Michelson, but rather in the fact that when calculating the path difference DELTA s = (s1 + s2) - (s3 + s4) between the running distances (s1 + s2) from semi-transparent mirror G to mirror S1 and back and the running distances (s3 + s4) from the semi-transparent mirror G to mirror S2 and back only the pure running distances have been taken into account, under the implicit condition that the mirrors S1 and S2 are reflected do not move and the reflection is therefore timeless, and this requirement is incorrect. 

  Because a reflection is a physical process in the three phases "reception of the incoming wave by a receivable (receiving antenna), oscillating (oscillating circuit) and radiating (transmitting antenna) structure", "oscillation of the structure" and "radiation of an outgoing wave from the structure" , and such a process with two energy conversions from wave energy into vibrational energy and back into wave energy cannot of course be timeless.  An illustrative example of this is provided by a sun-illuminated red area, because there the red color, which is the only reflected color, must be filtered out of the sunlight containing all colors, and passing a filter is of course not timeless, but, as is well known, requires a finite running time. 

  However, since the fact that a reflection cannot go on timelessly follows directly from Huygens' principle, it cannot be assumed that the calculation of the Michelson experiment was based on absolutely timeless reflections on mirrors S1 and S2, but rather has assumed that the reflection times are negligible and that the reflections at mirrors S1 and S2 can therefore be regarded as timeless. 

  However, the admissibility of such a prerequisite appears - at least in the case of the values from which the Michelson experiment was calculated at the time, i.e. a speed v = 30 km / s corresponding to the earth's orbital velocity around the sun or  v / c = 10 <-> <4>, a distance a between the mirrors S1 and S2 from the semitransparent mirror G of a = 11 m and a wavelength lambda o of the light used of lambda o = 0.59 m - extremely doubtful, because the path difference to be expected with these values
EMI35.1
 



  is only 18.65% of the wavelength lambda o and therefore corresponds to only a time difference of
EMI35.2
 



  compared to the negligible reflection times in the physically no longer realizable range of less than 10 <-> <1> <7> s should be. It can therefore be assumed that negligible reflection times were taken for granted when calculating the Michelson experiment, and the error in the calculation caused by this inaccurate condition (which is based in principle on the fact that the position of the mirror changes when reflection times are no longer negligible) S1 changed during the reflection) was not recognized.



  Such an error cannot occur when calculating the Michelson test taking into account the Doppler effect, because each of the transmissions on the four transmission links G-S1, S1-G, G-S2 and S2-G each occur with the occurrence of the Doppler effect the wave radiation and cancellation of the Doppler effect occurring on the transmission side during wave reception is to be considered separately, and with a complete transmission comprising the sub-processes "oscillation of the transmitter, wave radiation, wave transmission, wave reception and oscillation of the receiver", the length a of the transmission path caused by the transmission corresponding phase shift
 
EMI36.1
  the receiver vibration against the transmitter vibration is already set, so it doesn't matter

   how long a reflection process lasts from the beginning of the wave reception in the forward transmission to the start of the wave radiation in the back transmission or at what point in time a further phase shift
EMI36.2
 effective retransfer begins. When the Michelson experiment is calculated taking into account the Doppler effect, the duration of the reflection time on the total phase shift has
EMI36.3
  no effect in the case of forward and backward transmission, provided that the reflection time is not arbitrarily set to zero, contrary to its character of a transit time, as in the original calculation of the Michelson experiment, because a reflection time of zero would mean that the mirror would remain in the same position during the reflection ,

   while the cancellation of the Doppler effect during wave reception (multiplication of the oscillation period by
EMI36.4
  and the occurrence of the Doppler effect in the case of wave radiation (multiplication of the oscillation period by
 
EMI36.5
 As already explained at the beginning, are based on the change in the position of the receiver or transmitter or the (receiver, oscillator and transmitter forming) mirror during the reception or radiation of a wave (only a finite time can change by multiplying by the multiplication factor , however, the time zero does not change when multiplying). It can therefore also be said that the Doppler effect had to be taken into account in order to eliminate the error in the original calculation of the Michelson experiment.



  Otherwise, the above list of frequencies, wavelengths and phase shifts on the individual transmission links of the Michelson test arrangement shows that, according to the above general proof, the phase shift
EMI36.6
  the vibration caused by the waves transmitted via the transmission links 1 and 2 and the mirror S1 in the semitransparent mirror G.
EMI37.1
  exactly the same as the phase shift
EMI37.2
  is the vibration which is caused by the waves transmitted via the transmission links 3 and 4 and the mirror 2 in the semi-transparent mirror G, and thus the phase shift difference of the two vibrations
EMI37.3
  is zero and this result changes due to the independence of DELTA @e from alpha even when the test arrangement is rotated by -90 ° to alpha 1 = -90 °,

    alpha 2 = +90 DEG alpha 3 = 0 DEG and alpha 4 = -180 DEG did not change, and due to the lack of change in the phase shift difference when the test arrangement was rotated by -90 DEG, a shift in the interference fringes in the receiver image of the Michelson test arrangement was also not to be expected. It is now proven not only in general, but also specifically for the Michelson test arrangement, that the result of the Michelson experiment would have been predictable from the outset, taking into account the Doppler effect.



  In summary, regarding the question raised above in the context of the discussion of the theoretical foundations of the present measurement method, whether the result of the Michelson experiment is a valid reason for the assumption that the speed of the absolute movement of the earth in space cannot be measured, the following can be determined:



  1. The result of the Michelson experiment was to be expected. On the basis of the Galilei transformation, this necessarily results when the Doppler effect is taken into account.



  The fact that a different result had been expected in the Michelson experiment was due to impermissible neglect in the calculation of the Michelson experiment, in particular the neglect or disregard of the Doppler effect and the neglect of the reflection times or the incorrect assumption of a zero reflection time due to the mirrors of the Michelson experiment.



  2. The knowledge of the "principle of the constancy of the speed of light" on which the special theory of relativity is based, ie the fact that the speed of propagation of electromagnetic waves in a vacuum, in relation to any inertial system, is independent of the movement of this system, is in agreement with Maxwell's field theory, according to the speed of propagation of electromagnetic waves in a vacuum
EMI38.1
  is exclusively dependent on the properties of the vacuum for storing and transmitting electromagnetic energy, i.e. on the dielectric and permeability of the vacuum, but not on movements of any kind.



  The "constancy of the speed of light" has the consequence for the reasons mentioned at the outset that every movement of a transmitter of electromagnetic waves to a Doppler effect for the waves emitted by the transmitter and every movement of a receiver of electromagnetic waves to a "reverse Doppler effect" for the leads waves received by the receiver and the Doppler effect thus occurs not only in the case of relative movements between the transmitter and receiver, but also in the case of absolute movements of the transmitter and the moving receiver first occurs during wave radiation and is then canceled again when the wave is received and the Doppler effect for this reason should have been taken into account when calculating the Michelson experiment.



  An interpretation of the "principle of the constancy of the speed of light" in the sense of equating the speed of propagation of electromagnetic waves with the speed of propagation of the same in a moving inertial system (ratio of the length of a transmission path in the moving inertial system to the time required by the light to pass through it) would therefore be inadmissible because same speed of propagation in all directions in a moving inertial system with a fixed transmitter and receiver would be equivalent to the absence of a transmitter-side Doppler effect and the receiver-side "reverse Doppler effect" would then lead to an oscillation frequency in the receiver that is different from the oscillation frequency in the transmitter, which the Experience contradicts.



  3. Due to the Doppler effect, the propagation speed of electromagnetic waves in a moving inertial system depends on the direction of the transmission path relative to the direction of movement of the inertial system, so that e.g. the movement speed of the moving inertial system can be determined from the difference between the propagation speeds in the direction of movement of the moving inertial system and in the opposite direction.



  4. A determination of the propagation speed of electromagnetic waves in a moving inertial system by means of phase shift measurement, e.g. in the Michelson experiment it is impossible because of the occurrence of the Doppler effect in the wave radiation from a moving transmitter and the cancellation of the Doppler effect when receiving a wave with a receiver moving with the transmitter. The speed of propagation in a moving inertial system can only be determined by measuring the time required by an electromagnetic wave to travel through a transmission path in the moving inertial system or the time difference between the two times required to run through two differently directed transmission paths.



   5. The introduction of the Lorentz transformation to explain the result of the Michelson experiment was superfluous, because the result of the Michelson experiment can be explained on the basis of the Galilei transformation, specifically with the Doppler effect as shown above.



  All theories theoretically underpinning and / or based on the same, and the hypotheses and conclusions drawn in this context, such as the hypothesis of the "Lorentz contraction" and the hypothesis of the "non-existence of a material ether" and in particular also were superfluous The conclusion of a "fundamental unobservability of absolute movements" lacked the necessary basis due to the explanation of the Michelson experiment on the basis of the Galilei transformation or because of the superfluous introduction of the Lorentz transformation to explain the result of the Michelson experiment.



  6. The demand for invariance of physical theories compared to the Lorentz transformation lacks factual justification because the Lorentz transformation is superfluous.



  It should be noted that the so-called relativistic mass increase at movement speeds v that are no longer negligible compared to the speed of light c is based on the Galilei transformation from the Doppler effect or the anisotropy of the spatial energy distribution associated with the Doppler effect, and so on Lorentz transformation is therefore superfluous in this regard too.



  The assumption that the speed of the absolute movement of the earth in space is not measurable is not only based on the result of the Michelson experiment, which has now been over 100 years ago, in which the measured path difference zero was very little different from that in absolute terms Rotation of the test arrangement by 90 ° expected path difference
 
EMI40.1
 (= 2. 0.11 µm = 0.22 µm according to the above derivation), but currently primarily on the practical experience with radio-based range finders, and there in particular on the high measuring accuracy of approx. 10, which is independent of the direction of the measuring section <-> <6> for disposable range finders (such as

  Global Positioning System), in which the length of the measuring section is determined by indirectly measuring the transit time of electromagnetic waves over the measuring section and multiplying the measured transit time by the propagation speed c of electromagnetic waves. However, since the transit time tL of an electromagnetic wave over a transmission path of length a is the same in an inertial system moving at speed v at an angle alpha between the transmission path and the direction of movement of the inertial system after the Galileo transformation
 
EMI40.2
 and thus the product ctL of propagation speed c and transit time tL at alpha = 0 ° and 180 ° equal
 
EMI41.1
 is

   with a speed v = 250 km / s corresponding to the orbital speed of the sun around the galaxy center a maximum tolerance of
EMI41.2
 the measured length
EMI41.3
  compared to the actual length a of the transmission path or, in the worst case, a measuring accuracy of only 0.8. 10th <-3> result against which the actually achieved high measuring accuracy of approx. 10 <-> <6> can practically be regarded as zero measurement error.



  The high measurement accuracy achieved, like the results of the Michelson experiment at the time, only seemed to be explainable by replacing the Galilei transformation with the Lorentz transformation, with which, as already mentioned above in connection with the Michelson experiment, an apparent velocity v = 0 of the absolute movement of the earth and therefore a transit time that is independent of the absolute movement of the earth and the direction of the measuring section
 
EMI41.4
 or a measured length ctL = a which corresponds exactly to the actual length a of the measuring section, but which, on the other hand, would of course also exclude a determination of v by measuring the (with any v zero) difference in the transit times on opposite, equally long transmission sections.



  To explain the high measuring accuracy achieved with the one-way range finders, just as with the Michelson experiment, the Lorentz transformation would not have been necessary at all, because with the one-way range finders it was not the transit time of electromagnetic waves over the measuring section, but the phase shift between a modulation vibration for modulation the carrier oscillation of the transmitter and the demodulated reception oscillation obtained after transmission over the measuring section to the receiver and demodulation in the receiver is measured and has already been demonstrated in general terms in connection with the Michelson experiment,

   that on the basis of the Galilei transformation, taking into account the Doppler effect, results in a phase shift of the vibration caused in the receiver by the received electromagnetic waves compared to the vibration generated by the transmitter, which is independent of the movement speed v of the transmitter and receiver-carrying inertial system and independent the angle alpha between the transmission path from the transmitter to the receiver and the direction of movement of the inertial system is exactly the same as the phase shift resulting at v = 0 and thus corresponds exactly to the distance a between the transmitter and receiver and, as a result, the high measuring accuracy of the one-way range finder can be expected from the start was.



  However, this general proof only referred to unmodulated vibrations, as used in the Michelson experiment, but with unmodulated vibrations, as with the Michelson experiment, one can only measure less than 2 differences in the phase shifts occurring over two different transmission paths, while one measures the absolute phase shift over one Transmission path requires a modulated oscillation with a "wavelength" of the modulation oscillation that is greater than the length of the transmission path, because the measurement result for phase shifts of more than one wavelength or more than 2 would no longer be unambiguous.



   It should therefore be shown in the following using a derivation of the same type as in the above general proof that the same applies to modulated vibrations as to unmodulated vibrations, i.e. the phase shift of the carrier vibration caused by the received electromagnetic waves in the receiver compared to the carrier vibration generated by the transmitter and the phase shift of the demodulated received vibration compared to the modulation vibration on the transmitter side, regardless of the movement speed v of the inertial system carrying the transmitter and receiver and regardless of the angle alpha between the transmission path from the transmitter to the receiver and the direction of movement of the inertial system, is exactly the same as the phase shift that results at v = 0 and so that it corresponds exactly to the distance a between transmitter and receiver:



  To simplify the illustration, an amplitude-modulated oscillation should be considered in which the initial zero crossing of a sinusoidal carrier oscillation FTräg (t) = Asin omega ot at time t = 0 with the initial zero crossing of a sinusoidal modulation oscillation
 
EMI43.1
  coincides and the amplitude-modulated oscillation resulting from the modulation of the carrier oscillation with the modulation oscillation
 
EMI43.2
  is composed of the superposition of three unmodulated oscillations, namely the carrier oscillation with the frequency fo, the upper sideband oscillation with the frequency
EMI43.3
  and the lower sideband frequency
EMI43.4
 For the transmission from the transmitter to the receiver, each of these three unmodulated vibrations can now be considered individually,

   and thus on the transmission path for the frequency f of the carrier wave the frequency (f + fm) of the upper sideband wave and the frequency (f - fm) of the lower sideband wave result according to the derivations carried out above in connection with the Michelson experiment
EMI43.5
 



  with which the transmission of the amplitude-modulated vibration within a moving inertial system from a transmitter permanently stationed in the inertial system via the transmission link to a receiver stationed in the inertial system can be mathematically represented in its individual phases as follows:



  Electromagnetic vibrations generated by the transmitter
EMI43.6
 
EMI44.1
 



  Electromagnetic waves emitted by the transmitter on the transmission path at the transmitter location, due to the Doppler effect in the radiation by a factor
 
EMI44.2
 changed frequencies from the oscillation frequency fo of the carrier oscillation to the frequency f of the carrier wave and from the oscillation frequency
 
EMI44.3
  the upper sideband oscillation to the frequency (f + fm) of the upper sideband wave and from the oscillation frequency
EMI44.4
  the lower sideband oscillation to the frequency (f - fm) of the lower sideband wave
EMI44.5
 



  Electromagnetic waves emitted by the transmitter onto the transmission link at the location of the receiver stationed at the end of the transmission link at a distance a from the transmitter after passing through the transmission link with the phase shifts of the carrier wave corresponding to the length a of the transmission link
EMI44.6
 
 



  the upper sideband wave
EMI44.7
 
EMI45.1
 and the lower sideband wave
EMI45.2
 
EMI45.3
 



  Electromagnetic vibrations in the receiver caused by the received electromagnetic waves as a result of the cancellation of the Doppler effect on reception by a factor
 
EMI45.4
 changed frequencies from the frequency f of the carrier wave to the oscillation frequency fo of the carrier oscillation and the frequency (f + fm) of the upper sideband wave to the oscillation frequency
EMI45.5
 the upper sideband oscillation and from the frequency (f - fm) of the lower sideband wave to the oscillation frequency
EMI45.6
 the lower sideband vibration
EMI45.7
 
EMI46.1
 



  For the phase shifts
EMI46.2
 the carrier oscillation Asin caused in the receiver by the received waves
EMI46.3
  compared to the carrier oscillation Asin omega ot generated by the transmitter and the demodulated reception oscillation caused by the received waves in the receiver
EMI46.4
 compared to the modulation vibration generated by the transmitter m. sin omega mot results
EMI46.5
 



  and as can be seen, these phase shifts are exactly the same as the phase shifts, regardless of the movement speed v of the inertial system carrying the transmitter and receiver, and regardless of the angle alpha between the transmission path from the transmitter to the receiver and the direction of movement of the inertial system
EMI46.6
 
 which would result at v = 0 with the wavelengths lambda o and lambda mo over the transmission path a, and thus correspond exactly to the distance a between transmitter and receiver.



  The two phase shifts measure in radio-based rangefinders
 
EMI47.1
 only the phase shift
EMI47.2
 the demodulated receive oscillation compared to the modulation oscillation on the transmitter side, since only
EMI47.3
 Due to the "wavelength" lambda mo of the modulation oscillation which is greater than the length a of the measuring section, a clear measurement result lying in the range from 0 to 2
 
EMI47.4
 delivers. Because a "wavelength"
 
EMI47.5
  is - more correctly an oscillation period
EMI47.6
  the modulation oscillation) corresponds to a phase shift of 2, the measured phase shift corresponds
EMI47.7
 exactly the length a of the measuring section to be measured.

  To achieve the measurement accuracy of 10 mentioned <-> However, the phase shift must be <6>
EMI47.8
 can be measured precisely on angular seconds and the frequency accuracy of the modulation frequency is better than 10 if possible <-> <7>, which would be associated with considerable difficulties in the case of pure amplitude modulation and is therefore realized in the radio-technical one-way range finders by means of pulse code modulation with a repetition frequency of the entirety of the code signals representing a "modulation oscillation" representing the "modulation frequency".



   Because the measured phase shift
EMI48.1
 the demodulated receive oscillation compared to the modulation oscillation on the transmitter side, as demonstrated above, regardless of the movement speed v of the inertial system carrying the transmitter and receiver and regardless of the angle alpha between the measuring path and the direction of movement of the inertial system
 
EMI48.2
 exactly the same as the phase shift
EMI48.3
 which would result at v = 0, the measured length a of the measuring section is also included
 
EMI48.4
 equal to the product of the propagation speed c of electromagnetic waves and the transit time
 
EMI48.5
 which would result at v = 0, i.e. the general idea

   that with radio one-way range finders indirectly via the phase shift
EMI48 / 6
d of 4 minutes each (corresponding to 1 DEG earth rotation) and the measurement values of the individual measurements are stored for 6 hours each and then combined with measurement values of the measurement carried out after 6 hours to calculate the amount and direction of the speed of movement of the earth, so that then receives 90 values for the magnitude and direction of the speed of movement of the earth, from which extreme values are eliminated and mean values are formed from the remaining values and thus all uncertainties can be eliminated,

   but when carrying out the measurements in the equator area, the total costs for the measuring device and the carrying out of the measurements are influenced only relatively slightly by the number of receivers required for the measuring device, so that the advantage of a restriction to four receivers is of little importance even if possible disadvantages of this limitation as the mentioned measurement uncertainties can be eliminated.



  If one therefore decides to carry out measurements in the equatorial range, it is more expedient to use a larger number of receivers instead of such a restriction to four receivers and thereby to enable an improved procedure which enables a direct measurement of approximate values of the amount and direction of the speed vector allows absolute earth movement and thus also brings with it a greater sensitivity:



  In principle, this improved procedure is based on the fact that, as with the above-mentioned variant of the procedure with 4 receivers, a measurement is carried out every 4 minutes or after 1 DEG earth rotation and the number of receivers and thus the number of transmission link pairs is increased so much that in one of these measurements one of the transmission link pairs has almost the same direction as the speed vector of the absolute earth movement and thus the angle alpha becomes so small that cos alpha can be set to 1 with good accuracy and the two relationships mentioned above for
EMI59.1
  for the relevant measurement and the relevant transmission link pair are as follows:
EMI59.2
 



  The number of receivers required with this improved procedure depends on the accuracy that the approximation value resulting from the direct measurement of
EMI59.3
 should have. If, for example, 24 receivers E are used, which, as shown schematically in FIGS. 6 and 7, are evenly distributed near the equator in a plane essentially parallel to the earth's surface on a circle with the radius R around the transmitter S, then the angular distance between two neighboring ones is Receivers 360 DEG / 24 = 15 DEG and thus the maximum possible directional deviation between the direction of the speed vector of the absolute earth movement and the direction of the mentioned transmission link pair, which in the above measurement has almost the same direction as the speed vector of the absolute earth movement,

   half 7.5 DEG of this angular distance 15 DEG, so that alpha is a maximum of 7.5 DEG and thus cos alpha is a minimum of 0.9914 and the maximum measurement error
 
EMI59.4
 0.008634 = 0.8634% is therefore less than 1% for 24 recipients. Accordingly, a maximum measurement error of less than 2% would result for 16 receivers, a maximum measurement error of less than 5% for 10 receivers and a maximum measurement error of less than 10% for 8 receivers.



  In the exemplary embodiment of a device for carrying out the present measuring method in the above-mentioned improved method, which is shown schematically in FIGS. 6 and 7, 24 receivers E are provided, which are in the plane 3 essentially parallel to the surface 1 of the earth 2 on a circle with the radius R are evenly distributed around the transmitter S at an angular distance of 15 °. The transmitter S is arranged at a height h above the equator of the earth 2 and lies in the same plane 3 as the receiver E, of which the earth axis 4 corresponds over its entire length to the sum of the transmitter height h and half the earth diameter D / 2 has constant distance (h + D / 2).

  The transmitter S emits an electromagnetic wave in the form of a light pulse in the course of 12 hours, preferably every 4 minutes during the night or in each case after 1 DEG earth rotation in all directions of level 3 over a relatively short period of time, which is generally significantly less than one second out. From each of the 24 receivers E distributed in a circle around the transmitter S, the exact arrival time of the electromagnetic wave or the light pulse emitted by the transmitter S is determined and registered, to the extent possible to 0.1 ns, but in any case to significantly less than 1 ns exactly.

  The registered arrival times are then forwarded in the pause between two light pulses emitted by the transmitter to a control and evaluation center, where the time difference DELTA t of the registered arrival times of the wavefront is formed for each pair of receivers E diagonally opposite one another at an angle of 180 ° is saved.

  From the largest in terms of amount of all the time differences DELTA t, which are formed from the arrival times determined during the 12 hours, and the distance a between the transmitter S and the receiver E corresponding to the radius R, the scalar amount of the speed vector of the absolute movement of the earth in space can then be obtained or its ratio
EMI60.1
 to the propagation speed c of electromagnetic waves with an accuracy of 1% from the above for
EMI60.2
  derived relationship to
EMI60.3
 



   be determined. The direction of this speed vector corresponds approximately to the direction in which a vector points from the transmitter S to the receiver E with the larger of the two arrival times at the time the two arrival times with the greatest time difference DELTA t mentioned. A more precise determination of the direction can be made with the help of the above relationship
 
EMI60.4
 or in the present case with a = R using the relationship
EMI61.1
 from the other stored time differences DELTA t and the spatial directions resulting from the assigned transmission times and the position of the assigned receiver pairs. It is also possible in this way to determine the absolute value of the speed vector more precisely, provided the time differences DELTA t can be determined with greater accuracy than 1%.



  How big the distance a between transmitter S and receivers E or the radius R has to be made depends primarily on how big the speed v of the absolute movement of the earth in space or how big this speed of the absolute earth movement presumably determining speed of the absolute movement of our galaxy in space, and also of the accuracy with which the time difference DELTA t should be measured and how small the time units can be made in which the time difference DELTA t is measured.



  As the smallest possible unit of time in which the time difference DELTA t can be measured, the duration of a half-oscillation of the natural oscillation occurring in an atomic clock should probably be assumed at present, e.g. for a cesium atomic clock with a natural frequency of 9 192 631 770 Hz or a natural oscillation period of approx. 0.10878 ns, the smallest possible time unit of 0.05439 ns. If one further assumes that the time difference DELTA t should be measured with an accuracy that should be approximately 1% in the worst case, then the time difference DELTA t that is to be measured must not be significantly less than 100. 0.05439 ns, i.e. not less than 5.5 ns.

  In the extremely unlikely event that the speed of the absolute movement of our galaxy would be zero, the lowest possible speed of the absolute movement of the earth in space is the orbital speed of the sun around the center of our galaxy, i.e. 250 km / s. In this case it would result from the relationship above
EMI61.2
 a minimum required radius R or a minimum required distance a between transmitter S and receivers E of
 
EMI61.3
 surrender.



  However, it is certainly not to be assumed that the speed of the absolute movement of our galaxy in space is zero, but, as already mentioned above, it is more likely that due to the relatively high relative speeds of other galaxies compared to our galaxy of up to 50,000 km / s, that the speed of the absolute movement of our galaxy in space is a multiple of the orbital speed of the sun around the galaxy center and is probably well over 1000 km / s.

  Assuming the geometric mean between the highest possible speed of approx. 250,000 km / s and the lowest possible speed of approx. 250 km / s, the speed of the absolute movement of our galaxy should be around 7900 km / s, and if one would assume that the ratio of the speed of the galaxy to the speed of the sun around the galaxy center would be about the same as the ratio of the speed of the sun around the galaxy to the speed of the earth around the sun, if the speed of the absolute movement of our galaxy was about 2000 km / s.

  With regard to the measured relative speeds to other galaxies, it can therefore be assumed that the speed of the absolute movement of our galaxy is probably in the range of around 1000 km / s to 10,000 km / s, i.e. on average around 5000 km / s should lie. This estimate of the speed of the absolute movement of our galaxy is important because at galaxy speeds of 5000 km / s and more, at which the speed of the absolute movement of the earth is practically equal to the galaxy speed, for a measuring accuracy of approx. 1% at least required distance a between transmitter S and receivers E or the minimum required radius R to approx.

   Would decrease 50 m, which would eliminate the difficulties highlighted above with the arrangement of receivers at a height of several kilometers and also the necessity of arranging the measuring device in the equator area to avoid these difficulties.



  For these and other reasons such as the possibility of dispensing with such small units of time as the 0.05 ns mentioned as a measuring unit for DELTA t, and the resultant possibility of dispensing with extremely costly cutting-edge technology for the construction of the receivers in the case of speeds of absolute earth movement over 5000 km / s Before setting up the measuring device described above to carry out the present measuring method with 24 receivers, it is advisable to carry out a preliminary test in which range the speed of the absolute earth movement is approximately.

  For such a test, a measurement accuracy of 10% would be sufficient in the worst case (i.e. at a speed of the absolute earth movement of only 250 km / s), so that one could get by with a distance a between transmitter and receiver of approx. 100 m. In addition, such a test would only require a single pair of transmission links with a transmitter and two receivers, which could be arranged approximately parallel to the earth's surface in Central European latitudes, as indicated by dashed lines in Fig. 6, namely at an angle of 54.73561 ° to the earth's axis in a north-south direction.

  With such an arrangement of the transmission link pair, a first direction which the transmission link pair takes at a first point in time is at right angles to a second direction which the transmission link pair takes up 8 hours after the first point in time, and both the first and the second direction are at right angles to one another third direction, which the transmission link pair takes 16 hours after the first point in time, so that with three measurements at intervals of 8 hours each from the three measured time differences DELTA t1, DELTA t2 and DELTA t3, the speed v of the absolute movement of the earth in space increases
EMI63.1
  can be determined and the direction of movement of the absolute earth movement in the form of 3 angles
EMI63.2
 



   between the speed vector of the absolute earth movement and the mentioned first, second and third direction. To eliminate measurement uncertainties, a measurement can be carried out in the same way as explained above every 4 minutes or after every 1 DEG earth rotation, whereby then three time differences DELTA t measured at intervals of 8 hours each determine the size and direction form the time differences DELTA t1, DELTA t2 and DELTA t3 of the speed vector of the absolute earth movement. In this way, 120 values are obtained for the amount and direction of the earth's speed of movement, from which the extreme values are then eliminated in order to eliminate measurement uncertainties and mean values are formed from the remaining values.

  Since such a transmission link pair, as previously mentioned, would only have a length of 2,100 m = 200 m and could be arranged approximately parallel to the earth's surface in Central European latitudes, such a test device could be installed with only one transmission link pair or with only one transmitter and 2 receivers without difficulty on the site of a university and would still be within the budget range of university institutes in terms of cost.



  If, however, this cost for a test device is to be avoided at first, one could also use the "Global Positioning System" that has now been set up for a first estimate of the amount and direction of the speed of the absolute movement of the earth in space.

  To do this, one would have to use a so-called "precision code receiver", which firstly receives the exact positions of three satellites at the time of their start of radiation as well as the exact times of the start of radiation by receiving the so-called "navigation messages" and secondly the time shift tbias of the " precision code receiver "existing quartz clock compared to that applicable to the satellites,

   time "tsv" as "GPS time" is determined and via the "navigation massages" the time deviations DELTA tsv applicable to the individual satellites are also transmitted by tsv and therefore for each of the three satellites in addition to the exact position of the satellite at the time of its radiation start and the exact time of the start of radiation can also deliver the exact time in time units of ns for the satellite in question, including its time deviation DELTA tsv.

  With the exact positions of the three satellites at the time of their start of radiation as well as the respective position of a separate receiver arranged on the earth, the distances a1, a2 and a3 of the three satellites from the receiver at the time of their start of radiation and the fictitious from these distances Terms
 
EMI65.1
 from the three satellites in their positions at the time of their start of radiation to the receiver located on earth.

  These fictitious transit times plus transit time errors, which are caused by tropospheric and ionospheric refraction, are determined within the "precision code receiver" from the measured phase shifts of the demodulated received signal compared to the comparison signal generated in the "precision code receiver" and to that of the "precision code receiver" issued position of the same processed. Conversely, the stated runtime errors or their percentage of the fictitious runtimes can be calculated from this output position and the actual position.



  The real terms
EMI65.2
 cannot, however, be determined with the "precision code receiver", because it is not the transit time but the phase shift that is measured, and the transit time is then determined from the measured phase shift, and as has already been demonstrated above, it is not the real but the fictitious one running time
 
EMI65.3
 To measure the real transit times, therefore, a separate receiver is required, which measures the time of arrival of the wavefront sent by the satellite at the start of the radiation at the receiver. Such a measurement is of course only possible if such a wavefront actually exists.

  Now, with the "Global Positioning System", the individual satellites transmit during different, non-coinciding time periods, so that pauses are switched on for each individual satellite between successive transmission time periods and accordingly there is a start of radiation at the beginning of each transmission time period, but also during the pauses in the satellite the carrier is switched off (which would undoubtedly make sense for reasons of energy consumption) or whether only the modulation is switched on at the beginning of the radiation and the carrier remains switched on even during the breaks, could not be determined.

  In the latter case, switching on the modulation would also form a wavefront, but it would be much weaker than if the carrier and modulation were switched on at the same time, and given the fact that the modulation level in GPS is below the natural noise level, it is very likely no longer in the receiver would be perfectly identifiable. So here is a possible handicap for the use of the GPS system for a first estimate of the speed of the absolute earth movement, but this may be overcome by a temporary special control of the satellites caused by the GPS control station to switch off the carrier during the pauses in the transmission of the satellites could, if the control station would be able to do such a control at all.

  However, if it is assumed that a clear wavefront is emitted each time a satellite begins to emit radiation, then the necessary precautions must also be taken so that the wavefront can be clearly identified at the receiving location. For this purpose, a receiver with a pronounced directivity, e.g. uses a horn antenna with a cavity resonator connected directly to the base of the horn, which is precisely aligned with the position of the satellite at the time of the radiation of the wavefront. With such a directional receiver, the modulation level can even be raised so far from the natural noise level that the wavefront caused by the mere activation of the modulation (without switching off the carrier during the breaks) can also be identified.

   The real transit time tL between the time of the emission of the wavefront from the satellite and the arrival of the wavefront at the receiver is then determined in such a way that by means of the precise time, which is output by the "precision code receiver" and is valid for the satellite concerned, at the same time as that of the "precision code supplied "the time of the radiation of the wavefront from the satellite, the supply of counting pulses to a counter is switched on and at the time of the arrival of the wavefront at the receiver by means of a NAND gate located in the counting pulse line and connected via a GHz amplifier to the coupling loop of the cavity resonator is turned off.

  With the measured real transit time tL and the fictitious transit time determined in the manner described above from the position of the satellite supplied by the "precision code receiver" and the position of the receiver
 
EMI67.1
  then becomes the difference
EMI67.2
  between real and fictitious term determined
EMI67.3
 



  results. With the three spatial directions, which result from the positions of the three satellites provided by the "precision code receiver" and the position of the receiver for the three transmission links from the three satellites to the receiver, and which result from the above relationship for
 
EMI67.4
  resulting relationship
EMI67.5
  between the maturity differences
EMI67.6
  On the three transmission paths and the angles alpha 1, alpha 2 and alpha 3 between these transmission paths and the speed vector of the absolute earth movement, the amount and direction of the speed vector of the absolute movement of the earth in space can then be determined according to the rules of spherical trigonometry.

  However, it should be noted that this only results in a relatively rough approximation for the amount and direction of the speed vector sought, because the runtime errors mentioned above, which are caused by tropospheric and ionospheric refraction, are included in the measured runtime values tL and the differences Can significantly falsify DELTA tL.

  You would therefore have the fictitious terms
EMI68.1
  Correct in the manner indicated above with the aid of the position output by the "precision code receiver" and the actual position of the receiver so that the runtime errors resulting from refraction are compensated for, and then with these corrected fictitious runtimes the differences DELTA tL between real and fictitious Determine the transit time and then the amount and direction of the speed vector sought in order to obtain an at least reasonably correct approximate value which could then serve as the basis for the design of the test device described above.

  With the help of the "Global Positioning System" and an additional simple microwave directional receiver, it could only be proven in principle that the speed of the absolute movement of the earth in space is measurable and in what order of magnitude it is, while for more precise measurements at least the effort for the test device described above with two oppositely directed transmission lines of the same length and atomic clocks in the receivers at the ends of the two transmission lines would have to be driven.



  This shows in FIG. 8 how such a device for carrying out the present measurement method, such as said test device with a transmitter and two receivers or the embodiment schematically shown in FIGS. 6 and 7 with a transmitter and 24 receivers, can advantageously be designed in detail Block diagram shown of the structure of such a measuring device or more precisely a pair of transmission links of such a measuring device with a transmitter 5 and two identically designed receivers 6 and 7, which are arranged in opposite directions at the same distance a or R from the central transmitter 5 (in which in Fig 6 and 7 are 12 such transmission link pairs with 24 receivers E and a central transmitter S in an arrangement as provided in FIG.



  In the measuring device in FIG. 8, the transmitter 5 comprises a laser beam source 8, preferably a neodymium giant pulse laser with a pulse duration of 1 ns and a power during the pulse duration of 109 W (energy radiation 1 Ws / pulse), a laser beam coaxial with the laser beam axis 9 conical mirror 10 with a cone opening angle of 90 ° and the conical mirror 10 ring-shaped surrounding beam limiting means, which are formed by two truncated cone-shaped reflection-free boundary surfaces 11 and 12 with a cone opening angle beta, which is at a transmitter height h above the ground 13 and a distance a or R the receiver 6 and 7 from the transmitter 5 at least
 
EMI69.1
 and a control and evaluation center integrated in the measuring device in FIG. 8 in the transmitter 5.



  This control and evaluation center comprises in its control part in detail as control means for controlling the times of the radiation of electromagnetic waves or laser pulses from the transmitter 5 and for activating the receivers 6 and 7 shortly before and for deactivating them shortly after the radiation of a laser pulse Quartz oscillator 14 acting as a timer with an oscillation frequency of 17.954359 MHz, the 32-stage binary counter 15 working as a frequency divider with a cut-off frequency of 100 MHz, which reduces the frequency of the oscillator 14 to a frequency of approx.
EMI69.2
   Hz at the counter output or

   reduced to output pulses of the counter every 4 minutes (sidereal time), the bistable multivibrator 16 which serves to initiate the radiation of the laser pulses from the transmitter 5 and to activate and deactivate the receivers 6 and 7, which serves as a timer for the activation phase of the receivers 6 and 7 and in the same falling triggering of the laser pulse serving oscillator 17 with an oscillation frequency of 65.536 kHz, the AND circuit 19 serving to connect the output of the oscillator 17 to the counting input of the counter 18 and the 16-stage counter 18 operating as a frequency divider with a cutoff frequency of 250 kHz, which the frequency of the oscillator 17 to a frequency of 1 Hz at the counter output or

   to output pulses of the counter 18 at its one counter output 20 one second after switching through the AND circuit 19 and at its other counter output 21 half a second after switching through the AND circuit 19, and the connecting line 22 from the output of the oscillator 14 to the input of the counter 15 for transmitting the oscillator vibrations as counting pulses to the counter input, the connecting line 23 from the output of the oscillator 17 via the AND circuit 19 to the input of the counter 18 for transmitting the oscillating vibrations as counting pulses to the counter input, the connecting line 24 from the output of the counter 15 to the switch-on input of the bistable multivibrator 16 for transmitting the output pulse of the counter 15, which occurs every 4 minutes, as a switch-on pulse to the bistable multivibrator 16, the connecting lines 25, 26,

   27 and 28 from the output of the bistable multivibrator 16 to the reset input of the counter 16 and the switching input of the AND circuit 19 for transmitting the output signal of the bistable multivibrator 16 as a reset pulse to the counter 18 and as a switching signal to the AND circuit 19, the connecting line 29 to Connection of the output of the bistable multivibrator 16 via the connecting line 25 with the control signal lines 30 leading to the receivers 6 and 7 for transmitting the output signal of the bistable multivibrator 16 via the connecting lines 25 and 29 and the control line 30 as an activation signal to the receivers 6 and 7 Connection lines 31 and 32 from the 1 output of the counter 18 to the trigger signal input of the laser beam source 8 for the transmission of the half-second after the AND circuit 19 has been switched through,

   the laser pulse triggering an output signal of the counter 18 to the laser beam source 8 and the connecting line 33 from the 0 output of the counter 18 to the reset input of the bistable multivibrator 16 for the transmission of the other output signal of the counter which takes place one second after the AND circuit 19 has been switched on and serves as a reset pulse 18 to the bistable multivibrator 16.



  In its evaluation section, the control and evaluation center integrated in the transmitter 5 comprises in each case two computing means for calculating the approximate amount and direction of the speed vector of the absolute movement of the earth in space, two 24-stage binary counters 34 and 35 working as pulse counters with a cutoff frequency of 1 MHz for each transmission link pair from two oppositely directed transmission links of the same length or the associated receiver pair 6, 7 for taking over and counting pulses from the associated receivers 6 and 7, the total number z1 and z2 of the transmission duration on the one or

   corresponds to the other of the two transmission links of the respective transmission link pair, and a computer 36 for forming the difference DELTA z = z1 - z2 between the counter readings z1 of the counter 34 and z2 of the counter 35 reached after the end of the counting and for storing the differences DELTA z of all transmission link pairs or

   All associated receiver pairs 6, 7 after each of the measurements that take place every 4 minutes and for storing the exact times of the individual measurements supplied by an integrated clock and for determining the direction of each transmission link pair in space for each measurement from these times and for storing the assigned spatial direction each saved DELTA z and also to calculate the amounts <SEP> DELTA e.g. <SEP> of the differences DELTA z and to compare them and to save the largest difference in terms of amount <SEP> DELTA e.g. <SEP> after each measurement and to compare these largest differences in terms of amount <SEP> DELTA e.g. <SEP> of the individual measurements to determine the maximum difference in amount <SEP> DELTA e.g. <SEP> max of all measurements and to determine the amount of speed v of the absolute movement of the earth

   in space according to the relationship v = <SEP> DELTA e.g. <SEP> max. Tz. c <2> / 2R from the difference <SEP> DELTA e.g. <SEP> max, the propagation speed c of electromagnetic waves, the transmitter-receiver distance R (or a) and that of a counting unit of <SEP> DELTA e.g. <SEP> max assigned time period Tz and for determining the direction of the speed vector of the absolute movement of the earth in space by interpolation between the DELTA z values surrounding the difference DELTA zmax and the assigned stored directions.

  Furthermore, the control and evaluation center integrated in the transmitter 5 includes in its evaluation part the display device 37 for displaying the values of the amount and direction of the speed vector of the absolute movement of the earth in space determined by the computer 36, the connecting lines 38 and 39 from the counters 34 and 35 to the computer 36 for transferring the counter readings of the counters 34 and 35 to the computer 36, the connecting line 40 for connecting the 1 output of the counter 18 via the connecting line 31 to the computer 36 for transmitting the laser pulse that triggers the laser pulse and thus the time of the measurement determining an output signal of the counter 18 to the computer 36, the connecting line 41 from the computer 36 to the display device 37 and the connecting lines 42, 43,

   44 and 45 from the computer 36 to the reset inputs of the counters 34 and 35 and the control signal line 46 for transmitting a reset signal output by the computer 36 after the acceptance of the counter readings z1 and z2 of the counters 34 and 35 and the processing of the same to the counters 34 and 35 as well via the control signal line 46 to the receivers 6 and 7.



  The receivers 6 and 7 provided in the measuring device in FIG. 8 (and a further 22 such receivers in the exemplary embodiment shown schematically in FIGS. 6 and 7) are, as already mentioned, of identical design and form the one belonging to a pair of transmission links with oppositely directed transmission lines of equal length Receiver pair (12 such receiver pairs are provided in the embodiment in FIGS. 6 and 7).

   Each of these identically designed receivers, that is to say the receivers 6 and 7 in FIG. 8, comprises a photocell 47 which responds without delay and has a response time of less than 0.01 ns and a cut-off frequency above 100 GHz for receiving the laser pulses emitted by the transmitter 5 separate power supply 48 for the photocell 47, which is switched on via the control signal line 30 from the control part 14-33 of the control and evaluation center 14-46 integrated in the transmitter 5 about half a second before the radiation of a laser pulse and about

   half a second after this radiation is switched off again, a threshold circuit 49 connected to the signal output of the photocell 47 with a cut-off frequency of 100 GHz and a threshold value which, to avoid incorrect measurements, is five to ten times the level of the output signal of the photocell 47 at maximum daylight case, a NAND gate 50 connected to the output of the threshold circuit 49 with a cut-off frequency of 100 GHz for interrupting the counting pulse transmission via the counting pulse line 51, a cesium atomic clock 52 operating as a timer with a vibration frequency of 9.19263177 GHz and one of the atomic clocks in the satellites of the "Global Positioning Systems" corresponding frequency constancy of 10 <-> <1> <8>,

   which emits pulses with a repetition frequency of 18.38526354 GHz as counting pulses (their pulse repetition frequency is achieved by multiplying the frequency of the actual oscillator frequency of the cesium atomic clock by approx. 10 MHz), a 41-stage binary counter 53 working as a frequency divider with a cutoff frequency of 100 GHz, which the pulse repetition frequency of the counting pulses delivered by the atomic clock 52 to a frequency of 0.00836064989 Hz at the counter output or

   reduced to the output pulses of the counter 53 every two minutes (sidereal time), another 20-stage binary counter 54 serving as a time indicator with a cut-off frequency above 1 kHz to indicate the time since the synchronization of the atomic clocks 52 of all receivers one after the other in time units of 2 minutes, one with its Counting input connected to the counting pulse line 51 is a 24-stage binary counter 55 with a cut-off frequency of 100 GHz, which is stopped when a laser pulse arrives at the photocell 47 as a result of the interruption of the counting pulse line 51 caused by the photocell 47 and caused by the NAND gate 50, and therefore the specifies the exact time of arrival of a laser pulse in time units of 0.05439 ns, one for counting the count of the counter 55 after the interruption of the pulse line 51,

   also 24-stage binary counter 56 with a cut-off frequency of 1 MHz, an oscillator 57 serving as a counting pulse generator for the counter 55 with an oscillation frequency of 200 kHz, an AND circuit 58 serving to connect the output of the oscillator 57 to the counting input of the counter 56, one for Comparison of the incrementally increasing counter reading of the counter 56 with the counter reading of the counter 55 serving after the interruption of the counting pulse line 51, on the input side connected to all the counting stages of the two counters 55 and 56, with a limit frequency of 2 MHz and a minimum for a response of the Comparator circuit 59 required corresponding minimum comparison period of 0.5 micros, one connected on the input side to the output of the threshold circuit 49,

   for outputting a stop signal to the NAND gate 50 and a switching signal to the AND circuit 58 provided bistable multivibrator 60 with a cutoff frequency of 10 GHz, a connecting line 61 from the output of the oscillator 57 via the AND circuit 58 to the input of the counter 56 Transmission of the oscillator oscillations as counting pulses to the counter input, a signal line 62 connected between the AND circuit 58 and the counter 56 to the connecting line 61 for the transmission of the oscillator oscillations emitted by the oscillator 57 via the AND circuit 58 as counting pulses to the counting input of the counter 34 respectively.

   35, the connecting lines 63, 64 and 65 from the output of the threshold circuit 49 to the switching input of the NAND gate 50 and the switch-on input of the bistable multivibrator 60 for transmitting an output signal of the threshold circuit 49 as an interrupt signal to the NAND gate 50 and as a switch-on signal to the bistable multivibrator 60, the connecting lines 66, 67 and 68 from the output of the bistable multivibrator 60 to the switching input of the AND circuit 58 and via the further connecting line 64 to the switching input of the NAND gate 50 for transmitting the output signal of the bistable multivibrator 60 as a switching signal to the AND circuit 58 and as a hold signal to the NAND gate 50,

   a connecting line 69 from the output of the comparator 59 to the reset input of the bistable multivibrator 60 for transmitting the output signal of the comparator, given the same count of the counters 55 and 56, from the comparator 59 as a reset signal to the bistable multivibrator 60 for the purpose of ending the switching through of the AND circuit 58 and Interruption of the count pulse line 51 through the NAND gate 50, a connection 70 from the count pulse output of the atomic clock 52 to the count input of the counter 53, the connections 71, 72 and 73 from the output of the counter 53 to the reset input of the counter 55 and to the count input of the counter 54 for transmission the output signal of the counter 53 as a reset pulse on the counter 55 and as a count pulse on the counter input of the counter 54, a connecting line 74 from which can be switched on via the control line 30,

   provided for the photocell 47 separate power supply 48 to the photocell 47 and a connecting line 75 from the signal output of the photocell 47 to the input of the threshold circuit 49 for transmitting the output signal of the photocell 47 to the threshold circuit 49 and the end of the control signal line 46 leading to the reset input of the counter 56 for transmission the reset signal output by the computer 36 after the counter readings of the counters 34 and 35 have been taken over and processed by the counter 56.



   The components and connections 49-53, 55, 60, 63-66 and 68-72 provided in the receiver 6 and 7 with cut-off frequencies in the range from 1 to 100 GHz are combined in an integrated circuit, which can achieve up to the high cut-off frequencies 100 GHz is implemented in the gallium arsenide technology developed for high-definition television for such high cut-off frequencies and expediently either also contains the photocell 47 as an integrated component or can also be arranged within an evacuated glass bulb surrounding the photocell 47, in the latter case To limit the number of supply lines to the glass bulb, the counter 56 and the comparator 59 can advantageously also be included in the integrated circuit.



  The mode of operation of the measuring device shown in FIG. 8 or more precisely the one pair of transmission links of such a measuring device shown in FIG. 8 is as follows:



  Before the measuring device is put into operation, all receivers and the transmitter of the measuring device are synchronized in that the counters 53 assigned to the atomic clocks 52 and the counter 15 assigned to the quartz oscillator 14 are simultaneously set to zero at the same location. For this purpose, e.g. a reset input to the counter 15 and each counter 53, not shown in FIG. Approx. 1 m long transmission line with a cut-off frequency of 100 GHz connected, and the free ends of the transmission lines of all receivers and the transmitter are brought together at one point and applied with a pulse of 0.01 ns pulse duration from a neodymium solid-state laser.

  The transit time of the pulses on these transmission lines from the point of application to the counter 53 or 15 is between 3.3 and 4 ns, depending on the relative dielectric constant epsilon rel of the dielectric in the transmission lines, but since the transmission lines are all of exactly the same length, they meet Pulse all at the same time or within a time range of less than 0.01 ns at the counters 53 of all receivers and the counter 15 of the transmitter, so that the counter 15 and the counter 53 (which are on the input side from the connected atomic clocks 52 with a Pulse sequence of approximately 0.05 ns pulse duration) are all set to zero at the same time and then that of the atomic clocks 52 or

   the counting pulses delivered to the quartz oscillator 14 count from zero, the counts of the counters 53 of all receivers because of the high frequency constancy of the atomic clocks 52 from FIG. 10 <-> <1> <8> are the same for almost 2 years at any point in time and only then can the counter readings of counters 53 differ from one another by one counting unit or approx. 0.05 ns.



  When the measuring device in FIG. 8 is started up, the power supplies of the receivers 6 and 7 and, if appropriate, all other receivers (apart from the separate power supplies 48 of the photocells 47) are already switched on because of the atomic clocks 52 and the counter 53 already running, the NAND gates 50 are switched through, the counters 55 run with the same counter reading as the counters 53, the counters 56 are at zero, the bistable multivibrators 60 are in the zero state, the AND circuits 58 are blocked, the oscillators 57 and the counters 54 run, the threshold value circuits 49 are ready for operation and the photocells 47 and their separate power supplies 48 are not switched on.

  Likewise, when the measuring device in FIG. 8 is started up, the power supply to the transmitter 5 is already switched on, the oscillators 14 and 17 and the clock integrated into the computer 36 are running, the computer clock is set to sidereal time, the counters 18, 34 and 35 are at zero, the AND circuit 19 is blocked, the bistable multivibrator 16 is in the zero state, the laser beam source 8, the computer 36 and the display device 37 are connected to voltage, and the bistable multivibrator 16 is not shown in FIG Set signal input constantly fed a set signal that holds the bistable multivibrator 16 in the zero state.



  For the commissioning of the measuring device in FIG. 8, this setting signal is switched off and the automatic further course of the measurements is started. The oscillator 14 outputs on the connecting line 22 to the counter 15 further counting pulses, which let the counter 15 continue to run until within the next 4 minutes after switching off the set signal via the connecting line 24 to the bistable multivibrator 16, which emits a switch-on pulse which bistable multivibrator 16 switches from the zero state to the 1 state.

  With this changeover to the 1 state, the bistable multivibrator 16 emits an output signal which, firstly, via the connecting lines 25, 26 and 27 as a reset signal to the counter 18, secondly via the connecting lines 25, 26 and 28 as a switching signal of the AND circuit 19 and third, via the connecting lines 25 and 29 and the control lines 30 as an input signal to the separate power supplies 48 for the photocells 47 in the receivers 6 and 7 and, if appropriate, all other receivers. The switch-on signal supplied to the power supplies 48 via the control line 30 switches on the separate power supplies 48 for the photocells 47 and thus activates the receivers 6 and 7 and, if appropriate, all further receivers.

  A reset pulse is obtained from the reset signal supplied to the counter 18 via the connecting line 27 by a differentiator provided at the reset signal input of the counter 18, which resets the counter 18 to zero. The switching circuit signal supplied to the AND circuit 19 via the connecting line 28 switches the AND circuit 19 and thus the counting pulse line 23 from the oscillator 17 to the counter 18, so that the counter 18 from the time when the bistable multivibrator 16 switches to the 1 state starts up and, starting from the zero reading, counts the oscillator vibrations emitted by the oscillator onto the counting pulse line 23.

   Half a second after the start of the count, the counter 18 outputs an output pulse to its counter output 21, which is fed via the connecting lines 31 and 32 to the trigger signal input of the laser beam source 8 and via the connecting lines 31 and 40 to the computer 36. With its integrated computer clock set to sidereal time, the computer 36 registers the exact point in time at which this output pulse of the counter 18 arrives via the connecting line 40, which at the same time forms the point in time at which a laser pulse is triggered at the laser beam source 8 and thus the point in time of a measurement,

   and from this registered point in time then calculates the direction of the transmission link pair formed by the transmitter 5 and the receivers 6 and 7 (and, if appropriate, all further transmission link pairs) in space at this time and stores this direction in a memory location, on which, after the measurement, it is then stored the amount of the velocity component of the velocity vector of the absolute earth movement falling in this direction is also stored. In addition, the output pulse of the counter 18 fed to the trigger signal input of the laser beam source 8 via the connecting line 32 triggers the emission of a laser pulse from the laser beam source 8 and thus the implementation of a measurement.

  Half a second after the measurement has been carried out or one second after the start of the count, the counter 18 then outputs an output pulse to its counter output 20, which is fed via the connecting line 33 to the reset input of the bistable multivibrator 16 and causes the bistable multivibrator 16 to be reset to the zero state . As a result, the output signal previously output by the bistable multivibrator 16 to the connecting line 25 is terminated, and thus the switching through of the AND circuit 19 and the supply of counting pulses from the oscillator 17 to the counter 18 are stopped, and also via the connecting lines 25, 29 and 30 also the separate power supplies 48 for the photocells 47 are switched off and thus the receivers 6 and 7 (and possibly all other receivers) are deactivated again.



  The measurement that takes place about half a second before this deactivation of the receiver begins with the emission of a laser pulse from the laser beam source 8. As already mentioned, a giant neodymium pulse laser with a pulse duration of 1 ns and a power during serves as the laser beam source 8 the pulse duration of 10 <9> W, as it has been used for distance measurement according to the radar principle for longer distances up to 30 km.

  The high pulse power of the laser beam source 8 is necessary so that the laser pulse arriving at the photocells 47 all natural light sources such as direct and reflected daylight and also all possible artificial light sources such as e.g. the headlights of cars, etc., far outshine them, thereby making it possible, by means of the threshold value circuit 49, to exclude a response of the receivers to such other light sources and thus to make incorrect measurements impossible. The pulse power of 10 <9> W is however designed for a length a or R of the transmission paths up to 30 km and can be limited if this transmission path length is limited to e.g. 3 km can be significantly reduced.

  In principle, the short pulse duration of only 1 ns can be attributed to the high pulse power, since such high powers of 1 GW cannot, of course, be maintained over a longer period. The short pulse duration of only 1 ns in connection with the high pulse power is of particular advantage for the present measuring method, since the measurement of the time of arrival of the laser pulse in the receiver, as already mentioned, in time units Tz = 0.05439 ns per counter unit of the counter 55 takes place and the rising edge of the incoming laser pulse should therefore be so steep that the relatively high threshold value of the threshold circuit 49 is exceeded within less than 0.1 ns or better still 0.05 ns, because with a pulse duration of only 1 ns Of course, you can expect the duration of the rising edge of the pulse to be less than 0.1 ns,

   and given the very high pulse power, it can also be expected that less than 50% of this rising edge will pass before the threshold value of the threshold value circuit 49 is exceeded. A comparison of FIGS. 9 and 9a to 9i with FIGS. 1 and 1a to 1i clearly shows that in the present measuring method the rising edge of a pulse is to be equated with the wave front of an electromagnetic wave, because such a comparison immediately reveals that the rising edge of a pulse emitted by transmitter S at each of the 9 points in time shown in these figures (t-to) = 0To to (t-to) = 8To at the same point in the area between transmitter S and receiver E as the wavefront of one of Transmitter S emitted electromagnetic wave.

  The same naturally also applies to a laser pulse of 1 ns pulse duration, which is a wave train of several hundred thousand successive electromagnetic waves with frequencies of the order of 10 <-> <1> Is <5> Hz and accordingly also has a real wavefront. In principle, the aforementioned comparison shows that it only depends on the wavefront of an electromagnetic wave emitted by transmitter S or on the rising edge of a pulse emitted by transmitter S, but not whether the transmitter emits the electromagnetic wave until the arrival of the Wavefront maintained at the receiver or not, or whether the pulse width of the pulse emitted by the transmitter is larger, smaller or significantly smaller than the transit time of the rising edge of the pulse from the transmitter to the receiver.

  For this reason, the short pulse duration of the laser pulse emitted by the laser beam source 8 of only 1 ns also has no adverse effects on the present measurement method or the measurement results achievable with it. The high pulse power of the laser pulse of 10 <9> W, on the other hand, makes it advisable to design the conical mirror 10 as a solid metal cone, which is ground and polished to a high gloss on its surface, since the full pulse power of 10 W falls on the conical mirror 10 at the moment of the laser pulse being emitted by the laser beam source 8 without such training there is a risk of damage to the mirror surface.

   The total energy of a laser pulse is 10 <9> W pulse power and 1 ns = 10 <-> <9> s pulse duration is only 1 Ws, but also the energy stored in a metal paper capacitor of 24 mu F charged to 300 V is only approx. 1 Ws, and nevertheless, with a breakdown of the same, the electrode gap of the metal paper capacitor can be 0.1 mm is readily possible to evaporate the entire electrode area in the breakdown area, which is known to be used deliberately in the so-called burnout of metal paper capacitors to eliminate defects in the dielectric. Despite the high pulse power of 10 <9> W, however, is the average power consumption of the laser beam source 8 with a laser pulse every 4 minutes, even with an efficiency of the laser beam source of only 0.1%, only about 4 W and thus negligibly low.



  The laser pulse emitted by the laser beam source 8 strikes at a length a or R of the transmission paths of 3 km (provided that
EMI81.1
  after approx. 10 microseconds for receivers 6 and 7, the time difference between the arrival at one and the other receiver 6 or 7, assuming an assumed speed of absolute earth movement of 5000 km / s, a maximum of approx. 333 ns or about 6129 time units Tz of 0.05439 ns and thus about 6129 counting units of the counters 55 provided in the receivers 6, 7.

  Immediately after the arrival of the laser pulse, the photocell 47, which responds without delay, emits an output pulse which is significantly above the threshold value of the threshold value circuit 49 within a time period of less than 0.1 ns, which depends on the duration of the rising edge of the laser pulse, and which unimpededly triggers the threshold value circuit 49 happens and is supplied via the connecting lines 63, 64 and 65 to the switching inputs of the NAND gate 50 and the bistable multivibrator 60 and the NAND gate 50 in the blocking state and the bistable multivibrator 60 in the 1 state.

  The NAND gate 50, when switched to the off state, interrupts the counting pulse line leading from the atomic clock 52 to the counter 55 within a period of less than 0.05 ns after the time at which the output signal of the photocell 47 exceeds the threshold value of the threshold circuit 49 51 and thus stops the counter 55 which has been running at the same counter reading with the counter 53 up to this point in time with a time delay of less than 0.1 ns after the laser pulse arrives at the photocell 47, so that the counter reading of the counter 55 now at the same time an inaccuracy of a counting unit indicates the time of arrival of the laser pulse at the photocell 47 or the receiver.

  This completes the actual measurement, and the subsequent processes only concern the saving of this measured value, the transmission of the same to the control and evaluation center and the evaluation carried out there, as well as the preparation of the receiver for the next measurement.

  To secure the measured value or to maintain the interruption of the counting pulse line 51 and thus to maintain the count of the stopped counter 55, the bistable multivibrator 60 switched to the 1 state simultaneously with the blocking of the NAND gate 50 delivers within a period of less than 0 , 1 ns after the blocking of the NAND gate 50 and thus still during the arrival of the approximately 1 ns lasting laser pulse at the photocell 47 via the connecting lines 66, 68 and 64, a stop signal to the switching input of the NAND gate 50, which the blocking of the NAND gate 50 is maintained even after the arrival of the laser pulse until the counter reading of the counter 55 has been transferred to the control and evaluation center and the bistable multivibrator 60 is switched back to the zero state by the comparator 59.

  The transfer of the counter reading of the stopped counter 55 to the counter 34 in the control and evaluation center takes place in that the oscillator 57 to the counter 56 via the counting pulse line 61 and the AND circuit 58, which are generated by the bistable multivibrator 60 at the moment of the switchover is switched through to the 1 state via the connecting lines 66 and 67, as long as supplies counting pulses until the counter 56 has reached the same counter reading as the counter 55, and the same counting pulses via the signal line 62 also to the counter 34 in the control and Evaluation center in the transmitter 5 feeds so that the counter 34 is constantly brought to the same counter reading as the counter 56.

  As soon as the counter 56 has reached the same counter reading as the counter 55, the comparator 59 connected to all the count stages of both counters 55 and 56 outputs a coincidence signal on the connecting line 69, which is fed to the bistable multivibrator 60 as a reset pulse and the bistable multivibrator 60 again set back to the zero state and thus the switching signal given by the bistable multivibrator 60 via the connecting lines 66 and 67 to the AND circuit 58 is ended, so that the AND circuit 58 is blocked and thereby the counting pulse line 61 is interrupted and thus the supply of Counting pulses from the oscillator 57 to the two counters 56 and 34 cease upon reaching the same counter reading as that of the counter 55.

  The count of the counter 55 located in the receiver is thus already transferred to the counter 34 located in the control and evaluation center in the transmitter 5. Simultaneously with the blocking of the AND circuit 58 or the termination of the switch-on pulse which until then has been delivered by the bistable multivibrator 60 to the AND circuit 58, that from the bistable multivibrator 60 is also transmitted to the NAND gate via the connecting lines 66, 68 and 64 50 stopped signal and the NAND gate 50 is switched through again so that the count line 51 is no longer interrupted and the counter 55 can therefore be supplied by the atomic clock 52 again via the count line 51 and the counter 55 therefore immediately after the reset of the bistable multivibrator 60 continues to the zero state,

   until, approximately 2 minutes after the arrival of the laser pulse at the photocell 47, at the moment when the counter 53 passes the counter reading 0, by a reset pulse at this point in time from the counter 53 via the connecting lines 71 and 72 to its reset input, also on the is brought to the current counter reading 0 and then again runs with the same counter reading with the counter 53.



  The maximum period of time for the transmission of counting pulses from the oscillator 57 to the counters 56 and 34, at just under one and a half minutes, is somewhat less than the two minutes after which the counter 55 is reset, so that the counter 55 is reset to the counter reading 0 during this transfer is excluded. A possible time shift of the maximum one and a half minute transmission time compared to the 2 minute reset time until an overlap of both times is also excluded because the quartz oscillator 14 in the reduction ratio 1: 512 = 1: 2 <9> runs synchronously with the atomic clock 52 and with the frequency constancy of the quartz oscillator 14 of FIG. 10 <-> <8> such time shifts are limited to fractions of a second per year.

  The time period of the transmission of counting pulses from the oscillator 57 to the counters 56 and 34, which appears to be relatively long, is related to the relatively large number of stages of the counters 56 and 34 of 24 binary stages and the relatively low oscillator frequency of the oscillator 57 of only 200 kHz. The large number of stages of the counters 56 and 34 is necessary, however, because a comparison of the counter readings of two counters by a comparator requires the same number of stages of the two counters and the counter 55 also has 24 binary stages and these 24 binary stages with time units of 0.05439 ns per counter unit are necessary with the present measuring device to determine the upper limit of the measuring range for the speed of the absolute earth movement of 250,000 km / s or
EMI84.1
 
 to reach.

  By increasing the oscillator frequency of the oscillator 57, however, a corresponding reduction of this one and a half minute counting pulse transmission time would be entirely possible, but with an increase in the oscillator frequency of the oscillator 57 and thus the counting frequency of the counter 56, an increase in the effort for the comparator 59 would also have to be accepted. which is unnecessary given that the one and a half minutes are available.



  The counter readings of the counters 55, which have been transmitted from all receiver pairs of the measuring device to the assigned counter pairs 34, 35 in the control and evaluation center after these one and a half minutes, are now processed by the computer 36. The computer 36 begins processing 90 s after the receipt of the signal indicating the time of the measurement and arriving via the connecting line 40. Before the actual evaluation, the computer 36 can possibly also check the correspondence of the counts of the counters 56 and 34 (or 35) via the line 46 for safety. The means necessary for this are not shown in FIG. 8 to simplify the representation in the measuring device.

  The evaluation begins with the transfer of the counter readings of the counter pairs 34, 35 assigned to the receiver pairs 6, 7 into the computer 36 and the formation of the difference z1-z2 of the counter readings of each counter pair. In order to take into account the possibility that one of the two counter readings of a pair of counters is slightly above the counter reading zero and the other is slightly below the counter reading zero, in the case of one close to the maximum counter reading 2 <2> <4> = 16 777 216 positive difference (z1-z2) subtract the maximum count from the difference and in the case of a negative difference close to the maximum count (z1-z2) add the maximum count to the difference to give the difference correct difference DELTA z = z1-z2.

  The differences ascertained by the computer are then stored in a signed manner on the storage locations already mentioned, on which the assigned directions and the measurement time are already stored. A negative sign of the difference DELTA z means that the speed component of the speed vector of the absolute earth movement corresponding to the difference points in the opposite direction to the stored direction.

  The computer 36 then checks the differences DELTA z determined during this measurement either by designing the measuring device with a multiplicity of receiver pairs (such as, for example, in the exemplary embodiment shown schematically in FIGS. 6 and 7) by comparing the different ones determined during this measurement Differences DELTA z assigned to one another, or if the measuring device is designed with only one pair of receivers, by comparing the correctness of the difference DELTA z determined in this measurement with the differences DELTA z determined in previous measurements (which, for example,

   by converting the DELTA z values into each other using the relationship
EMI85.1
 is possible due to the proportionality of DELTA t APPROX DELTA z) and does not exclude any obviously correct differences that do not fit into the frame by marking them in their assigned storage locations from further processing. In measuring devices with a large number of receiver pairs (as in FIGS. 6 and 7), the amounts are then of the remaining differences DELTA z recognized as at least approximately correct <SEP> DELTA e.g. <SEP> formed from which the difference with the highest amount <SEP> DELTA e.g. <SEP> is selected and saved separately.

  In the case of measuring devices with only one pair of receivers, in which there is only one difference DELTA z for each measurement, not only a difference DELTA z recognized as incorrect, but also the two assigned differences which result 8 and 16 hours later, are excluded from further processing. After marking the differences DELTA z recognized as incorrect, in their storage locations and, if necessary, searching out and separately storing the difference with the highest amount during the current measurement <SEP> DELTA e.g. <SEP>, the computer 36 still sends a reset pulse to the reset inputs of the counters 34, 35 and 56 via the connecting lines 42, 43, 44, 45 and 46, as a result of which these counters are reset to zero and the measuring device is thus set for a new one Measurement is ready.

   The computer 36 can advantageously store the separately stored highest amount <SEP> DELTA e.g. Pass on <SEP> or the speed v resulting from this for preliminary orientation via the connecting line 41 to the display device 37, which displays this speed v if it is greater than the previously displayed speed v.



  In the case of measuring devices with a large number of receiver pairs, a series of measurements, i.e. after 180 measurements, from the separately stored 180 highest difference amounts <SEP> DELTA e.g. <SEP> of the individual measurements the maximum difference in amount <SEP> DELTA e.g. <SEP> max selected and from this for the relationship v APPROX <SEP> DELTA e.g. <SEP> max.

  Tz. c <2> / 2R between the difference <SEP> DELTA e.g. <SEP> max, that of a counting unit of <SEP> DELTA e.g. <SEP> max assigned time period Tz of the counter 55, the propagation speed c of electromagnetic waves and the transmitter-receiver distance R from the computer 36 determines the amount of the speed v of the absolute movement of the earth in space and in the event that a speed v over 30,000 km / s results in a new determination according to the relationship
 
EMI87.1
  made and the speed v determined in this way is displayed in the display device 37. The direction of the speed vector of the absolute movement of the earth in space is determined by the computer 36 by interpolation between which the difference <SEP> DELTA e.g. <SEP> max surrounding DELTA z values and the assigned stored directions determined and also displayed in the display device 37.



  For measuring devices with only one pair of receivers, at the end of a series of measurements, i.e. after 360 measurements, then from the computer 36 from the differences DELTA z stored in the storage locations by combining three differences DELTA z1, DELTA z2, DELTA z3 in succession at an interval of 8 hours according to the relationship
EMI87.2
 a number of difference amounts corresponding to the difference between 120 and the number of marked stored DELTA z values <SEP> DELTA e.g. <SEP> determines from this number of difference amounts <SEP> DELTA e.g. <SEP> then the mean <SEP> DELTA e.g. <SEP> medium formed and from this according to the relationship v APPROX <SEP> DELTA e.g. <SEP> medium.

  Tz. c <2> / 2a between the difference <SEP> DELTA e.g. <SEP> medium, that of a counting unit of <SEP> DELTA e.g. <SEP> by means of the assigned time span Tz of the counter 55, the propagation speed c of electromagnetic waves and the transmitter-receiver distance a determines the amount of the speed v of the absolute movement of the earth in space and in the event that a speed v of over 30,000 km / s results in a new determination according to the relationship
EMI87.3
 made and the speed v determined in this way is displayed in the display device 37.

  In this case, the direction of the speed vector of the absolute movement of the earth in space is determined such that from the number of difference amounts mentioned <SEP> DELTA e.g. <SEP> exactly the mean <SEP> DELTA e.g. <SEP> means the corresponding difference <SEP> DELTA e.g. <SEP> is selected, then from the memory the stored directions of this difference <SEP> DELTA e.g. <SEP> assigned three DELTA z values DELTA z1, DELTA z2 and DELTA z3 and then the direction of the velocity vector of the absolute movement of the earth in space in the form of 3 angles alpha 1 = arccos (DELTA z1 / <SEP> DELTA e.g. <SEP> medium), alpha 2 = arccos (DELTA z2 / <SEP> DELTA e.g. <SEP> medium and alpha 3 = arccos ( <SEP> DELTA z3 / <SEP> DELTA e.g. <SEP> medium) between the speed vector of the absolute earth movement and the ones taken from the memory,

   determine the directions assigned to the three DELTA z values DELTA z1, DELTA z2 and DELTA z3 and can thus be determined by the computer 36. The direction of movement of the absolute earth movement determined in this way is then likewise displayed in the display device 37.



  After completing the series of measurements of 180 measurements in measuring devices with a large number of receiver pairs or 360 measurements in measuring devices with only one pair of receivers and display of the determined amount and direction of the speed vector of the absolute movement of the earth in space in the display device 37, the bistable multivibrator 16 is shown Computer 36 is again continuously supplied with a set signal which holds the bistable multivibrator 16 in the zero state, and the overall measurement comprising 180 or 360 individual measurements is thus ended.



  In summary, it should finally be mentioned that the measuring device described above is designed for a speed range of absolute earth movement from 250 km / s to 250,000 km / s and a range of the transmitter-receiver distance of 1 km to 30 km can achieve a measurement accuracy of 1% within these ranges with the measuring device described above.

   However, since measurements already carried out show that the speed of the absolute movement of our galaxy and with that of our earth in space is in the order of 5000 km / s +/- 50%, the speed measuring range could be significant (e.g. to 2000 km / s up to 20,000 km / s) can be restricted, which means that, with the measurement accuracy remaining the same, the upper limit frequencies of the receiver components can be reduced from 100 GHz to e.g. 10 GHz and thus of course significant simplifications in the construction of the measuring device or a reduction of the minimum required transmitter-receiver distance to e.g. 100 m or partial reductions in both respects.