WO2009082992A1 - Indicateur de direction - Google Patents

Indicateur de direction Download PDF

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Publication number
WO2009082992A1
WO2009082992A1 PCT/DE2008/001835 DE2008001835W WO2009082992A1 WO 2009082992 A1 WO2009082992 A1 WO 2009082992A1 DE 2008001835 W DE2008001835 W DE 2008001835W WO 2009082992 A1 WO2009082992 A1 WO 2009082992A1
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WO
WIPO (PCT)
Prior art keywords
direction indicator
satellite
location
measuring device
receiver
Prior art date
Application number
PCT/DE2008/001835
Other languages
German (de)
English (en)
Inventor
Manfred Pfalzgraf
Original Assignee
Enerday Gmbh
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Enerday Gmbh filed Critical Enerday Gmbh
Publication of WO2009082992A1 publication Critical patent/WO2009082992A1/fr

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Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
    • G01C21/20—Instruments for performing navigational calculations

Definitions

  • the invention relates to a direction indicator which is adapted to indicate at the location of the direction indicator a direction in which - from the viewpoint of the direction indicator - a remote location from the direction indicator, the direction indicator means for determining one's own relative position in relation to the remote location.
  • the invention relates to a motor vehicle with a direction indicator, in particular a land vehicle.
  • the energy consumption is high. This applies in particular taking into account the fact that for the use of balloons and airships and a considerable logistical and manufacturing effort is inevitable.
  • Skyblowers like balloons and airships, have the disadvantage that they can not be used in all weather conditions.
  • skywaves contribute to light pollution and thereby affect the operation of observatories and the life of migratory and nocturnal insects. For these reasons, a building permit is required for sky lights in Germany.
  • the object of the invention is to provide a device, hereinafter referred to as a direction indicator, which indicates the direction to a remote location in a reliable and widely visible manner with less energy consumption.
  • the invention is based on a generic direction indicator characterized in that the direction indicator comprises a system which serves the self-sufficient supply of the direction indicator and a mobile further consumer with energy.
  • the direction indicator is useful if it is designed for operation in different places, since then only the problem of constantly new orientation results. If the direction indicator is combined with a device that is also mobile, then the direction indicator can be usefully merged with this device, especially if the direction indicator and the mobile further consumer share an energy source.
  • the system is a fuel cell system. This is a particularly reliable, durable and powerful power supply to cover the energy needs of a direction indicator is possible even in remote locations.
  • the further consumer comprises an air conditioning system.
  • air conditioners are very popular and often built as mobile units, for example, for their use in tent camps.
  • the direction indicator comprises a receiver for terrestrial television or radio and / or a receiver for a terrestrial television broadcasting system.
  • the direction indicator can detect signals from one or more stationary radio transmitters or satellites and calculate position and / or direction information from the received signals.
  • the direction indicator comprises a satellite receiver, which is designed to receive the transmission signals of a geostationary satellite, in particular a geostationary communications satellite.
  • the reception of the signals of a geostationary satellite is particularly advantageous because the position of a geostationary satellite does not change in the sky, a satellite antenna therefore does not have to track a trajectory and a detected direction of reception can be evaluated more easily for a position and / or direction determination It is not time-dependent.
  • the direction indicator comprises a receiver for a radio navigation system, in particular a satellite navigation receiver.
  • the use of a receiver for a radio navigation system, in particular a satellite navigation receiver is therefore often advantageous for position and / or direction determination tasks, since radio navigation systems and satellite navigation receivers have features that are intended to perform position or direction determination tasks.
  • an embodiment of the direction indicator according to the invention is advantageous, in which the direction indicator comprises a measuring device for detecting a strength and / or a direction and / or a gradient of a gravitational field.
  • the direction indicator comprises a measuring device for detecting a strength and / or a direction and / or a gradient of a gravitational field.
  • the earth gravity field is suitable for this, since it largely meets these requirements.
  • the direction indicator comprises a measuring device for detecting a position change, in particular an inertial navigation system, in particular a gyrocompass.
  • a measuring device for detecting a change in position, in particular an inertial navigation system such as a gyrocompass is particularly advantageous if the direction indicator is to indicate a direction even if it is to be used on a means of transport, such as a ship.
  • the direction indicator comprises a measuring device for detecting a strength and / or a direction and / or a gradient of an acceleration, in particular linear acceleration.
  • the detection of a strength and / or a direction and / or a gradient of an acceleration, in particular a linear acceleration is particularly advantageous if - for example due to radio shading of navigation satellites - temporarily no other means for position or direction determination are available so that a coupling navigation method is used.
  • the direction indicator comprises a geophone or a seismometer or a sounder.
  • Geophones, seismometers and echosounders convert sound waves or infrasonic waves that propagate in the earth's crust into electrical signals.
  • the system behavior of the earth's crust with respect to the propagation of sound waves or infrasonic waves can be detected by systematic measurements. Utilizing the knowledge gained about the system behavior, measured sound waves or infrasonic waves can be assigned to a specific location for which the system behavior is characteristic. In this way, the location of the direction indicator can be determined.
  • the direction indicator comprises a measuring device for detecting a strength and / or a direction and / or a gradient of a
  • the direction indicator comprises a measuring device for detecting a strength and / or a direction and / or a gradient of a Coriolis acceleration. Rotational position changes can advantageously be achieved by micromechanical angular rate Sensors are detected.
  • the direction indicator comprises a device for performing dead reckoning.
  • a dead reckoning is particularly advantageous if - for example due to radio shading of navigation satellites - temporarily no other means for position or direction determination are available.
  • an embodiment of the direction indicator according to the invention is expedient in which it has an operating mode in which a position and / or direction determination is made on the assumption that the position and / or the location of the direction indicator does not change relative to the earth's surface. If the mentioned boundary conditions exist, certain input parameters are dispensable. Consequently, a more efficient position and / or direction determination can be carried out since measured values from change sensors do not have to be taken into account.
  • the direction indicator has an operating mode in which a position and / or direction determination is made on the assumption that the position and / or the location of the fuel cell system can change or change relative to the earth's surface. This also makes it possible to determine the position and / or direction when the direction indicator on a means of transport, for example a ship, is used while driving.
  • the direction indicator comprises an electric motor for aligning a receiving antenna, which is powered by a fuel cell system of the direction indicator with electrical energy. By automating the antenna operation, the comfort and acceptance of the direction indicator according to the invention are increased.
  • the direction indicator comprises an electric motor, which is designed to change an elevation angle and / or a horizontal angle of the receiving antenna.
  • a specific separate adjustability of the elevation angle and / or the horizontal angle simplifies an evaluation of the setting data for position and / or position determination.
  • the direction indicator comprises an electric motor for aligning the direction-indicating part of the direction indicator, wherein the electric motor is supplied with electrical energy by a fuel cell system of the direction indicator.
  • the invention is based on a generic motor vehicle, in particular a land vehicle, in that it comprises a direction indicator according to the invention.
  • the invention further relates to an air conditioner with a direction indicator according to the invention. - S -
  • FIG. 1 shows a sketch for a plan view of a section of the earth's surface with imaginary geometrical locations on the earth's surface, from which a first or a second geostationary satellite appears at the same elevation angle;
  • FIG. 2 shows a side view of a direction indicator according to the invention with a display device for
  • GPS Global Positioning System
  • the space segment of GPS consists of a number of low-flying satellites that continuously broadcast their orbit data and highly accurate time stamps.
  • the time stamps each contain information about when they were sent out.
  • the GPS receiver built into today's vehicles evaluates the received lane data and timestamps.
  • the GPS receiver also records the difference in time of arrival of the time stamps from different satellites that the GPS receiver can receive.
  • the arrival time of a time stamp at the GPS receiver is determined by the time of despatch and the term of the GPS. Timing depends on the way from the satellite to the GPS receiver. Based on the transmitted orbit data, the GPS receiver continuously calculates the current position of each of the satellites it is currently receiving.
  • the transmission speed of the time markers (radio signals) from a satellite to the GPS receiver corresponds approximately to the speed of light and is also known, taking into account various correction methods.
  • an equation can be established that describes the relationship between an initially unknown current local time of the GPS receiver and the current distance to the satellite. If neither a location coordinate of the GPS receiver nor its local time is known, the time signals must be received from at least four GPS satellites, so that the equation system can be solved with the available input parameters.
  • the available input parameters for the solution of the system of equations then consist of the four timestamps (in relation to the satellite time), the position coordinates of the four timestamp transmitters (satellites) and the four relative time-of-arrival of the timestamps (based on a local time of the receiver). Receiver .
  • the result of the solution of the equation system are three
  • the three location coordinates are usually specified in a spherical coordinate system, so for example, the geographical longitude, the latitude and the altitude above sea level or the distance from the center of the earth. If the height of the GPS receiver is known - for example, because it is a land vehicle - the system of equations simplifies, and it becomes soluble when it receives only three GPS satellites. However, the reception of a GPS satellite can not be replaced by a vehicle-mounted clock in most practical applications, since the accuracy of today's quartz watches for GPS positioning is not sufficient.
  • a GPS receiver can determine its location on the earth's surface in latitude and longitude with a view of at least four satellites. If the altitude of the place is known, the view also extends to only three satellites.
  • a pair of bodies has exactly six independent positional features (degrees of freedom). This also applies to a vehicle with navigation system in relation to the globe. Since the vehicle speed is much lower than the speed of light, relativistic effects are disregarded here.
  • Three of the six positional data are the three spatial coordinates previously discussed (Translational degrees of freedom) such as longitude, latitude and altitude above sea level.
  • the other three positional data are positional coordinates (rotational degrees of freedom) referred to as yaw angle, pitch angle (inclination), and roll angle (roll angle) in aviation and marine.
  • the pitch angle and roll angle of a stationary object can be determined relatively simply and reliably from the direction of gravity at the location of the object.
  • the direction of the center of the earth can easily be determined by two spirit levels or setting scales arranged in the same plane, or in two parallel planes.
  • the two spirit levels or setting cars must span a two-dimensional coordinate system, in other words, they must not be arranged parallel to one another.
  • a tetrahedral or pyramid-like construction can be chosen, in which a circular level or a single perpendicular or common pendulum with two rotational degrees of freedom is suspended and replaces the pendulum hands of the two setting scales.
  • the object of the present invention to provide a display device which indicates the direction to a remote location in a reliable and widely visible manner with low energy consumption, thus requires a means with which, so to speak, the yaw angle of a reference part of the display device with respect to the direction to the remote Location can be determined.
  • the (pure) GPS receiver described above is not able to do this. Therefore, navigation systems are often equipped with a geomagnetic field sensor in order to also be able to calculate a current direction of the vehicle in relation to the geographic north direction.
  • a direction indicator equipped with a GPS receiver, a geomagnetic field sensor, and a yaw rate calculator would generally be capable of determining its yaw angle with respect to the direction to the remote location.
  • the determination of the yaw angle also requires the determination of the position of the direction indicator.
  • a sole determination of the geographic or magnetic north direction would be sufficient only if the direction indicator happens to be on the same geographical or on the same magnetic longitude or latitude circle as the remote location, which is generally not to go out.
  • a satellite system such as GPS or Galileo is highly complex and very expensive, so there will be very few such systems, including user charges and Availability of commercial, political and military intentions will depend less operator.
  • the use of the earth's magnetic field to determine a direction is not easy.
  • the direction of the geomagnetic field lines depends on the vicinity of the magnetic field compass, for example on the presence of metal objects. Even then, apart from such local influences, it must be borne in mind that the natural orientation of the earth's magnetic field also has irregularities on the earth's surface.
  • AD Kucar et al. "Al-Quiblah and Satellites Signal Cove- rage over KSA and the Arab World," King Fahd University of Petroleum and Minerals, Dhahran, describes the location dependence of horizontal angle (azimuth angle) and elevation angle (elevation angle) of geostationary communications and television satellites. From the point of view of any place on earth, each of the geostationary commu- nication and television satellites is always located in the same place of the firmament, as long as it is visible from the chosen location. Therefore, a satellite receiving antenna need not be tracked when aligned with a geostationary satellite. In other words, horizontal angle and elevation angle of the receiving direction remain constant. The horizontal angle is the yaw angle of the satellite receiving antenna.
  • the elevation angle is the pitch angle of the satellite receiving antenna.
  • Each location on the Earth's surface has a specific pair of elevation and horizontal angles with respect to the horizontal plane and with respect to a particular geostationary satellite, ie the imaginary connecting line between satellite and center of the earth (gravitational direction). Elevation angles from 0 to 90 ° are possible. Horizontal angles of 0 ° to 90 ° and 270 ° to 360 ° occur in the northern hemisphere. In the southern hemisphere, horizontal angles are from 90 ° to 270 °.
  • the earth is spherical, and it is also disregarded here that the earth's surface has mountains, i. is not exactly spherical.
  • the geometrical location for all locations with the same elevation angle to a geostationary satellite is a so-called spherical circle (usually small circle), whose center within the globe on an imaginary connecting line (plumb line) between the rotation axis of the earth (or the center of the earth) and the geostationary satellite, with the connecting line passing through the earth equator.
  • the spherical circle is a great circle and at an elevation angle of 90 ° (zenith) the spherical circle is a circle degenerated to a point.
  • the following location determination is possible with a measuring device if the elevation angle to two differently positioned geostationary satellites and the gravitational direction are measured.
  • the measuring device is located at the location of the direction-indicating part of the direction indicator. If the measuring device is arranged at a fixed relative distance and direction away from the direction indicator, the method described below can be supplemented by a coordinate transformation which is known per se to improve the accuracy of the directional display from the measuring device.
  • the measuring device measures the elevation angle (first elevation angle) relative to a first geostationary satellite whose position is known on the geostationary orbit.
  • the measuring device measures the elevation angle (second elevation angle) to a second geostationary satellite whose position is known in geostationary orbit.
  • the position of the first satellite in geostationary orbit and the first elevation angle determines the radius of the associated imaginary spherical circle (first spherical circle) on the earth's surface.
  • the position of the second satellite in geostationary orbit and the second elevation angle determine the radius of the associated imaginary spherical circle (second spherical circle) on the earth's surface.
  • the two intersection points of the first spherical circle with the second spherical circle are determined.
  • a sign of a horizontal angle difference between the first and second geostationary satellites is measured, wherein the horizontal angle difference plus 180 ° does not exceed or does not fall below minus 180 °.
  • the acute or obtuse angle is determined, which completes the obtuse angle to 180 °.
  • the horizontal angle difference is equal to the horizontal angle of the second satellite minus the horizontal angle of the first satellite. All horizontal angles are viewed here in the direction of gravity.
  • the sign of the horizontal angle difference may be determined, for example, by measuring a first horizontal angle to the first satellite with respect to a horizontal reference orientation of the measuring device and by measuring a second horizontal angle to the second satellite with respect to the reference orientation. If the sign of the thus determined horizontal angle difference between a first satellite and a second satellite with a western position (as that of the first satellite) is positive, the location of the measuring device is on that intersection of the two circles located in the northern hemisphere. If the sign of the thus determined horizontal angle difference is negative, the location of the measuring device is on that point of intersection of the two circles located in the southern hemisphere. When the detected horizontal angle difference is 0 ° or 180 °, is a
  • the determination and evaluation of the horizontal angles can be completely dispensed with if it is known, due to other circumstances, whether the measuring device is located in the northern or southern hemisphere. In this case, the measuring device can be considerably simplified, since then no Horizontal angle, but only elevation angle need to be measured. This method is advantageous at low latitudes.
  • a reference direction at the location of the measuring device must be known or determined at least in a different way, for example with a magnetic field compass.
  • a booster For example, a transmitter of a Local Multipoint Distribution Service (LMDS) system, a Multichannel Multipoint Distribution Service (MMDS) system, a radio station, a base station, or a WiMax access point.
  • LMDS Local Multipoint Distribution Service
  • MMDS Multichannel Multipoint Distribution Service
  • the procedure is similar to the altitude measurement with a sextant known from the maritime industry. Due to overexposure, position determination is possible during the day only by means of less light celestial bodies - especially the sun. This type of position determination has the disadvantage that with the measurement, the measurement time must be recorded and in the evaluation of the apparent course of the celestial body must be considered before the sky.
  • the only natural celestial bodies that do not change their location in the sky are the Polarstern and the Southern Cross, which are usually visible only at night. In the event of cloud cover or fog conditions, which - depending on the local climatic conditions - can last for days or even weeks, such position determination in the optical range is possible neither during the day nor at night.
  • the determination of the position by means of detecting the height and horizontal angle of a geostationary satellite avoids all the aforementioned disadvantages.
  • the satellite receiver has a control means with which the satellite receiving antenna first a first - for example - helical or cycloidal scanning pattern follows until a detectable radio signal from a satellite is detected from which a position parameter is known or transmitted, received and decoded.
  • the control means taking into account the previously scanned area and / or previously detected position parameters of already detected satellites, reduces the scanning area step by step.
  • the scan pattern can be changed. For example, a cycloidal scan pattern may be applied first and then, when the desired satellite has been detected, continued with a spiral scan pattern to more accurately align the satellite receive antenna.
  • the accuracy of measuring the satellite's elevation and horizontal angles depends on the magnitude of the angle measurement errors.
  • the accuracy of the measurement of the direction to the center of the earth can be improved by increasing the measuring base, that is, with an "extension" of the (electronic) spirit level or setting scale or enlargement of the (electronic) can weigher.
  • the measurement accuracy for the height and horizontal angle can be increased by increasing the diameter of the parabolic mirror of the satellite receiving antenna.
  • LNB Low Noise Block Converter
  • skew here: polarization angle
  • the LNB skew depends on both the skew offset (polarization angle) of the satellite and the latitude and longitude of the satellite receiver.
  • the LNB can be rotated back and forth around its axis with the satellite receiving antenna already aligned such that the amplitude or quality of the received signal becomes maximum.
  • the set LNB skew can then be read and evaluated taking into account the satellite's known skew offset.
  • the measurable LNB skew thus represents a possibility for a satellite - in addition to the elevation angle and the horizontal angle - to obtain a further measured value with which the determined geographical position information can be refined or whose plausibility can be checked.
  • the LNB - after alignment of the satellite receiving antenna - rotated by 90 ° about its axis. Then it is turned back and forth until the amplitude or quality of the received signal is at a minimum. Thereafter, the LNB is turned back or further rotated by 90 °. This has the advantage that the minimum can usually be measured with higher accuracy than the maximum.
  • the accuracy of the determination of the direction to the remote location depends in particular on the distance to the remote location in addition to the previously discussed measurement errors.
  • the direction determination is the more accurate the further the distant place is removed from the site. Rough calculations have shown that with the above method sufficient accuracy on the order of a few degrees may be only with greater effort, so for example with satellite receiving antennas with greater resolution, ie with a diameter of more than 1 m or VLTI technique (Very Large Telescope interferometer) will be determined if the distance to the remote location is less than 300 km. This is roughly equivalent to the distance between the Medina and Mecca.
  • the satellite receiving antenna may have a collapsible structure, as described in DE 41 37 974 Al.
  • the position determination over two horizontal angles then has an optimal geometrical measurement accuracy if the two imaginary projections 10, 12 of the two directions of reception to the two geostationary satellites 14, 16 perpendicularly intersect the earth's surface 18 at the location 20 of the measuring device.
  • FIG. 1 shows the views from the perspective of the second satellite 16, which is why the spherical circle 11 belonging to the first satellite appears elliptical, that is to say somewhat compressed in the equatorial direction.
  • the projection circuit 15 In the case shown in the figure, the imaginary projections of the two satellites 14, 16 on the equator 22 and the location 20 of the measuring device span an imaginary isosceles ball triangle at a right angle at the location 20 of the measuring device and one angle ex at the other two - arranged on the equator 22 - on corners.
  • Each of the three sides 24, 26, 28 of the ball triangle forms a section of each other of three large circles 22, 30, 32, wherein the longer side 28 forms a portion of that great circle 22, which is referred to as equator 22.
  • equator 22 When the mirror triangle with sides 10, 12, 28 in the figure is added a mirror image "flipped down" on page 28, it will be appreciated that the side 28 forms a diagonal of a ball square. Due to the isotropy of the spherical surface is then also seen that the length of the height 34 of this ball triangle is as large as half the length of the diagonal 28, that of the equator (Hypothenuse).
  • the amount of longitude difference between the location of the first satellite 14 and the location 20 of the measuring device is the same as the amount of longitude difference between the location of the second satellite 16 and the location 20 of the measuring device and the same Latitude of the location 20 of the measuring device.
  • a first geostationary satellite 14 should be selected which (whose projection onto the equator 22) is located as far as possible from the longitude of the location 20 of the measuring device as far as the location 20 of the measuring device Latitude north of the equator 22 is located.
  • a second geostationary satellite 16 should be selected, which (whose projection onto the equator 22) is as far as longitudes west of the longitude of the location 20 of the measuring device as the location 20 of the measuring system. at latitudes north of the equator 22.
  • the position determination is based on a measurement of only two elevation angles.
  • the two satellites 14, 16 should be selected such that the elevation angles of the two satellites 14, 16 are as strong as possible relative to one another and additionally also with respect to the two elevation angles of 0 ° and 90 °, which are already known anyway because of the gravitational direction differ as much as possible. Therefore, when determining only two elevation angles, it may be considered expedient to select a first satellite 14 for the position determination which, as viewed by the measuring device, has an elevation angle of as accurately as 30 ° and a second satellite 16 which, from the point of view of the measuring device, has one Has elevation angle of as close to 60 °.
  • the direction indicator 36 shown in side view in FIG. 2 comprises a mast-like structure 38 with a satellite receiving antenna 40 rotatable in horizontal angle (azimuth) and elevational (elevation) directions for at least two television satellites 14, 16.
  • the antenna and its rotary mechanism is under a radome 41, to protect them from weather conditions such as sandstorms.
  • a satellite receiving antenna 40 a flat antenna having a phased array can also be used.
  • a position of the satellite receiving antenna 40 is calculated by a controller 42 of the direction indicator 36.
  • the controller 42 transmits the calculation result to a motor controller 44, which drives one or more electric motors to align the satellite receiving antenna 40.
  • a first motor serves to adjust the elevation angle and a second motor to adjust the horizontal angle of the satellite receiving antenna 40.
  • a third motor may be provided for the adjustment of the LNB skew.
  • the controller 42 calculates the setting data for the antenna motor controller 44 to locate and focus on geostationary satellites 14, 16 to be targeted.
  • the satellite receiving antenna 40 may be gimbaled in at least one (preferably two, typically two-piece) axes.
  • the inner gimbal suspension serves to adjust the elevation angle, since the value range to be covered here is generally smaller than the value range of the horizontal angle.
  • the imaginary center line of each suspension axle runs in each case through a center of gravity, in particular preferably through a center of gravity, of the part of the satellite receiving antenna 40 suspended from the suspension axle.
  • the direction indicator 36 has a fuel cell system 46 with a fuel tank 48 which is large enough, the time between two consecutive tank fillings a generous time reserve to bridge.
  • the fuel cell system 46 includes a solid oxide fuel cell (SOFC).
  • SOFC solid oxide fuel cell
  • the direction indicator 36 advantageously has a mast 52, on which the direction indicating part 54 of the direction indicator 36 is fixed so that it can be perceived from a greater distance.
  • the mast 52 may be mechanically fixed to the fuel cell system 46, so that the fuel cell system 46 gives the mast 52 a particularly advantageous intrinsic stability.
  • the direction indicator 36 may have means - for example a ground or sand screw 56 - with which it can be attached to the floor 58 or other stationary object (see for example DE 297 10 839 Ul).
  • a hand knob 60 or an electric motor driven by the fuel cell system 46 may be provided for screwing into the soil or sandy soil 58.
  • the direction indicating portion 54 may be powered by the fuel cell system 46 to adjust the indicated direction to the desired direction and / or to be electrically illuminated so that it is more readily perceptible to the eye at night or in difficult viewing conditions.
  • the direction-indicating part 54 can be arranged with an electric drive 53 around the mast 52 in the direction of the arrow 55 such that it can rotate around.
  • the mast 52 may serve to attach other infrastructure such as an information panel, a speaker, a bell mechanism, a directional antenna, a radio and / or television receiving antenna, a radio and / or lavishverteilantenne, a WiMax antenna and / or a mobile radio antenna.
  • a perch 62 for a bird of prey 64, in particular a hunting bird 64 may be attached to the mast.
  • the direction indicator 36 preferably has at least one NEN reformer 50 to provide primary fuel in secondary fuel for the actual chemoelectric conversion.
  • the direction indicator 36 can fulfill further supply functions and perform them with high reliability due to the supply by the fuel cell system 46.
  • the direction indicator 36 a first dispensing device for tapping primary fuel and / or a second dispensing device for tapping the secondary fuel, such as a hydrogen-containing gas, for additional consumers.
  • the direction indicator comprises one or more power, television, telephone, DSL, LAN and / or WLAN connections for one or more local subscribers.
  • the direction indicator according to the invention may in particular also be designed as a fuel cell-powered mobile air conditioning system, which can be used for example as a stand-alone unit in buildings or can also be carried in vehicles.
  • the fuel cell system and the actual components of the air conditioning system may be arranged in a unitary housing, said housing, in particular depending on the required air conditioning capacity, may have different dimensions.
  • the unit may typically have a shape similar to the shape of conventional mobile mains-powered air conditioners.
  • the direction indicator can then be displayed in a visually appealing manner. example, by a light, in particular a light pointer, such as using a laser made.
  • the direction display can also be combined with a reminder function that responds acoustically or visually, for example, to the usual in Islam prayer hours, for example, due to a real-time clock at certain times of the day.

Abstract

La présente invention concerne un indicateur de direction conçu pour indiquer, à l'endroit où il se trouve, une direction dans laquelle se situe un lieu distant de l'indicateur de direction, vu depuis cet indicateur. L'indicateur de direction comprend un moyen de détermination de sa propre position relative par rapport au lieu distant. L'indicateur de direction comprend un système (46) permettant d'assurer son alimentation en énergie (36) et celle d'un autre consommateur mobile de manière autarcique. La présente invention concerne également un véhicule automobile, ainsi qu'un système de climatisation pourvu d'un indicateur de direction selon l'invention.
PCT/DE2008/001835 2007-12-28 2008-11-06 Indicateur de direction WO2009082992A1 (fr)

Applications Claiming Priority (2)

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DE102007063028.1 2007-12-28
DE102007063028 2007-12-28

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