GB2445402A - Converting centrifugal force into a linear force - Google Patents

Abstract

A system that converts centrifugal force into a linear force comprises a mass 5 adapted to rotate about an axis 3, wherein the axis 3 is adapted to rotate in two planes these planes being perpendicular to each other and to the original axis. The resultant system causes imbalances of the generated centrifugal forces in order to generate a constant linear force.

Description

Mechanical Inertial Propulsion System

Specification (1)

An efficient system for converting the powerful and. easily generated centrifugal force into linear force. Such a system would find extensive use in all areas of the transportation industry. Most promisingly, on both the very large scale and the small scale it would, be useful in space. Most, particularly it lends itself easily to being powered atomically. There have been many examples of linear force generation from centrifugal systems occurring accidentally, a smooth efficient way of expressing this force has however so far evaded inventors.

Mechanical Inertial Propulsion System

Specification (2)

Referring to drawing '/? shows a framework construction containing a mass orbiting an axial bar / and restrained by an axial arm A . Shown pivot 3 is arranged either end of said framework in order to facilitate rotary motion perpendicular to that of said mass orbit. This apparatus could straightforwardly be constructed and enabled by common and familiar means. This obvious apparatus is included for completeness of the explanation of the operating function of the proposed propulsive idea. It is also obvious that this simpler apparatus has only the freedom to rotate shown axial bar / in one plane and not two as per proposal.

It is again the case that mutual rotations of orbiting mass and axial bar be exactly matched with respect to angular displacement. The facility to pause pivoted axial bar rotation is included this time, /vij / commences with said mass orbit continuing into the page and simultaneously the top of pivoted framework is rotating out of the page; axial rotation 4- orbit 3 of mass X shown in ft>a\ 2. The peripheral motion imposed on mass 2 is judged to conform to the description "partial external geodesic" (partial because said axial bar is confined to rotate only through one plane and not a possible two). This partial external geodesic has been shown to be energetically favoured by experiment. Once the above axial rotation had been commenced properly (beyond a threshold, exact parameters, yet to be accurately established), then the apparatus was seen to accelerate into the disposition described in diagram . If rotations of said axial bar and orbital displacement were faithfully continued for the next 1/4 cycle both in direction and angular velocity then an equal and opposite internal geodesic (partial) was the result. An action very much resisted by the apparatus; energetically disfavoured.

The end result of running the apparatus continuously this way was that no resultant force was observed emanating from the apparatus and the apparatus shook violently.

In this case axial bar rotation is paused at condition described in 3 ., dotted detail describing the continuing orbit of mass 2 the apparatus yielding a centrifugal force moment in the direction shown 5 5 the apparatus eventually coming to rest in the condition fic^ 4-. Both axial bar and orbital angular displacements can resume as before shown diagram 3 or said axial bar can proceed in the opposite direction at the same rate of rotation and to the eventual same effect, diagram Ft Either way, at the completion of the next prescribed 1/4 cycle axial bar is again paused in rotation for a further 1/4 cycle as per condition described diagram f £> The planar orbit 3 and the direction of a resultant centrifugal moment 5 is shown (out of the paper and to the left). Apparatus is then back to the condition described in diagram /y<j / after completing orbital transit portion described in or ^ ~£t clear, from the above that such an apparatus where said axial bar only has one plane available to rotate through, no matter how said axial bar rotation is punctuated or direction orientated, then no clear resultant force impulse will be experienced.

Mechanical Inertial Propulsion System Specification (3>

The cycle of mass (5) in this situation is dealt with in additional drawing showing what is happening to said mass as it transits clearly identifiable fragments of its action.I shows, with the apparatus turning 1/4 turn out of the plane of the paper, from the top, the mass 5" also haying processed 1/4 turn during, this interval, If-* Ion the diagram. Mass *T effectively processing during this phase, that is, mass 5 ' is actually moving away from axial bar it is orbiting when transiting this quadrant. The out of plane, perpendicular action effectively causes said mass 5 to a longer circumference of action, than would be the case were the orbit of mass to have remained planar. This inevitably translates to an increasing radius of action for mass 5" : as the out-plane action rotates uniformly (1:1 ratio with in-plane, orbital angular displacement) the further mass $ recedes from said out plane axiom so the effective radius of action said out-plane action increases until position; (/) is reached. Though the peripheral speed of mass (£) is constant here if not driven, the direct in-plane angular displacement will be proportionally reduced during said phase (£-> /). Out-plane angular displacement will need adjustment accordingly to maintain said 1:1 ratio. The effective increase in radius of orbit of mass 5T throughout said quadrant of action /.) constitutes; mass 5"' effectively moving away from said axial bar, with a consequent reduction in centrifugal force on the apparatus. However, transit of quadrant (J.-» jfc! sees a reciprocal action of radial dimunition with respect to the out of plane perpendicular axiom. This is a situation of increasing centrifugal force and energy would need to be put into the apparatus to re-establish mass S to a zero out-plane radius situation at axiom 2* as was enjoyed at axiom ty. ■;: /vij ^

Diagram A'^7 shows the said in and out plane actions continuing in phase and direction resulting in mass 5 again turning into the paper and receding from the out plane axis (instead of said mass $ transiting quadrant (db C) it is compelled to again transit quadrant in the opposite direction by said phased in and out plane actions.)fj^&/r»;ij6'. Transit axiom (^ to axiom (J) corresponds physically to said transit axiom (ft) to axiom (/), a further phase of effectively increasing radius and reducing centrifugal force. Constrained mass (5) then between axiom (/) and axiom directly analogous with previously mentioned transit axiom (/) to axiom (£), another reducing radius (effectively), increased centrifugal force and energy demanding situation, &). The cycle can then re-commence as from axiom (^.) toward axiom (/) as in illustration

.The above reasonings concur with experimental observations of an operating apparatus with intermittent force production with no resultant or overall imbalance. fyl & r*% 13 . again represent a mass ("5") orbiting an axiom bar, with again the assumed facility that said axiom bar can be manipulated, about the centre to advantage. Controlling gimbals or other means to do this are assumed but not shown as common engineering techniques could be contrived that could affect such assumed means. Axes t, 34,3 & /fare again shown about axiom, with the shown9/$ axes displayed into and out of the plane of the paper. Oblique diagram/'^ shows said mass ( S~.) and axial arm positioned along axis y into the plane of the paper; mass and axial arm therefore orbiting axes, a-c with axial bar aligned. Mass (£) would normally proceed from axis*? to axis>L in tne plane described by axes t,2 4-* However, coincidental with transit?-!, the axiom bar describes the movement shown (dotted arrows), one end of axiom bar from axis / to axisJif and simultaneously, the bottom end from axis3 to axis Jl,This, in turn describes a compound action adjusting the orbit of mass ( f) and said mass and axial arm take up the position shown, in diagram

Mechanical Inertial Propulsion System Specification (4)

Diagram ptyo shows the result of the compound actions previously described (in -plane/out - planes)with regard to the new disposition of mass (5") and said axial arm along axis I., in the plane f ,Z,3, if. Mass (/i) continues to orbit said axial bar now aligned along axesZ-^f-and (5^) is shown commencing a phase of uncomplexed orbit of IT radians in the plane /,4s3 ,2, ; completed shown in diagram fsq/lertydshows mas£ (5) now aligned along axis ?but as (5~) continues orbiting through the next tl/2 radians of the cycle the axial bar end stationed aforesaid aligned axis -transits IT/2 radians to align with axis 3, consequently the alter end of said axial bar simultaneously relocates alignment along axis f from along axis £ This complexed /O is equivalent in every way to the previously described /Q phase completed at the start of the cycle /"%/qin every way except direction and it returns the apparatus to the condition it occupied in said diagram

It is speculated herewith that the two complexed phases and single in plane or uncomplexed actions are not equivalent in affecting the apparatus described and a resultant force is expected intermittently in the direction of action of said uni-planar (in plane) action. The said completed phases and ^ are equivalent to actions displayed in diagrams/^ / and nq 5 wherewith, the outplane actions are allowing said mass (f) to move away from said restraining axial bar. So during this phase an attenuated centrifugal moment is speculated. With regard to the cycle outlined in fiafl to ^0*$, mass («f) is allowed to process twice through such complexed phases of action speculated as force reducing. However, with adjustments as outlined in diarams (8B), no corresponding equivalent complexed action, as in diagrams (ffy 3.) and (r.<j 7 ) is allowed, thus taking the equalising enhanced energy absorbing and force producing phase out of the system. This is done by allowing, as said, the orbiting mass (£ ) to complete an undisturbed IT radians of orbit before said complexed reassignments.

During the outplane phases outlined in TVZj ? to IS mass ({>') is effectively describing a "great circle" of action; straightening out somewhat said circular orbit. The circle thus described will have a larger circumference than one described for a plane orbit. This will be in proportion to an hypotenuse of a triangle drawn on a sphere; where the planar component and the out-plane component compose the other contributions to said triangle. The new circumference can be expressed asJ(jTpy r(Q?)X - ^

The increase in radius of action R=C/2lI. Note/if the peripheral (linear) speed be contrived to remain constant throughout the whole cycle, then as the effective radius increases the angular velocity decreases about said central axiom (precession). The out-plane component of regarded complexed phase does not necessarily have to concur exactly with the in-plane (planar)

contribution with respect to angular velocity. Dependent on testing for the most favourable dynamic parameters experimentally. The above system can be modified by combining the two complexed portions of the cycle into one action by moving the axial bar in the same circular action, as above but between two planes. Hot?/ This has to lie dane in twe \#ays between iwc consecutive cycles. (See t~ie\ Af )■ The detail of which is dealt with in being described in three dimensions 9 &/<9and therefore three; planes described&/<$£ also

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Mechanical Inertial Propulsion System

Specification (S)

Referring to drawing The familiar condition of mass (3) restrained to orbit an axiom (/.) by an axial arm ( X ) is shown in plan relief; rotation (4-) and restraining force ( &) and centrifugal directions ( 5 ). In/fi^this is shown in oblique with dimensions and/pinferred also an axial bar (70 has been included as a means of manipulating said orbit between planes. (A plane being composed of any two of said dimensions). At present mass (3) shown as rotating about the {Cf) dimension and within delineated plane (5,/^.

shows the direction of rotation of the axial bar about the axiom. This being a combination of rotations of said axial bar in the directionZ4&/5 and the ({!,/$ plane direction/$&/!f to eventually lie along shown/^/ dimension. The orbit of mass (3) with direction is shown ("40, before above axial rotation has taken place. Orbital angular displacement of 11/2 radians being identical to the displacement of said axial bar within said (tffl ) and (fi/0) planes during this action.

Note/ The apparatus will attempt to speed up through this portion of the cycle once said inter-planar motion has been initiated, in order to relieve all of the centrifugal moment. Arrangements could and should be made in order that said orbital angular displacement keep in step. The swinging of mass (3O will also attempt to continue beyond the allotted TT/2 radians of actions because of the inertia stored within the apparatus by this stage. The attempt for inter-planar movement in the same direction will be resisted beyond what is the high point by the apparatus. This is because the apparatus will enter the opposite mode, an effective "closing in" of the action, the above effectively being an "opening" action, allowing escape of mass (3 ) because of an effectively increasing radius of orbit. The closing action attempting to equivalently enhance an equal and opposite (balancing) restraining action. Said opening action described earlier could be described as an external geodesic (or convex geodesic). Said closing action being therefore rightly described as an internal or concave geodesic.

There are two ways of avoiding this second W2 radian portion being devoted to said balancing internal geodesic, one would be to pause any inter-planar movement directly after first regarded external geodesic mode or, manipulate said axial bar about the axiom in such a direction and speed that a further external geodesic be described. Either of these two options would be obviously energetically favoured. Subject to confirming experiment, with the second of the external geodesic mode coming in to play, (which can be sent in the direction as to bring the apparatus back to the original starting condition) the two external geodesies could be run back and forth indefinitely and even though said mass be restrained to orbit and continually change direction little or no centrifugal moment will accompany these actions. Particularly as aforementioned inertia driven overun can be easily absorbed in way by said bar manipulations and such would contribute to the smooth, running and continuity of these actions. It is speculated therefore, with good reason that utilising the above first option, that of pausing axial bar rotation after the initial TT/2 radian geodesic, that if said pause be of IT radians duration, then an imbalance along the dimension shown would be the result, in the direction of the paused planar mass transit. Then the use of a further geodesic, in the correct speed and direction will furnish another opportunity to pause again creating an imbalance along the same axis. The completion of this action returning the apparatus to the original starting condition, ready to re-run the cycle.

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Mechanical Inertial Propulsion System

Specification (6)

^ , shows said axial bar ( 7 ) into pause mode of II radians duration in propulsion condition; force arrowed in the direction ($"). The mass (*3) describing an equatorial orbit in the shown£,/i?plane between shown positions /0 to//., as confirmed in diagram /v^.The upper end of shown axial bar (7) aligned along the L°f) dimension is designated (/$ and the lower (/5). Through a duration of normal mass (3) orbit (If) corresponding to IT/2 radians end (f$) is rotated about axiom (/ .) by a period ofH/2 radians in the shownV,/0plane toward shown axiom/3, and simultaneously in the plane #,/0toward the axiom/I, also by a period TT/2 radians. The end result of all these actions is for said axial bar ( 7 >) to be disposed eventually along shown (/o) dimension, where inter-planar ( y ) action is again paused for a further period of IT radians. (Aforesaid inter-planar action causes end/5 to rotate within planes#,*? and'djO also toward axia f. and /0_by a corresponding displacement of again IT/2 radians). The overall result of this entire complex of activity is that mass (3 ) be disposed by the axial arm ( X) along the ^dimension in the direction of shown H axiom. During said subsequent pause to inter-planar displacements mass (g) again describes an equatorial orbit ofll radians duration about shown/0dimension this time, translating between axia and /✓?, force moment arrowed again in the direction (5"-'). Said axial arm along with mass (3 ) would then be disposed along axiom ft and at this point axial bar ( 7 ) rotation can again be commenced. A further external geodesic to forcelessly restore axial arm and mass ( 30 along axiom /O needs to be constructed during the next 1172 radian period of mass (3) orbit. Dotted detail infers the necessary rotation that shown axial bar ends/4& I fj describe about axiom (/).

As said axial arm (% ) attempts to describe a portion of equatorial orbit about shown /£? dimension, in the plane described and between the positions (directions) axia IX to axial bar end/^rotates about mam axiom (/ .) through a period of IT/2 radians within shown plane }Q, % between shown positions /Oto and simultaneously TT/2 radians within the/0, ^ plane between shown axia (positions) /£?to /^ Axial bar end /lit of course, rotates about axiom CO in equal and opposite fashion as described by axial bar end /^that is, within planes/C, % &Jo, 9 simultaneously and also simultaneously moving between axia // to $. and U to The consequences of the above manipulations is that the axial bar be again positioned along shown 9 dimension with the axial arm and mass (3 ) as said, along said/© axiom, paused with the apparatus ready to again describe the equatorial orbit, about said dimension, transiting between axia /Oand // as shown in 3 * Fi'tj ^

records the possibility, subject to experiment, of separating the positions (axia), away from the idea of a common axiom (/) about which occurs the mass (3) orbit and the described episodic rotations of the axial bar (7 ). In the extreme condition of this shown; mass (3) orbits axial centre (/) with the axial bar organised to rotate as required about a subordinate axial centre positioned at the /5" described end of said axial bar.

Again in the light of the above more detailed reasonings, this work continues to speculate that an apparatus that restrains a moving mass to orbit an axial centre, episodically manipulating said mass orbit between periods of equatorial and geodesic within a cycle of said apparatus function, such activity properly coordinated would provide a consistent and powerful episodic imbalance of force, within a singular apparatus as described. Numbers of such constructions, counter-rotated and suitably, mutually out phased within the cycle could be used to create a device demonstrating smooth, continuous inertial force generated by solid rotating mechanical means.

Mechanical Inertial Propulsion System

Specification (7)

Another way of using Drawing 3/Y and/^51s to assume that said axial bar ( 7 ) rotation is not paused; as shown in „ dotted detail describing(ponsequent ITradians of an equatorial orbit) Shown axial bar continues to move at the same rate of angular displacement and in the direction shown, as if a pause had taken place.

Said axial bar continues to rotate in the same direction within the/a, 2 plane, end /£-rotating between shown 1} & 9 axia. However, axial bar is at liberty to reverse the rotation described in within the plane, rotating between axia & , and completing to dispose along shown axiom , whilst still describing the necessary external geodesic. Note/ it is also possible that said axial bar rotation also continue in the same direction within said <f, 3 plane, end /£• migrating between axia It & tZ. to dispose said end Ik along axiom IX. at completion; this action also furnishing the necessary external geodesic. It is therefore feasible that there is more than one way to generate continuous consecutive geodesical actions and to have restrained mass (3) continually changing direction with only very little consequential force being involved, or going in or out of the system. In actuality, a small input of force to initiate another external geodesic after one is complete would emerge as a speeding up of said mass Q ) in geodesic orbit, as said mass (3) feels increasing radial escape from said axial centre (/). Once a small threshold of force necessary to initiate extra planar transit is exceeded mass ( 3 ) is reasonably speculated to hurl itself through said external geodesic action.

Centrifugal force is the natural consequence of a massive object when moving in a straight line then being caused to move at an angle offline. This submission makes the remarkable speculation that if the direction of a moving object is reversed in the usual manner by a restraining arm; that is in one plane, through IT radians over which this will happen, a powerful directional centrifugal moment will be a natural consequence. If the same action is continued through the other half of the cycle there will occur an equal and opposite centrifugal moment. However, if this other half cycle changes the direction of said mass again by 180° (IT radians) but utilising an external geodesic action as described above, then an almost negligible centrifugal moment will be the consequence. Therefore the two halves of the apparatus exhibiting one planar return followed by an extra planar return running consecutively will cause an imbalance in the forces across the system. An intermittent but continuing set of said powerful such imbalances could be generated by a succession of planar followed by an interplanar then a further planar action and so on. That is, TTradians of said equatorial rotation period, followed by a suitable external geodesic of less than IT72 radians period repeated indefinitely. Note/ IT radians of planar travel can be arranged always in the direction of axis /3 albeit travel taking place between axis , to axis lZ in one instance, followed by travel between travel between axis/0 fo t( after a suitable (in terms of direction) inter-planar recovery phase.

There are equivalent enantiomorphs of the above described system shown in extra drawing 5"/^, The first being described in detail in 3 to b, which has been referred to elsewhere in this work and fully described. Part of any practical expression would involve four enantiomorphic systems shown diagrammatically in parts 3 <, 7& S,3 aligned withalong their respective dimensions, /%3aligned with ^7 along mutual /O dimensions and?*}? &/%^aligned by their dimension. All disposed to initiate extra-planar activity in the directions shown. These orientations necessary to balance out stray forces, q demonstrates the directions of simultaneous equatorial transits after geodesic recovery, again orientated to balance out stray forces.

Mechanical Inertial Propulsion System.

Specification (8)

Drawing ^commencing from ft' , Mass ( 3) is configured orbiting an axial bar as in drawing^f. The starting condition selected is shown with said axial bar aligned along the q dimension with the axial arm aligned along the dimension, on the/tfaxis shown into the plane of the paper (diagram oblique). During a 1/4 cycle of normal planar orbital time (11/2 radians) the axial bar is turned by some powered gimbals means or some other suitable existing means about the central axiom connecting the said orbiting axial bar. Said axial bar rotation is a compound action, it is turned about said common central axiom from dimension to dimension % At the same time the axial bar is also rotated between dimension cf and dimension/e?, it comes to rest along dimension/<?. Effectively, the axial bar has rotated H/2 radians in thef", #plane and TT/2 radians in thef,/oplane; said axial bar has manoeuvred about said axial centre in a complex in-plane/ out-plane mode. The total effect of said complex rotations of axial bar and the normal progression of the orbit of Mass (3 ) is the delivery of the apparatus to the condition shown in diagram I v As said^with the axial bar aligned along the/odimension mass (3) inhabits the upper axis. Said axial bar is rendered immobile for a period of IT radians of orbital time, whilst mass (} ) translates between the upper ^ axis and the lower ? axis. A normal in-plane (planar) action.

Should mass (3 ) continue undisturbed then it would proceed away from the lower 7 axis toward the right f axis. However a further complex (j&? movement by said axial bar is included during this interval. The end result of which is shown arrowed in the second diagram which is a combination of the rotations of the axial bar through two planes. Axial bar moves around from alignment to dimension/oto align with dimension $, at the same time this rotation "added to", compounded with a rotation between said/t?dimension and the shown f dimension, alignments; whereon the axial bar comes to rest.) The result of said compounded rotations of the axial bar complexed with the equivalent natural orbital tendency of mass (3) during the same period would be, for the apparatus to become disposed as in diagram F>~a$5 , with mass (3) and the axial arm aligned along the/oaxis emerging from the page. Dotted detail represents an undisturbed (planar) orbital transit of again H radians through the plane /£?,#,/<7to again dispose along the/^dimension but into the plane of the paper. This being the starting condition to commence another cycle. Note/ in-plane (planar) transits occur in the same direction, along the % axis disposing, to the left of the paper. Whereas, both complexed components are disposed along the other $ axis to the right of the paper.

This submission speculates that an imbalance of centrifugal moments be the result of planar portions of the orbit of mass (3) at one side of an apparatus, operating as described above, with as described complex orbits for mass (3 ) operating on the opposite side of said apparatus. An important functional note here would be with regard to the directions of the rotation of the axial bar between dimensions during complex portions of the cycle. The first complex as shown in diagram/^/,, in order that mass (3) is moving away from said out-plane axiom as required, the axial bar must move in an anti-clockwise manner when viewed along axis from out of the plane of the paper; as shown. Further, said axial rotation must, simultaneously move in an anticlockwise manner when viewed along axis from the left hand side of the paper. For the second complex component 'X axial bar has to be rotating clockwise viewed along the ^axis trom above and anti-clockwise when viewed from the/0 axis again looking into the plane of the paper.

Mechanical Inertial Propulsion

Specification (9)

The peripheral linear displacement can again be calculated using Pythagoras. If the complexed rotations of said axial bar are assumed; Tl/2 radians of angular displacement through each of the two planes used and this being in step with TT/2 radians of mass (if) orbit of said axial bar. Then for fl/4 radians of action of the above actions the calculation becomes: - firstly as beforq/(IlD/8)2+ (IID/ 8)2 this will generate an hypotenuse or resultant for the contribution to the displacement of mass ($ ) caused by said complexed actions of said axial bar. A further contribution by said orbit of mass (5) about the axial bar also needs to be factored in on this occasion, so the new calculation for total mass (M) linear displacement becomes:- 6 ).

%-J* c

This peripheral linear displacement would constitute a "great circle" in the true sense. This equates to an enhanced radius calculated from multiplying the above calculated enhanced peripheral displacement by eight, to obtain a complete new two dimensional circumference C, then dividing this by 2IT. For a pitch of 1 metre (distance between said axial centre and said mass (/j)) an effective increase in radius to 1.73 metres from 1 metre. shows the normal track for the orbit of said mass (//!)-0 about an axial centre shown (/). Said orbit divided into quadrants at a standard pitch, or radius of 1 metre. Tangential tendency for the travel of mass ( //) is shown along the line (fo). At various times, in terms of the progress of said orbit the displacement of said tangential tendency is stepped off, with the corresponding angular displacement shown, along with the increasing radial pitch; distance C-/7. in the said orbital distance time frame. The dotted detail relating to the angle and pitch attained for a full quadrant of orbital displacement. This important distance being 1.86 metres, radially. The extra peripheral displacement caused by the out-plane component does equate to an increasing pitch mathematically; of course in reality distance C-// (pitch) is a constant 1 metre In regard to centrifugal force the neutral, zero force situation would obviously be for said out-plane angular displacement away from said axial centre to be equal to the in-plane, normal orbital angular displacement of mass (//) approaching said axial centre (/).

With the above parameters in force however this does not exactly happen. For one quadrant of normal massf//^orbit about axial centre above conditions prevailing, this will correspond to an in plane, planer peripheral displacement of 1.571 metres. For the above in-plane/ out-plane complex ($, this would correspond to a peripheral displacement (great circle) of 2.72 metres. The sum 2.72/1.57lx 90° in plane (planar) angular displacement -90° shows an out plane contribution of 66°. Therefore, the angle of turn approaching the central axiom for mass ) is 90° and the angle turned away from said axiom be 66°. Mass (5") will seek the equivalent of a straight line tangential escape from said axiom. Drawing 6a shows the tangential progress of mass (£-) away from shown axiom through the equivalent distance II/2 radians (IED/4 peripheral displacement) 1.571 metres in this case/fyj/fchown. The distance and angular displacement from said axiom being shown in dotted detail. Said angle being calculated at 57.25°, 90° - 57-25° = 22.75° this would constitute the angle turned away from said axiom in the time period (IX/2) radians of orbit, albeit in 2 dimensions. Distance axiom (/) to mass (£ ) increasing a calculated distance 0.86 metres during this time. The effective radius acting during said 6 complex action, calculated from said enhanced peripheral displacement, R= C/2TT =1.73 metres, which represents an increase in radius of 0.73 metres during this phase. Slightly less than the 0.86 metres required. This mismatch could be eliminated by further adjusting the working parameters of the apparatus.

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Mechanical Inertial. Propulsion System Specification (10)

The cycle as explained and illustrated above for a single orbiting mass, manipulated by some means to have 2 parts. One a complex in and out plane combination and planar component to each cycle. It is speculated here that in such a system that centrifugal force produced will not be the same in all directions. It is further speculated that the predominant imbalance produced would tend to be in one direction. However, there will be other much lesser imbalances in other directions which can be eliminated by outphasing and counter-rotating multiple single systems above. Such a device that may be deemed to realise the above speculations is outlined in drawingy?. A mass (5 ) is set up to rotate (I If.) about an axial bar (X >) by some propulsive means not shown. Said axial bar being secured as shown by some means to an inner frame, in turn pivoted and secured to shown outer frame by some gimbal means (# ). On an axis perpendicular to that occupied by said gimbals (# ) said outer frame is secured to the container of the device or payload by shown outer gimbals (/ty)-Necessary rotations to advantage of said framework about said gimbals being impelled and co-ordinated by some means not shown In this expression gimbals (/it) have the possibility of some linear motion shown (effectively carrying said axial bar + said inner and outer frames also) again propelled and co-ordinated to advantage by a means, not shown.

The contrived; by the above technique, that of the previously discussed in plane/ out plane complexing of mass (§) orbit of axiom (i) will occur at the alter end of the apparatus to where shown Qj) resultant force exhibits. Gimbals (/£) travel to and fro according to the direction of the movement of mass (jjf.) when aligned with said axiom bar (X ). During said transit, if such was ordinated in the direction (Q) shown, mass (5) would be made to experience propulsive slowing by the action of some means exhibiting through shown, motor rail (j>£): possibly linear induction. Mass (§), motion (PP) having ceased at the suitable moment, would be allowed to proceed through a planar orbital phase. A centrifugal moment will then be exhibited in direction 03) also said propulsive mass slowing will present a force in this direction. Mass (sf), due to its orbit will present at the opposite side of the apparatus travelling in the opposite direction and on aligning with (/ ) and/or (£ ) linear displacement (/If) resumes in the opposite direction also. A further motor rail (/X ) is again disposed to affect the motion of mass ($"), this time to speed it up. The consequences of this are felt as force in the direction (/3) again. When sufficient speed has been imbued to said mass (|f.) said motor rail (/%) disengaged and linear motion (/If) is ceased. A further complexed in plane/out plane action is completed as outlined previously and the now fast moving mass (S) is then, by this means orientated to be moving again in the opposite direction to engage with a further suitably disposed motor rail (/X) again to commence another phase of linear action as previously outlined.

This work speculates that said complexed component in the cycle causes an imbalance along the working axis of the apparatus consistently and intermittently in one direction only. The apparatus is made to leak energy in one main direction because of the imbalance generated in the centrifugal moments attending either end of said axis. To balance out any forces not occurring along said axis (it is acknowledged that to begin the outplane phase of the cycle that some energetic impulse must be delivered to said orbiting mass (5) perpendicular to the plane of said orbit), referring to drawing diagrammatical representation of how a multiplication and co-ordination of the described apparatus would balance out stray, unwanted forces.

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Mechanical Inertial Propulsion System Specification (11) _ ,

Sez OrQu/ci^ 7/?

The 2 planes along which said mobile mass is operating are shown, complete with shaped arrows stating the direction of masses during the cycle of activities. Arrows are shaped as growing narrower if the speed of said masses be decreasing, or growing wider if speed be increasing. Dotted arrows depict the changes of direction of masses , in plane at the forces out end and altering planes at the neutral end. The direction of rotations between planes are denoted ( ) out plane end ) in plane only end (7)- It is clear that all operations of the necessary 4 structures must be exactly in step with each other. Further, because of the dwell time associated with the neutral end of the structures then at least one more set of such structures out phased with the original would be required to affect continuous force.

Drawing outlines a modification and a simplification of the device as outlined in drawing^/<^2, doing away with the necessity for any linear movement of axial bar (^) facilitated at gimbals7/f//4Axes #^,/0are shown, planar mass transits are denoted (J), completed rotatory position is marked 6 . Axial bar (. 2, ), axiom (./), axial arm ( 3 ), motor rails ( f%.), mass (5"), force delivery pointed (/3). Axial bar rotations are pointed by continuous arrows and mass with axial arm transiting through the apparatus are shown in dotted detail. Complexed movements of mass and axial arm in response to manoeuvres of axial bar are assumed but not shown but have been detailed earlier. (Identical as per above previously evaluated system.) Masses (5) are effectively "unlocked" when running parallel to shown axis; a mass ( 50 increases radial distance from axiom (/) shown when running toward end where (ft) is pointed and in opposite fashion decreases said radial distance when running away from direction denoted (]% toward end assigned &, '

A mass ) running in this direction would be increasing its speed under the influence of a motor rail ( /Jl), force resultant of this action exhibiting in the direction (ft). Depending on how much energy is absorbed in causing the apparatus and payload to accelerate in direction 13 then residual energy contained as kinetic within (X) will be transferred by shown & complexed action to moving in the opposite direction along #axis shown, toward (ft) direction pointed. Note/ during complex procedure /-5". radius must, be held constant by some means. Note also, for a given mass (jf) peripheral speed about (/) decreases as centrifugal force increases but rotational kinetic energy decreases also. As mass (5") travels along shown motor rail {fZ) its speed is reduced the force released in doing so again emerging in direction (ft). Mass (5") releases from (jX) at a suitable point and the radius (/'-.5) is again locked and the mass is allowed to orbit in planar fashion to dispose on the opposite side of the -axis. The consequence of this is a centrifugal moment again pointed to exit in direction Q$). As mass arrives adjacent { IX) it is again released to move along axial arm (J, i.) and become again accelerated through that component as another cycle as outlined above begins. Note, during in plane phase to ensure constant force delivery (ft) a controlled reduction in said radius (/ -JjT) could be imbued this would also lead to a smooth take up at the motor rail as directions could be harmonised (5 f 12. ■) at this point.

Mechanical Inertial Propulsion System

Specification (12)

Referring to drawings t^fas an additional evaluation of constructions (3) of earlier cited submission, as pertinent in support of an explanation of the speculated function of the subject of the present submission. Centrifugal force would be . exerted in the direction ( // ') shown, parallel to arrowed direction (#). Drawing ^7 By/as side view andr«j2as front view of a single suggested element system.

Structure consists of a convenient number of masses ("4-) each articulated on (3) "hinged" axial arms to orbit a central axiom (/). For a portion equivalent to a TT/2 section of one complete cycle, said hinge ($) is described into the fully open condition of maximum orbital radius. There is contrived, no motion in said hinge perpendicular to said radial orbit at or during this phase and all said masses (j£) realising this side of the apparatus would be contrived to transit this phase in this way In this way a maximum possible centrifugal moment is always experienced by the apparatus in the same direction. Mass numbers and dispositions was speculated to give continuous force in said direction, shown (0,) and to cancel out all stray forces not appearing along direction (2jf); two back to back systems as shown, counter-rotating with two further systems arranged adjacently; all such systems being equivalent in every way, would be required. Each said counter-rotating back-to-back arrangement, of course orbiting its own counter operating axiom (/), rotation denoted as (5~). At any one time three masses here are disposed for each element system by said continuously open hinge, to be in a propulsion mode Or the equivalent, that is two masses disposed 22 .5° about either side the normal direction ({?), or just as equivalently transiting between these two extremes.

Said equivalent is as shown; one element mass aligned along axis (%) producing the full centrifugal moment for this mass and two at such an angle from axis ($?) as only to give half their value of available force to this direction; equivalent to two thirds delivered along said axis (,&); delivered at all times. Note/ 3/8 the available reaction mass is being used at any one time, the other 5/8 being manipulated in order to avoid opposing moments of force along dimension (if) and to re-establish element masses {If-) into the propulsion mode.

Said 5/8 of intermittently redundant mass being additional to any payload then this device would be most suitable in delivering small or moderate accelerations to relatively large payloads, with operating (rotating) speeds better to being high. Masses (l£) are equally separated either side of said axia ( /) therefore side to side centrifugal moments are balanced and contribute to the flywheel effect only in this system. This would equate to the missing 1/3 of said total centrifugal moment for hinged masses (4-) disposed into the "open hinged" maximal radial condition. It is clear that the element masses (4<) track for their orbit about axiom (/ ) is in the shape of a "Cardoid ' Systems that have manipulated masses to this shape of orbit in a planar (2 dimensional) fashion have demonstrated a small reaction, favouring a single direction.

Small in relation to the energy put into the system. This work speculates that the above suggestion; a maximal pitch and planar portion of the cycle along with the facility to take out element masses, out of this plane of action at another portion of the cycle would yield a far more efficient inbalancing of the system to advantage, if all relevant components be coordinated as prescribed. Outside the 2D planar portion of the cycle previously . described said hinge is either closing (£) or opening (7) for equal 1/3 portions of the total action. However, said hinge is re-established from fully closed to fully open condition by shown (in dotted detail) opening acceleration (IX ) phases, followed by an opening deceleration phase as mass (if.) is eased into position. It is clear therefore additional facility for energy distribution around the system would be required.

-I)-

Mechanical Inertial Propulsion System

Specification 13

Energy distribution in order for maximum efficiency to be realised. For example, energy could be stored pneumatically during said (/$ ) action for one mass and used to begin hinge closure for another mass (^); this being energetically demanding against said centrifugal moment. Further, masses (Jf) acceleration ((2 ), motion is accelerated in 3 dimensions before being restrained to 2 (masses being hurled into the propulsion phase). The angular velocity as combined in 3 dimensions will equate to 2 and by the law of conservation of angular momentum, said 2 dimensional orbit will speed up. Additionally, as masses radius of orbit is effectively reducing at said end of propulsion "2D" phase, again by said law of conservation of angular momentum, angular velocity is required to increase. As before this energy could be kept in balance by absorbing said increasing angular velocity pneumatically and redistributing the action to said opening and closing of said hinge mechanisms to order. Necessary machinery to do this would be un-novel and functionally familiar.

Note/ Energy should not escape from the system except to advantage. Any "in plane" action inevitably deviating away from direction ($) during mass (if-) transit, during propulsion phase is balanced because of the action of proposed counter-rotating dual arrangement and along with said extra planar (hinged) actions balanced by said back to back dualities would under such arrangements be transformed into a simple flywheel effect. Subject to experiment, the above reasonings set forth the system as a viable propulsion means and demonstrates that by manipulating tied orbiting masses between planar and geodesic modes, at diametrically opposite positions, substantial imbalance could be generated.

The reality of the response of a tied orbiting mass to adopt a 3 dimensional displacement to it's transit in order to minimise a centripetal moment; preferring a non linear (extra-planar) tangential escape, in the absence of a planar linear alternative also given a sufficient perpendicular initiating impulse, is demonstrated by the recovery of masses in the apparatus shown in drawingsThis action being familiar and useful for steam valves progressively opening according to rotational velocity. The faster is the orbit of the masses, the greater the outward and upward force caused by the centrifugal moment against the downward and inward acting gravitational moment. Without this restraining gravitational moment masses would spiral out from the axiom as far as physically allowed and by the law of conservation of angular momentum, if the out going motion be stopped and the centrifugal moment measured at any stage of this happening, then as the radius of orbit under test gets larger angular velocity gets smaller and centrifugal force gets smaller (though acting time for any direction diametrically away from the axiom gets larger).

Further, as said masses actively spiral out from the axiom and the quicker this occurs, then the greater is the absolute reduction in centrifugal force (the zero condition being tangential escape). Therefore as a mass moves between an equatorial transit progressively to a geodesic (under some adequate initiating impulse), by the same reasoning, as it does so, tension on a restraining tie (axiom to mass) would be reduced. A geodesic is an effective, somewhat of a straightening out of said equatorial orbiting curve, the effective further enhancement of this process to an effectively straight line can occur after said initial perpendicular impulse; depending on the speed of transit between equatorial mode and geodesic mode. The above being the case, for the situation of a single mass tied to orbit a constant axiom and by Correct manipulation of said orbit by direction and speed to successive geodesies; in theory it should be the orbiting mass in continually changing direction, to do so relatively forcelessly.

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Mechanical Inertial Propulsion System

Specification (14)

Emerging from the above is a secondary concept for the evolution of desired inertial propulsion. It shares the idea of complexed planar and non-planar rotations of singular masses. A single element of said evolved system (see drawings ^Vof a rotating (# ) mast (5~ ); means to accomplish all movements of the system are assumed, (not shown); common engineering techniques are available to realise this. Rotating with said mast would be equivalent pairs, mounted opposite each other, axial arms ( X ) with equivalent masses disposed at the alter ends of said axial arms. At the opposite ends of said axial arms to where said masses (J ) be affixed, axial arms be affixed said mast by a main pivot ( / ) means, allowing perpendicular direction of rotation to that exhibiting about mast ( 5") pointed ( £ ). Said rotating mast causes said masses to orbit, around it and consequent centrifugal force (?) shown, disposes said masses away from said mast shown i . . The larger radius is displayed (/3). Said masses (3') are deemed to have inertia in direction IX shown, this could be gravitational or due to the acceleration of the apparatus in the opposite direction to that pointed. Said mast has the capacity to extension in shown direction ( 7 ); energy into the action (/o) pointed. (Note optional pivoting of masses (3 ), {If) shown). Referred to extension of mast is of necessity a fast (ballistic) action, in order that said centrifugal force does not have time to require that masses (3) follow said extensive action.

Said ballistic extension of mast ( 5"), ( 7 ) imbues left shown axial arm (Z ) and right shown axial arm with respectively an anti-clockwise and a clockwise moment, opposing respective clockwise and anti-clockwise moments induced by centrifugal moments (&'). If, as said ballistic mast extension (7 ) is carried out quickly enough, the natural inertia IX of masses (3) will cause them not to follow instantaneously the centrifugal influence. In fact, the initial impulse, sufficiently strong, the moments would cause some motion of the masses in the direction (0; this being stabilised as motion (J ) proceeds. As it does so the apparatus attains the condition shown in drawing fZqi. The operating radius has diminished to /4- shown and the tendency (//) track for masses (3) under the influence of centrifugal force is shown. This action of compressing this radius of action is; against the natural tendency for the orbiting masses to escape tangentially. Therefore the apparatus will resist this and the only way for this to happen is that said motion ( f ) be resisted. Force released in doing this is pointed in direction (<$, as a short impulse. Note, masses are induced briefly into a spiral action. The peripheral (orbital) speed of said masses must be large in comparison to the linear motion ( 7 ) for release of force in this way; in plane velocity being effectively large compared to induced out plane motion (*f)-

When the impelling force is released from mast extension (7 ) and left to run free, then the disposition of the apparatus rapidly returns to that exhibited in drawing I, under impulse from centrifugal force ( 8') said mast reverses said extension (7 ) as said masses (J) respond to the tendency to move away from the main pivot to the maximum extent possible; on approaching this condition another impulsive mast ( $ ) extension could again be introduced. Practically, more than one duality of masses (3 ) could be affixed to the main pivot ( / .). For continuous force delivery, multiple and outphased elemental systems, as described above would be required. They could all be mounted on the same shaft, with equal numbers of rotations for mast parts ( 5 ), rotating clockwise and anti-clockwise to ensure balance. Each main pivot (t) could, by some means be rotated independently of the others.

Mechanical Inertial Propulsion System

Specification 15

For a given angular momentum conserved, with decreasing radius, centrifugal force increases. This would offset some of the loss of centrifugal force at the main pivot (' / -) due to lack of alignment with orbiting masses (3 ). However, decreasing radius, in relation to the increase of centrifugal force, the rotating kinetic energy is reduced. It is possible that energy could be released from the system by loss of said rotational kinetic energy to said linear impulse by said forced mast extension. However, it is speculated here that some of the energy needed to compress the radius of masses orbit will go into accelerating the apparatus and/ or payload.

Sub-note/ unless rotational peripheral speed (linear measurement) is high in comparison to the linear acceleration of mast ( 5 ), as previously described; the nearer to equivalence these two values are, then we will see earlier described loss of centrifugal force due to effective radius increase, caused by the perpendicular to the axis of rotation movement. In the earlier system this phenomena was put to use, here it exists also but must be minimised.

Mechanical Inertial Propulsion System

Claims (1)

1. Claims.

   Inertial propulsion generated by the mechanical manipulation of moving masses to cause a singular directional inbalance of incidental centrifugal and/or linear moments of force, the phenomenon of precession being controlled to advantage.

   Amendments to the claims have been filed as follows

   Claims.

   For the main part; a method for moving a system in a first direction, which system includes at least one moving mass adapted to orbit about a remote axiom. Said remote axiom also adapted to rotate in two planes, the only other planes possible when said orbiting plane be considered. First additional plane being coordinated perpendicular to said orbit, with the second additional plane coordinated in the direction perpendicular to said first additional plane. Considering the transient condition; said mass aligned along the line of rotation for said first additional plane and allowing for equal angular displacements through all said planes from this point, the directions of said additional displacements taking account of the orbiting direction of said mass. For n / 2 radians of all above displacements causing said orbiting mass to precess through part of one systemic cycle. Said mass being caused to follow a path which involves two such precession dominated portions involved in minimising and/or deflecting any would be centrifugal moment. With all displacements combining to cause said orbiting mass to assume an external geodesic path. This activity taking place in substantially the opposite direction to said first direction of the system. Said mass being delivered to a point whereby additional planar activity is ceased allowing a planar equatorial orbit of n radians duration, to take place in said system first direction, delivering a full centrifugal moment. Again two per cycle.

   To assemble constant force in said first direction balanced, in phase counter-rotating dualities of above outlined systems be multiplied; each duality coordinated out of phase to others, to exhibit at one time all phases of systemic action. Required gimbals, control and drive means being adaptable from familiar existing engineering means.

   Said moving mass restrained to orbit about a remote axiom by connecting axial arm means. Axiom located at the centre of an axial bar means; said axial bar also rotatable about said axiom through two planes as described above.

   Said precessional displacement phase being commensurate at perigee, said mass and axial arm aligned along said first additional plane tilt line. Planar orbital transit with equivalent rotational displacements about said tilt line and of tilt line deliver said orbiting mass to apogee. Said progression perigee to apogee, possessing a progressively increasing radial component through this portion of the cycle. As said orbiting mass proceeds. Considered V*

   cycle, from adjacent to said tilt line and line action to the perpendicular condition, said additional planes of action having an increasing effect,

   having an increasing radius of action as this part of the cycle proceeds. Apogee being the position of said orbiting mass perpendicular to and the furthest possible position from the end of said tilt line. In the middle of said tilt line, this being the position of greatest effect for said additional components on the direction of orbit of said mass. Overall, the length of mass orbit will continuously increase through the considered lA cycle, therefore continuously increasing, effectively the radius of said mass orbit; analog to the forceless condition of tangential mass escape from orbit. This system also analoging directly to the precessive behaviour of considered point mass elements within the rim of a rotating gyroscope. Wherewith, when a perpendicular and first extra planar rotation is supplied then a spontaneous tendancy for the system to invoke a precessional second extra plane to the action is the result. Causing said mass elements inhabiting said gyroscope rim to adopt said external geodesic orbits about their axial centre, until lA of extra planar action be complete and the direction of said orbiting mass elements lines up in the direction of said first extra planar rotative action.

   Four inner or outer counter-rotating have systems mounted at opposites as in phase quadruplets. Said quadruplets being suitably multiplied and out-phased along said shafts in order to give constant force faithfully in said first direction.

   In the second construction, hinges are arranged fixed on to a rim of a suitable wheel and by this means equivalent element masses, each affixed the end of a hinge at the furthest point away from said hinge pivot point are able imbued with a means of orbit in two ways. Firstly, in the plane of the turning wheel and secondly in a direction perpendicular to this, furnished by said hinge arrangements. Said wheel rotation and hinge movements being driven and co-ordinated by familiar engineering means.

   Said two actions being co-ordinated such that, at a first direction for this system, said hinges be in the fully open condition and for an arc period of about 1/8 of a wheel cycle either side of said first direction. At this stage and altogether lA of a complete cycle, said masses follow a flat equatorial orbit at maximum radius, delivering a full centrifugal moment. At a direction diametrically opposite to said first direction hinges being contrived in the fully closed condition exerting a minimal centrifugal moment.

   -IS -

   The system maintains an imbalance between the two extremes by the way in which said hinges be manipulated in between.

   As a particular hinge is opening a said affixed mass will adopt an external geodesic path or orbit around said wheel hub axiom and as said hinge closes an internal geodesic is then adopted.

   Engineered connecting means between said hinges undergoing these opposite transformations transferring energy from said energetically favoured external paths to assist operation of internal components. Said two processes being closer to balance within this expression because inclusion of said hinge facilities, meaning the absence of direct rigid link at constant radius.

   The ratio of wheel radius and hinge length being such that no jerkiness exist within said transformations operation, particularly at the entry to maximum radius condition. Co-ordination also being crucial to this. Said externally geodesic path transferring smoothly to said equatorial; three dimensional into two.

   Smooth and continuous force generation faithfully into said first direction would be effected by together mounting four wheel systems organised into two counter- rotating back to back structures.

   For the third expression, hinged masses are facilitated to orbit an axiom arranged perpendicular to said hinge rotation, such that a resulting centrifugal moment might cause said hinge masses to orbit said axiom at a condition of maximum radius. Said axiom being further facilitated that, it has the capacity to accelerate episodically and ballistically in a direction perpendicular to said mass equatorial orbit.

   Said axiom, at said optimum maximum radius condition being intermittently accelerated sufficiently strongly that the static inertia, operating perpendicularly to said orbital plane, prevents said hinges, under the influence of centrifugal moments, derived from angular momentum possessed by said masses, following and catching up. That the inertia of said masses at equatorial orbit be insufficient to accelerate said masses outward and upward quickly enough to keep up. Such an action causing contraction of said mass orbit, this taking effort by the system.

   Said acceleration of said axiom therefore being resisted, affording an impulse of force to the system in the direction opposite to said direction of axiom acceleration.

   Axiom travel ceasing at the end of a useful forceful period, said orbiting masses then restoring to said maximum radius equatorial orbit under the

   influence of said centrifugal moments persisting in the system. This being achieved relatively forcelessly within the context of the system, preceeding another strike of axiom acceleration.

   Counter-rotating axia, mounted on to the same axial centre and phased to strike at varied times could deliver constant force in the second direction, as stated, that being in the opposite direction to said axial strike.

   Suitable and familiar engineering means would be available and if correctly applied could drive said axial rotation and perpendicular acceleration.

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