WO2014006478A2 - Spacecraft docking in planetary orbit - Google Patents
Spacecraft docking in planetary orbit Download PDFInfo
- Publication number
- WO2014006478A2 WO2014006478A2 PCT/IB2013/001416 IB2013001416W WO2014006478A2 WO 2014006478 A2 WO2014006478 A2 WO 2014006478A2 IB 2013001416 W IB2013001416 W IB 2013001416W WO 2014006478 A2 WO2014006478 A2 WO 2014006478A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- kinetic energy
- rotor
- accumulators
- racks
- differentiated
- Prior art date
Links
- 238000003032 molecular docking Methods 0.000 title claims abstract description 13
- 238000010521 absorption reaction Methods 0.000 claims abstract description 33
- 230000033001 locomotion Effects 0.000 claims abstract description 15
- 238000010276 construction Methods 0.000 claims abstract description 11
- 238000009825 accumulation Methods 0.000 claims abstract description 9
- 230000000750 progressive effect Effects 0.000 claims abstract description 6
- 230000005540 biological transmission Effects 0.000 claims description 7
- 230000001965 increasing effect Effects 0.000 description 7
- 230000001939 inductive effect Effects 0.000 description 4
- 239000000243 solution Substances 0.000 description 4
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 230000004069 differentiation Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000005945 translocation Effects 0.000 description 2
- 230000002730 additional effect Effects 0.000 description 1
- 239000000872 buffer Substances 0.000 description 1
- 239000007853 buffer solution Substances 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000021715 photosynthesis, light harvesting Effects 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F7/00—Vibration-dampers; Shock-absorbers
- F16F7/10—Vibration-dampers; Shock-absorbers using inertia effect
- F16F7/1022—Vibration-dampers; Shock-absorbers using inertia effect the linear oscillation movement being converted into a rotational movement of the inertia member, e.g. using a pivoted mass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/646—Docking or rendezvous systems
- B64G1/6462—Docking or rendezvous systems characterised by the means for engaging other vehicles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F2232/00—Nature of movement
- F16F2232/06—Translation-to-rotary conversion
Definitions
- the present invention relates to a spacecraft docking in a planetary orbit that increases a tolerance of a velocity acceptable during connecting space modules.
- a connection of two manned or unmanned spacecrafts in the outer space requires providing the spacecrafts with appropriate docking systems having construction featuring homing functionality that enables for a correction of the modules being connected in relation to each other within a predetermined tolerance.
- This problem to be solved is to stabilize relative velocity of the objects being connected, as before the connection the objects should be in motion of substantially same velocity and substantially same direction. The problem appears when the objects that are to be connected may not be appropriately stabilized and in the moment of contact between them excessive impact energy is generated resulting from the mass and relative velocity of the objects.
- a buffer system of a docking object should feature a minimal effect of rebound after the operation of impact at different relative velocities.
- Such an operation in a limited extent is provided by the device for absorbing impact energy disclosed in international patent application W02004028864 disclosing a device for absorbing energy, in which kinetic energy is converted into kinetic energy of rotating masses.
- an element absorbing energy is connected with two toothed bars which by medium of toothed wheels drive kinetic energy rotor accumulators in forms of rods with moveable weights slidably mounted on the rods.
- WO2005121593 discloses a device for absorbing energy comprising a beater element cooperating with an energy dissipation arrangement comprising a toothed bar inducing rotation of rotating masses, thus causing a conversion of progressive movement kinetic energy resulted from an impact into kinetic energy of a rotational movement.
- the toothed bar drives a rotor by means of a toothed wheel, wherein the rotor cooperates with a moveable weights.
- the moveable weights are maintained in appropriate distance from a rotation axis by means of springs.
- the object of the present invention is to provide an increased efficiency of absorption and dissipation of energy of collision between objects being docked together at a greater tolerance of a relative velocity of these objects that possibly may occur during docking.
- a spacecraft docking in a planetary orbit comprising a conical external element of the shape conformable to the shapes of the elements connected thereto, and comprising at least one kinetic energy absorption rotor arrangement fixed to the bearing construction, in which kinetic energy of progressive movement is transformed into kinetic energy of rotational movement, wherein the arrangement comprises a moveable beater element cooperating with racks interengaged with toothed wheels driving the kinetic energy rotor accumulators of a given moment of inertia.
- At least two racks of the kinetic energy absorption rotor arrangement cooperating with the beater element interengage with toothed wheels of the kinetic energy rotor accumulators of differentiated capabilities of energy accumulation, wherein between the beater element and racks interengaged with toothed wheels of kinetic energy rotor accumulators differentiated gaps are defined providing differentiated idle stroke of the beater element relative to the racks.
- the kinetic energy rotor accumulators are preferably rotatively mounted on the independent body plates fastened to the bearing construction.
- the kinetic energy rotor accumulators preferably have differentiated moments of inertia.
- the kinetic energy rotor accumulators are preferably driven by means of toothed gears of differentiated transmission ratios that increase rotational velocities.
- the idle stroke of the rack driving the toothed wheel of the kinetic energy rotor accumulator having a capability of accumulation of higher energy is preferably greater than the idle stroke of the rack driving the toothed wheel of the kinetic energy rotor accumulator having a capability of accumulation of lower energy.
- the body plates preferably have through openings.
- a spacecraft in which according to the construction of the present invention a possibility of inducing rotational movement of consecutive kinetic energy rotor accumulators was implemented, provides an increased efficiency of absorption and dissipation of collision energy during docking at different random collision velocities.
- Particularly significant abrupt stepped increase of a capability of absorbing kinetic energy during collision of spacecrafts is obtained by inducing rotational movement of consecutive kinetic energy rotor accumulators of increasing moments of inertia or by inducing rotational movement of consecutive kinetic energy rotor accumulators which are gained with increasing rotational velocities by employment of gears of increasing transmission ratios that increase rotational velocities.
- the spacecraft according to the present invention is suitable for absorbing energy in case of collisions of small energy as well as in a case of collisions of higher energy.
- the device according to the present invention provides an efficient and very smooth shock absorption of collision, as an absorption of kinetic energy of progressive movement takes place with using kinetic energy rotor accumulators of the smallest moment of inertia.
- the device according to the present invention also provides appropriately efficient and smooth shock absorption, as kinetic energy absorption takes place with using several rotor accumulators of increasing energy absorption capabilities.
- Fig. 1 presents a general view of a spacecraft designed for docking in a planetary orbit depicting schematically buffering energy absorption rotor arrangements in broken-out sections,
- Fig. 3 shows a top view of the energy absorption rotor arrangement with rotor kinetic energy accumulators of the same moment of inertia with employment and of different transmission ratios
- Fig. 4 presents a top view of the energy absorption rotor arrangement with rotor kinetic energy accumulators of different moments of inertia.
- the spacecraft according to the present invention is provided with energy absorption rotor arrangement 1 , in which three racks 2 separated from each other are slidably mounted which by medium of toothed wheels 3 drive three kinetic energy rotor accumulators 4, 5, 6 of differentiated moments of inertia. Between the beater element 10 and particular racks 2 gaps 7, 8, 9 are formed defining an idle stroke of the beater element 10 relative to the racks 2.
- the gap 9 between the beater element 10 and the rack 2 driving the toothed wheel 3 of the kinetic energy rotor accumulator 6 efficient for accumulating the biggest energy is larger than the gap 8 between the beater element 10 and the rack 2 driving the toothed wheel 3 of the kinetic energy rotor accumulator 5 efficient for accumulating medium energy, whereas the gap 7 between the beater element 10 and the rack 2 driving the toothed wheel 3 of the kinetic energy rotor accumulator 4 efficient for accumulating the smaller energy is the smallest.
- elastic shock absorbing elements are arranged in forms of springs 15.
- Kinetic energy rotor accumulators 4, 5, 6 are rotatively installed on the separated body plates 11 fixed by medium of a mounting flanges 16 to the bearing construction 17 of the spacecraft, in the interior of a conical external element 12 of the shape conformable to the shapes of the elements connected thereto, and provided with at least one kinetic energy absorption rotor arrangement fixed to the bearing construction.
- the racks 2 are slidably guided in guides 18 mounted to the arched beater element 10. Through openings 19, 20 formed in the mounting flanges 16 enable for translocation of racks 2 and guides 23 of the beater element 10 to the interior of the bearing construction 17 of the spacecraft. Furthermore the guides 23 of the beater element 10 are slidably embedded in the front plate 24 of the external plating 25 of the spacecraft.
- kinetic energy rotor accumulators 6 of the same moments of inertia.
- a differentiation of capability of collision kinetic energy accumulation is in this embodiment obtained by employment of toothed gears of differentiated transmission ratio.
- a given transmission ratio is determined by the effective diameter of the toothed wheel 3a, 3b and 3c that cooperates with rack 2, and thus in the presented embodiments the kinetic energy rotor accumulator 6 driven by means of the toothed wheel 3a of the biggest effective diameter has the lowest kinetic energy absorption capability, the kinetic energy rotor accumulator 6 driven by means of the toothed wheel 3b of the medium effective diameter has the higher kinetic energy absorption capability, and the kinetic energy rotor accumulator 6 driven by means of the toothed wheel 3c of the smallest effective diameter has the highest kinetic energy absorption capability.
- the toothed wheel 3a of the biggest diameter has the effective diameter two-fold bigger than corresponding diameter of the toothed wheel 3c of the smallest diameter
- the kinetic energy rotor accumulator 6 driven by means of the toothed wheel 3c of the smallest effective diameter shall gain angular velocity two-fold greater than corresponding velocity of the kinetic energy rotor accumulator 6 driven by means of the toothed wheel 3a of the greatest effective diameter, thus it shall feature four-fold greater capability of rotational movement kinetic energy accumulation.
- the embodiment presented in Fig. 4 comprises kinetic energy rotor accumulators 4, 5 and 6 of differentiated moments of inertia and toothed gears of differentiated transmission ratios.
- the kinetic energy rotor accumulator 6 of the biggest moment of inertia is driven by means of the toothed wheel 3a of the greatest effective diameter, and the kinetic energy rotor accumulator 4 of the smallest moment of inertia is driven by means of the toothed wheel 3c of the smallest moment of inertia.
- Such a construction provides a possibility of defining a smooth characteristic of a capability of vibration kinetic energy of the device according to the present invention.
- unidirectional couplings are also employed, though not presented on the drawing, and arranged between the toothed wheels 3 and kinetic energy accumulators 4, 5, 6.
- the function of these unidirectional couplings is transferring a torque onto kinetic energy rotor accumulators, and after absorption of energy, when angular velocity of the toothed wheel 3 shall be smaller than angular velocity of corresponding kinetic energy rotor accumulator 4, 5, 6, the unidirectional coupling is disconnecting thus it enables for unrestricted rotation of the kinetic energy rotor accumulator 4, 5, 6.
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
- Vibration Dampers (AREA)
Abstract
A spacecraft docking in a planetary orbit comprising a conical external element of the shape conformable to the shapes of the elements connected thereto, and comprising at least one kinetic energy absorption rotor arrangement fixed to the bearing construction, in which kinetic energy of progressive movement is transformed into kinetic energy of rotational movement, wherein the arrangement comprises a moveable beater element cooperating with racks interengaged with toothed wheels driving the kinetic energy rotor accumulators of a given moment of inertia, characterized in that at least two racks (2) of the kinetic energy absorption rotor arrangement (1) cooperating with the beater element (10) interengages with toothed wheels (3, 3a, 3b, 3c) of the kinetic energy rotor accumulators (4, 5, 6) of differentiated capabilities of energy accumulation, wherein between the beater element (10) and racks (2) interengaged with toothed wheels (3, 3a, 3b, 3c) of kinetic energy rotor accumulators (4, 5, 6) differentiated gaps (7, 8, 9) are defined providing differentiated idle stroke of the beater element (10) relative to the racks.
Description
SPACECRAFT DOCKING IN PLANETARY ORBIT
The present invention relates to a spacecraft docking in a planetary orbit that increases a tolerance of a velocity acceptable during connecting space modules.
A connection of two manned or unmanned spacecrafts in the outer space requires providing the spacecrafts with appropriate docking systems having construction featuring homing functionality that enables for a correction of the modules being connected in relation to each other within a predetermined tolerance. However particular problem to be solved is to stabilize relative velocity of the objects being connected, as before the connection the objects should be in motion of substantially same velocity and substantially same direction. The problem appears when the objects that are to be connected may not be appropriately stabilized and in the moment of contact between them excessive impact energy is generated resulting from the mass and relative velocity of the objects.
As elements absorbing impact energy in spacecraft docking systems elastic buffer arrangements are employed, such as in a known docking mechanism disclosed in patent application US3608848.
A buffer system of a docking object should feature a minimal effect of rebound after the operation of impact at different relative velocities. Such an operation in a limited extent is provided by the device for absorbing impact energy disclosed in international patent application W02004028864 disclosing a device for absorbing energy, in which kinetic energy is converted into kinetic energy of rotating masses. In this known solution an element absorbing energy is connected with two toothed bars which by medium of toothed wheels drive kinetic energy rotor accumulators in forms of rods with moveable weights slidably mounted on the rods. An appropriate progressiveness of energy absorption is obtained in this known solution by employment of the moveable weights located as close to the rotation axis of the rotor with the rods as possible in order that a moment of inertia of the rotor in the initial phase of energy absorption be as small as possible. In further movement phase while the rotor starts to rotate, the weights start to translocate under influence of centrifugal force and move away from the rotation axis along the rod axis, until they
reach the rod end limiters and in such weight positions the biggest moment of inertia of rotor is achieved that enables for absorption of the increased kinetic energy.
International application WO2005121593 discloses a device for absorbing energy comprising a beater element cooperating with an energy dissipation arrangement comprising a toothed bar inducing rotation of rotating masses, thus causing a conversion of progressive movement kinetic energy resulted from an impact into kinetic energy of a rotational movement. In one of disclosed embodiments of this known solution, the toothed bar drives a rotor by means of a toothed wheel, wherein the rotor cooperates with a moveable weights. In order to provide a progressive change of a moment of inertia of the rotor during a process of energy absorption, the moveable weights are maintained in appropriate distance from a rotation axis by means of springs. The known solutions do not provide effective absorption of energy at different velocities of colliding objects during docking operation that are difficult to predict. Therefore the object of the present invention is to provide an increased efficiency of absorption and dissipation of energy of collision between objects being docked together at a greater tolerance of a relative velocity of these objects that possibly may occur during docking.
According to the present invention there is provided a spacecraft docking in a planetary orbit comprising a conical external element of the shape conformable to the shapes of the elements connected thereto, and comprising at least one kinetic energy absorption rotor arrangement fixed to the bearing construction, in which kinetic energy of progressive movement is transformed into kinetic energy of rotational movement, wherein the arrangement comprises a moveable beater element cooperating with racks interengaged with toothed wheels driving the kinetic energy rotor accumulators of a given moment of inertia. At least two racks of the kinetic energy absorption rotor arrangement cooperating with the beater element interengage with toothed wheels of the kinetic energy rotor accumulators of differentiated capabilities of energy accumulation, wherein between the beater element and racks interengaged with toothed wheels of kinetic energy rotor accumulators differentiated gaps are defined providing differentiated idle stroke of the beater element relative to the racks.
The kinetic energy rotor accumulators are preferably rotatively mounted on the independent body plates fastened to the bearing construction.
The kinetic energy rotor accumulators preferably have differentiated moments of inertia.
The kinetic energy rotor accumulators are preferably driven by means of toothed gears of differentiated transmission ratios that increase rotational velocities.
The idle stroke of the rack driving the toothed wheel of the kinetic energy rotor accumulator having a capability of accumulation of higher energy, is preferably greater than the idle stroke of the rack driving the toothed wheel of the kinetic energy rotor accumulator having a capability of accumulation of lower energy.
The body plates preferably have through openings.
A spacecraft, in which according to the construction of the present invention a possibility of inducing rotational movement of consecutive kinetic energy rotor accumulators was implemented, provides an increased efficiency of absorption and dissipation of collision energy during docking at different random collision velocities. Particularly significant abrupt stepped increase of a capability of absorbing kinetic energy during collision of spacecrafts is obtained by inducing rotational movement of consecutive kinetic energy rotor accumulators of increasing moments of inertia or by inducing rotational movement of consecutive kinetic energy rotor accumulators which are gained with increasing rotational velocities by employment of gears of increasing transmission ratios that increase rotational velocities.
The spacecraft according to the present invention is suitable for absorbing energy in case of collisions of small energy as well as in a case of collisions of higher energy. In the first instance the device according to the present invention provides an efficient and very smooth shock absorption of collision, as an absorption of kinetic energy of progressive movement takes place with using kinetic energy rotor accumulators of the smallest moment of inertia. In the second instance, the device according to the present invention also provides appropriately efficient and smooth shock absorption, as kinetic energy absorption takes place with using several rotor accumulators of increasing energy absorption capabilities.
In case of collisions of greater energy an additional effect occurs consisting in that collision kinetic energy is in a great part accumulated in the rotor accumulators featuring lower energy absorption capability before the rotor accumulators featuring higher energy absorption capability are actuated. Such a sequence of energy absorption provides smoother operation of the chair according to the present invention during actuation of next rotor accumulators, even those of the greatest capability of energy absorption featuring the biggest moment of inertia.
The exemplary embodiments of the present invention are presented below in connection with the attached drawings on which:
Fig. 1 presents a general view of a spacecraft designed for docking in a planetary orbit depicting schematically buffering energy absorption rotor arrangements in broken-out sections,
Fig. 3 shows a top view of the energy absorption rotor arrangement with rotor kinetic energy accumulators of the same moment of inertia with employment and of different transmission ratios, and
Fig. 4 presents a top view of the energy absorption rotor arrangement with rotor kinetic energy accumulators of different moments of inertia.
As presented in the embodiment of Fig. 1 and Fig. 2, the spacecraft according to the present invention is provided with energy absorption rotor arrangement 1 , in which three racks 2 separated from each other are slidably mounted which by medium of toothed wheels 3 drive three kinetic energy rotor accumulators 4, 5, 6 of differentiated moments of inertia. Between the beater element 10 and particular racks 2 gaps 7, 8, 9 are formed defining an idle stroke of the beater element 10 relative to the racks 2. The gap 9 between the beater element 10 and the rack 2 driving the toothed wheel 3 of the kinetic energy rotor accumulator 6 efficient for accumulating the biggest energy is larger than the gap 8 between the beater element 10 and the rack 2 driving the toothed wheel 3 of the kinetic energy rotor accumulator 5 efficient for accumulating medium energy, whereas the gap 7 between the beater element 10 and the rack 2 driving the toothed wheel 3 of the kinetic energy rotor accumulator 4 efficient for accumulating the smaller energy is the smallest. In order to decrease impact in the initial stage, during contacting the beater element 10 with
particular racks 2, between the beater element 10 and each rack 2 elastic shock absorbing elements are arranged in forms of springs 15.
Kinetic energy rotor accumulators 4, 5, 6 are rotatively installed on the separated body plates 11 fixed by medium of a mounting flanges 16 to the bearing construction 17 of the spacecraft, in the interior of a conical external element 12 of the shape conformable to the shapes of the elements connected thereto, and provided with at least one kinetic energy absorption rotor arrangement fixed to the bearing construction. The racks 2 are slidably guided in guides 18 mounted to the arched beater element 10. Through openings 19, 20 formed in the mounting flanges 16 enable for translocation of racks 2 and guides 23 of the beater element 10 to the interior of the bearing construction 17 of the spacecraft. Furthermore the guides 23 of the beater element 10 are slidably embedded in the front plate 24 of the external plating 25 of the spacecraft.
As shown in the embodiment of Fig. 3, in the kinetic energy absorption rotor arrangement 1 are employed kinetic energy rotor accumulators 6 of the same moments of inertia. A differentiation of capability of collision kinetic energy accumulation is in this embodiment obtained by employment of toothed gears of differentiated transmission ratio. In a case of toothed gear employment, a given transmission ratio is determined by the effective diameter of the toothed wheel 3a, 3b and 3c that cooperates with rack 2, and thus in the presented embodiments the kinetic energy rotor accumulator 6 driven by means of the toothed wheel 3a of the biggest effective diameter has the lowest kinetic energy absorption capability, the kinetic energy rotor accumulator 6 driven by means of the toothed wheel 3b of the medium effective diameter has the higher kinetic energy absorption capability, and the kinetic energy rotor accumulator 6 driven by means of the toothed wheel 3c of the smallest effective diameter has the highest kinetic energy absorption capability.
In the embodiment presented in Fig. 3, the toothed wheel 3a of the biggest diameter has the effective diameter two-fold bigger than corresponding diameter of the toothed wheel 3c of the smallest diameter, what in case of the same velocities of translocation of racks 2 and usage of kinetic energy rotor accumulators of the same moment of inertia results in that the kinetic energy rotor accumulator 6 driven by means of the toothed wheel 3c of the smallest effective diameter shall gain angular
velocity two-fold greater than corresponding velocity of the kinetic energy rotor accumulator 6 driven by means of the toothed wheel 3a of the greatest effective diameter, thus it shall feature four-fold greater capability of rotational movement kinetic energy accumulation.
The embodiment presented in Fig. 4 comprises kinetic energy rotor accumulators 4, 5 and 6 of differentiated moments of inertia and toothed gears of differentiated transmission ratios. The kinetic energy rotor accumulator 6 of the biggest moment of inertia is driven by means of the toothed wheel 3a of the greatest effective diameter, and the kinetic energy rotor accumulator 4 of the smallest moment of inertia is driven by means of the toothed wheel 3c of the smallest moment of inertia. Such a construction provides a possibility of defining a smooth characteristic of a capability of vibration kinetic energy of the device according to the present invention.
In an alternative embodiment which is not illustrated on the drawing, where for driving the kinetic energy rotor accumulator of the greatest moment of inertia is employed a toothed gear with a toothed wheel of the smallest effective diameter, and for driving the kinetic energy rotor accumulator of the smallest moment of inertia is employed a gear with a toothed wheel of the greatest effective diameter, the biggest progressiveness of vibration energy absorption shall be obtained.
In the described embodiments unidirectional couplings are also employed, though not presented on the drawing, and arranged between the toothed wheels 3 and kinetic energy accumulators 4, 5, 6. The function of these unidirectional couplings is transferring a torque onto kinetic energy rotor accumulators, and after absorption of energy, when angular velocity of the toothed wheel 3 shall be smaller than angular velocity of corresponding kinetic energy rotor accumulator 4, 5, 6, the unidirectional coupling is disconnecting thus it enables for unrestricted rotation of the kinetic energy rotor accumulator 4, 5, 6.
In a result of a differentiation of widths of the gaps 7, 8, 9 the kinetic energy rotor accumulators 4, 5, 6 are actuated successively beginning with the kinetic energy rotor accumulator 4 of the smallest moment of inertia, and ending with the kinetic energy rotor accumulator 6 of the biggest moment of inertia. The best effects are obtained in such an order of accumulator arrangement where the rack of the
smallest gap shall be guided on the line overlapping the direction of a component of impact force. In a case of a bigger impact force all kinetic energy rotor accumulators 4, 5, 6 shall be driven, wherein the kinetic energy rotor accumulator 4 of the smallest moment of inertia shall gain in such a case the highest angular velocity, the kinetic energy rotor accumulator 5 of the medium moment of inertia shall gain a medium angular velocity, and the kinetic energy rotor accumulator 6 of the greatest moment of inertia shall gain the smallest angular velocity.
Claims
1. A spacecraft docking in a planetary orbit comprising a conical external element of the shape conformable to the shapes of the elements connected thereto, and comprising at least one kinetic energy absorption rotor arrangement fixed to the bearing construction, in which kinetic energy of progressive movement is transformed into kinetic energy of rotational movement, wherein the arrangement comprises a moveable beater element cooperating with racks interengaged with toothed wheels driving the kinetic energy rotor accumulators of a given moment of inertia, characterized in that at least two racks (2) of the kinetic energy absorption rotor arrangement (1) cooperating with the beater element (10) interengages with toothed wheels (3, 3a, 3b, 3c) of the kinetic energy rotor accumulators (4, 5, 6) of differentiated capabilities of energy accumulation, wherein between the beater element (10) and racks (2) interengaged with toothed wheels (3, 3a, 3b, 3c) of kinetic energy rotor accumulators (4, 5, 6) differentiated gaps (7, 8, 9) are defined providing differentiated idle stroke of the beater element (10) relative to the racks.
2. The spacecraft according to Claim 1 , characterized in that the kinetic energy rotor accumulators (4, 5, 6) are rotatively mounted on the independent body plates (11) fastened to the bearing construction (17).
3. The spacecraft according to Claim 1 or 2, characterized in that the kinetic energy rotor accumulators (4, 5, 6) have differentiated moments of inertia.
4. The spacecraft according to Claim 1 or 2 or 3, characterized in that the kinetic energy rotor accumulators (4, 5, 6) are driven by means of toothed gears of differentiated transmission ratios that increase rotational velocities.
5. The spacecraft according any one of Claims 1-4, characterized in that the idle stroke of the rack (2) driving the toothed wheel (3) of the kinetic energy rotor accumulator (5, 6) having a capability of accumulation of higher energy, is greater than the idle stroke of the rack (2) driving the toothed wheel (3) of the kinetic energy rotor accumulator (4) having a capability of accumulation of lower energy.
6. The spacecraft according any one of Claims 2-5, characterized in that the body plates (11) have through openings (19, 20).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PLP.399783 | 2012-07-03 | ||
| PL399783A PL399783A1 (en) | 2012-07-03 | 2012-07-03 | Spaceship for docking in planetary orbit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| WO2014006478A2 true WO2014006478A2 (en) | 2014-01-09 |
| WO2014006478A3 WO2014006478A3 (en) | 2014-03-13 |
Family
ID=47264262
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/IB2013/001416 WO2014006478A2 (en) | 2012-07-03 | 2013-07-02 | Spacecraft docking in planetary orbit |
Country Status (2)
| Country | Link |
|---|---|
| PL (1) | PL399783A1 (en) |
| WO (1) | WO2014006478A2 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10611504B2 (en) | 2014-08-26 | 2020-04-07 | Effective Space Solutions Ltd. | Docking system and method for satellites |
| US10625882B2 (en) | 2017-03-06 | 2020-04-21 | Effective Space Solutions Ltd. | Service satellite for providing in-orbit services using variable thruster control |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3608848A (en) | 1968-10-21 | 1971-09-28 | North American Rockwell | Docking mechanism |
| WO2004028864A1 (en) | 2002-09-24 | 2004-04-08 | Lucjan Lagiewka | Method and device for vehicle protection |
| WO2005121593A1 (en) | 2004-06-11 | 2005-12-22 | Georg Piontek | Device for transforming kinetic energy |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| PL357620A1 (en) * | 2002-12-09 | 2004-06-14 | Macrodynamix Sa | Kinetic energy accumulator, particularly of the energy of moving spatial objects |
| CA2473981C (en) * | 2004-07-14 | 2012-11-27 | Macdonald Dettwiler Space And Advanced Robotics Ltd. | Spacecraft docking mechanism |
| PL392181A1 (en) * | 2010-08-19 | 2012-02-27 | Centrum Badawczo-Rozwojowe Epar Spółka Z Ograniczoną Odpowiedzialnością | Method of the kinetic energy storage and the rotor device for storage and dissipation of kinetic energy |
-
2012
- 2012-07-03 PL PL399783A patent/PL399783A1/en unknown
-
2013
- 2013-07-02 WO PCT/IB2013/001416 patent/WO2014006478A2/en active Application Filing
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3608848A (en) | 1968-10-21 | 1971-09-28 | North American Rockwell | Docking mechanism |
| WO2004028864A1 (en) | 2002-09-24 | 2004-04-08 | Lucjan Lagiewka | Method and device for vehicle protection |
| WO2005121593A1 (en) | 2004-06-11 | 2005-12-22 | Georg Piontek | Device for transforming kinetic energy |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10611504B2 (en) | 2014-08-26 | 2020-04-07 | Effective Space Solutions Ltd. | Docking system and method for satellites |
| US10625882B2 (en) | 2017-03-06 | 2020-04-21 | Effective Space Solutions Ltd. | Service satellite for providing in-orbit services using variable thruster control |
| US11117683B2 (en) | 2017-03-06 | 2021-09-14 | Astroscale Israel, Ltd. | Service satellite for providing in-orbit services using variable thruster control |
| US11286061B2 (en) | 2017-03-06 | 2022-03-29 | Astroscale Israel, Ltd. | Service satellite for providing in-orbit services using variable thruster control |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2014006478A3 (en) | 2014-03-13 |
| PL399783A1 (en) | 2012-12-03 |
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