CN112478199B - Satellite flexible repeatable folding and unfolding defense device for resisting physical impact - Google Patents
Satellite flexible repeatable folding and unfolding defense device for resisting physical impact Download PDFInfo
- Publication number
- CN112478199B CN112478199B CN202011354243.7A CN202011354243A CN112478199B CN 112478199 B CN112478199 B CN 112478199B CN 202011354243 A CN202011354243 A CN 202011354243A CN 112478199 B CN112478199 B CN 112478199B
- Authority
- CN
- China
- Prior art keywords
- connecting plate
- joint hinge
- synchronous belt
- cylinder body
- upper connecting
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000007123 defense Effects 0.000 title claims abstract description 12
- 230000007246 mechanism Effects 0.000 claims abstract description 56
- 239000000872 buffer Substances 0.000 claims abstract description 43
- 210000001503 joint Anatomy 0.000 claims abstract description 42
- 230000004224 protection Effects 0.000 claims abstract description 15
- 230000001360 synchronised effect Effects 0.000 claims description 65
- 239000011241 protective layer Substances 0.000 claims description 21
- 230000003139 buffering effect Effects 0.000 claims description 10
- 230000006835 compression Effects 0.000 claims description 8
- 238000007906 compression Methods 0.000 claims description 8
- 238000004880 explosion Methods 0.000 claims description 8
- 239000004744 fabric Substances 0.000 claims description 6
- 239000010410 layer Substances 0.000 claims description 6
- 229920002748 Basalt fiber Polymers 0.000 claims description 5
- 229920005830 Polyurethane Foam Polymers 0.000 claims description 5
- 239000011358 absorbing material Substances 0.000 claims description 5
- 229920006231 aramid fiber Polymers 0.000 claims description 5
- 230000000149 penetrating effect Effects 0.000 claims description 5
- 239000011496 polyurethane foam Substances 0.000 claims description 5
- 239000002759 woven fabric Substances 0.000 claims description 4
- 238000007789 sealing Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 7
- 239000011248 coating agent Substances 0.000 abstract description 3
- 238000000576 coating method Methods 0.000 abstract description 3
- 239000002585 base Substances 0.000 description 9
- 230000001681 protective effect Effects 0.000 description 6
- 238000010521 absorption reaction Methods 0.000 description 3
- 230000002035 prolonged effect Effects 0.000 description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 239000012634 fragment Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000006750 UV protection Effects 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000003513 alkali Substances 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical group [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
-
- 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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
-
- 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
- B64G1/52—Protection, safety or emergency devices; Survival aids
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Buildings Adapted To Withstand Abnormal External Influences (AREA)
Abstract
The invention discloses a satellite flexible repeatable folding and unfolding defense device for resisting physical impact, and particularly relates to the technical field of ultrahigh-speed impact spacecraft protection. The utility model provides a resist flexible satellite of physics striking can repeatedly roll over and expand defense device, which comprises a motor, can repeatedly roll over and expand mechanism and butt joint locking mechanism, can repeatedly roll over and expand the mechanism and include root joint hinge, middle part joint hinge and top joint hinge, root joint hinge is used for driving middle part joint hinge and rotates, middle part joint hinge is used for driving top joint hinge and rotates, top joint hinge is used for driving butt joint locking mechanism and rotates, the flexible inoxidizing coating is equipped with multistage buffer, butt joint locking mechanism includes telescopic tube, inhale piece and electromagnetic lock body, telescopic tube all establishes at top joint hinge, inhale all be equipped with the buttcover plate on piece and the electromagnetic lock body. By adopting the technical scheme of the invention, the problems of poor protection effect and limited protection performance of the existing space debris protection structure are solved, and the space debris protection structure can be used for prolonging the service life of a satellite.
Description
Technical Field
The invention relates to the technical field of protection of ultra-high-speed collision spacecrafts, in particular to a satellite flexible and repeatable folding and unfolding defense device for resisting physical collision.
Background
The space environment deteriorates day by day, the increase speed of the number of space fragments is accelerated, and each aerospace nation develops kinetic energy anti-satellite weapons vigorously, so that the in-orbit operation safety of the spacecraft is seriously threatened; the existing space debris protection technology adopts a passive protection structure, is basically used for large-scale spacecrafts such as space stations and the like, can only defend millimeter-level space debris attack, and has poor protection effect and limited protection performance. It is necessary to design an active space debris protection load to replace the traditional fixed external-hanging passive protection structure, so that the survival capability of the satellite is improved, and the service life of the satellite in orbit is prolonged.
Disclosure of Invention
The invention aims to provide a satellite flexible and repeatable folding and unfolding defense device for resisting physical impact, and solves the problems that an existing space debris protective structure is poor in protective effect and limited in protective performance.
In order to achieve the purpose, the technical scheme of the invention is as follows: a satellite flexible repeatable folding and unfolding defense device for resisting physical impact comprises a motor, a repeatable folding and unfolding mechanism and a butt joint locking mechanism, wherein the motor is symmetrically arranged on a satellite body, the repeatable folding and unfolding mechanism is connected with the motor and comprises a root joint hinge, a middle joint hinge and a top joint hinge, the root joint hinge is in the same structure and is rotatably connected to an output shaft of the motor, a first lower connecting plate, a first upper connecting plate and a first synchronous belt pulley are arranged between the root joint hinge and the middle joint hinge, the root joint hinge is used for driving the first lower connecting plate and the first synchronous belt pulley to rotate, a second lower connecting plate, a second upper connecting plate, a second synchronous belt pulley and a third synchronous belt pulley are arranged between the middle joint hinge and the top joint hinge, the middle joint hinge is arranged on the first upper connecting plate, and the middle joint hinge is used for driving the second lower connecting plate and the third synchronous belt pulley to rotate, a first synchronous belt is arranged between the second synchronous belt pulley and the first synchronous belt pulley, a top joint hinge is arranged on a second upper connecting plate, a third lower connecting plate, a third upper connecting plate and a fourth synchronous belt pulley are arranged between the top joint hinge and the butt locking mechanism, the top joint hinge is used for driving the third lower connecting plate to rotate, a second synchronous belt is arranged between the fourth synchronous belt pulley and the third synchronous belt pulley, flexible protective layers are arranged between the third upper connecting plate and the third lower connecting plate, between the second upper connecting plate and the second lower connecting plate and between the first upper connecting plate and the first lower connecting plate, multistage buffers respectively positioned on the third lower connecting plate, the second lower connecting plate or the first lower connecting plate are symmetrically arranged on two sides of each flexible protective layer, and the multistage buffers can be corresponding to different impact speeds of the third upper connecting plate and the first lower connecting plate, The second upper connecting plate or the first upper connecting plate provides a multi-stage buffering and speed reducing function; the butt joint locking mechanism comprises telescopic sleeves, suction pieces and electromagnetic lock bodies matched with the suction pieces, the four telescopic sleeves are symmetrically arranged on a third upper connecting plate of each repeatable folding and unfolding mechanism, butt joint plates are arranged on the suction pieces and the electromagnetic lock bodies, and a compression sleeve and an explosion bolt in a compression state are arranged between each butt joint plate and the corresponding third upper connecting plate.
The principle and the effect of the technical scheme are as follows: can repeatedly roll over exhibition mechanism under conventional state and be in the contraction state, utilize the motor to drive root joint hinge when the threat of space piece is sensed to the satellite body and rotate, utilize first synchronous pulley after root joint hinge rotates, first synchronous belt and second synchronous pulley drive middle part joint hinge and rotate, utilize third synchronous pulley after middle part joint hinge rotates, second synchronous belt and fourth synchronous pulley drive top joint hinge rotate, make two can repeatedly roll over exhibition mechanism in this scheme expand and start explosion bolt, the telescopic sleeve extension this moment makes electromagnetic lock body and inhale the piece with two can repeatedly roll over exhibition mechanism fixed connection together, thereby annular encirclement has been realized to the satellite body, can effectually prevent the destruction of space piece to the satellite body, the life of satellite body has been prolonged.
Further, the root joint hinge comprises a space cylindrical cam and a lead screw penetrating through the center of the space cylindrical cam; the two ends of the space cylindrical cam are respectively provided with an end cover matched with the lead screw, each end cover is provided with a bearing matched with the lead screw, a coupler is connected between one end of the lead screw and the motor, the other end of the lead screw is connected with the first synchronous belt pulley, the lead screw is in threaded connection with a nut, a roller connecting piece is arranged on the nut, a bolt in threaded connection with the nut is arranged on the roller connecting piece in a penetrating mode, and a cam roller matched with the space cylindrical cam is arranged on the roller connecting piece.
Through the arrangement, the motor can drive the lead screw and the nut to rotate, and the nut can drive the cam roller to move along the track on the space cylindrical cam through the roller connecting piece after rotating, so that the space cylindrical cam rotates by a certain angle, and the rotation of the flexible protective layer is realized.
Further, the shape of the lead screw is a step shape.
Through the arrangement, the limit of the nut can be realized by means of the screw rod in the step shape, and the stability of the scheme is enhanced.
Furthermore, the multistage buffer comprises a first-stage buffer mechanism, a second-stage buffer mechanism and a third-stage buffer mechanism, the first-stage buffer mechanism comprises a first cylinder body, a shell and a piston rod connected in the shell in a sliding manner, a first end cover is arranged at the top of the first cylinder body, a gap is formed between the first cylinder body and the piston rod, a base is arranged at the bottom of the first cylinder body, an oil filling hole seat is arranged at the bottom of the shell, O-shaped sealing rings are arranged between the oil filling hole seat and the first cylinder body and between the base and the shell, an oil seal is arranged between the piston rod and the first cylinder body, and a return spring connected with the base is wrapped on the piston rod; the second-stage buffer mechanism comprises a second cylinder body coated outside the first cylinder body, and a buffer energy-absorbing material is filled in the second cylinder body; the third-stage buffer mechanism comprises a third cylinder body fixedly connected to the bottom of the second cylinder body, and an air spring connected between the third cylinder body and the second cylinder body.
Through the arrangement, when the space debris strikes the repeated folding and unfolding mechanism, different buffering forces can be provided through the reset spring, the buffering energy-absorbing material and the air spring according to the striking speed, the buffering effect is improved, and the service life of the repeated folding and unfolding mechanism in class is prolonged.
Furthermore, the flexible protective layer comprises an aramid fiber cloth protective layer, polyurethane foam and a basalt fiber woven fabric buffer layer which are sequentially arranged from inside to outside.
Compared with the prior art, the beneficial effect of this scheme:
1. the repeatable folding and unfolding mechanism is more flexible and reliable compared with a passive protection structure, still has certain defense capacity in the non-unfolded and semi-unfolded states, can be folded and folded when the satellite body is subjected to danger warning relief of space debris impact, and does not affect signal receiving of devices such as a satellite-borne antenna and a radar;
2. the screw pair of the screw rod has a self-locking function, so that the repeatable folding and unfolding mechanism is stable and reliable;
3. the scheme adopts the multi-stage buffer and the flexible protective layer to be matched for use, has compact structure, excellent buffering and energy absorption performance and excellent protective performance, can make different buffering adjustment according to the impact degree, and has better buffering and energy absorption coordination;
4. according to the scheme, the electromagnetic lock body and the suction piece are used for butt joint and locking, so that the stability and the strength of the scheme are enhanced, the butt joint precision of the mechanism is reduced, and the butt joint reliability is higher;
5. the scheme has wide application range, can be applied to satellite impact kinetic energy defense, important space equipment such as space stations and space telescopes, and can also be applied to buffering and anti-collision of important ground facilities, equipment and the like.
Drawings
Figure 1 is a schematic structural view of a satellite flexible and repeatable folding and unfolding defense device for resisting physical impact,
figure 2 is a schematic view of the structure of the folded state of the satellite flexible re-deployable defense apparatus against physical impacts according to the present invention,
figure 3 is a schematic view of the present invention showing the unfolded state of the re-deployable mechanism,
figure 4 is a schematic view of the root joint hinge of the present invention,
figure 5 is a schematic diagram of the structure of a multi-stage buffer according to the present invention,
figure 6 is a schematic view of the structure of the docking locking mechanism of the present invention,
figure 7 is a schematic view of the construction of the telescopic sleeve according to the invention,
fig. 8 is a schematic structural view of a flexible armor layer according to the present invention.
Detailed Description
The present invention will be described in further detail below by way of specific embodiments:
reference numerals in the drawings of the specification include: the device comprises a satellite body 1, a motor 2, a root joint hinge 3, a middle joint hinge 4, a top joint hinge 5, a lead screw 6, a nut 7, an end cover 8, a roller connecting piece 9, a cam roller 10, a first lower connecting plate 11, a first synchronous pulley 12, a first upper connecting plate 13, a flexible protective layer 14, a multi-stage buffer 15, a second synchronous pulley 16, a first synchronous belt 17, a third synchronous pulley 18, a second lower connecting plate 19, a second upper connecting plate 20, a fourth synchronous pulley 21, a third lower connecting plate 22, a third upper connecting plate 23, a second synchronous belt 24, an aramid fiber cloth protective layer 25, polyurethane foam 26, a basalt fiber cloth buffer layer 27, a first cylinder body 28, a piston rod 29, a first end cover 30, a base 31, a shell 32, an oil filling hole seat 33, a reset spring 34, a second cylinder body 35, a buffer energy absorption material 36, a third cylinder body 37, an air spring 38, a telescopic sleeve 39, a nut 7, an end cover 8, a cam roller connecting piece 9, a cam roller 10, a first synchronous pulley 11, a fourth synchronous pulley 21, a third synchronous pulley 22, a third synchronous pulley 23, a third synchronous pulley, a fourth synchronous pulley, Suction piece 40, electromagnetic lock body 41, butt plate 42, explosion bolt 43, primary sleeve 44, secondary sleeve 45, tertiary sleeve 46, compression spring 47.
Examples
As shown in figures 1 to 8: a satellite flexible repeatable folding and unfolding defending device for resisting physical impact comprises a motor 2 symmetrically arranged on a satellite body 1, a repeatable folding and unfolding mechanism and a butt joint locking mechanism, wherein the repeatable folding and unfolding mechanism comprises a root joint hinge 3, a middle joint hinge 4 and a top joint hinge 5 which are identical in structure, the root joint hinge 3 comprises a space cylindrical cam and a lead screw 6 penetrating through the center of the space cylindrical cam, cam grooves of different shapes can be designed according to the requirement of a rotation angle in the root joint hinge 3, the middle joint hinge 4 and the top joint hinge 5, and the cam grooves of all the space cylindrical cams in the embodiment are right-handed; the step shape is adopted to the shape of lead screw 6, both ends are the optical axis about lead screw 6, both ends all are located outside the space cylindrical cam about lead screw 6, the equal block in both ends of space cylindrical cam has end cover 8 with lead screw 6 matched with, all be equipped with on every end cover 8 with lead screw 6 matched with bearing, be connected with the shaft coupling between the left end of lead screw 6 and the motor 2, the right-hand member coaxial coupling of lead screw 6 has first synchronous pulley 12, threaded connection has nut 7 on the lead screw 6, be equipped with roller connecting piece 9 on the nut 7, roller connecting piece 9 is the ring piece, wear to be equipped with the bolt with nut 7 threaded connection on the roller connecting piece 9, be equipped with on the roller connecting piece 9 with space cylindrical cam matched with cam roller 10, even the cylinder piece of stepped shape of cam roller 10, the bottom adhesion of cam roller 10 is on the roller connecting piece, the top sliding connection of cam roller 10 is in the cam groove.
A first lower connecting plate 11, a first synchronous belt wheel 12 and a first upper connecting plate 13 are arranged between the root joint hinge 3 and the middle joint hinge 4, a first support plate is welded on the first lower connecting plate 11, and the first support plate is hinged with a spatial cylindrical cam on the root joint hinge 3; a first synchronous belt wheel 12 is inserted at the rear side of a screw rod on the root joint hinge 3, a first support rod is welded between a first upper connecting plate 13 and a space cylindrical cam of the middle joint hinge 4, a flexible protective layer 14 and a multi-stage buffer 15 positioned at two sides of the flexible protective layer 14 are arranged between the first upper connecting plate 13 and a first lower connecting plate 11, a second synchronous belt wheel 16 is coaxially connected at the rear side of the screw rod on the middle joint hinge 4, a first synchronous belt 17 is connected between the second synchronous belt wheel 16 and the first synchronous belt wheel 12, and a third synchronous belt wheel 18 is coaxially connected at the front side of the screw rod on the middle joint hinge 4; a second lower connecting plate 19 and a second upper connecting plate 20 are arranged between the middle joint hinge 4 and the top joint hinge 5, a second support plate is hinged between the second lower connecting plate 19 and a space cylindrical cam on the middle joint hinge 4, a second support rod is welded between the second upper connecting plate 20 and the top joint hinge 5, and a flexible protective layer 14 and multistage buffers 15 positioned on two sides of the flexible protective layer 14 are arranged between the second upper connecting plate 20 and the second lower connecting plate 19; a second supporting rod is hinged between the space cylindrical cam of the top joint hinge 5 and the second upper connecting plate 20, a fourth synchronous pulley 21, a third lower connecting plate 22 and a third upper connecting plate 23 are arranged between the top joint hinge 5 and the butt joint locking mechanism, the front side of a screw rod of the top joint hinge 5 is coaxially connected with the fourth synchronous pulley 21, a second synchronous belt 24 is connected between the fourth synchronous pulley 21 and the third synchronous pulley 18, and a third supporting plate is hinged between the third lower connecting plate 22 and the space cylindrical cam of the top joint hinge 5; a flexible protective layer 14 and a multi-stage buffer 15 positioned at two sides of the flexible protective layer 14 are arranged between the third lower connecting plate 22 and the third upper connecting plate 23.
The flexible protective layers 14 all comprise aramid fiber cloth protective layers 25, polyurethane foams 26 and basalt fiber woven fabric buffer layers 27 which are sequentially arranged from inside to outside. The basalt fiber woven fabric on the outer layer has the characteristics of high specific strength, excellent high temperature resistance, acid and alkali resistance, strong ultraviolet resistance, good insulativity and the like, has a good crushing effect on space fragments, and has good mechanical properties; polyurethane foam 26 plays the supporting role to the overall structure of flexible inoxidizing coating 14, also has excellent cushioning effect to space debris, and the aramid fiber cloth of inlayer can further intercept space debris, and has stronger kinetic energy absorbing capacity, and this flexible inoxidizing coating 14 structure has obtained the application in space facilities such as space station, and the protective effect is obvious, compares in the passive protective structure ability of tradition of equal quality and has improved more than 50%.
The multi-stage buffers 15 all comprise a first-stage buffer mechanism, a second-stage buffer mechanism and a third-stage buffer mechanism, the first-stage buffer mechanism comprises a first cylinder 28, a shell 32 and a piston rod 29 connected in the shell 32 in a sliding manner, a first end cover 30 is arranged at the top of the first cylinder 28, a gap between the first cylinder 28 and the piston rod 29 is arranged below the first end cover 30 and used for flowing oil, a base 31 is arranged at the bottom of the first cylinder 28, the shell 32 is fixedly arranged in the first cylinder 28, an oil filling hole seat 33 arranged on the base 31 is arranged at the bottom of the shell 32, oil filling holes are commonly penetrated through the oil filling hole seat 33 and the center of the base, O-shaped sealing rings are arranged between the oil filling hole seat 33 and the first cylinder 28 and between the base 31 and the shell 32, oil seals are adopted between the piston rod 29 and the first cylinder 28, a linear bearing is also arranged between the piston rod 29 and the inner wall of the first cylinder 28, a return spring 34 is connected between the bottom of the piston rod 29 and the base 31; the second-stage buffer mechanism comprises a second cylinder body 35 connected to the bottom of the first cylinder body 28, the second cylinder body 35 is filled with a buffer energy-absorbing material 36 positioned below the base 31, and the buffer energy-absorbing material 36 of the embodiment is an aluminum honeycomb buffer material; the third-stage buffer mechanism comprises a third cylinder 37 fixedly connected to the bottom of the second cylinder 35, and an air spring 38 connected with the second cylinder 35 is arranged in the third cylinder 37. The multi-stage buffers 15 may provide a multi-stage buffering and decelerating function for the corresponding third upper connecting plate 23, second upper connecting plate 20 or first upper connecting plate 13 according to different impact speeds.
The butt joint locking mechanism comprises telescopic sleeves 39, suction pieces 40 and electromagnetic lock bodies 41 matched with the suction pieces 40, the four telescopic sleeves 39 are symmetrically arranged on the third upper connecting plate 23 of each repeatable folding and unfolding mechanism, the suction pieces 40 and the electromagnetic lock bodies 41 are fixedly connected with butt joint plates 42, and explosion bolts 43 and the telescopic sleeves 39 are arranged between the two butt joint plates 42 and the corresponding third upper connecting plates 23 respectively. The telescopic sleeve 39 comprises a primary sleeve 44, a secondary sleeve 45 sleeved outside the primary sleeve 44 and a tertiary sleeve 46 sleeved outside the secondary sleeve 45, wherein the primary sleeve 44, the secondary sleeve 45 and the tertiary sleeve 46 are coated with a compression spring 47.
The working process of the scheme is as follows: when the device is not in operation, the compression spring 47 is in a compression state under the connection action of the explosion bolt 43, the first-stage sleeve 44 and the second-stage sleeve 45 are not extended, and meanwhile, the two repeatable folding and unfolding mechanisms are in a folding state and attached to two sides of the satellite body 1.
When the autonomous sensing early warning system of the satellite body 1 senses that space debris threats approach or are in a high risk area, the motors 2 on two sides of the satellite body 1 are started, the nuts 7 and the first synchronous belt pulleys 12 are driven to rotate by the lead screws 6 of the root joint hinges 3 after the motors 2 are started, the cam rollers 10 can be driven to move along the cam grooves of the space cylindrical cam through the roller connecting pieces 9 after the nuts 7 rotate, so that the root joint hinges 3 are driven to rotate by a fixed angle, the nut 7 stops moving when moving from one side of the lead screws 6 to the other side, and the root joint hinges 3 rotate by 60 degrees in the embodiment; after the first synchronous belt wheel 12 rotates, the first synchronous belt wheel 17 and the second synchronous belt wheel 16 drive the screw rod 6 of the middle joint hinge 4 to rotate, and the screw rod 6 at the position drives the nut 7 and the third synchronous belt wheel 18 after rotating, in the embodiment, the rotation of the nut 7 of the middle joint hinge 4 can realize that the middle joint hinge 4 rotates for 240 degrees; the third synchronization then drives the fourth synchronous pulley 22 to rotate through the second synchronous belt 25, and the fourth synchronous pulley 22 can drive the lead screw 6 of the top joint hinge 5 to rotate after rotating, and similarly, in this embodiment, the top joint hinge 5 can rotate 90 °, and when the root joint hinge 3, the middle joint hinge 4 and the top joint hinge 5 rotate to corresponding angles, the electromagnetic lock bodies 41 and the suction pieces 40 of the two repeatable folding and unfolding mechanisms are opposite and located on the same plane. Explosion bolt 43 explosion unblock on two repeatable expansion mechanisms this moment, compression spring 47 drives one-level sleeve 44 and second grade sleeve 45 roll-off under the effect of its elasticity to telescopic tube 39's extension has been realized, make electromagnetic lock body 41 and inhale piece 40 and offset, can lock electromagnetic lock body 41 circular telegram this moment, and the suction that electromagnetic lock body 41 produced is 3000N, has realized the annular protective layer to satellite body 1 after two repeatable expansion mechanisms link together.
The foregoing are merely examples of the present invention and common general knowledge of known specific structures and/or features of the schemes has not been described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (5)
1. The utility model provides a but resist satellite flexibility repeated exhibition defense device of physics striking which characterized in that: the device comprises a motor, a repeatable folding and unfolding mechanism and a butt joint locking mechanism, wherein the motor is symmetrically arranged on a satellite body, the repeatable folding and unfolding mechanism is connected with the motor, the repeatable folding and unfolding mechanism comprises a root joint hinge, a middle joint hinge and a top joint hinge which are identical in structure, the root joint hinge is rotatably connected to an output shaft of the motor, a first lower connecting plate, a first upper connecting plate and a first synchronous belt pulley are arranged between the root joint hinge and the middle joint hinge, the root joint hinge is used for driving the first lower connecting plate and the first synchronous belt pulley to rotate, a second lower connecting plate, a second upper connecting plate, a second synchronous belt pulley and a third synchronous belt pulley are arranged between the middle joint hinge and the top joint hinge, the middle joint hinge is arranged on the first upper connecting plate and used for driving the second lower connecting plate and the third synchronous belt pulley to rotate, and a first synchronous belt is arranged between the second synchronous belt pulley and the first synchronous belt pulley, the top joint hinge is arranged on the second upper connecting plate, a third lower connecting plate, a third upper connecting plate and a fourth synchronous belt wheel are arranged between the top joint hinge and the butt joint locking mechanism, the top joint hinge is used for driving the third lower connecting plate to rotate, a second synchronous belt is arranged between the fourth synchronous belt wheel and the third synchronous belt wheel, flexible protective layers are respectively arranged between the third upper connecting plate and the third lower connecting plate, between the second upper connecting plate and the second lower connecting plate, and between the first upper connecting plate and the first lower connecting plate, two sides of each flexible protective layer are symmetrically provided with a plurality of stages of buffers respectively positioned on the third lower connecting plate, the second lower connecting plate or the first lower connecting plate, the multistage buffer can provide multistage buffering and speed reducing functions for the corresponding third upper connecting plate, the second upper connecting plate or the first upper connecting plate according to different impact speeds; the butt joint locking mechanism comprises telescopic sleeves, suction pieces and electromagnetic lock bodies matched with the suction pieces, the four telescopic sleeves are symmetrically arranged on a third upper connecting plate of each repeatable folding and unfolding mechanism, butt joint plates are arranged on the suction pieces and the electromagnetic lock bodies, and the two butt joint plates are respectively provided with the telescopic sleeves and the explosion bolts in a compression state between the corresponding third upper connecting plates.
2. The flexible, repeatable runout protection for satellites against physical impacts according to claim 1, wherein: the root joint hinge comprises a spatial cylindrical cam and a lead screw penetrating through the center of the spatial cylindrical cam; the space cylindrical cam comprises a space cylindrical cam body and is characterized in that end covers matched with a screw rod are arranged at two ends of the space cylindrical cam body, each end cover is provided with a bearing matched with the screw rod, a coupler is connected between one end of the screw rod and a motor, the other end of the screw rod is connected with a first synchronous belt pulley, a nut is in threaded connection with the screw rod, a roller connecting piece is arranged on the nut, a bolt in threaded connection with the nut is arranged on the roller connecting piece in a penetrating mode, and a cam roller matched with the space cylindrical cam body is arranged on the roller connecting piece.
3. A satellite flexible re-deployable shelter against physical impact as claimed in claim 2, wherein: the shape of the lead screw is a step shape.
4. A satellite flexible re-deployable shelter against physical impact as claimed in claim 3, wherein: the multistage buffer comprises a first-stage buffer mechanism, a second-stage buffer mechanism and a third-stage buffer mechanism, the first-stage buffer mechanism comprises a first cylinder body, a shell and a piston rod connected in the shell in a sliding manner, a first end cover is arranged at the top of the first cylinder body, a gap is arranged between the first cylinder body and the piston rod, a base is arranged at the bottom of the first cylinder body, an oil filling hole seat positioned on the base is arranged at the bottom of the shell, O-shaped sealing rings are arranged between the oil filling hole seat and the first cylinder body and between the base and the shell, an oil seal is adopted between the piston rod and the first cylinder body, and a return spring connected with the base is wrapped on the piston rod; the second-stage buffer mechanism comprises a second cylinder body coated outside the first cylinder body, and a buffer energy-absorbing material is filled in the second cylinder body; the third-stage buffer mechanism comprises a third cylinder body fixedly connected to the bottom of the second cylinder body, and an air spring connected between the third cylinder body and the second cylinder body.
5. A satellite flexible re-deployable shelter against physical impact as claimed in any one of claims 1 to 4, wherein: the flexible protective layer comprises an aramid fiber cloth protective layer, polyurethane foam and a basalt fiber woven fabric buffer layer which are sequentially arranged from inside to outside.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011354243.7A CN112478199B (en) | 2020-11-27 | 2020-11-27 | Satellite flexible repeatable folding and unfolding defense device for resisting physical impact |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011354243.7A CN112478199B (en) | 2020-11-27 | 2020-11-27 | Satellite flexible repeatable folding and unfolding defense device for resisting physical impact |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112478199A CN112478199A (en) | 2021-03-12 |
| CN112478199B true CN112478199B (en) | 2022-06-14 |
Family
ID=74935781
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011354243.7A Active CN112478199B (en) | 2020-11-27 | 2020-11-27 | Satellite flexible repeatable folding and unfolding defense device for resisting physical impact |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112478199B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113187314A (en) * | 2021-05-12 | 2021-07-30 | 哈尔滨工业大学建筑设计研究院 | Hexagonal inflatable unfolding building module applied to moon building |
| CN113309251A (en) * | 2021-05-12 | 2021-08-27 | 哈尔滨工业大学建筑设计研究院 | Composite wall structure applied to moon building |
| CN113338674B (en) * | 2021-06-02 | 2022-09-20 | 哈尔滨工业大学建筑设计研究院 | Moon pit type manned moon building structure based on future moon base and construction method |
| CN113955161B (en) * | 2021-12-10 | 2023-06-20 | 北京科技大学 | Capturing device and capturing method for space non-cooperative target |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101342947A (en) * | 2008-08-20 | 2009-01-14 | 哈尔滨工业大学 | Space fragment and micrometeoroid impact resistant protection mechanism capable of inflating and expanding on rails |
| GB0921427D0 (en) * | 2009-12-07 | 2010-01-20 | Phs Space Ltd | Apparatus for spacecraft |
| CN107697319A (en) * | 2017-07-03 | 2018-02-16 | 北京空间飞行器总体设计部 | A kind of flexible protective structure based on high-performance fiber fabric and foam |
| CN108516109A (en) * | 2018-03-29 | 2018-09-11 | 北京卫星环境工程研究所 | Umbellate form space junk or micrometeoroid protection device for spacecraft |
| CN109455315A (en) * | 2018-09-28 | 2019-03-12 | 北京空间机电研究所 | A kind of space junk and bullet block protective device and system |
-
2020
- 2020-11-27 CN CN202011354243.7A patent/CN112478199B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101342947A (en) * | 2008-08-20 | 2009-01-14 | 哈尔滨工业大学 | Space fragment and micrometeoroid impact resistant protection mechanism capable of inflating and expanding on rails |
| GB0921427D0 (en) * | 2009-12-07 | 2010-01-20 | Phs Space Ltd | Apparatus for spacecraft |
| CN107697319A (en) * | 2017-07-03 | 2018-02-16 | 北京空间飞行器总体设计部 | A kind of flexible protective structure based on high-performance fiber fabric and foam |
| CN108516109A (en) * | 2018-03-29 | 2018-09-11 | 北京卫星环境工程研究所 | Umbellate form space junk or micrometeoroid protection device for spacecraft |
| CN109455315A (en) * | 2018-09-28 | 2019-03-12 | 北京空间机电研究所 | A kind of space junk and bullet block protective device and system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112478199A (en) | 2021-03-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112478199B (en) | Satellite flexible repeatable folding and unfolding defense device for resisting physical impact | |
| CN108688793B (en) | Folding and unfolding mechanism for wings of barrel-type launching unmanned aerial vehicle | |
| CN110487131B (en) | Grid rudder unfolding and locking mechanism for aerospace transport vehicle | |
| JP5694306B2 (en) | Telescopic structure | |
| CN112498749B (en) | Flexible deployable initiative defense device | |
| US8356541B2 (en) | Vehicle protective structure | |
| US8800797B2 (en) | Heat and explosion resistant cargo container | |
| WO2011142784A2 (en) | Apparatus for extending and retracting an armor system for defeating high energy projectiles | |
| CN109455315B (en) | Space debris and projectile arresting and protecting device and system | |
| CN103693188A (en) | Wing folding and unfolding mechanism of unmanned aerial vehicle | |
| US8522664B2 (en) | Hydraulic energy redirection and release system | |
| CN108649314A (en) | A kind of novel double-layer scissors parabolic cylinder expandable truss antenna assembly | |
| RU2521451C2 (en) | Space vehicle landing device | |
| US11149719B2 (en) | EdDrive propellantless propulsion system | |
| CN113562197B (en) | Large-scale air of space constructs thoughtlessly moves flexible cabin | |
| CN109577504B (en) | Pneumatic resilience type semi-active debris flow impact resistance device | |
| CN110155375B (en) | Space debris protective structure | |
| RU2675042C1 (en) | Spacecraft landing device | |
| CN105651117A (en) | Foldable shield | |
| CN109441294A (en) | The detachable protection airtight plugging plate driving device of subway rail mounted and plugging device | |
| CN108516109B (en) | Umbrella-shaped space debris or micro-fluidic star protection device for spacecraft | |
| CN108730325B (en) | A kind of low impact applied to deployable structure is from locking hinge | |
| CN108678514A (en) | New type explosion proof cabin | |
| CN107458624B (en) | Spring telescopic type deployable mechanism | |
| CN215598228U (en) | Antiriot vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |