CN106516168B - A kind of full protection flexibility expansion re-entry deceleration device - Google Patents
A kind of full protection flexibility expansion re-entry deceleration device Download PDFInfo
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- CN106516168B CN106516168B CN201610844568.0A CN201610844568A CN106516168B CN 106516168 B CN106516168 B CN 106516168B CN 201610844568 A CN201610844568 A CN 201610844568A CN 106516168 B CN106516168 B CN 106516168B
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- Prior art keywords
- support bar
- frame
- flexibility
- slidably connected
- protection
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- 210000003625 skull Anatomy 0.000 claims abstract description 16
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical group [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 239000011796 hollow space material Substances 0.000 claims description 3
- 239000012774 insulation material Substances 0.000 claims description 3
- 230000035939 shock Effects 0.000 abstract description 7
- 238000005516 engineering process Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 12
- 230000003139 buffering effect Effects 0.000 description 3
- 239000003638 chemical reducing agent Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005422 blasting Methods 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- 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
- B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Building Environments (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention discloses a kind of full protection flexibility expansion re-entry deceleration devices, including load cabin main body, and it is blunt nosed that load cabin lower body is connected with rigid solar heat protection；The upper end of load cabin main body is equipped with the frame that is slidably connected, it is slidably connected at the top of frame and skull is installed, the load cabin main body junction blunt nosed with rigid solar heat protection is provided with hinged seat and screw hole support, the lower end of lower support bar is connect with hinged seat, the upper end of lower support bar and the lower end of upper support bar connect, and the upper end of upper support bar is connect with the frame that is slidably connected；Leeward flexibility thermal protection struc ture and windward side flexibility thermal protection struc ture are connected separately on upper support bar and lower support bar；The retarder is using connecting rod unfolding mechanism, increase leeward thermal protection struc ture, so that reaching can reduce on the requirement of fairing of launch vehicle envelope, incoming flow/shock wave is overcome to influence retarder rear end, flight environment of vehicle can be improved again, improve load volume, enter for celestial body outside following load ground, slow down, landing provides a kind of Technology Ways.
Description
Technical field
The invention belongs to spacecraft enter with return technique field, be specifically related to a kind of full protection flexibility expansion and reenter
Retarder.
Background technique
It mainly includes traditional for having ballistic or half the ballistic reducer structure that (into) enters ability again in the world at present
Rigidly fix formula and novel two kinds of flexible expansion.For it is traditional rigidly fix formula retarder for, its advantage is that solar heat protection
Structure is attached to entire outer surface and carries out full protection, under the premise of this full protection structure type, retarder matter to retarder
Heart position can deviate central axle designs, generate one and be greater than 0 ° of trim ang1e of attack, so that retarder is made to have certain lift,
Achieve the purpose that improve Airflow Environment, realize that half ballistic enters flight again (into)；The disadvantage is that because entire retarder is that rigidity is solid
Fixed pattern structure is limited retarder volume and load transportation ability by rocket radome fairing envelope constrained, can not meet current
Actual needs.
Formula retarder is rigidly fixed for traditional, the flexible expansion retarder in later period is developed.However, for new
For the flexible expansion retarder of type, there are inflatable expansion and mechanical two kinds of expansion in the world at present, its advantage is that pneumatically
Face and thermal protection struc ture are flexible deployable structure, and when transmitting collapses, (into) enters preceding expansion again, by rocket radome fairing envelope constrained compared with
Small, under identical radome fairing envelope, volume and load transportation ability are better than the fixed retarder of conventional rigid；The disadvantage is that pneumatic
Face is class " umbrella " formula configuration and is mounted on retarder front end, only half is protected retarder.It therefore is to avoid incoming flow to retarder
Rear end is directly washed away, and mass center is generally designed on center shaft, and trim ang1e of attack is 0 °, and such retarder there is no liter
Power, flight environment of vehicle rather harsh.Even in addition, under 0 ° of angle of attack state, to prevent shoulder shock wave from making to retarder rear end
At influence, flexible expansion retarder axial dimension is significantly less than pneumatic face diameter, this also limits deceleration to a certain extent
The volume and load transportation ability of device.
Therefore, capacity value, while pneumatic face and solar heat protection can be guaranteed under the premise of full protection structure type by designing one kind
Structure is that the re-entry deceleration device of flexible deployable structure is always those skilled in the art's strategic point technical problem to be solved.
Summary of the invention
The present invention provides a kind of full protection flexibility expansion re-entry deceleration device in view of the deficiencies of the prior art, has complete anti-
The flexible expansion function of shield, so that reaching can reduce to the requirement of fairing of launch vehicle envelope and overcome incoming flow/shock wave to subtracting
Fast device rear end influences, improves load volume, achievees the purpose that improve flight environment of vehicle.
In order to solve the above-mentioned technical problems, the present invention provides a kind of full protection flexibility expansion re-entry deceleration devices, including
Load cabin main body, it is blunt nosed that load cabin lower body is fixedly connected with rigid solar heat protection；The upper end of load cabin main body is equipped with sliding and connects
Frame is connect, the frame that is slidably connected is slided up and down by slide-and-guide bar；It is slidably connected at the top of frame and skull is installed；Load cabin main body with
The blunt nosed junction of rigid solar heat protection is provided with hinged seat and screw hole support, and the lower end of lower support bar is connect with hinged seat, lower support
The upper end of bar and the lower end hinge of upper support bar connect, and the upper end of upper support bar is connect with the frame hinge that is slidably connected.Pass through hinge
The gathering and expansion for realizing upper support bar and lower support bar are connected, be connected by a hinge while the pneumatic face of full protection may be implemented is whole
The gathering and expansion of a structure；It is connected separately with leeward flexibility thermal protection struc ture on the upper support bar and lower support bar and meets
After wind face flexibility thermal protection struc ture, upper support bar and lower support bar rotate in place, flexible thermal protection struc ture is propped up completely, to realize
Retarder full protection function.
Further, hinge connection is connected by shaft hinge.
Further, auricle corresponding with hinged seat position, upper support bar are installed at the top of the frame that is slidably connected
Upper end connect with auricle shaft；The bottom of the frame that is slidably connected is provided with sleeve corresponding with screw hole support position,
The upper end of upper support bar is connect with auricle shaft allows upper support bar to collapse and be unfolded, and sleeve is used to install flexible drive list
Member and slide-and-guide bar.
Further, the sleeve inner is equipped with elastic drive unit, and the slide-and-guide bar passes through sleeve connection
To screw hole support, the slide-and-guide bar top is equipped with head limited block.
Further, the joint of the upper support and lower support bar is coated with band locking unit；Band locking unit
It is coated on the joint of upper support bar and lower support bar, is locked to realize and be collapsed to retarder.
Further, the rigid solar heat protection is blunt nosed bores configuration for double-layer ball, and outer layer is rigid heat insulation material, and internal layer is aluminium bee
Nest sandwich, the structure type can not only play the role of improving resistance coefficient, ablative thermal protection, may also function as landing shock resistance
Buffer function.
Further, the load cabin main body is cylinder-shaped thin wall structure, and inside is cavity structure, and inner chambers are for filling
Carry load.
Further, the skull is arched hollow space structure, and inside is equipped with drag parachute, and skull on ground or can reenter atmosphere
It integrally opens before layer, is loaded and unloaded in load cabin main body convenient for load cargo；It can also be in the transonic speed stage after atmospheric reentry
Arch cover on the outside of skimming pulls out drag parachute, secondary speed-reducing.
The beneficial effect of the present invention and the prior art is:
(1) for the present invention compared with full protection rigidly fixes formula structure, the retarder is leeward using connecting rod unfolding mechanism, increase
The technical solution of face solar heat protection, expansion function, can significantly drop before collapsing, reenter when designed unfolding mechanism having pneumatic surface launching
It is low to fairing of launch vehicle envelope demand；
(2) present invention is compared with half protects flexible expansion structure, and designed full protection structure can stop incoming flow to subtracting
Fast device rear end is directly washed away, and centroid position can deviate central axle designs, a little trim ang1e of attack is generated, to make to slow down
Device has certain lift, improves Airflow Environment；Full protection flexibility expansion again (into) enter reducer structure for the following load ground outside
Celestial body enters, slows down, landing provides a kind of new Technology Ways；
(3) under 0 ° of angles-of-attack state, increased leeward flexibility thermal protection struc ture can overcome shoulder shock wave to deceleration
Device rear end influences, and when windward side and leeward flexibility thermal protection struc ture are propped up completely, can be realized retarder full protection function
Energy；Under the conditions of identical pneumatic face diameter, axial height can be significantly greater than half and protect flexible expansion structure, to a certain extent
Improve the volume and load transportation ability of retarder；
(4) the ball taper double-layer cavity structure of the blunt nosed use of rigid solar heat protection, can provide the landing of effect suitable with the leg that lands
Buffering, it is integrated with bearing function to realize solar heat protection.
Detailed description of the invention
Fig. 1 is a kind of pneumatic face unfolded state structural schematic diagram of full protection flexibility expansion re-entry deceleration device of the present invention；
Fig. 2 is a kind of pneumatic face rounding state structural schematic diagram of full protection flexibility expansion re-entry deceleration device of the present invention；
Fig. 3 is that a kind of rigid solar heat protection of full protection flexibility expansion re-entry deceleration device of the present invention is blunt nosed to be connected with load cabin main body
Connect schematic diagram；
Fig. 4 is a kind of mount structure schematic diagram that is slidably connected of full protection flexibility expansion re-entry deceleration device of the present invention；
Fig. 5 is a kind of load cabin main body of full protection flexibility expansion re-entry deceleration device of the present invention and the frame gathering that is slidably connected
Assembly relation schematic diagram under state；
Fig. 6 is a kind of load cabin main body of full protection flexibility expansion re-entry deceleration device of the present invention and the frame expansion that is slidably connected
Assembly relation schematic diagram under state；
Fig. 7 is a kind of support rod assembly relation schematic diagram of full protection flexibility expansion re-entry deceleration device of the present invention；
Fig. 8 is a kind of flexible thermal protection struc ture assembly relation signal of full protection flexibility expansion re-entry deceleration device of the present invention
Figure；
Rounding state schematic diagram when Fig. 9 is a kind of transmitting of full protection flexibility expansion re-entry deceleration device of the present invention；
Figure 10 is a kind of unfolded state schematic diagram before reentering atmosphere of full protection flexibility expansion re-entry deceleration device of the present invention；
Figure 11 is ramming head lid status diagram after a kind of expansion of full protection flexibility expansion re-entry deceleration device of the present invention.
Wherein, the solar heat protection of 1- rigidity is blunt nosed, the windward side 2- flexibility thermal protection struc ture, and 3- is slidably connected frame, 4- elastic drive unit,
5- slide-and-guide bar, 6- skull, 7- upper support bar, 8- lower support bar, 9- load cabin main body, 10- band locking unit, 11- back
Wind face flexibility thermal protection struc ture 11,12- hinged seat, 13- screw hole support, 14- auricle, 15- sleeve, the head 16- limited block.
Specific embodiment
Below in conjunction with attached drawing, the invention will be further described.
As shown in Figure 1 and 2, wherein Fig. 1 and Fig. 2 is that the pneumatic face of full protection flexibility expansion re-entry deceleration device is unfolded respectively
Structural schematic diagram when state and rounding state, a kind of full protection flexibility expansion re-entry deceleration device of the invention include rigidity
Solar heat protection is blunt nosed 1, windward side flexibility thermal protection struc ture 2, the frame 3 that is slidably connected, elastic drive unit 4, slide-and-guide bar 5, skull 6, on
Support rod 7, lower support bar 8, load cabin main body 9, band locking unit 10 and leeward flexibility thermal protection struc ture 11, load cabin main body
9 are located on rigid solar heat protection blunt nosed 1 and are connected therewith using screw；The upper end of the load cabin main body 9 is equipped with sliding and connects
Frame 3 is connect, the frame 3 that is slidably connected is slided up and down by slide-and-guide bar 5；The top of the frame 3 that is slidably connected is equipped with
Skull 6；As shown in Fig. 2, band locking unit 10 is coated on the joint of upper support bar 7 Yu lower support bar 8, retarder is collapsed
Locking.
As shown in figure 3, the rigid solar heat protection blunt nosed 1 is located at the total bottom, configuration is bored for double-layer ball, both may be used
Play the role of ablative thermal protection, shock resistance buffering can also be taken into account；The rigid solar heat protection blunt nosed 1 and 9 junction of load cabin main body is equal
Even several hinged seats 12 of setting and 4 screw hole supports 13, hinged seat 12 are used to connect lower support bar 8, and screw hole support 13 is used to
Slide-and-guide bar 5 is connected, the lower end of lower support bar 8 is connect with hinged seat 12, under the upper end of lower support bar 8 and upper support bar 7
End is connected by shaft hinge, and the upper end of upper support bar 7 is connect with the frame 3 that is slidably connected by shaft hinge, and upper support bar 7 is under
Support rod 8 is evenly distributed on be slidably connected frame 3 and 9 surrounding of load cabin main body；It is separately connected on upper support bar 7 and lower support bar 8
There are leeward flexibility thermal protection struc ture 11 and windward side flexibility thermal protection struc ture 2.
As shown in figure 4, removing skull 6 and the schematic diagram containing skull 6 for the frame 3 of the invention that is slidably connected, be slidably connected frame 3
For a cylinder-shaped thin wall structure, several support rod auricles are accordingly uniformly arranged with hinged seat 12 being slidably connected 3 top of frame
14, for connecting the upper end of upper support bar 7；4 sleeves are accordingly uniformly arranged with screw hole support 13 being slidably connected 3 bottom of frame
15, for installing elastic drive unit 4 and slide-and-guide bar 5, before atmospheric reentry, the frame 3 that is slidably connected is in elastic drive unit 4
It moves under driving along slide-and-guide bar 5, is unfolded so that upper support bar 7 and lower support bar 8 be driven to rotate；Skull 6 as shown in Figure 4 is pacified
Mounted in 3 top of frame that is slidably connected, skull 6 is an arched hollow space structure, and inside is equipped with drag parachute；Skull 6 on ground or can reenter
It integrally opens before atmosphere, is loaded and unloaded in load cabin main body 9 convenient for load cargo；It can also be in the transonic speed after atmospheric reentry
Stage skim outside arch cover, pull out drag parachute, secondary speed-reducing.
As shown in Fig. 5 ~ 6,3 sets of frame are slidably connected in load cabin main body 9, and slide-and-guide bar 5 passes through sleeve 15 and is connected to
Screw hole support 13, elastic drive unit 4 is in sleeve 15.As shown in figure 5, being slidably connected when retarder is in rounding state
Frame 3 is located at 9 top of load cabin main body, and elastic drive unit 4 is compressed energy-storage state, wherein I (12:1) in Fig. 4, II (12:
1) corresponding I, II when, III (10:1) retarder is in rounding state, the CONSTRUCTED SPECIFICATION enlarged drawing of III part；Band locking unit
10 are coated on the joint of upper support bar 7 Yu lower support bar 8, lock to realize and collapse to retarder；As shown in fig. 6, reentering
Before atmosphere, band locking unit 10 is unlocked.After band locking unit 10 unlocks, elastic drive unit 4 releases energy, driving
The frame 3 that is slidably connected is moved along slide-and-guide bar 5 to blunt nosed 1 direction of rigid solar heat protection, when slide-and-guide bar 5 head limited block 16 with
It is slidably connected after the top structure contact of frame 3, movement stops, wherein IV (8:1) in Fig. 5, and V (8:1), VI (8:1) are respectively
IV, V when retarder is in unfolded state, the CONSTRUCTED SPECIFICATION enlarged drawing of VI part.
As shown in fig. 7, the upper end of upper support bar 7 is connect with auricle 13 by shaft, the upper end of upper support bar 7 and lower support
The upper end of bar 8 is connected by shaft；The lower end of lower support bar 8 is connect with hinged seat 12 by shaft；Band locking unit 10 wraps
The joint of upper support bar 7 Yu lower support bar 8 is overlayed on, is locked to realize and be collapsed to retarder；Band locking unit 10 unlocks
Afterwards, the frame 3 that is slidably connected is moved along slide-and-guide bar 5 toward blunt nosed 1 direction of rigid solar heat protection, to drive upper support bar 7 and lower support
Bar 8 is unfolded.
As shown in figure 8, the frame 3 that is slidably connected is blunt toward rigid solar heat protection along slide-and-guide bar 5 after band locking unit 10 unlocks
First 1 direction movement, so that upper support bar 7 and lower support bar 8 be driven to be unfolded, windward side flexibility thermal protection struc ture 2 and leeward are flexible
Thermal protection struc ture 11 is connected on lower support bar 8 and upper support bar 7 by the way of riveting, suture, windward side flexibility thermal protection struc ture 2
It is the three-dimensional carbon fibrage heat insulation material for having tension function with leeward flexibility thermal protection struc ture 11, support rod rotate in place
Afterwards, flexible thermal protection struc ture is propped up completely, to realize retarder expansion, full protection function.
By taking the earth reenters return as an example, workflow of the invention is as follows:
As shown in figure 9, overall structure is in rounding state shown in Fig. 9 and is located in rocket radome fairing in transmitting.It is leeward
Face flexibility thermal protection struc ture 11 and windward side flexibility thermal protection struc ture 2 collapse between upper support bar 7 and lower support bar 8；Band locking
Unit 10 is coated on flexible thermal protection struc ture 2 and connects with 11 outside of leeward flexibility thermal protection struc ture, upper support bar 7 with lower support bar 8
At head；Skull 6 is in close state.
Before reentering atmosphere, the blasting bolt on band locking unit 10 starts, and the unlock of band locking unit 10 is cast aside；Elasticity
Driving unit 4 releases energy, and the frame 3 that is slidably connected is driven to move downward along slide-and-guide bar 5, drives upper support bar 7, lower support bar
8 and windward side flexibility thermal protection struc ture 2 thereon, leeward flexibility thermal protection struc ture 11 be unfolded together；When the head of slide-and-guide bar 5
After limited block 16 is contacted with the top structure for the frame 3 that is slidably connected, movement stops, and the pneumatic face of full protection is fully deployed, such as Figure 10 institute
Show.
During reentering, structure carries out aerodynamic decelerator by the pneumatic face of full protection of expansion, when flying speed be reduced to across
When velocity of sound, the outside arch cover on skull 6 is cast aside, pulls out drag parachute secondary speed-reducing, as shown in figure 11.
In landing mission, landing shock is absorbed by the cavity structure and internal layer aluminum honeycomb material of rigid solar heat protection blunt nosed 1
Ability realizes buffering.
There are many concrete application approach of the present invention, the above is only a preferred embodiment of the present invention, it is noted that for
For those skilled in the art, without departing from the principle of the present invention, it can also make several improvements, this
A little improve also should be regarded as protection scope of the present invention.
Claims (7)
1. a kind of full protection flexibility expansion re-entry deceleration device, including load cabin main body (9), which is characterized in that the load
It is blunt nosed (1) that cabin main body (9) lower end is fixed with rigid solar heat protection；The upper end of the load cabin main body (9) is equipped with the frame that is slidably connected
(3), the frame that is slidably connected (3) is slided up and down by slide-and-guide bar (5)；Pacify at the top of the frame that is slidably connected (3)
Equipped with skull (6)；The junction of the load cabin main body (9) and rigid solar heat protection blunt nosed (1) is provided with hinged seat (12) and spiral shell
The lower end of hole support (13), lower support bar (8) is connect with hinged seat (12), upper end and upper support bar (7) of lower support bar (8)
The connection of lower end hinge, the upper end of upper support bar (7) is connect with the frame that is slidably connected (3) hinge；The upper support bar (7) and lower branch
Leeward flexibility thermal protection struc ture (11) and windward side flexibility thermal protection struc ture (2) are connected separately on strut (8)；The upper support
The joint of bar (7) and lower support bar (8) is coated with band locking unit (10).
2. a kind of full protection flexibility expansion re-entry deceleration device according to claim 1, which is characterized in that the hinge
Connection is connected by shaft hinge.
3. a kind of full protection flexibility expansion re-entry deceleration device according to claim 1, which is characterized in that the sliding
Auricle (14) corresponding with hinged seat (12) position, the upper end of upper support bar (7) and auricle are installed at the top of connection frame (3)
(14) it is connected by shaft；The bottom of the frame that is slidably connected (3) is provided with set corresponding with screw hole support (13) position
Cylinder (15).
4. a kind of full protection flexibility expansion re-entry deceleration device according to claim 3, which is characterized in that the sleeve
(15) internal to be equipped with elastic drive unit (4), the slide-and-guide bar (5) passes through sleeve (15) and is connected to screw hole support
(13), head limited block (16) are installed at the top of the slide-and-guide bar (5).
5. a kind of full protection flexibility expansion re-entry deceleration device according to claim 1, which is characterized in that the rigidity
Solar heat protection blunt nosed (1) is that double-layer ball bores configuration, and outer layer is rigid heat insulation material, and internal layer is aluminum honeycomb sandwich.
6. a kind of full protection flexibility expansion re-entry deceleration device according to claim 1, which is characterized in that the load
Cabin main body (9) is cylinder-shaped thin wall structure, and inside is cavity structure.
7. a kind of full protection flexibility expansion re-entry deceleration device according to claim 1, which is characterized in that the skull
It (6) is arched hollow space structure, inside is equipped with drag parachute.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610844568.0A CN106516168B (en) | 2016-09-23 | 2016-09-23 | A kind of full protection flexibility expansion re-entry deceleration device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610844568.0A CN106516168B (en) | 2016-09-23 | 2016-09-23 | A kind of full protection flexibility expansion re-entry deceleration device |
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| Publication Number | Publication Date |
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| CN106516168A CN106516168A (en) | 2017-03-22 |
| CN106516168B true CN106516168B (en) | 2019-01-29 |
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| CN201610844568.0A Expired - Fee Related CN106516168B (en) | 2016-09-23 | 2016-09-23 | A kind of full protection flexibility expansion re-entry deceleration device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108128483B (en) * | 2017-12-07 | 2021-05-18 | 北京空间技术研制试验中心 | Space station material descending aircraft |
| CN109855480B (en) * | 2019-04-02 | 2023-10-03 | 北京星际荣耀空间科技有限公司 | Solid carrier rocket sub-level recovery structure and ballistic trajectory-lifting type reentry spacecraft |
| CN111017262B (en) * | 2019-11-28 | 2021-07-13 | 北京空间机电研究所 | Inflatable reentry deceleration flexible unfolding structure folding and unfolding method |
| CN111619827A (en) * | 2020-06-02 | 2020-09-04 | 北京空间技术研制试验中心 | Inflatable expansion type living cabin for spacecraft |
| CN112623179B (en) * | 2020-12-23 | 2022-11-22 | 中国科学院力学研究所 | Recoverable flexible formula transmission nacelle |
| CN113665811B (en) * | 2021-09-13 | 2024-07-26 | 北京理工大学 | Unmanned delivery vehicle of software |
| CN113928573B (en) * | 2021-11-19 | 2023-04-18 | 中国直升机设计研究所 | Sliding fairing with guiding and buffering functions |
| CN114180107B (en) * | 2021-12-07 | 2023-07-14 | 北京空间机电研究所 | Heat-proof and speed-reducing parachute cabin device for recovering fairing parachute |
| CN115339659B (en) * | 2022-08-05 | 2024-09-20 | 哈尔滨工业大学（威海） | Load storage cabin for separated type return device |
| CN115285375B (en) * | 2022-08-05 | 2024-08-06 | 哈尔滨工业大学（威海） | Separated type reflector system |
| CN116039968B (en) * | 2022-09-09 | 2024-05-17 | 太原理工大学 | Flexible connecting cable structure and pneumatic drogue for tensioning cable rods thereof |
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| US7837154B2 (en) * | 2006-09-30 | 2010-11-23 | Astrium Gmbh | Deployable heat shield and deceleration structure for spacecraft |
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| CN105584645A (en) * | 2016-01-13 | 2016-05-18 | 北京空间技术研制试验中心 | Semi-rigid mechanically-unfolded deceleration entering landing device |
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| WO2016132331A1 (en) * | 2015-02-20 | 2016-08-25 | Ali S.C.A.R.L. | Opening servomechanism for aerospace platforms and mechanical components |
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|---|---|---|---|---|
| US6467731B1 (en) * | 1999-03-24 | 2002-10-22 | Lockheed Martin Corporation | Integrated sample return capsule |
| US7837154B2 (en) * | 2006-09-30 | 2010-11-23 | Astrium Gmbh | Deployable heat shield and deceleration structure for spacecraft |
| CN104627390A (en) * | 2014-12-18 | 2015-05-20 | 北京空间机电研究所 | Mars exploration landing buffer device |
| CN105584645A (en) * | 2016-01-13 | 2016-05-18 | 北京空间技术研制试验中心 | Semi-rigid mechanically-unfolded deceleration entering landing device |
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| CN106516168A (en) | 2017-03-22 |
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