CN106516168A - Fully-protected flexible unfolding re-entry aeroshell - Google Patents
Fully-protected flexible unfolding re-entry aeroshell Download PDFInfo
- Publication number
- CN106516168A CN106516168A CN201610844568.0A CN201610844568A CN106516168A CN 106516168 A CN106516168 A CN 106516168A CN 201610844568 A CN201610844568 A CN 201610844568A CN 106516168 A CN106516168 A CN 106516168A
- Authority
- CN
- China
- Prior art keywords
- support bar
- main body
- deceleration device
- expansion
- flexibility
- 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.)
- Granted
Links
- 210000003625 skull Anatomy 0.000 claims description 15
- 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
- 238000010276 construction Methods 0.000 claims 1
- 230000035939 shock Effects 0.000 abstract description 7
- 239000002775 capsule Substances 0.000 abstract 4
- 241000132092 Aster Species 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 8
- 230000000694 effects Effects 0.000 description 4
- 230000003139 buffering effect Effects 0.000 description 2
- 239000003638 chemical reducing agent Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 241000256844 Apis mellifera Species 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000004888 barrier function Effects 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
- 238000004146 energy storage Methods 0.000 description 1
- 210000003141 lower extremity Anatomy 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 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
Abstract
The invention discloses a fully-protected flexible unfolding re-entry aeroshell comprising a load capsule main body. A rigid thermal protection blunt nose is connected to the lower end of the load capsule main body. A sliding connecting frame is installed at the upper end of the load capsule main body. A head cover is arranged at the top of the sliding connecting frame. Hinged seats and threaded hole bearings are arranged at the connection between the load capsule main body and the rigid thermal protection blunt nose. The hinged seats are connected with the lower parts of lower support bars. The upper parts of the lower support bars are connected with the lower parts of upper support bars. The upper parts of the upper support bars is connected with the sliding connecting frame. A leeward side flexible thermal protection structure and a windward side flexible thermal protection structure are respectively connected to the upper support bars and the lower support bars. The fully-protected flexible unfolding reentry aeroshell uses a connecting-bar unfolding mechanism and adds the leeward side flexible thermal protection structure, thereby not only reducing the requirement of the fairing envelope of a launch vehicle and avoiding the impact of the inflow/shock wave on the rear-end of the aeroshell, but also improving the flight environment and increasing the loading volume to provide a technological path for the entrance, deceleration and landing of future load extraterrestrial asters.
Description
Technical field
The invention belongs to spacecraft into return technique field, be specifically related to a kind of full protection flexibility expansion and reenter
Decelerator.
Background technology
Possess at present ballistic or half ballistic in the world again（Enter）Enter the reducer structure of ability mainly including traditional
Rigidly fix formula and two kinds new of flexible expansion.For it is traditional rigidly fix formula decelerator for, its advantage is solar heat protection
Structure is attached to whole outer surface and carries out full protection to decelerator, on the premise of this full protection version, decelerator matter
Heart position just can be designed with off-center axle, generate a trim ang1e of attack more than 0 °, so that decelerator possesses certain lift,
Reaching improves Airflow Environment, realizes half ballistic again（Enter）Enter the purpose of flight；Which has the disadvantage because whole decelerator is solid for rigidity
Fixed pattern structure, by rocket trouserss envelope constrained, limits decelerator volume and load transportation ability, can not meet current
Be actually needed.
Formula decelerator is rigidly fixed for traditional, the flexible expansion decelerator in later stage is developed.However, for new
For the flexible expansion decelerator of type, there is inflated type to launch and two kinds of mechanical type expansion at present in the world, its advantage is pneumatic
Face and thermal protection struc ture are flexible deployable structure, draw in, again during transmitting（Enter）Enter front expansion, by rocket trouserss envelope constrained compared with
Little, under identical trouserss envelope, volume and load transportation ability are better than the fixed decelerator of conventional rigid；Which has the disadvantage pneumatic
Face is class " umbrella " formula configuration and is arranged on decelerator front end, decelerator simply half is protected.Therefore it is to avoid flowing to decelerator
Rear end is directly washed away, and barycenter is generally designed on center shaft, and trim ang1e of attack is 0 °, and such decelerator 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 decelerator rear end
Into impact, flexible expansion decelerator axial dimension is significantly less than pneumatic face diameter, and this also limit deceleration to a certain extent
The volume and load transportation ability of device.
Therefore, designing one kind can be on the premise of full protection version, it is ensured that capacity value, while pneumatic face and solar heat protection
Structure is that the re-entry deceleration device of flexible deployable structure is always those skilled in the art's strategic point technical barrier to be solved.
The content of the invention
The present invention provides a kind of full protection flexibility expansion re-entry deceleration device for the deficiencies in the prior art, possesses complete anti-
Shield is flexible to launch function, can reduce to fairing of launch vehicle envelope requirement so as to reach, can overcome flowing again/shock wave is to subtracting
Fast device rear end affects, improves load volume, reaches the purpose for improving flight environment of vehicle.
In order to solve above-mentioned technical problem, the invention provides a kind of full protection flexibility expansion re-entry deceleration device, including
Load cabin main body, it is blunt nosed that load cabin main body lower end is fixedly connected with rigid solar heat protection；The upper end of load cabin main body is provided with slip 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 bearing, and the lower end of lower support bar is connected with hinged seat, lower support
The upper end of bar and the lower end chain connection of upper support bar, the upper end of upper support bar and the frame chain connection that is slidably connected.By hinge
The gathering and expansion of upper support bar and lower support bar is realized in connection, is connected through the hinge while can realize that the pneumatic face of full protection is whole
The gathering of individual structure and expansion；It is connected to lee face flexibility thermal protection struc ture and meets on described upper support bar and lower support bar
Wind face flexibility thermal protection struc ture, after upper support bar is rotate in place with lower support bar, flexible thermal protection struc ture is propped up completely, so as to realize
Decelerator full protection function.
Further, described chain connection is connected by shaft hinge.
Further, the auricle corresponding with hinged seat position, upper support bar are installed at the top of the described frame that is slidably connected
Upper end be connected with auricle rotating shaft；The bottom of the described frame that is slidably connected is provided with the sleeve corresponding with screw support position,
The upper end of upper support bar is connected with auricle rotating shaft and upper support bar is drawn in and is launched, and sleeve is used for installing flexible drive list
Unit and slide-and-guide bar.
Further, described sleeve inner is provided with elastic drive unit, and described slide-and-guide bar passes through sleeve connection
To screw bearing, head limited block is installed at the top of described slide-and-guide bar.
Further, described upper support is coated with band locking unit with the joint of lower support bar；Band locking unit
The joint of upper support bar and lower support bar is coated on, is locked so as to realize drawing decelerator in.
Further, described 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 aluminum honeybee
Nest sandwich, the version can not only play raising resistance coefficient, ablative thermal protection effect, may also function as landing shock resistance
Cushioning effect.
Further, described load cabin main body is cylinder-shaped thin wall structure, and inner side is cavity structure, and inner chambers are used to fill
Carry load.
Further, described skull is arched hollow space structure, and inner side is equipped with drag parachute, and skull on ground or can reenter air
It is overall before layer to open, it is easy to load goods to load and unload toward in load cabin main body；Transonic speed stage that can also be after atmospheric reentry
Arch cover on the outside of skimming, pulls out drag parachute, secondary speed-reducing.
The present invention with the beneficial effect of prior art is：
（1）The present invention compared with full protection rigidly fixes formula structure, prevented using connecting rod development mechanism, increase lee face by the decelerator
The technical scheme of heat, draws in when designed development mechanism possesses pneumatic surface launching, reenters front expansion function, and it is right to significantly reduce
Fairing of launch vehicle envelope demand；
（2）Compared with half protects flexible expansion structure, designed full protection structure can stop to flow to decelerator the present invention
Rear end is directly washed away, and centroid position can be designed with off-center axle, generates a little trim ang1e of attack, so that deceleration utensil
Standby certain lift, improves Airflow Environment；Full protection flexibility expansion is again（Enter）Enter reducer structure for celestial body outside following load ground
Into, slow down, land there is provided a kind of new Technology Ways；
（3）Under 0 ° of angles-of-attack state, after the lee face flexibility thermal protection struc ture of increase can overcome shoulder shock wave to decelerator
End affects, and when windward side and lee face flexibility thermal protection struc ture are propped up completely, can realize decelerator full protection function；
Under the conditions of identical pneumatic face diameter, its axial height can be significantly greater than half and protect flexible expansion structure, improve to a certain extent
The volume and load transportation ability of decelerator；
（4）The ball taper double-layer cavity structure of the blunt nosed employing of rigid solar heat protection, can provide the landing buffer of effect suitable with landing lower limb,
Realize solar heat protection integrated with bearing function.
Description of the drawings
Fig. 1 is a kind of pneumatic face deployed condition structural representation of full protection flexibility expansion re-entry deceleration device of the invention；
Fig. 2 is a kind of pneumatic face rounding state structural representation of full protection flexibility expansion re-entry deceleration device of the invention；
Fig. 3 be a kind of full protection flexibility expansion re-entry deceleration device of the invention rigid solar heat protection it is blunt nosed be connected with load cabin main body show
It is intended to；
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 invention；
Fig. 5 is a kind of load cabin main body and the frame rounding state that is slidably connected of full protection flexibility expansion re-entry deceleration device of the invention
Under assembly relation schematic diagram；
Fig. 6 is a kind of load cabin main body and the frame deployed condition that is slidably connected of full protection flexibility expansion re-entry deceleration device of the invention
Under assembly relation schematic diagram；
Fig. 7 is a kind of support bar assembly relation schematic diagram of full protection flexibility expansion re-entry deceleration device of the invention；
Fig. 8 is a kind of flexible thermal protection struc ture assembly relation schematic diagram of full protection flexibility expansion re-entry deceleration device of the invention；
Rounding state schematic diagram when Fig. 9 is a kind of transmitting of full protection flexibility expansion re-entry deceleration device of the invention；
Figure 10 is that a kind of full protection flexibility expansion re-entry deceleration device of the invention reenters deployed condition schematic diagram before air；
Figure 11 be a kind of full protection flexibility expansion re-entry deceleration device of the invention expansion after ramming head lid view.
Wherein, the solar heat protection of 1- rigidity is blunt nosed, and 2- windward sides flexibility thermal protection struc ture, 3- are slidably connected frame, 4- elastic drive units,
5- slide-and-guide bars, 6- skulls, 7- upper support bars, 8- lower support bars, 9- load cabin main bodys, 10- band locking units, the 11- back ofs the body
Wind face flexibility thermal protection struc ture 11,12- hinged seats, 13- screw bearings, 14- auricles, 15- sleeves, 16- head limited blocks.
Specific embodiment
Below in conjunction with accompanying drawing, the invention will be further described.
As shown in Figure 1 and 2, wherein Fig. 1 and Fig. 2 are the pneumatic face expansion of full protection flexibility expansion re-entry deceleration device respectively
Structural representation when state and rounding state, a kind of full protection flexibility expansion re-entry deceleration device of the present 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 bar 7, lower support bar 8, load cabin main body 9, band locking unit 10 and lee face flexibility thermal protection struc ture 11, load cabin main body
9 are located on rigid solar heat protection blunt nosed 1 and are connected using screw therewith；The upper end of described load cabin main body 9 is provided with slip and connects
Frame 3 is connect, the described frame 3 that is slidably connected is slided up and down by slide-and-guide bar 5；The top of the described frame 3 that is slidably connected is provided with
Skull 6；As shown in Fig. 2 band locking unit 10 is coated on the joint of upper support bar 7 and lower support bar 8, decelerator is drawn in
Locking.
As shown in figure 3, described rigid solar heat protection blunt nosed 1 is located at the total bottom, which is double-layer ball cone configuration, both may be used
Ablative thermal protection effect is played, shock resistance buffering can be also taken into account；Described rigid solar heat protection blunt nosed 1 is equal with 9 junction of load cabin main body
Even several hinged seats 12 of setting and 4 screw bearings 13, hinged seat 12 are used for connecting lower support bar 8, and screw bearing 13 is used for
Connection slide-and-guide bar 5, the lower end of lower support bar 8 is connected 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 connected by shaft hinge with the frame 3 that is slidably connected, and upper support bar 7 is with
Support bar 8 is evenly distributed on be slidably connected frame 3 and 9 surrounding of load cabin main body；Upper support bar 7 is connected respectively with lower support bar 8
There is lee face flexibility thermal protection struc ture 11 with 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 present invention frame 3 that is slidably connected, be slidably connected frame 3
For a cylinder-shaped thin wall structure, several support bar auricles are accordingly uniformly arranged with hinged seat 12 at the top of the frame 3 that is slidably connected
14, for connecting the upper end of upper support bar 7；Being slidably connected, 3 bottom of frame is accordingly uniformly arranged 4 sleeves with screw bearing 13
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
Drive lower edge slide-and-guide bar 5 to move, launch so as to drive upper support bar 7 to rotate with lower support bar 8；Skull 6 is pacified as shown in Figure 4
It is mounted at the top of the frame 3 that is slidably connected, skull 6 is an arched hollow space structure, and inner side is equipped with drag parachute；Skull 6 on ground or can be reentered
Integrally open before atmosphere, be easy to load goods toward handling in load cabin main body 9；Transonic speed that can also be after atmospheric reentry
Stage skim outside arch cover, pull out drag parachute, secondary speed-reducing.
As shown in Fig. 5 ~ 6, the frame 3 that is slidably connected is enclosed within load cabin main body 9, and slide-and-guide bar 5 is connected to through sleeve 15
Screw bearing 13, elastic drive unit 4 are mounted in sleeve 15.As shown in figure 5, when decelerator is in rounding state, being slidably connected
Frame 3 be located at load cabin main body 9 at the top of, elastic drive unit 4 be compressed energy-storage state, I in wherein Fig. 4（12:1）, II（12:
1）, III（10:1）Corresponding I, II when decelerator is in rounding state, the CONSTRUCTED SPECIFICATION enlarged drawing of III part；Band locking unit
10 joints for being coated on upper support bar 7 and lower support bar 8, lock so as to realize drawing decelerator in；As shown in fig. 6, reentering
Before atmosphere, band locking unit 10 is unlocked.After band locking unit 10 is unlocked, elastic drive unit 4 releases energy, and drives
The frame 3 that is slidably connected is moved to blunt nosed 1 direction of rigid solar heat protection along slide-and-guide bar 5, when slide-and-guide bar 5 head limited block 16 with
It is slidably connected after the top structure contact of frame 3, motion stops, IV in wherein Fig. 5（8:1）, V（8:1）, VI（8:1）Respectively
IV, V when decelerator is in deployed condition, the CONSTRUCTED SPECIFICATION enlarged drawing of VI part.
As shown in fig. 7, the upper end of upper support bar 7 is connected by rotating shaft with auricle 13, the upper end of upper support bar 7 and lower support
The upper end of bar 8 is connected by rotating shaft；The lower end of lower support bar 8 is connected by rotating shaft with hinged seat 12；Band locking unit 10 is wrapped
The joint of upper support bar 7 and lower support bar 8 is overlayed on, is locked so as to realize drawing decelerator in；Band locking unit 10 is unlocked
Afterwards, the frame 3 that is slidably connected is moved toward blunt nosed 1 direction of rigidity solar heat protection along slide-and-guide bar 5, so as to drive upper support bar 7 with lower support
Bar 8 launches.
As shown in figure 8, after band locking unit 10 is unlocked, the frame 3 that is slidably connected is blunt toward rigidity solar heat protection along slide-and-guide bar 5
The motion of 1 direction, so as to drive upper support bar 7 to launch with lower support bar 8, windward side flexibility thermal protection struc ture 2 and lee face flexibility
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 possess the three-dimensional carbon fibrage heat insulation material of tension function with lee face flexibility thermal protection struc ture 11, support bar rotate in place
Afterwards, flexible thermal protection struc ture is propped up completely, so as to realize decelerator expansion, full protection function.
So that the earth reenters return as an example, the workflow of the present invention is as follows：
As shown in figure 9, overall structure is located in rocket trouserss in the rounding state shown in Fig. 9 in transmitting.Lee face is soft
Property thermal protection struc ture 11 and windward side flexibility thermal protection struc ture 2 draw between upper support bar 7 and lower support bar 8；Band locking unit
10 are coated on the outside of flexible thermal protection struc ture 2 and lee face flexibility thermal protection struc ture 11, the joint of upper support bar 7 and lower support bar 8；
Skull 6 is closed.
Before reentering air, the blasting bolt on band locking unit 10 starts, and the unblock of band locking unit 10 is cast aside；Elasticity
Driver element 4 releases energy, and drives the frame 3 that is slidably connected to move downward along slide-and-guide bar 5, drives upper support bar 7, lower support bar
8 and thereon windward side flexibility thermal protection struc ture 2, lee face flexibility thermal protection struc ture 11 launch together；When the head of slide-and-guide bar 5
After limited block 16 is contacted with the top structure of the frame 3 that is slidably connected, motion stops, and the pneumatic face of full protection is fully deployed, such as Figure 10 institutes
Show.
During reentering, structure by launch the pneumatic face of full protection carry out aerodynamic decelerator, when flight speed be reduced to across
During 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.
Concrete application approach of the present invention is a lot, and the above is only the preferred embodiment of the present invention, it is noted that for
For those skilled in the art, under the premise without departing from the principles of the invention, some improvement can also be made, this
A little improvement also should be regarded as protection scope of the present invention.
Claims (8)
1. a kind of full protection flexibility expansion re-entry deceleration device, including load cabin main body（9）, it is characterised in that described load
Cabin main body（9）It is blunt nosed that lower end is fixed with rigid solar heat protection（1）；Described load cabin main body（9）Upper end the frame that is slidably connected is installed
（3）, the described frame that is slidably connected（3）By slide-and-guide bar（5）Slide up and down；The described frame that is slidably connected（3）Top peace
Equipped with skull（6）；Described load cabin main body（9）It is blunt nosed with rigid solar heat protection（1）Junction be provided with hinged seat（12）And spiral shell
Hole bearing（13）, lower support bar（8）Lower end and hinged seat（12）Connection, lower support bar（8）Upper end and upper support bar（7）'s
Lower end chain connection, upper support bar（7）Upper end and the frame that is slidably connected（3）Chain connection；Described upper support bar（7）With lower
Strut（8）On be connected to lee face flexibility thermal protection struc ture（11）With windward side flexibility thermal protection struc ture（2）.
2. a kind of full protection flexibility expansion re-entry deceleration device according to claim 1, it is characterised in that described hinge
Connection is connected by shaft hinge.
3. a kind of full protection flexibility expansion re-entry deceleration device according to claim 1, it is characterised in that described slip
Connection frame（3）Top be provided with and hinged seat（12）The corresponding auricle in position（14）, upper support bar（7）Upper end and auricle
（14）Connected by rotating shaft；The described frame that is slidably connected（3）Bottom be provided with and screw bearing（13）The corresponding set in position
Cylinder（15）.
4. a kind of full protection flexibility expansion re-entry deceleration device according to claim 3, it is characterised in that described sleeve
（15）Inside is provided with elastic drive unit（4）, described slide-and-guide bar（5）Through sleeve（15）It is connected to screw bearing
（13）, described slide-and-guide bar（5）Top is provided with head limited block（16）.
5. a kind of full protection flexibility expansion re-entry deceleration device according to claim 1, it is characterised in that it is described upper
Strut（7）With lower support bar（8）Joint be coated with band locking unit（10）.
6. a kind of full protection flexibility expansion re-entry deceleration device according to claim 1, it is characterised in that described rigidity
Solar heat protection is blunt nosed（1）Configuration is bored for double-layer ball, outer layer is rigid heat insulation material, and internal layer is aluminum honeycomb sandwich construction.
7. a kind of full protection flexibility expansion re-entry deceleration device according to claim 1, it is characterised in that described load
Cabin main body（9）For cylinder-shaped thin wall structure, inner side is cavity structure.
8. a kind of full protection flexibility expansion re-entry deceleration device according to claim 1, it is characterised in that described skull
（6）For arched hollow space structure, inner side 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106516168A true CN106516168A (en) | 2017-03-22 |
| CN106516168B CN106516168B (en) | 2019-01-29 |
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ID=58344174
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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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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108128483A (en) * | 2017-12-07 | 2018-06-08 | 北京空间技术研制试验中心 | Space station goods and materials downlink aircraft |
| CN109855480A (en) * | 2019-04-02 | 2019-06-07 | 北京星际荣耀空间科技有限公司 | Solid Launch Vehicle grade recovery structure and ballistic, trajectory-lift formula Reentry vehicle |
| CN111017262A (en) * | 2019-11-28 | 2020-04-17 | 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 |
| CN112623179A (en) * | 2020-12-23 | 2021-04-09 | 中国科学院力学研究所 | Recoverable flexible formula transmission nacelle |
| CN113665811A (en) * | 2021-09-13 | 2021-11-19 | 北京理工大学 | Software unmanned delivery aircraft |
| CN113928573A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Sliding fairing with guiding and buffering functions |
| CN114180107A (en) * | 2021-12-07 | 2022-03-15 | 北京空间机电研究所 | Heat-insulation-prevention speed reducing umbrella cabin device for fairing parachute recovery |
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| CN109855480A (en) * | 2019-04-02 | 2019-06-07 | 北京星际荣耀空间科技有限公司 | Solid Launch Vehicle grade recovery structure and ballistic, trajectory-lift formula Reentry vehicle |
| 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 |
| CN111017262A (en) * | 2019-11-28 | 2020-04-17 | 北京空间机电研究所 | Inflatable reentry deceleration flexible unfolding structure folding and unfolding method |
| 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 |
| CN112623179A (en) * | 2020-12-23 | 2021-04-09 | 中国科学院力学研究所 | Recoverable flexible formula transmission nacelle |
| CN113665811A (en) * | 2021-09-13 | 2021-11-19 | 北京理工大学 | Software unmanned delivery aircraft |
| CN113928573A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Sliding fairing with guiding and buffering functions |
| 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 |
| CN114180107A (en) * | 2021-12-07 | 2022-03-15 | 北京空间机电研究所 | Heat-insulation-prevention speed reducing umbrella cabin device for fairing parachute recovery |
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| CN106516168B (en) | 2019-01-29 |
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