CN108516109A - Umbellate form space junk or micrometeoroid protection device for spacecraft - Google Patents
Umbellate form space junk or micrometeoroid protection device for spacecraft Download PDFInfo
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- CN108516109A CN108516109A CN201810272904.8A CN201810272904A CN108516109A CN 108516109 A CN108516109 A CN 108516109A CN 201810272904 A CN201810272904 A CN 201810272904A CN 108516109 A CN108516109 A CN 108516109A
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- protective cover
- umbellate form
- space junk
- slide cartridge
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- 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
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- 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
- B64G1/56—Protection against meteoroids or space debris
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- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
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Abstract
The invention discloses a kind of umbellate form space junks or micrometeoroid protection device for spacecraft, including umbellate form protective cover, flexible springs and controllable hinge, wherein, umbellate form protective cover is closely spliced into umbrella-shaped structure by polylith triangle protection face board, it is connect with the controllable slide cartridge for sliding setting on main support rod by side support bar on the inside of every block of plate, with the shock of space junk or micrometeroroid, umbellate form protective cover can change the inclined direction of protective cover along sliding of the controllable slide cartridge on main support rod, reduce impact damage.The present invention substantially reduces space junk and is directly exerted oneself to protective cover, increases protective cover to space junk buffer time, improves the protective capacities to space junk, and protective capacities highest promotes 40 times or more.
Description
Technical field
The invention belongs to space junks and micrometeroroid environmental protection domain technology field, and in particular to a kind of spacecraft
Umbellate form space junk or micrometeoroid protection device.
Background technology
" space junk ", also known as space trash are mankind's solar-system operation abandonments in the waste in space, are space environments
Primary pollution source.Since emitting first man made earth satellite from nineteen fifty-seven, space junk sum alreadys exceed 4,000 ten thousand, always
Quality has reached millions of kilograms, and the space junk that ground-based telescope and radar can observe increases about 200 every year on average, greatly
9200 are had been over now in 10 centimetres of space junks.Space junk is mainly distributed on 2000 kilometers of low orbits below
Area, they constitute a serious threat to the spacecraft of terrestrial space.
Space junk size range include micron order, grade, Centimeter Level or even meter level, wherein Centimeter Level and its more than
Space junk be mainly carrier rocket Upper Stage, task end spacecraft, work when abandon object, unexpectedly disintegrate it is broken
Piece, alundum (Al2O3) residue, sodium k particle etc.；Grade space junk is mainly spacecraft surface flakes, sputtering object, three
Al 2 O residue, sodium k particle, micrometeroroid, unexpected disintegration fragment etc.；Micron-sized space debris includes mainly that peeling is broken
Piece, sputtering object, alundum (Al2O3) dust, micrometeroroid etc..
Space junk more than 10 centimetres will cause spacecraft destructiveness to be damaged, due to that can pass through ground telescope at present
Or radar measuring its track, the strategy that early warning is evaded can be taken to be effectively prevented its injury；Centimeter Level space junk can also
Cause spacecraft thoroughly to damage, there is no practicable safeguard procedures at present, unique method be on Spacecraft guidance and control and operation,
Trying to reduce makes spacefarer and spacecraft that the risk of mortality damage occur；Grade space junk can result in spacecraft surface
Generation hits hole or even bulkhead is made to perforate, and impact site is different, and the degree of harm also has very big difference.Wherein, table 1 lists sky
Between fragment essential information.
The essential information of 1 space junk of table
It is more than the large space fragment of 10cm to size, the measure mainly taken monitoring and evaded；Small space below to 1cm
Fragment mainly takes the measure of protection；And size is more than the space plain piece of 1cm, protection leads into the increase for bringing weight
This is drastically increased.The speed of LEO, space junk is thousands of metre per second (m/s)s, and when colliding with spacecraft, relative velocity can
Up to 10km/s or more, thus it is very risky.
Micrometeroroid refers to the solid particles for originating from comet and asteroid belt and being moved in interstellar space.Micrometeroroid
May occur to hit and cause the damage of spacecraft with spacecraft, type and the degree of damage depend on spacecraft size, configuration,
The characteristics such as working time and micrometeroroid quality, density, speed.This impact damage includes the rupture of pressure vessel, porthole
Degeneration, thermal control coating layer split, the reduction of thermal protective performance and the damage of antenna system etc..
Currently, for space junk and micrometeoroid protection method, spacecraft uses different measures to avoid space
The hypervelocity impact of fragment and micrometeroroid, the space junk for size more than 10cm are hit since the kinetic energy that it has is very big
It will produce catastrophic collapse when hitting spacecraft, however the overwhelming majority in these fragments can be tracked by ground observation equipment and be seen
It surveys, therefore, spacecraft is hidden by the way of active dodge；It is less than the space junk of 1cm for size, since it has
Kinetic energy it is smaller, not will produce catastrophic collapse usually when hitting spacecraft, therefore spacecraft is given using the method for passive protection
With protection.For the fragment between 1-10cm, the kinetic energy having due to it is larger and does not observe, and spacecraft is not prevented effectively
Shield measure, therefore these fragments become dangerous debris.
Whipple safeguard structures are currently mainly used in the protection of space junk, i.e., one piece is arranged before spacecraft bulkhead
Incoming projectiles are crushed by buffer board, or even fusing, vaporization, form fragment cloud cluster, to become the point load of impact from space debris
At face load, the intensity of shock loading is reduced, reduces the damage that spacecraft bulkhead is subjected to.People call this structure type
Whipple safeguard structures, are shown in Fig. 1.
But with the drastically deterioration of space debris environment, the problem of protective capacities deficiency gradually appears.People are based on
Whipple safeguard structures develop various structures, these structures can be divided into according to the number of plies of damping screen：Single buffer screen protection knot
Structure, double buffering screen safeguard structure and more damping screen safeguard structures.Compared to Whipple safeguard structures, these safeguard structures are prevented
Shield ability, which has, significantly to be promoted, therefore also referred to as enhanced safeguard structure.Below with single layer screen enhancing safeguard structure and more
Illustrate for layer safeguard structure.
The enhanced safeguard structure of single layer screen includes cellular board Sandwich Plates and foamed aluminium safeguard structure.The panel phase of front layer
When the panel of the damping screen in Whipple safeguard structures, rear layer is equivalent to the rear wall in Whipple safeguard structures.Cellular board
According to the difference of panel, aluminum deck honeycomb plate structure and carbon fiber honeycomb plate structure can be divided into (referring to document
I.W.Members.Vers ion 4.0 of the IADC Protect ion Manual[R].Germany,2009.)。
(for MS compared with Whipple safeguard structures, multilayer surge guard structure increases damping screen to multilayer surge guard structure
Number (3-5 layers general), as shown in Figure 2.The increase of damping screen number makes bullet in impact protective structure, multilayer buffering
Screen can intercept bullet layer by layer, ensure that bullet can be adequately crushed, or even fusing and vaporization, and a large amount of kinetic energy is made to become
For interior energy.After panus shock when wall, since particle size in panus and speed are all very small, the damage of rear wall is dropped significantly
It is low, to improve protective capacities.Compared with typical Whipple safeguard structures, multilayer surge guard structural shielding ability improves
Nearly 40%.
Later, aerospace expert had also been proposed a kind of density gradient type safeguard structure, as shown in Figure 3.Density gradient material is
A kind of material of wave impedance increasing or decreasing is formed in thickness direction.Density gradient type safeguard structure is buffered by one layer of density gradient
Screen, protection spacing and rear wall composition.Density gradient damping screen is in crash direction according to multiple made of wave impedance production decline law
Close screen.This is a kind of new spatial fragment protective structure different from previous enhanced safeguard structure.
But the case where these materials or structure are consideration space junk frontal impacts, and often it is directed to single space
Fragment or micrometeroroid.If large area is installed on spacecraft, it will greatly increase the weight of spacecraft, and can only
It is fixed on spacecraft.
Invention content
The goal of the invention of the present invention is to provide a kind of for the umbellate form space junk of spacecraft or micrometeoroid protection dress
It sets, which puts before being positioned over spacecraft to be protected, using protective device relative to the inclined original of space junk incident direction
It manages to substantially reduce the impact strength of space junk, it is also possible to be further decreased using the high speed rotation of protective device
The impact damage of space junk.
For the umbellate form space junk or micrometeoroid protection device of spacecraft, including umbellate form protective cover, flexible springs,
And it is fixed on spacecraft to realize the controllable hinge of umbellate form protective cover direction change, wherein umbellate form protective cover is by polylith three
Angular protection face board is closely spliced into umbrella-shaped structure, and every piece of protection face board inside by chaining part and engages collateral
Strut is connect with the controllable slide cartridge for sliding setting on main support rod, and the vertex of each triangle protection face board is connected to altogether on slide cartridge one,
Main support rod passes through slide cartridge one and slide cartridge one is fixed on the top of main support rod by flexible springs, main support rod end
It is fixedly connected with controllable hinge, with the shock of space junk or micrometeroroid, umbellate form protective cover can be along controllable slide cartridge in master
Sliding on supporting rod and the inclined direction for changing protective cover, reduce impact damage.
Wherein, flexible springs are extension spring.
For the umbellate form space junk or micrometeoroid protection device of spacecraft, including umbellate form protective cover, flexible springs,
And it is fixed on spacecraft to realize the controllable hinge of umbellate form protective cover direction change, wherein umbellate form protective cover is by polylith three
Angular protection face board is closely spliced into umbrella-shaped structure, and every piece of protection face board inside by chaining part and engages collateral
Strut is connect with the controllable slide cartridge for sliding setting on main support rod, and the vertex of each triangle protection face board is connected to altogether on slide cartridge one,
Main support rod passes through the main shaft of slide cartridge one and controllable slide cartridge, and controllable slide cartridge is fixed on main support rod by flexible springs
On end, main support rod end is fixedly connected with controllable hinge, with the shock of space junk or micrometeroroid, umbellate form protective cover
The inclined direction of protective cover can be changed along sliding of the controllable slide cartridge on main support rod, reduce impact damage.
Wherein, flexible springs are high compression spring.
Wherein, the quantity of triangle protection face board is more than 12.
Wherein, chaining part is hinge arrangement.
Wherein, protective cover uses aluminium alloy, titanium alloy, Nextel the ceramics either homogenous material of Kevlar fibers or multiple
Condensation material is made.
Wherein, protection skin plate is density gradient type protection of space debris panel.
Wherein, the inclination angle size of umbellate form protective cover is realized by the back-and-forth motion of controllable slide cartridge.
The protection of space debris device of the present invention, can substantially reduce space junk and directly be exerted oneself to protective cover, increase
Protective cover is to space junk buffer time, so as to improve the protective capacities to space junk, withThe protective cover at inclination angle is
Example, protective capacities improve 4 times, if increasing spring structure or elastic material as buffering, protective capacities improves 40 times
More than.
Description of the drawings
Fig. 1 is the schematic diagram of Whipple safeguard structures in the prior art；
Fig. 2 is the schematic diagram of multilayer surge guard structure in the prior art；
Fig. 3 is the schematic diagram of density gradient type space debris prevention structure；
Fig. 4 is umbellate form protective cover in the umbellate form space junk or micrometeoroid protection device for spacecraft of the present invention
Structural schematic diagram.；
Fig. 5 is the umbellate form space junk or micrometeoroid protection device for spacecraft of the embodiment of the invention
Structural schematic diagram；
Wherein：1, protective cover；2, chaining part；3, side support bar；4, controllable slide cartridge；5, main support rod；6, flexible springs；
7, slide cartridge one.
Fig. 6 is being filled for the umbellate form space junk of spacecraft or micrometeoroid protection for another specific implementation mode of the present invention
The structural schematic diagram set；
Wherein：1, protective cover；2, chaining part；3, side support bar；4, controllable slide cartridge；5, main support rod；6, flexible springs；
7, slide cartridge one.
Fig. 7 is that the umbellate form space junk or micrometeoroid protection device for spacecraft of the present invention receives space junk punching
Stress when hitting and resolution of velocity schematic diagram.
Specific implementation mode
Below in conjunction with attached drawing, invention is further described in detail, but this is only exemplary, it is no intended to this
The protection domain of invention carries out any restrictions.Patent of the present invention is further described below in conjunction with the accompanying drawings.
Core of the invention is to pass through reduction using large area protective cover and flexible springs with controllable angle of inclination
Angle of inclination reduces active force of the perpendicular acting on protective cover, and it is gentle to increase buffer time by using flexible springs
Distance is rushed, to realize the purpose slowed down to space junk and protected.
Typical case's Whipple structural schematic diagrams mentioned in the present invention are given referring to Fig. 1, Fig. 1.As seen from Figure 1, it passes
The Whipple safeguard structures of system are the sheet metal of a single layer (it is aluminium alloy to give typical material here).Space junk (phase
When hitting Ballet Shop in one) it is first to strike safeguard structure layer, it is then possible to strike on spacecraft again and (is here
" the rear wall " hit).
The schematic diagram of multilayer surge guard structure in the prior art is given referring to Fig. 2, Fig. 2.As seen from Figure 2, phase
Compared with monolayer composite structure, multilayer proofing structure is that multiple protective layers form a protection array perhaps.Space junk (is equivalent to one
A shock Ballet Shop) only be possible to strike on spacecraft (this again after multilayer proofing structure (i.e. multilayer proofing screen)
In be hit " rear wall ").
The schematic diagram of density gradient type space debris prevention structure is given referring to Fig. 3, Fig. 3.As seen from Figure 3, this
In traditional single protective layer is replaced using the protective layer of density gradient structure, and density gradient structure is then the density of material
Graded is presented with thickness, is the equal of the superposition of multilayer homogeneous density material.Space junk (is equivalent to a shock
Ballet Shop) it is first to strike density gradient structure (i.e. density gradient screen here), it is then possible to strike on spacecraft again
(being " the rear wall " hit here).
In the umbellate form space junk or micrometeoroid protection device for spacecraft for showing the present invention referring to Fig. 4, Fig. 4
The structural schematic diagram of umbellate form protective cover.As seen from the figure, tiltable protective cover of the invention is umbrella-shaped structure, and protective cover is opened
It is " umbrella " shape, the tilt adjustable of umbrella afterwards.Wherein, " umbrella " type protective cover is made of 12 pieces of triangle protection face boards, and every piece anti-
Protection slab is connect by side support bar with the controllable slide cartridge on main support rod.
The structure of protective device in the embodiment of the invention is shown referring to Fig. 5, Fig. 5, wherein the specific implementation
The protective device of one of mode includes the aluminum alloy protective cover 1 of umbellate form, flexible springs 6, and is fixed on spacecraft with reality
The controllable hinge (being not shown, which is fixed on spacecraft) that existing umbellate form protective cover direction changes, wherein umbellate form protects
Cover is closely spliced into umbrella-shaped structure by polylith triangle protection face board, passes through the chaining part of hinge 2 on the inside of every piece of protection face board
And the side support bar 3 engaged is connect with the controllable slide cartridge 4 for sliding setting on main support rod 5, each triangle protection face board
Vertex be connected to altogether on slide cartridge 1, main support rod passes through and slide cartridge 1 and slide cartridge 1 is fixed on main branch by flexible springs 6
On the top of strut 5, the end of main support rod 5 is fixedly connected with controllable hinge, with the shock of space junk or micrometeroroid,
Umbellate form protective cover can change the inclined direction of protective cover 1 along sliding of the controllable slide cartridge on main support rod 5, reduce and hit damage
Wound.In this embodiment, flexible springs are to draw high spring.
The structure of protective device in another specific implementation mode of the present invention is shown referring to Fig. 6, Fig. 6, wherein the specific reality
The celestial body protective device of mode, including umbellate form protective cover 1, flexible springs 6 are applied, and are fixed on spacecraft to realize umbellate form
The controllable hinge that protective cover direction changes, wherein umbellate form protective cover 1 is closely spliced into umbrella knot by polylith triangle protection face board
Structure, every piece of protection face board inside are slided by the chaining part of hinge 2 and the side support bar engaged 3 on main support rod 5
The controllable slide cartridge 4 of dynamic setting connects, and the vertex of each triangle protection face board is connected to altogether on slide cartridge 1, and main support rod 5 passes through slide cartridge
1 and controllable slide cartridge 4 main shaft, and controllable slide cartridge 4 is fixed on the end of main support rod 5 by flexible springs 6, main branch
The end of strut 5 is fixedly connected with controllable hinge, and with the shock of space junk or micrometeroroid, umbellate form protective cover can be along can
It controls sliding of the slide cartridge on main support rod and changes the inclined direction of protective cover, reduce impact damage.In the specific implementation mode
In, flexible springs are high compression spring.
In above two specific implementation mode, the inclination angle size of umbrella protective cover can pass through the back-and-forth motion of controllable slide cartridge
To realize.
After the space junk that quality is m, sectional area is s is struck with speed V on protective cover, it is assumed that the thickness of protective cover
The average crashworthiness hit intensity P of cover material is protected to be calculated by following formula when protective cover does not penetrate for d.
P × s × d=0.5 × m × (Vs in θ)2
Then have：
P=0.5 × m × (Vs in θ)2/s/d
Therefore, when protective cover inclination angle theta is smaller, then protect the impact strength that cover material is subject to smaller.When θ isWhen, due toThen compared with vertical incidence protective cover, protective capacities improves 4 times.
In general, the thickness of protection cover material is 0.1-0.3cm.
Referring to Fig. 7, the collapsing length or reduction length d of spring and limit stress F by the space junk quality of quasi- protection and
Speed determines.See below formula：
F × d=0.5 × m × V2
To the space junk that quality is 1g, when speed is 10km/s, by formula above it is found that F × d=5 × 104J。
In no spring, the buffer distance of protective cover is up to the thickness of protective cover, usually 0.1cm magnitudes, it is assumed that bullet
The minimum 1cm of buffer distance of spring, then the buffer distance of protective cover can at least improve 10 times, therefore, impact resistant capability is at least
Improve 10 times or more.
Third is fixed on using controllable hinge on spacecraft in the end of " umbrella ", and protective cover may be implemented in controllable hinge
Direction changes.Controllable hinge can utilize the variation of the realization protective device direction such as geared system.
Therefore, by the way that by protective cover, relative to impact from space debris direction, there are certain inclination angles, in combination with spring buffer
The protective capacities of anti-impact from space debris can be improved 40 times or more by device.
Although giving detailed description and explanation to the specific implementation mode of patent of the present invention above, it should be noted that
Be, we can the conception of patent according to the present invention various equivalent changes and modification are carried out to the above embodiment, produced by
Function still covered without departing from specification and attached drawing spirit when, should all be within the protection domain of patent of the present invention.
Claims (9)
1. for the umbellate form space junk or micrometeoroid protection device of spacecraft, including umbellate form protective cover, flexible springs, with
And it is fixed on spacecraft to realize the controllable hinge of umbellate form protective cover direction change, wherein umbellate form protective cover is by polylith triangle
Shape protection face board is closely spliced into umbrella-shaped structure, passes through chaining part and the collateral support engaged on the inside of every piece of protection face board
Bar is connect with the controllable slide cartridge for sliding setting on main support rod, and the vertex of each triangle protection face board is connected to altogether on slide cartridge one, main
Supporting rod is passed through and slide cartridge one and slide cartridge one is fixed on the top of main support rod by flexible springs, main support rod end with
Controllable hinge is fixedly connected, and with the shock of space junk or micrometeroroid, umbellate form protective cover can be along controllable slide cartridge in main branch
Sliding on strut and the inclined direction for changing protective cover, reduce impact damage.
2. umbellate form space junk as described in claim 1 or micrometeoroid protection device, wherein flexible springs are to stretch bullet
Spring.
3. for the umbellate form space junk or micrometeoroid protection device of spacecraft, including umbellate form protective cover, flexible springs, with
And it is fixed on spacecraft to realize the controllable hinge of umbellate form protective cover direction change, wherein umbellate form protective cover is by polylith triangle
Shape protection face board is closely spliced into umbrella-shaped structure, passes through chaining part and the collateral support engaged on the inside of every piece of protection face board
Bar is connect with the controllable slide cartridge for sliding setting on main support rod, and the vertex of each triangle protection face board is connected to altogether on slide cartridge one, main
Supporting rod passes through the main shaft of slide cartridge one and controllable slide cartridge, and controllable slide cartridge is fixed on to the end of main support rod by flexible springs
On end, main support rod end is fixedly connected with controllable hinge, and with the shock of space junk or micrometeroroid, umbellate form protective cover can
Change the inclined direction of protective cover along sliding of the controllable slide cartridge on main support rod, reduces impact damage.
4. umbellate form space junk as claimed in claim 3 or micrometeoroid protection device, wherein flexible springs are high compression
Spring.
5. the umbellate form space junk as described in claim 1 or 3 or micrometeoroid protection device, wherein triangle protection face board
Quantity be more than 12.
6. the umbellate form space junk as described in claim 1 or 3 or micrometeoroid protection device, wherein chaining part is hinge knot
Structure.
7. the umbellate form space junk as described in claim 1 or 3 or micrometeoroid protection device, wherein protective cover is closed using aluminium
Gold, titanium alloy, either the homogenous material of Kevlar fibers or composite material are made Nextel ceramics.
8. the umbellate form space junk as described in claim 1 or 3 or micrometeoroid protection device, wherein protection skin plate is close
Spend gradient type protection of space debris panel.
9. the umbellate form space junk as described in claim 1 or 3 or micrometeoroid protection device, wherein umbellate form protective cover inclines
Angle size is realized by the back-and-forth motion of controllable slide cartridge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810272904.8A CN108516109B (en) | 2018-03-29 | 2018-03-29 | Umbrella-shaped space debris or micro-fluidic star protection device for spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810272904.8A CN108516109B (en) | 2018-03-29 | 2018-03-29 | Umbrella-shaped space debris or micro-fluidic star protection device for spacecraft |
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| Publication Number | Publication Date |
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| CN108516109A true CN108516109A (en) | 2018-09-11 |
| CN108516109B CN108516109B (en) | 2020-04-03 |
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| CN201810272904.8A Active CN108516109B (en) | 2018-03-29 | 2018-03-29 | Umbrella-shaped space debris or micro-fluidic star protection device for spacecraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104223A (en) * | 2019-06-11 | 2019-08-09 | 中国科学院沈阳自动化研究所 | It is armoring outside a kind of Space Facilities based on flexible structure |
| CN112478199A (en) * | 2020-11-27 | 2021-03-12 | 南京航空航天大学 | Satellite flexible repeatable folding and unfolding defense device for resisting physical impact |
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| CN102514737A (en) * | 2011-11-08 | 2012-06-27 | 西安交通大学 | Lightweight filled composite protective structure for space debris |
| CN103072705A (en) * | 2013-01-29 | 2013-05-01 | 北京空间飞行器总体设计部 | Device for preventing condensable volatile material from entering satellite sensor |
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| CN1085177A (en) * | 1992-08-26 | 1994-04-13 | 丁震东 | Handle the method and apparatus that minces with the showy space of withdrawal |
| JP2010285137A (en) * | 2009-06-12 | 2010-12-24 | Keisuke Ozawa | Space debris reducing apparatus |
| WO2011070349A1 (en) * | 2009-12-07 | 2011-06-16 | Phs Space Limited | Apparatus for spacecraft |
| CN102514737A (en) * | 2011-11-08 | 2012-06-27 | 西安交通大学 | Lightweight filled composite protective structure for space debris |
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| CN110104223A (en) * | 2019-06-11 | 2019-08-09 | 中国科学院沈阳自动化研究所 | It is armoring outside a kind of Space Facilities based on flexible structure |
| CN110104223B (en) * | 2019-06-11 | 2023-08-08 | 中国科学院沈阳自动化研究所 | Outer armor of spatial equipment based on flexible structure |
| CN112478199A (en) * | 2020-11-27 | 2021-03-12 | 南京航空航天大学 | Satellite flexible repeatable folding and unfolding defense device for resisting physical impact |
| CN112478199B (en) * | 2020-11-27 | 2022-06-14 | 南京航空航天大学 | Satellite flexible repeatable folding and unfolding defense device for resisting physical impact |
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| Publication number | Publication date |
|---|---|
| CN108516109B (en) | 2020-04-03 |
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