CN107697319A - A kind of flexible protective structure based on high-performance fiber fabric and foam - Google Patents
A kind of flexible protective structure based on high-performance fiber fabric and foam Download PDFInfo
- Publication number
- CN107697319A CN107697319A CN201710532861.8A CN201710532861A CN107697319A CN 107697319 A CN107697319 A CN 107697319A CN 201710532861 A CN201710532861 A CN 201710532861A CN 107697319 A CN107697319 A CN 107697319A
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- screen
- foam
- fiber
- flexible protective
- structure based
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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
Abstract
The invention discloses a kind of flexible protective structure based on high-performance fiber fabric and foam, including damping screen, foam, filling screen and rear wall；Damping screen is used for cracking space fragment, and foam is used for the decrement or swell increment for adjusting safeguard structure, and filling screen is used to disintegrate Debris Clouds, and rear wall is used to capture Debris Clouds, and damping screen, foam, filling screen, rear wall pass through sticker successively adhesion.The present invention realizes the compression of structure foldable integral, is easy to launch, compensate for the defects of traditional defense structural reliability is relatively low by designing filling screen；By adhesion foam, the technique effect that the overall protection spacing of structure breaks through the limitation of rocket dome space is reached, has significantly enhanced protective capacities, solve the problems, such as that traditional defense Structural Energy Dissipation is excessive and environmental suitability is poor.
Description
Technical field
The present invention relates to a kind of flexible protective structure based on high-performance fiber fabric and foam, be particularly suitable for use in spacecraft
Impact from space debris is resisted, belongs to space junk passive protection technical field.
Background technology
Space junk easily causes spacecraft and polytype damage occurs, and species and the degree of damage depend on spacecraft
Size, configuration, the quality of working time and space junk, density, speed, the characteristic such as crash direction.The class of impact damage
Type includes wallboard perforation, pressure vessel rupture, air port glass is degenerated, thermal control performance reduces and sealed compartment leakage.
Shock for space junk threatens, and aerospace engineering common practice is：The space junk of spacecraft is hit first
Hit risk to be assessed, and then take certain safeguard procedures to improve the ability that spacecraft resists impact from space debris, protection is arranged
Apply including adjustment spacecraft layout, change flight attitude, using the strong material of protective capacities, set up special safeguard structure.It is right
In long-term in-orbit manned spacecraft, general synthesis improves existence of the spacecraft in space debris environment using above-mentioned measure
Ability.Wherein, special precautions structure is very effective preventive means, and international space station and other large-scale low rails are transported for a long time
The usual safeguard procedures of capable spacecraft.
In the prior art, conventional special precautions structure is Whipple safeguard structures and stuffed Whipple shield structure.
The principle of Whipple safeguard structures is as follows：Particle produces shock wave after hitting damping screen, if particle stroke speed is sufficiently high, shape
Into reflected shock wave intensity it is sufficiently large, it is possible to make shock particle fragmentation, liquefaction until vaporization, and forms panus, so as to will
Impact energy is distributed on greater area of rear wall, and then eliminates or reduce damage of the particle to rear wall；Wall capture panus afterwards,
Protect spacecraft interior instrument equipment.Buffering screen material should have the characteristics that：Density is low；Have to bullet (or secondary fragmentation)
Good breaking capacity；Panus is set to produce big angle of flare；Reduce the stroke speed of panus；Damping screen is caused broken in itself
Bits threaten the damage of rear wall small.In view of barrier propterty, the rigidity of structure and the requirement for protecting cost, the outer general aluminium of damping screen
Alloy material.Further to disintegrate bullet debris particles coming, panus speed is effectively reduced, foreign countries are using in outer damping screen and rear wall
Centre increase filling screen, filling screen is general to choose high elastic modulus, high intensity, the fibrous material of low-density.In equal surface density
Under, the protective capacities of stuffed Whipple shield structure is far above Whipple safeguard structures, and this is also stuffed Whipple shield structure (filling screen
For Nextel312+kevlar) the reason for international space station high risk zone is used widely.But at present used in foreign countries
The filling screen material country can not obtain, it is therefore desirable to from the domestic filling screen material with premium properties.
In recent years, there are some new spacecrafts, such as gas-filled unfolded spacecraft, its compressed before transmission, folding
Reduce transmitting volume, it is inflating expanded after entering the orbit to form huge nacelle.Traditional rigid shielding structure can not compress or fold, nothing
Method meets the needs of gas-filled unfolded spacecraft.
The content of the invention
Present invention solves the technical problem that it is：Overcome the deficiencies in the prior art, the invention provides one kind to be based on high-performance
The flexible protective structure of fabric and foam, by designing filling screen, the compression of structure foldable integral is realized, is easy to launch,
It compensate for the defects of traditional defense structural reliability is relatively low；By adhesion foam, the overall protection spacing of structure is reached and has broken through
Rocket dome space limitation technique effect, significantly enhance protective capacities, solve traditional defense Structural Energy Dissipation it is excessive and
The problem of environmental suitability is poor.
The present invention technical solution be：
A kind of flexible protective structure based on high-performance fiber fabric and foam, including damping screen, foam, filling screen and after
Wall；Damping screen is used for cracking space fragment, and foam is used for the decrement or swell increment for adjusting safeguard structure, and filling screen is used to disintegrate
Debris Clouds, rear wall are used to capture Debris Clouds, and damping screen, foam, filling screen, rear wall pass through sticker successively adhesion.
In a kind of above-mentioned flexible protective structure based on high-performance fiber fabric and foam, the damping screen uses plate
Shape structure, damping screen are formed by basalt fibre braiding, and the braiding number of plies of damping screen is no less than three layers.
In a kind of above-mentioned flexible protective structure based on high-performance fiber fabric and foam, the material of the foam is adopted
With polyurethane, the density of foam is not more than 0.05g/cm3, the compression ratio of foam is not less than 80%.
In a kind of above-mentioned flexible protective structure based on high-performance fiber fabric and foam, the filling screen uses plate
Shape structure, filling screen are formed by basalt fibre braiding.
In a kind of above-mentioned flexible protective structure based on high-performance fiber fabric and foam, the filling screen includes the
One screen and the second screen；First screen and the fitting of the second screen, adhesion foam between the first screen and damping screen, glue between the second screen and rear wall
Even foam.
In a kind of above-mentioned flexible protective structure based on high-performance fiber fabric and foam, first screen and second
Screen uses platy structure, and the first screen is formed by basalt fibre braiding, and the second screen is formed by aramid fiber braiding.
In a kind of above-mentioned flexible protective structure based on high-performance fiber fabric and foam, the braiding of first screen
The number of plies is set to three layers, and the braiding number of plies of the second screen is set to two layers.
In a kind of above-mentioned flexible protective structure based on high-performance fiber fabric and foam, the basalt fibre
Fibre density is not more than 2.7g/cm3, the fiber stretch modulus of basalt fibre is not less than 70GPa, and the fiber of basalt fibre is drawn
Stretch intensity and be not less than 2100MPa, the woven surface density of basalt fibre is not more than 0.04g/cm2。
In a kind of above-mentioned flexible protective structure based on high-performance fiber fabric and foam, the rear wall uses tabular
Structure, rear wall are formed by aramid fiber or kevlar fiber braiding, and the braiding number of plies of rear wall is no less than Floor 12.
In a kind of above-mentioned flexible protective structure based on high-performance fiber fabric and foam, the aramid fiber or triumphant
Cottonrose hibiscus tow dimension fibre density no more than 1.5g/cm3, the fiber stretch modulus of aramid fiber or kevlar fiber is not less than
The tensile strength of fiber of 80GPa, aramid fiber or kevlar fiber is not less than 3600MPa, aramid fiber or kevlar fiber
Woven surface density no more than 0.03g/cm2。
Compared with the prior art, the invention has the advantages that：
【1】The panus that the present invention is formed is powdered substance, and damping screen and filling screen are broken, melt bullet, high intensity
The rear wall that the fine braiding of aramid fiber forms is compared to wall after traditional metal, using the teaching of the invention it is possible to provide higher impact carrying, foam it is compressible or
Expansion, safeguard structure itself is foldable, possesses more preferable adaptability, has boundless market prospects and great engineering should
Use potentiality.
【2】Compact overall structure of the present invention, suitable for various working environments, and there is longer service life, in complexity
Under operating mode still can good operation, have it is versatile, applied widely the characteristics of.
Brief description of the drawings
Fig. 1 is the structure chart of the present invention
Wherein：1 damping screen；2 foams；3 filling screens；301 first screens；302 second screens；Wall after 4；
Embodiment
To make the solution of the present invention more understand, explanation and specific embodiment are made further to the present invention below in conjunction with the accompanying drawings
Description：
As shown in figure 1, a kind of flexible protective structure based on high-performance fiber fabric and foam, including damping screen 1, foam
2nd, filling screen 3 and rear wall 4；Damping screen 1 is used for cracking space fragment, and foam 2 is used for decrement or the expansion for adjusting safeguard structure
Amount, filling screen 3 are used to disintegrate Debris Clouds, and rear wall 4 is used to capturing Debris Clouds, damping screen 1, foam 2, filling screen 3, after
Wall 4 passes through sticker successively adhesion.
Preferably, damping screen 1 uses platy structure, and damping screen 1 is formed by basalt fibre braiding, the braiding of damping screen 1
The number of plies is no less than three layers.
Preferably, the material of foam 2 uses polyurethane, and the density of foam 2 is not more than 0.05g/cm3, the compression ratio of foam 2
Not less than 80%.
Preferably, filling screen 3 uses platy structure, and filling screen 3 is formed by basalt fibre braiding.
Preferably, filling screen 3 includes the first screen 301 and the second screen 302；First screen 301 and the second screen 302 are bonded, and first
Adhesion foam 2 between screen 301 and damping screen 1, adhesion foam 2 between the second screen 302 and rear wall 4.
Preferably, the first screen 301 and the second screen 302 use platy structure, the first screen 301 woven by basalt fibre and
Into the second screen 302 is formed by aramid fiber braiding.
Preferably, the braiding number of plies of the first screen 301 is set to three layers, and the braiding number of plies of the second screen 302 is set to two layers.
Preferably, the fibre density of basalt fibre is not more than 2.7g/cm3, the fiber stretch modulus of basalt fibre is not
Less than 70GPa, the tensile strength of fiber of basalt fibre is not less than 2100MPa, and the woven surface density of basalt fibre is not
More than 0.04g/cm2。
Preferably, rear wall 4 uses platy structure, and rear wall 4 is formed by aramid fiber or kevlar fiber braiding, rear wall 4
The braiding number of plies is no less than Floor 12.
Preferably, the fibre density of aramid fiber or kevlar fiber is no more than 1.5g/cm3, aramid fiber or triumphant cottonrose hibiscus
The fiber stretch modulus for dimension of towing is not less than 80GPa, and the tensile strength of fiber of aramid fiber or kevlar fiber is not less than
The woven surface density of 3600MPa, aramid fiber or kevlar fiber is no more than 0.03g/cm2。
The present invention operation principle be：
During rocket launching, safeguard structure folds, and foam 2 compresses, and reduces volume, spacecraft in orbit when, safeguard structure
Expansion, foam 2 expand, and spacecraft position to be protected effectively are coated, when impact from space debris safeguard structure, by basalt fibre
The rapid dispersion and fining space junk of damping screen 1 formed is woven, the sky after the 3 pairs of crushing of filling screen formed by aramid fiber braiding
Between fragment carry out deceleration interception, carrying out barrier comprehensively to remnants space junk by the kevlar fiber rear wall 4 that forms of braiding receives
Collection.
The content not being described in detail in description of the invention is known to the skilled person technology.
Claims (10)
- A kind of 1. flexible protective structure based on high-performance fiber fabric and foam, it is characterised in that：Including damping screen (1), bubble Foam (2), filling screen (3) and rear wall (4)；Damping screen (1) is used for cracking space fragment, and foam (2) is used to adjust safeguard structure Decrement or swell increment, filling screen (3) are used to disintegrate Debris Clouds, and rear wall (4) is used to capture Debris Clouds, damping screen (1), foam (2), filling screen (3), rear wall (4) pass through sticker successively adhesion.
- 2. a kind of flexible protective structure based on high-performance fiber fabric and foam according to claim 1, its feature exist In：The damping screen (1) uses platy structure, and damping screen (1) is formed by basalt fibre braiding, the braiding layer of damping screen (1) Number is no less than three layers.
- 3. a kind of flexible protective structure based on high-performance fiber fabric and foam according to claim 1, its feature exist In：The material of the foam (2) uses polyurethane, and the density of foam (2) is not more than 0.05g/cm3, the compression ratio of foam (2) is not Less than 80%.
- 4. a kind of flexible protective structure based on high-performance fiber fabric and foam according to claim 1, its feature exist In：The filling screen (3) uses platy structure, and filling screen (3) is formed by basalt fibre braiding.
- 5. a kind of flexible protective structure based on high-performance fiber fabric and foam according to claim 1, its feature exist In：The filling screen (3) includes the first screen (301) and the second screen (302)；First screen (301) and the second screen (302) fitting, the Adhesion foam (2) between one screen (301) and damping screen (1), adhesion foam (2) between the second screen (302) and rear wall (4).
- 6. a kind of flexible protective structure based on high-performance fiber fabric and foam according to claim 5, its feature exist In：First screen (301) and the second screen (302) use platy structure, the first screen (301) woven by basalt fibre and Into the second screen (302) is formed by aramid fiber braiding.
- 7. a kind of flexible protective structure based on high-performance fiber fabric and foam according to claim 6, its feature exist In：The braiding number of plies of first screen (301) is set to three layers, and the braiding number of plies of the second screen (302) is set to two layers.
- 8. a kind of flexible protective structure based on high-performance fiber fabric and foam according to claim 6, its feature exist In：The fibre density of the basalt fibre is not more than 2.7g/cm3, the fiber stretch modulus of basalt fibre is not less than 70GPa, the tensile strength of fiber of basalt fibre are not less than 2100MPa, and the woven surface density of basalt fibre is not more than 0.04g/cm2。
- 9. a kind of flexible protective structure based on high-performance fiber fabric and foam according to claim 1, its feature exist In：Wall (4) uses platy structure after described, and rear wall (4) is formed by aramid fiber or kevlar fiber braiding, the volume of rear wall (4) Tissue layer number is no less than Floor 12.
- 10. a kind of flexible protective structure based on high-performance fiber fabric and foam according to claim 9, its feature exist In：The fibre density of the aramid fiber or kevlar fiber is no more than 1.5g/cm3, aramid fiber or kevlar fiber Fiber stretch modulus is not less than 80GPa, and the tensile strength of fiber of aramid fiber or kevlar fiber is not less than 3600MPa, The woven surface density of aramid fiber or kevlar fiber is no more than 0.03g/cm2。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710532861.8A CN107697319B (en) | 2017-07-03 | 2017-07-03 | A kind of flexible protective structure based on high-performance fiber fabric and foam |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710532861.8A CN107697319B (en) | 2017-07-03 | 2017-07-03 | A kind of flexible protective structure based on high-performance fiber fabric and foam |
Publications (2)
| Publication Number | Publication Date |
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| CN107697319A true CN107697319A (en) | 2018-02-16 |
| CN107697319B CN107697319B (en) | 2019-10-22 |
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| CN201710532861.8A Active CN107697319B (en) | 2017-07-03 | 2017-07-03 | A kind of flexible protective structure based on high-performance fiber fabric and foam |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109455315A (en) * | 2018-09-28 | 2019-03-12 | 北京空间机电研究所 | A kind of space junk and bullet block protective device and system |
| CN110155375A (en) * | 2018-10-26 | 2019-08-23 | 北京机电工程研究所 | Space debris prevention structure |
| CN111268179A (en) * | 2020-02-24 | 2020-06-12 | 四川航天系统工程研究所 | Protective structure for lunar surface living cabin body |
| 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 |
| CN114455099A (en) * | 2022-01-11 | 2022-05-10 | 航天科工空间工程发展有限公司 | Space debris protection structure for spacecraft and preparation method thereof |
| CN114476130A (en) * | 2022-02-09 | 2022-05-13 | 航天科工空间工程发展有限公司 | Resistance mechanics enhancing accessory for space flexible unfolding structure |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023137082A1 (en) * | 2022-01-11 | 2023-07-20 | WildStar, LLC | Space debris capture apparatus and methods for implenting the same |
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| CN105659754B (en) * | 2011-12-09 | 2014-08-13 | 北京空间飞行器总体设计部 | A kind of filled type Whipple safeguard structure and preparation method based on silicon carbide fibre fabric |
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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 |
| CN105659754B (en) * | 2011-12-09 | 2014-08-13 | 北京空间飞行器总体设计部 | A kind of filled type Whipple safeguard structure and preparation method based on silicon carbide fibre fabric |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109455315A (en) * | 2018-09-28 | 2019-03-12 | 北京空间机电研究所 | A kind of space junk and bullet block protective device and system |
| CN110155375A (en) * | 2018-10-26 | 2019-08-23 | 北京机电工程研究所 | Space debris prevention structure |
| CN111268179A (en) * | 2020-02-24 | 2020-06-12 | 四川航天系统工程研究所 | Protective structure for lunar surface living cabin body |
| CN111268179B (en) * | 2020-02-24 | 2021-11-09 | 四川航天系统工程研究所 | Protective structure for lunar surface living cabin body |
| 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 |
| CN114455099A (en) * | 2022-01-11 | 2022-05-10 | 航天科工空间工程发展有限公司 | Space debris protection structure for spacecraft and preparation method thereof |
| CN114476130A (en) * | 2022-02-09 | 2022-05-13 | 航天科工空间工程发展有限公司 | Resistance mechanics enhancing accessory for space flexible unfolding structure |
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| Publication number | Publication date |
|---|---|
| CN107697319B (en) | 2019-10-22 |
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