CN107140238B - Kinetic energy efficient dissipation protective screen - Google Patents
Kinetic energy efficient dissipation protective screen Download PDFInfo
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- CN107140238B CN107140238B CN201710316128.2A CN201710316128A CN107140238B CN 107140238 B CN107140238 B CN 107140238B CN 201710316128 A CN201710316128 A CN 201710316128A CN 107140238 B CN107140238 B CN 107140238B
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- 230000001681 protective effect Effects 0.000 title claims abstract description 41
- 239000000463 material Substances 0.000 claims abstract description 39
- 239000011148 porous material Substances 0.000 claims abstract description 18
- 239000012634 fragment Substances 0.000 claims abstract description 10
- 239000006260 foam Substances 0.000 claims abstract description 6
- 239000000956 alloy Substances 0.000 claims abstract description 5
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 4
- 230000001413 cellular effect Effects 0.000 claims abstract description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 13
- 238000005096 rolling process Methods 0.000 claims description 11
- 229910052782 aluminium Inorganic materials 0.000 claims description 9
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 9
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 7
- 229910000861 Mg alloy Inorganic materials 0.000 claims description 6
- 229920005830 Polyurethane Foam Polymers 0.000 claims description 6
- 239000011496 polyurethane foam Substances 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 5
- 230000035939 shock Effects 0.000 claims description 5
- 238000005728 strengthening Methods 0.000 claims description 4
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 claims description 3
- 239000011777 magnesium Substances 0.000 claims description 3
- 229910052749 magnesium Inorganic materials 0.000 claims description 3
- 238000007745 plasma electrolytic oxidation reaction Methods 0.000 claims description 3
- 238000013329 compounding Methods 0.000 claims description 2
- 230000010354 integration Effects 0.000 abstract description 2
- 238000010438 heat treatment Methods 0.000 description 6
- 229910001094 6061 aluminium alloy Inorganic materials 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 3
- 238000005253 cladding Methods 0.000 description 3
- 238000005098 hot rolling Methods 0.000 description 3
- 239000010936 titanium Substances 0.000 description 3
- 229910052719 titanium Inorganic materials 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 238000005422 blasting Methods 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 239000003822 epoxy resin Substances 0.000 description 2
- 229910001234 light alloy Inorganic materials 0.000 description 2
- 229920000647 polyepoxide Polymers 0.000 description 2
- 238000004663 powder metallurgy Methods 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 239000011825 aerospace material Substances 0.000 description 1
- 229910000808 amorphous metal alloy Inorganic materials 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 210000003850 cellular structure Anatomy 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000013467 fragmentation Methods 0.000 description 1
- 238000006062 fragmentation reaction Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000021715 photosynthesis, light harvesting Effects 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
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- 238000005498 polishing Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000004381 surface treatment Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B15/043—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of metal
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
- B32B3/28—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by a layer comprising a deformed thin sheet, i.e. the layer having its entire thickness deformed out of the plane, e.g. corrugated, crumpled
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- Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a kinetic energy high-efficiency dissipation protective screen, which comprises a high-performance wave impedance gradient material, a porous material and a back plate which are sequentially welded or adhered, wherein the high-performance wave impedance gradient material is formed by arranging two or more material components in a sequence from high wave impedance to low wave impedance; the porous material of the second layer has a cellular or foam porous structure and can further absorb the kinetic energy of the fragments; the back plate of the third layer is an alloy back plate, which mainly plays a role in fixing and simultaneously dissipates the kinetic energy of the fragments again. The protective structure has the characteristics of light weight, high integration level, small occupied space, flexible use and the like, can efficiently dissipate and disperse the kinetic energy of space debris, and greatly improves the capacity of resisting the space debris of the spacecraft on the premise of not increasing the weight and the occupied space.
Description
Technical Field
The invention relates to the technical field of space debris protection, in particular to a kinetic energy efficient dissipation space debris protection structure.
Background
The extreme high pressure generated by space debris impact exceeds the yield strength of spacecraft materials by tens to hundreds of times, and can penetrate through the surface of a spacecraft to damage internal devices and systems, so that the function of the spacecraft is seriously damaged, and even the spacecraft is completely disintegrated/explodes to fail.
The material properties have a great influence on the protective capacity of the protective structure. The selection of the spacecraft protection material requires that the spacecraft protection material can effectively break the coming space debris and transmit and dissipate more impact energy of the space debris so as to achieve the purposes of resisting impact and effectively protecting the spacecraft. Compared with the foreign countries, the protection of the spacecraft is greatly different in China due to the limitation of the preparation capacity of the advanced protection material. Some shields improve the crushing capacity of space debris (CN 102514737A, CN 102490912A) by sacrificing surface smoothness and surface allotype treatment, or adopt two-layer or multilayer shield design (CN 102514737A, CN105109709A, CN 103466104A) to resist space debris impact, make the structure become complicated, and occupy a large amount of valuable space resources on the spacecraft.
Due to the harsh requirements of aerospace material engineering application, the development of a kinetic energy high-efficiency dissipation protection structure with the characteristics of low density, simple structure, small volume, flexible application and the like has important significance.
Disclosure of Invention
Aiming at the severe situation of the space debris environment and the urgent need of spacecraft debris protection, the invention provides a novel space debris protection structure with the characteristic of high-efficiency kinetic energy dissipation, and the safety and the reliability of a spacecraft are improved.
The invention takes the limited density of the protective screen as the constraint condition, ensures the lightening of the protective structure, adopts the integrated plane single protective screen structure, reduces the distance between the protective screen and the bulkhead, and releases more usable space.
The invention is realized by adopting the following technical scheme:
the kinetic energy efficient dissipation protective screen comprises high-performance wave impedance gradient materials, porous materials and a back plate which are sequentially welded or adhered, wherein the high-performance wave impedance gradient materials of the first layer are formed by two or more material components which are sequentially arranged from high wave impedance to low wave impedance, the outer surface serving as an impacted surface has the highest wave impedance, space debris is fully crushed, the subsequent low impedance part changes the transmission path and time of shock waves, and the kinetic energy of the debris is fully dispersed and dissipated; the porous material of the second layer has a cellular or foam porous structure and can further absorb the kinetic energy of the fragments; the back plate of the third layer is an alloy back plate, which mainly plays a role in fixing and simultaneously dissipates the kinetic energy of the fragments again.
The high-performance wave impedance gradient material comprises alloy materials such as titanium alloy, aluminum alloy or magnesium alloy.
Wherein the high-performance wave impedance gradient material is prepared by a rolling or powder metallurgy method.
Further, the surface of the high-performance wave impedance gradient material is treated in a surface strengthening treatment mode.
The surface strengthening mode comprises micro-arc oxidation or surface shot blasting, and the hardness and the strength of the windward side of the protective screen are improved.
Wherein the porous material is aluminum honeycomb plate, foamed aluminum, foamed magnesium and/or polyurethane foam.
The back plate is a light alloy back plate made of aluminum alloy or magnesium alloy.
Further, the thickness ranges of the high-performance wave impedance gradient material, the porous material and the back plate are 0.5-2.0mm, 1.5-5.0mm and 0.2-0.5mm respectively.
Further, the constraint of limiting the density of the protective screen ensures that the weight of the protective structure is not increased.
Wherein the surface density of the protective structure is equal to that of the aluminum alloy with the thickness of 1 mm.
The protective structure integrates the high-performance wave impedance gradient material, the porous material and the back plate, is arranged in front of the bulkhead for a certain distance, and can replace a protective screen of a typical aluminum alloy Whipple structure. The protective structure has the characteristics of light weight, high integration level, small occupied space, flexible use and the like, can efficiently dissipate and disperse the kinetic energy of space debris, and greatly improves the capacity of resisting the space debris of the spacecraft on the premise of not increasing the weight and the occupied space. The proposed protective structure guarantees surface planarity, reduces the distance between the protective screen and the bulkhead, frees up more usable space,
drawings
Fig. 1 is a schematic structural diagram of a kinetic energy efficient dissipation space debris protection structure of the invention.
Wherein, 1, high-performance wave impedance gradient material layer; 2. a layer of porous material; 3. a back plate; 4. A bulkhead.
Detailed Description
The following is a description of the present invention, which is further illustrated by the following embodiments. The following detailed description, of course, is merely illustrative of various aspects of the invention and is not to be construed as limiting the scope of the invention.
The kinetic energy high-efficiency dissipation space debris protection structure disclosed by the invention is composed of a protection screen, a space S and a bulkhead 4 as shown in figure 1, and is characterized in that the kinetic energy high-efficiency dissipation protection screen is adopted. The kinetic energy high-efficiency dissipation protective screen is composed of a high-performance wave impedance gradient material 1, a porous material 2 and a back plate 3, the density of the protective screen is limited as a constraint condition, the thicknesses of the high-performance wave impedance gradient material, the porous material and the back plate are optimally designed, and the protective performance is improved while the structure is kept light.
The first layer is a high performance wave impedance gradient material consisting of two or more material components arranged in order of wave impedance from high to low. The impacted surface has the highest wave impedance, the effect of fully crushing space fragments is achieved, the transmission path and time of the shock wave are changed by the subsequent low impedance part, the internal energy conversion of the shock wave is increased, and the initial kinetic energy of the space fragments is dispersed and dissipated. In addition, according to the shockwave principle, when a shockwave propagates from a high-impedance material into a low-impedance material, a shockwave and a rarefaction wave are transmitted and reflected at the interface, respectively. The reflected rarefaction waves can cause further fragmentation and dispersion of the space debris. When the material components are selected, the influence of other space environment effects, such as atomic oxygen, space irradiation and the like, is avoided, and common aerospace metal materials are adopted, such as: titanium alloys, aluminum alloys, magnesium alloys, and the like. The wave impedance gradient material is prepared by rolling or powder metallurgy and other methods. The hardness and the strength of the windward side of the protective screen can be improved by surface strengthening treatment modes such as micro-arc oxidation, surface shot blasting and the like, or ceramics, amorphous alloy and the like can be generated, so that the capacity of crushing space fragments is increased.
The second layer is made of porous material, the material is composed of cellular structure such as honeycomb or foam, and the material can be aluminum honeycomb plate, foamed aluminum, foamed magnesium, polyurethane foam and the like. The loose porous material can play a buffering role, change a shock wave transmission path again, increase the transmission time and improve the crushing degree of space fragments. Meanwhile, as the porous material is subjected to large-scale plastic deformation, a large amount of heat is accumulated to melt or even gasify the material, so that kinetic energy is converted into internal energy, and the effect of dissipating the kinetic energy is achieved. It can be bonded to the low impedance surface of the first layer of wave impedance gradient material by welding or adhesion.
The third layer is a back plate and plays a role in fixing, so that the protective screen can keep higher integrity after being impacted. But also can play a role in blocking space debris again and improving the protective performance. Light alloy such as aluminum alloy or magnesium alloy can be used as the back plate. And combining the porous material with the second layer of porous material in a welding or adhering mode to form an integrated protective screen structure.
After the protective screen is formed, the protective screen is placed in front of a bulkhead (or important parts such as components, pipelines and subsystems needing protection) at a certain distance, and the distance can be optimized and adjusted according to actual engineering application conditions and aiming at different spacecrafts and different parts.
Example (b):
the protective structure comprises:
a first layer: TC4 titanium alloy with the thickness of 0.3mm and 6061 aluminum alloy with the thickness of 0.2 mm;
a second layer: 1.7mm PR-6710 polyurethane foam;
and a third layer: 0.2mm thick 6061 aluminum alloy.
The first layer is made of TC4 titanium alloy (4.17g/cm3) and 6061 aluminum alloy (2.69g/cm3) into a wave impedance gradient material by a rolling composite method, the second layer of polyurethane foam is adhered to a low impedance surface of the wave impedance gradient material by a two-component epoxy resin adhesive, and the third layer of aluminum alloy is adhered to the polyurethane foam by the two-component epoxy resin adhesive to finally form the kinetic energy efficient dissipation protective screen.
The surface density of the prepared protective screen is equal to that of aluminum alloy with the thickness of 1mm, and the distance between the protective screen and the bulkhead is 100 mm. Through verification, compared with the traditional aluminum alloy Whipple structure, the protective performance of the structure is greatly improved at 3.5-6.5 km/s.
The rolling preparation process and parameters of the wave impedance gradient material are as follows:
the plate is cut into the specification of 100mm × 100mm, the compounded surface is polished by a steel brush, then TC4 titanium alloy (4.17g/cm3) with the thickness of 0.3mm and 6061 aluminum alloy (2.69g/cm3) with the thickness of 0.2mm are stacked, four corners are riveted, and then the plate is placed into a heating furnace for heating.
(1) Surface treatment: the oxide film on the surface of the titanium alloy and the aluminum alloy is disadvantageous to the roll-cladding, and therefore, the oxide film on the surface thereof needs to be removed before the roll-cladding. In this embodiment, the surface oxide film is removed by mechanical polishing, and then the surface is rinsed with alcohol or the like.
(2) Riveting: during the roll cladding process, the surface may be re-oxidized due to differences in the mechanical properties (deformation resistance, plasticity and elongation) of titanium and aluminum, and during hot rolling. Therefore, the plates need to be riveted, and one purpose is to fix the two plates, so that the plates are easy to bite in the rolling process, and the rolled piece is prevented from being dislocated in the rolling process; another object is to prevent the treated surface from re-oxidizing.
(3) Heating: the purpose of the heating is to reduce the deformation resistance and improve the bonding performance of the composite panel. The temperature used in this example is 420-460 ℃ and the heating time is 15-30 min.
(4) Hot rolling and compounding: and heating the riveted titanium/aluminum plate sample, preserving heat for a certain time, taking out, and sending the titanium/aluminum plate sample into a roll gap for rolling to generate a certain reduction. The parameters of the two-roll mill in the hot rolling process are as follows: roller for rolling
The rolling speed is 0.2-0.6 m/s; the maximum rolling force is 100 t.
Although particular embodiments of the present invention have been described and illustrated in detail, it should be understood that various equivalent changes and modifications can be made by those skilled in the art without departing from the spirit of the invention, and that the resulting functional effects are within the scope of the invention as defined by the appended claims and drawings.
Claims (6)
1. The kinetic energy efficient dissipation protective screen comprises a planar high-performance wave impedance gradient material, a porous material and a back plate which are sequentially welded or adhered, wherein the high-performance wave impedance gradient material of the first layer is prepared by rolling and compounding two or more material components, the wave impedances are sequentially arranged from high to low, the outer surface as an impacted surface has the highest wave impedance, space debris is fully crushed, the subsequent low impedance part changes the transmission path and time of shock waves, and the kinetic energy of the debris is fully dispersed and dissipated; the porous material of the second layer has a cellular or foam porous structure and can further absorb the kinetic energy of the fragments; the back plate of the third layer is an alloy back plate which mainly plays a role in fixing and simultaneously dissipates the kinetic energy of fragments again, and the high-performance wave impedance gradient material comprises titanium alloy, aluminum alloy or magnesium alloy; and the weight of the protective structure is not increased by taking the limited density of the protective screen as a constraint condition, wherein the surface density of the protective structure is equal to that of the aluminum alloy with the thickness of 1 mm.
2. The kinetic energy efficient dissipation shield of claim 1, wherein the high performance wave impedance gradient material has its surface treated by surface strengthening treatment.
3. The kinetic energy high efficiency dissipative protective shield of claim 2, wherein the surface enhancement comprises micro-arc oxidation or surface peening to increase the stiffness and strength of the windward side of the shield.
4. The kinetic energy high efficiency dissipative protective shield of any of claims 1 to 3, wherein the cellular material is aluminum honeycomb, aluminum foam, magnesium foam, or polyurethane foam.
5. The kinetic energy efficient dissipation shield of claim 1, wherein the back plate is a lightweight alloy back plate of aluminum alloy or magnesium alloy.
6. The kinetic energy high efficiency dissipative protective shield of any of claims 1 to 3, wherein the thickness of the high performance wave impedance gradient material, the porous material, and the backing plate ranges from 0.5 to 2.0mm, 1.5 to 5.0mm, and 0.2 to 0.5mm, respectively.
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| CN201710316128.2A CN107140238B (en) | 2017-05-08 | 2017-05-08 | Kinetic energy efficient dissipation protective screen |
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| CN201710316128.2A CN107140238B (en) | 2017-05-08 | 2017-05-08 | Kinetic energy efficient dissipation protective screen |
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| CN107140238B true CN107140238B (en) | 2020-07-28 |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109131947B (en) * | 2018-08-16 | 2020-04-14 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ultra-high-speed impact protection device and method |
| CN110155375B (en) * | 2018-10-26 | 2020-08-21 | 北京机电工程研究所 | Space debris protective structure |
| CN109822293B (en) * | 2019-02-19 | 2021-07-02 | 西安建筑科技大学 | Preparation method of gradient material along thickness direction and application of magnesium alloy |
| US12103702B2 (en) | 2019-10-15 | 2024-10-01 | General Electric Company | Removeable fuselage shield for an aircraft |
| CN111645884B (en) * | 2020-06-17 | 2021-11-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Frame honeycomb structure, honeycomb sandwich structure and fiber filling type protection configuration |
| CN113212809B (en) * | 2021-04-22 | 2022-09-27 | 上海空间电源研究所 | On-orbit dissipative vibration friction protection method for transmitting active section |
| CN113401372A (en) * | 2021-06-22 | 2021-09-17 | 北京宇航系统工程研究所 | Impact reduction separation structure suitable for initiating explosive device |
| CN113636109B (en) * | 2021-08-30 | 2023-04-21 | 北京卫星环境工程研究所 | Filling type protection structure design method for spacecraft |
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| CN1902046A (en) * | 2004-01-19 | 2007-01-24 | 伊兰科有限公司 | High impact strength, elastic, composite, fibre, metal laminate |
| CN101603799A (en) * | 2009-07-03 | 2009-12-16 | 中国科学院力学研究所 | Novel protective structure of gradient composite space |
| CN102490912A (en) * | 2011-11-08 | 2012-06-13 | 西安交通大学 | Space debris prevention structure of spacecraft |
| CN102514737A (en) * | 2011-11-08 | 2012-06-27 | 西安交通大学 | Lightweight filled composite protective structure for space debris |
| CN104029827A (en) * | 2014-06-13 | 2014-09-10 | 南京理工大学 | Fiber rod filling corrugated sandwich structure |
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2017
- 2017-05-08 CN CN201710316128.2A patent/CN107140238B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1902046A (en) * | 2004-01-19 | 2007-01-24 | 伊兰科有限公司 | High impact strength, elastic, composite, fibre, metal laminate |
| CN101603799A (en) * | 2009-07-03 | 2009-12-16 | 中国科学院力学研究所 | Novel protective structure of gradient composite space |
| CN102490912A (en) * | 2011-11-08 | 2012-06-13 | 西安交通大学 | Space debris prevention structure of spacecraft |
| CN102514737A (en) * | 2011-11-08 | 2012-06-27 | 西安交通大学 | Lightweight filled composite protective structure for space debris |
| CN104029827A (en) * | 2014-06-13 | 2014-09-10 | 南京理工大学 | Fiber rod filling corrugated sandwich structure |
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