CN110920938A - Space flight vehicle structure with ultra-light, large expansion ratio and ultra-low temperature working environment - Google Patents
Space flight vehicle structure with ultra-light, large expansion ratio and ultra-low temperature working environment Download PDFInfo
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- CN110920938A CN110920938A CN201911166605.7A CN201911166605A CN110920938A CN 110920938 A CN110920938 A CN 110920938A CN 201911166605 A CN201911166605 A CN 201911166605A CN 110920938 A CN110920938 A CN 110920938A
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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
- B64G1/58—Thermal protection, e.g. heat shields
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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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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Abstract
The patent discloses an ultralight, big expansion ratio, ultra-low temperature operational environment's space shuttle structure, this structure is aerifyd the expansion from rigidizing layer and is laminated film cover, light structural slab, the flexible loop bar between layer, telescope tube, organic fiber net, multiunit accuse pressure valve including the multilayer. Aiming at the problem that the mass, the size and the effect of a heat-proof structure on a spacecraft conflict with each other to limit the application of extreme materials with temperature requirements on the spacecraft in a large quantity, the structure of the large-scale ultralow-temperature heat-proof structure which is a multilayer film cover structure after being unfolded utilizes the space unfolding structure and the self-rigidization principle to control a pressure control valve group to inflate, maintain pressure and deflate according to a certain sequence, and the pressure control valve group is matched with local gravity and a telescopic sleeve rod to realize unfolding and shaping. The structure is large in expansion ratio, simple in modeling and extremely light in weight, and the ultralow-temperature heat-proof performance can be guaranteed and the pressure of a carrying system can be reduced.
Description
Technical Field
The invention relates to an ultralow-temperature heat-proof structure, which is an ultralow-weight large-expansion-ratio aerospace craft heat-proof structure capable of providing medium and short-term stable ultralow temperature in a vacuum environment.
Background
In the current fields of advanced scientific research and application such as superconduction, magnetic suspension and the like, the requirements of the use of related equipment and materials on the environment temperature are high, wherein the environment temperature requirement of a superconducting element is lower than the critical temperature 77K of high-temperature superconduction, the temperature requirement is extreme, and the requirement on an ultralow-temperature heat-proof technology is high. Ultra-low temperature heat protection technology generally depends on methods such as vacuum heat insulation, radiation reduction of a heat shield, multi-layer heat insulation components and the like. The conventional heat-proof device is made of metal or composite material with high strength and excellent low-temperature adaptability, represents a Dewar flask, and has small size, heavy weight and high manufacturing cost; the ultralow temperature environment of the experimental place is basically designed by adopting a multilayer structure, the ultralow temperature environment is realized by liquid gas such as liquid nitrogen or the like or by utilizing the vaporization latent heat of gas such as nitrogen, helium and the like and assisted by a refrigerator, a spacer exists between the inner container and the shell, so that the heat insulation effect is not ideal, the defects of high cost, large structural mass and the like are overcome, and the defects of the low temperature environment realized by the method are further highlighted when the required space for the experiment is large and the time is long. The defects of large mass and high cost of the system generate great pressure on a launching and propelling system, and limit the application and realization of the existing ultralow-temperature heat protection device on space vehicles such as spacecrafts, so that a great deal of use of superconducting materials and other materials with extreme temperature requirements in the space environment faces great difficulty.
The space inflation unfolding structure is made of flexible materials (films or coated fabrics), the structure shape is unfolded along with the internal pressure through inflation, and the space inflation unfolding structure can be folded and packaged before launching and lifting, so that the launching volume is greatly saved; after entering the track, the track is unfolded through inflation, and then a forming and curing technology is carried out to ensure that the track has sufficient strength and rigidity. The space inflation unfolding structure breaks through the size and mass limitations of the traditional mechanical unfolding structure, has the advantages of strong designability, simple structure, small launching volume, large expansion ratio, light weight, low cost and the like, and can effectively solve the launching and unfolding problems of the large-scale spacecraft structure.
This patent is based on space inflation development technique, combines traditional heat protection principle, explains one kind and can provide the super low temperature of short-term stability under the vacuum environment big scaling ratio space craft heat protection structure of ultralight.
Disclosure of Invention
1. Objects of the invention
In order to overcome the defects of large mass, small modeling, high cost and the like of the existing ultralow-temperature heat-proof structure, a reliable temperature environment is provided for components with extreme temperature requirements such as superconducting elements on a spacecraft, the aerospace craft structure of the ultralow-temperature working environment of the patent utilizes the advantages of light mass, large expansion ratio and the like of a space inflation expansion structure and the advantages of the external vacuum environment of the aerospace craft, the heat-proof efficiency is improved by constructing a shell, a heat shield plate and an inner container through expansion and solidification of a thin film structure, and large, light, medium and short-term ultralow-temperature experiments and working environments can be provided on the aerospace craft.
2. Technical scheme
This patent can be realized through following technical scheme: the device comprises a multi-layer inflatable self-rigidizing laminated film cover, a light structural plate, an interlayer telescopic sleeve rod, a telescopic sleeve, an organic fiber net and a pressure control valve group.
The whole structure of the aerospace craft in the ultra-light, large-expansion-ratio and ultra-low temperature working environment is represented as a multilayer spherical shell which is symmetrical around a central shaft.
The multilayer inflatable expandable curable film cover is a main heat-proof structure, has three layers in total, and is made of Kapton-Al-Kapton (polyimide-aluminum foil-polyimide) laminated films, the inner surface and the outer surface of each layer of cover are respectively coated with a coating type heat-proof coating, the cover is in a folded state after being launched along with an arrow and before reaching a space designated position, gas is injected layer by layer from inside to outside after the cover is stably placed in a track to realize expansion, the cover is cured and shaped by utilizing the self-rigidifying capacity of the laminated films, the cover is represented as a multilayer spherical shell, the film cover sequentially plays the roles of a shell, a heat shielding plate and an inner container from outside to inside, and the heat-proof coatings are coated on the inner surface and the outer surface of each. Each layer of film cover is sequentially connected with the corresponding telescopic rod section and the telescopic sleeve section through a small sandwich type flange structure, and the innermost film cover is connected with the edge of the central light structure circular plate through a flange structure. After the space part between each layer of film cover is unfolded and shaped, the vacuum degree which is the same as that of the external environment is achieved through the pressure control valve on the sleeve, and the heat-proof capacity is maximized. A certain amount of gas is reserved between the innermost film cover and the light structure plate, initial low temperature is provided, heat is stored in the temperature rising process, the heat-proof pressure of the film is shared, and the temperature rising can be effectively slowed down. And the space formed between the innermost film cover and the light-weight structural plate is used as an experiment or working environment of the target component.
The light structure plate is designed by adopting a honeycomb aluminum plate structure, the plate is provided with vent holes to ensure the gas circulation of an upper space and a lower space formed by the plate and the innermost film cover, and the lower surface of the plate is connected with an organic fiber net in an annular area concentric with the plate to transfer load. The light structural plate is used as a layout substrate of an experimental device or a superconducting element, the normal direction of the plate is required to be coincident with the gravity direction during installation, the total structural mass can be effectively controlled, and meanwhile, the light structural plate has certain rigidity and can bear corresponding loads.
The telescopic loop bars are composed of polyimide organic plastics with good heat insulation performance and low-temperature adaptability, four groups are provided, the four groups are evenly distributed along the outer side circumference of the light structural slab, and each group is composed of a thin hollow bar and a thick hollow cylinder. The four groups of telescopic rods are unfolded in a spring mechanical opening mode, the relative positions of the film covers are controlled after the film covers are unfolded and shaped, the phenomenon that the heat-proof function is lost due to direct contact of the film covers caused by external disturbance or self disturbance of an aircraft is avoided, and the telescopic rods do not bear force.
The sleeve group is made of the same material as the telescopic loop bar, and is a control component at the bottom relative position among all layers of film covers, and one of the main force bearing and force transmission components. The sleeve is opened in a passive automatic unfolding mode along with gravity, a base point is provided for the unfolding of each layer of film covers, meanwhile, pressure control valves are embedded in the side wall of the sleeve group and the upper and lower sealing plates, and gas is conveyed between each layer of film covers through the opening and closing of the pressure control valves, so that the unfolding and solidification of the film covers and the exhaust between the covers are realized. The base section of the sleeve group is used as a substrate to be connected with the spacecraft.
The organic fiber net is connected with the light structure plate and the upper closing plate of the sleeve group, and the organic fiber net and the sleeve group are used as a force transmission path to transmit the structure load to the spacecraft body. The organic fiber net material is made of organic fibers with high strength, low density and low thermal conductivity, the weaving mode of the fiber net needs to ensure that the organic fiber net has excellent mechanical and thermal insulation properties, the fiber net can play a role of bearing force and simultaneously the solid heat conduction from the innermost film cover to the light structure plate can not be increased, and the integral quality of the structure is prevented from being increased.
3. Advantageous effects
This patent compares with the traditional heat protection structure of spacecraft, need not carry refrigeration or heating equipment in the working process, can provide stable operational environment temperature for superconducting components and parts in the short and medium term under the extremely low condition of initial temperature, and the heat protection is effectual, and temperature variation is slow, and the characteristics of make full use of space environment vacuum can adapt to the temperature demand of multiple other types after the appropriate adjustment. The heat-proof structure in this patent utilizes the design idea that the space expanded the structure, simple structure, and is with low costs, and the quality is light, and the scaling ratio is big, and designability is strong, has practiced thrift the delivery space and has alleviateed transmitting system's pressure.
Drawings
The patent is further described below with reference to the accompanying drawings.
FIG. 1 is a schematic structural diagram of the general structure of an aerospace vehicle.
FIG. 2 is a schematic view of the structure of the aerospace vehicle in an undeployed state.
Fig. 3 is a schematic view taken along the plane H-H in fig. 1.
Fig. 4 is a detailed view of the telescoping rod section numbered 6 in fig. 1.
Fig. 5 is a detail view of the telescopic sleeve region numbered 7 in fig. 1.
See fig. 1, 1 is an inner laminated film cover, 2 is a middle laminated film cover, 3 is an outer laminated film cover, 4 is an aluminum honeycomb plate with a through hole, 5 is a conical organic fiber net, 6 is a telescopic sleeve rod group, 7 is a telescopic sleeve group, 8 is a working space formed by the inner laminated film cover and the aluminum honeycomb plate, 9 is a cavity formed by the inner laminated film cover and the middle laminated film cover, and 10 is a cavity formed by the middle laminated film cover and the outer laminated film cover.
See fig. 3 and 11 are flange connecting bolts of the inner laminated film cover and the edge of the aluminum honeycomb plate.
See fig. 4, 12 is a flange connection block of the inner laminated film cover, 13 is an inner flange cover, 14 is a telescopic rod hollow cylinder section, 15 is a telescopic rod hollow section fixing bolt group, 16 is an internal spring, 17 is a flange connection block of the middle laminated film cover, 18 is a middle flange cover, 19 is a middle flange bolt group, 20 is a telescopic rod hollow rod section, 21 is a flange connection block of the outer laminated film cover, 22 is an outer flange cover, and 23 is an outer flange bolt group.
Referring to fig. 5, 24 is an upper closing plate, 25 is an upper closing plate pressure control valve group, 26 is a flange connection bolt group of the upper closing plate and an outer sleeve, 27 is an outer sleeve side wall pressure control valve group, 28 is an outer sleeve, 29 is a flange connection bolt group of an inner sleeve and an outer sleeve, 30 is an outer sleeve flange cover, 31 is an inner sleeve side wall pressure control valve group, 32 is an inner sleeve, 33 is a base section upper pressure control valve group, 34 is a flange connection bolt group of the inner sleeve and a base section, 35 is a base section side wall pressure control valve group, 36 is a base section, and 37 is a connection bolt group of the base section and the aircraft.
Detailed Description
The laminated film covers 1, 2 and 3 are thin-wall spherical shells after being unfolded, the laminated film cover 1 is made into a flange connecting block 12 at the tail end connecting part, the flange connecting block 12 is made of the same material as the organic plastic film part of the laminated film cover 1 and is integrated with the laminated film cover 1, the flange edge of the aluminum honeycomb plate 4, the flange connecting block 12 and an inner flange cover 13 form sandwich type flange connection and are fastened by flange connecting bolts 11 penetrating through three parts, the flange connecting bolts 11 are uniformly arranged along the edge circumference of the aluminum honeycomb plate 4, the number of the bolts, the materials and the sizes are selected according to requirements, and the air tightness of the sandwich type flange connection is ensured.
Similarly, the laminated film covers 2 and 3 are respectively connected with the flanges of the telescopic rod hollow cylinder section 14 and the telescopic rod hollow rod section 20, and the laminated film covers 1, 2 and 3 are respectively connected with the flanges of the closing plate 24, the outer sleeve 28, the inner sleeve 32 and the base section 36 by adopting a sandwich type flange connection structure. The number of the components related to each group of sandwich type flange connection in the telescopic loop bar area 6 can be recorded as (14, 17, 18), (20, 21, 22) according to the form of (flange edge, flange connection block at the tail end of the laminated film cover, flange cover), the corresponding flange connection bolts are bolts 19 and 23 in sequence, the flange connection bolts are uniformly distributed in the circumferential direction around the axes of the telescopic rod hollow cylinder section 14 and the hollow rod section 20, and the number, the material and the size of the bolts are selected according to specific requirements. By the same method, the number of the components related to each group of sandwich type flange connection in the telescopic sleeve region 7 is marked as (24, 12, 28), (28, 17, 30), (32, 21, 36), the corresponding flange connection bolts are bolts 26, 29, 34 in sequence, the flange connection bolts are circumferentially and uniformly distributed around the symmetric axis of the sleeve, and the number, the material and the size of the bolts are selected according to specific requirements. Simple structure and strong designability.
The size of aluminum honeycomb panel 4 needs and the size cooperation of lamination film cover 1, provides the flange reason for sandwich type flange joint at the edge, distributes the even air vent of multiunit circumference on the board, and the lower surface has boss and organic fiber net cooperation, and the normal direction of board is whole symmetry axis direction promptly and needs and the direction of gravity, avoids the too big stability that disturbs overall structure of side load. The upper and lower panels and core dimensions of the honeycomb panel may be selected according to specific load requirements.
The telescopic loop bar group 6 comprises four groups of telescopic loop bars which are evenly distributed along the circumferential direction of a symmetrical shaft of the whole structure, and each group of telescopic loop bars is divided into a telescopic link hollow cylinder section 14 and a telescopic link hollow bar section 20. One end of the hollow cylinder section 14 is inserted into a hole formed by the aluminum honeycomb panel 4 and the inner flange cover 13, the bolt group 15 distributed circumferentially around the axis of the hollow cylinder section 14 is fixed on the inner flange cover 13, a spring 16 is arranged in a hollow cavity of the hollow cylinder section 14 and serves as an expansion device of the telescopic sleeve rod, the outer diameter of each section of the telescopic rod hollow rod section 20 is respectively matched with the inner diameter of the hollow cylinder section 14 and the inner flange cover 18, the inner diameter of the hollow rod section 20 can be freely designed according to the requirement of the whole weight, and the telescopic sleeve rod is not of a force bearing structure. If the weight requirement is rich, the telescopic sleeve rod can be made into a solid rod without segmentation.
The main components of the telescopic sleeve group 7 are an upper closing plate 24, an outer sleeve 28, an inner sleeve 32 and a base section 36, the upper closing plate 24 is inlaid with a pressure control valve group 25, the middle side wall of the outer sleeve 28 is inlaid with a pressure control valve group 27, the middle side wall of the inner sleeve 32 is inlaid with a pressure control valve group 31, the middle parts of the upper plate and the side wall of the base section 36 are inlaid with pressure control valve groups 33 and 25 respectively, the pressure control valve groups are distributed circumferentially around a symmetry axis, the types and the number sizes of the pressure control valves need to be selected according to specific target requirements, and the pressure control valves are required to be as simple and light as possible. The inner and outer diameter dimensions of the inner and outer sleeves need to be matched with each other, and the bottom connecting bolt of the base section 36 is matched with the main body of the spacecraft, so that other types of connecting structures can be changed.
The organic fiber web 5 has various design methods, can be replaced by various structures such as mechanical unfolding and shape memory material unfolding, and can meet specific bearing requirements, quality requirements and heat insulation requirements.
The film covers 1, 2 and 3 are made of Kapton-Al-Kapton (polyimide-aluminum foil-polyimide) laminated films, the inner surface and the outer surface of each film cover are covered with coating type thermal control coatings, the thickness of each layer of material of the inner laminated film cover 1 can be selected according to the pressure requirement of a working space 8 and the load requirement of a carrier rocket, the radiation characteristic types of the inner thermal control coating and the outer thermal control coating of each laminated film cover are selected according to the heat preservation requirement of the working space 8 and the radiation intensity of an external space, when the working space 8 provides an ultralow temperature working environment for the superconducting element, the outer surface of the laminated film cover selects ZKS white paint as a thermal control coating, and the inner surface selects S781 aluminum powder paint as a thermal control coating.
The materials of the telescopic rod group, the sleeve group and the organic fiber net need to be selected from polyimide organic plastics with the characteristics of low heat conductivity, strong mechanical property, strong low-temperature adaptability, light density and the like.
Before reaching the appointed track position, the ultralow temperature heat-proof structure is folded, the sleeve group 7 and the telescopic loop bar 6 are folded, the spring 16 is compressed, the film covers 1, 2 and 3 are folded on the upper surface and the lower surface of the aluminum honeycomb plate 4 in a folding mode similar to an umbrella, the fiber net 5 is folded inside, and the ultralow temperature heat-proof structure is placed in a liquid helium or liquid nitrogen environment cabin. After the target track position is reached, firstly, injecting low-temperature gas reaching the yield pressure of the film cover 1 into the working space 8 according to the paths of the pressure control valve groups 33 and 25, realizing the complete unfolding of the film cover 1, the organic fiber net 5 and the sleeve group 7 under the combined action of gravity, maintaining the pressure of the working space 8 until the film cover 1 is solidified and molded, and then unloading to the target pressure; secondly, gas reaching the yield pressure of the film cover 2 is injected into the cavity 9 according to the paths of the pressure control valve groups 33 and 27, the film cover 2 is unfolded, and the pressure of the cavity 9 is maintained until the film cover 2 is solidified and molded; thirdly, gas reaching the yield pressure of the film cover 3 is injected into the cavity 10 according to the paths of the pressure control valve groups 33 and 31, the film cover 3 is unfolded, and the pressure of the cavity 10 is maintained until the film cover 3 is solidified and molded; finally, according to the paths of the pressure control valve groups 27, 33, 35 and 31, 35, the gas in the cavities 10, 9 is discharged in sequence, the vacuum degree equal to the external vacuum degree is required to be achieved, the pressure control valve 25 maintains the pressure of the working space at a target value, the expansion process is realized, the weight of the heat protection system is reduced to the maximum extent while the large-size working space 8 is constructed, the heat exchange among the film covers is almost completely realized in a radiation mode, the heat transfer among the entities is reduced to the minimum, the effect of providing a stable ultralow temperature environment in a large space and in a short period for target components in the vacuum environment of the spacecraft is achieved without carrying any refrigerating or heating equipment.
Claims (4)
1. The utility model provides an ultralight, big expansion ratio, ultra-low temperature operational environment's space shuttle structure, aerifys expansion self-rigidization layer and laminates film cover, light structural slab, flexible loop bar between layer, telescope tube, organic fiber net, multiunit accuse pressure valve, its characterized in that including the multilayer: aiming at the problem that the mass, the size of a heat-insulating space and the heat-insulating effect of the ultra-low temperature heat-insulating device on the spacecraft conflict with each other so as to limit the great application of extreme materials with temperature requirements such as superconducting components and the like on the spacecraft, the large ultra-low temperature heat-insulating structure which is expressed as a multi-layer film cover structure after being unfolded is constructed, and the space unfolding structure and the self-rigidifying principle are utilized, the pressure control valve group is controlled according to a certain sequence to inflate, maintain pressure and deflate the space between the self-rigidifying multi-layer laminated film covers, the expansion and the shaping of each layer of film-combined cover are realized by matching with the local gravity and the telescopic loop bar, so that the cavity between each layer of film-combined cover reaches the vacuum degree which is the same as the external space environment, the heat exchange between the inner layer and the outer layer of film-combined cover is reduced to the maximum extent, the stable ultralow temperature environment can be provided for temperature-demand extreme devices such as superconducting elements and the like in a medium-short period under a vacuum environment under the condition that refrigeration or heating equipment is not carried; the aerospace craft structure of the ultralow temperature working environment is stored in low temperature environments such as liquid nitrogen or liquid helium before being launched, and enters a working state after being unfolded and shaped, the expected position is suspended outside the aerospace craft and does not conflict with other loads on the aerospace craft, a working space of a service object is provided by a cavity formed by an innermost laminated film cover and a light structural plate after being unfolded, the occupied space before the device is unfolded is small, the expansion ratio is large, the unfolded laminated film cover has certain strength and rigidity, the aerospace craft structure is simple in structure and light in overall mass, the aerospace craft structure is convenient to carry and launch, and the pressure of a carrying and power system can be reduced while the ultralow temperature heat-proof performance is ensured.
2. The ultra-light, high-aspect-ratio, ultra-low temperature operating environment aerospace vehicle structure of claim 1, wherein: the multilayer inflatable unfolding self-rigidizing laminated film cover is made of Kapton-Al-Kapton (polyimide-aluminum foil-polyimide) laminated films, the inner surface and the outer surface of each layer of film cover are covered with coating type thermal control coatings, the tail end of each laminated film cover is provided with a connecting block integrated with the film cover, and the connecting block and a light structural plate, an interlayer telescopic sleeve rod or a telescopic sleeve correspond to a structure to form a sandwich type flange connection, so that the tail end of the laminated film cover is ensured to be airtight.
3. The ultra-light, high-aspect-ratio, ultra-low temperature operating environment aerospace vehicle structure of claim 1, wherein: the light structure plate is designed by adopting an aluminum honeycomb plate structure, gas with certain pressure is kept in a cavity formed by the expanded innermost laminated film cover and the light structure plate to store heat, vent holes are formed in the plate to ensure the circulation of the gas in the upper space and the lower space of the plate, and the normal direction (namely the direction of the integral symmetry axis of the device) of the light structure plate is superposed with the direction of local gravity in a working state so as to ensure that the organic fiber net is pulled along the direction of the integral symmetry axis in the working state and prevent the occurrence of lateral load from threatening the structural stability of the device.
4. The ultra-light, high-aspect-ratio, ultra-low temperature operating environment aerospace vehicle structure of claim 1, wherein: the materials of the interlayer telescopic loop bar, the telescopic sleeve and the organic fiber net are selected from polyimide organic plastics with the characteristics of low thermal conductivity, strong mechanical property, strong high-low temperature adaptability, light density and the like.
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| CN201911166605.7A CN110920938A (en) | 2019-11-25 | 2019-11-25 | Space flight vehicle structure with ultra-light, large expansion ratio and ultra-low temperature working environment |
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| CN201911166605.7A CN110920938A (en) | 2019-11-25 | 2019-11-25 | Space flight vehicle structure with ultra-light, large expansion ratio and ultra-low temperature working environment |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111645885A (en) * | 2020-05-27 | 2020-09-11 | 上海卫星工程研究所 | Method and structure for installing and fixing high-temperature heat shield |
| CN112498749A (en) * | 2020-10-30 | 2021-03-16 | 北京空间机电研究所 | Flexible deployable active defense device |
| CN113022892A (en) * | 2021-01-28 | 2021-06-25 | 北京空间飞行器总体设计部 | Airship protection cover capable of being repeatedly unfolded and folded |
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2019
- 2019-11-25 CN CN201911166605.7A patent/CN110920938A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111645885A (en) * | 2020-05-27 | 2020-09-11 | 上海卫星工程研究所 | Method and structure for installing and fixing high-temperature heat shield |
| CN111645885B (en) * | 2020-05-27 | 2021-12-31 | 上海卫星工程研究所 | Method and structure for installing and fixing high-temperature heat shield |
| 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 |
| CN112498749A (en) * | 2020-10-30 | 2021-03-16 | 北京空间机电研究所 | Flexible deployable active defense device |
| CN113022892A (en) * | 2021-01-28 | 2021-06-25 | 北京空间飞行器总体设计部 | Airship protection cover capable of being repeatedly unfolded and folded |
| CN113022892B (en) * | 2021-01-28 | 2022-07-29 | 北京空间飞行器总体设计部 | Airship protection cover capable of being repeatedly unfolded and folded |
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