CN113335534A - Phase-change heat absorption type air charging and exhausting device for passive air charging and exhausting system close to spacecraft - Google Patents
Phase-change heat absorption type air charging and exhausting device for passive air charging and exhausting system close to spacecraft Download PDFInfo
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- CN113335534A CN113335534A CN202110651261.XA CN202110651261A CN113335534A CN 113335534 A CN113335534 A CN 113335534A CN 202110651261 A CN202110651261 A CN 202110651261A CN 113335534 A CN113335534 A CN 113335534A
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- 238000010521 absorption reaction Methods 0.000 title claims abstract description 39
- 238000007599 discharging Methods 0.000 claims abstract description 71
- 239000012782 phase change material Substances 0.000 claims abstract description 29
- 230000008859 change Effects 0.000 claims abstract description 20
- 239000000463 material Substances 0.000 claims description 5
- 239000011358 absorbing material Substances 0.000 claims description 3
- 238000005452 bending Methods 0.000 claims description 3
- 230000014759 maintenance of location Effects 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 238000005192 partition Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 12
- 230000008569 process Effects 0.000 abstract description 8
- 230000009467 reduction Effects 0.000 abstract description 6
- 230000000694 effects Effects 0.000 description 5
- 238000004088 simulation Methods 0.000 description 5
- FZERHIULMFGESH-UHFFFAOYSA-N N-phenylacetamide Chemical compound CC(=O)NC1=CC=CC=C1 FZERHIULMFGESH-UHFFFAOYSA-N 0.000 description 4
- 229960001413 acetanilide Drugs 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000011156 evaluation Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
Abstract
The invention discloses a phase change heat absorption type air charging and discharging device for a passive air charging and discharging system close to a spacecraft. And the phase change material filling area is filled with a heat absorption phase change material to reduce the temperature of air flowing back into the aircraft cabin. The heat absorption capacity of the heat absorption area is further enhanced by integrating the rectification heat conduction of the air inlet grille and the drainage function of the drainage cover shell. The phase-change heat absorption type air charging and exhausting device designed based on the invention can effectively reduce the pressure difference between the inside and the outside of the cabin in the flying process of the aircraft, and meanwhile, the temperature of the backflow high-temperature gas entering the cabin is obviously reduced, and the safety of the aircraft is ensured. The device not only has good comprehensive performance of pressure relief and temperature reduction, but also has simple structure and convenient application, and shows great application prospect in the aerospace field.
Description
Technical Field
The invention belongs to the technical field of aerospace, and particularly relates to a phase change heat absorption type air charging and discharging device for a passive air charging and discharging system of a near space vehicle.
Background
The near space aircraft has the characteristics of ultra-long range, extremely-high speed maneuverability, subversive sudden-prevention survival ability and the like, the aircraft can maneuver and fly in the near space for a long time, the surface of the aircraft is in a pneumatic heating environment with high Mach number, high dynamic pressure and high enthalpy, and the gas in the cabin is quickly heated and pressurized under the action of pneumatic heating heat flow. In addition, the near space aircraft is in power flight in the atmosphere for a long time, in a large airspace and in a wide speed range, and is in the face of an external atmospheric environment which changes rapidly, particularly in the climbing process, the pressure outside the aircraft cabin is reduced rapidly along with the rapid increase of the flight height, the pressure inside the aircraft cabin is increased, and the pressure outside the aircraft cabin is reduced, so that a large pressure difference exists between the inner wall surface and the outer wall surface of the aircraft cabin, and a wave-transmitting shell with low mechanical strength can deform and crack in the serious situation, so that the aircraft fails. For this purpose, charging and discharging systems must be introduced to balance the pressure difference inside and outside the cabin and ensure the safety of the aircraft.
The air charging and exhausting system of the aircraft in the aerospace field can be divided into an active type and a passive type. The active pressure control is mainly realized by adding an air charging and discharging system, an air supply system and a monitoring system in the cabin to adjust the pressure in the cabin in real time. The system has higher control precision, so the system is commonly used for designing manned spacecraft cabin sections and the like sensitive to pressure in the cabin, but the system needs to use more auxiliary equipment, so the complexity of the whole system of the aircraft is higher, and the overall performance of the aircraft is reduced. Compared with an active air charging and discharging system, the passive pressure control system is relatively simple, and air charging and discharging holes are designed at reasonable positions on the surface of the aircraft structure, so that the load of the pressure difference between the inside and the outside of the cabin borne by the structure is reduced. Due to its simple structure and relatively low requirements for the overall structural design of the aircraft, passive inflation and exhaust systems have been widely used in the fairing structural design of launch vehicles.
The passive air charging and discharging system usually adopts a simple open pore structure, although the pressure difference between the inside and the outside of the cabin can be well balanced, the problem that high-temperature air heated by outside air flows back to the cabin exists, and high-temperature failure of instruments in the cabin can be caused in serious cases.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide a phase-change heat absorption type air charging and discharging device for a passive air charging and discharging system close to a space vehicle.
In order to achieve the purpose, the invention adopts the technical scheme that:
a phase change endothermic charging and discharging device for a passive charging and discharging system for a near space vehicle, comprising:
the air inlet grille is used for flattening the air charging/discharging flow and simultaneously increasing the effective heat exchange area of high-temperature gas and the air charging/discharging device, and the air charging/discharging flow enters from one axial end of the air charging/discharging device;
the phase-change material filling area is circumferentially arranged on the side of the periphery of the air inlet grille in a surrounding manner and is filled with a phase-change heat absorbing material so as to absorb the heat of high-temperature gas and reduce the temperature of backflow air;
the drainage cover is used for bending an airflow path, prolonging the retention time of air in the device and improving the heat exchange performance of the device, is arranged at the other axial end of the air inlet grille and consists of a flat cover plate and a side plate which is connected to the edge of the flat cover plate and extends towards the air inlet grille, and axial intervals are reserved between the flat cover plate and the air inlet grille and between the flat cover plate and the phase-change material filling area.
The height of air inlet grille is axial distance and is 30 ~ 50mm, phase change material filling area is in air inlet grille axial's one end and air inlet grille parallel and level, exceeds air inlet grille 1 ~ 3mm at the other end.
The air inlet grille is of a cylindrical structure, the inner diameter of the air inlet grille is 100-110 mm, the outer diameter of the air inlet grille is 102-112 mm, a plurality of holes with the cross sections of 14-15 mm multiplied by 14-15 mm and arranged orderly are arranged in the middle of the air inlet grille, and the thickness of a metal partition plate between the holes is 0.8-0.9 mm.
The phase-change material filling area is of an annular column structure, the inner diameter of the phase-change material filling area is 102-112 mm, the outer diameter of the phase-change material filling area is 140-150 mm, and the phase-change material filling area is hollow and filled with a phase-change heat-absorbing material.
The lateral plate of the drainage cover casing comprises a wide opening part and an equal-diameter part, the necking end of the wide opening part is connected with the edge of the flat cover plate, the wide opening end is connected with one end of the equal-diameter part, and the other end of the equal-diameter part is opened.
The maximum outer diameter of the drainage housing is 180-190 mm, the minimum outer diameter of the drainage housing is 150-160 mm, and the thickness of the shell is 1 mm.
The phase-change material filling area and the drainage cover casing are fixedly connected through a plurality of fixing lugs.
The invention also claims a near space vehicle with the phase-change heat absorption type air charging and discharging device arranged in the cabin body.
Compared with the prior art, the invention has the beneficial effects that:
(1) starting from the requirements of reducing the temperature of high-temperature backflow gas and protecting instruments in an aircraft cabin, important evaluation indexes such as pressure difference between the inside and the outside of the aircraft cabin and the temperature of gas entering the aircraft cabin are comprehensively considered, the phase-change heat absorption type air charging and discharging device for the passive air charging and discharging system close to the spacecraft is reasonably designed, and the comprehensive performance of the phase-change heat absorption type air charging and discharging device is researched through a numerical simulation method.
(2) The phase-change heat absorption type air charging and exhausting device designed based on the invention can effectively reduce the pressure difference between the inside and the outside of the cabin in the flying process of the aircraft, and simultaneously obviously reduce the temperature of the backflow high-temperature gas entering the cabin, thereby ensuring the safety of the aircraft. The device not only has good comprehensive performance of pressure relief and temperature reduction, but also has simple structure and convenient application, and shows great application prospect in the aerospace field.
Drawings
Fig. 1 is a structural front view of a phase-change heat absorption type air charging and discharging device.
Fig. 2 is a perspective view of the phase-change heat absorption type charging and discharging device.
Fig. 3 is a schematic cross-sectional view (hidden grid) of the phase-change endothermic inflator 1/4.
Fig. 4 is a schematic structural view of a drainage casing of the phase-change heat absorption type air charging and discharging device.
Fig. 5 shows the gas flow path (hidden grid, opposite to the flow path in the exhaust stage) in the inflation stage of the phase-change endothermic inflator.
FIG. 6 is a schematic view of the phase change heat absorption type inflation and exhaust device of the present invention installed in a cylindrical aircraft cabin.
FIG. 7 is a plot of surface air temperature pressure during flight of a cylindrical aircraft.
FIG. 8 is a graph showing the variation of the pressure difference between the inside and the outside of the cabin during the flight of the cylindrical aircraft.
FIG. 9 is a temperature change curve of the returned air after the temperature of the air charging and discharging device is reduced during the flight of the cylindrical aircraft.
Fig. 10 is a schematic view of the phase change heat absorption type air charging and discharging device of the present invention installed in a pyramid-like aircraft cabin.
FIG. 11 is a surface aerodynamic heat flow density change curve of a pyramid-like aircraft in flight.
FIG. 12 is a graph of surface air pressure changes during flight of a pyramid-like aircraft.
FIG. 13 is the variation curve of the pressure difference between the inside and outside of the cabin during the flight of the pyramid-like aircraft.
FIG. 14 is a temperature change curve of the returned air after the temperature of the air charging and discharging device is reduced in the flight process of the pyramid-like aircraft.
Number designation in the figures: 1. the structure comprises an air inlet grid, 2. a phase change material filling area, 3. a drainage housing, 3-1. a drainage housing flat cover plate, 3-2. a drainage housing wide opening part, 3-3. a drainage housing constant diameter part, 4. a fixed lug, 5. a cylindrical aircraft cabin body, 6. a pyramid-like aircraft nose cone cabin and 7. a pyramid-like aircraft rear cabin.
Detailed Description
The embodiments of the present invention will be described in detail below with reference to the drawings and examples.
The phase-change heat absorption type air charging and discharging device of the passive air charging and discharging system of the near space aircraft is reasonably designed based on the requirements of reducing the temperature of high-temperature backflow gas and protecting instruments in an aircraft cabin and comprehensively considering important evaluation indexes such as pressure difference between the inside and the outside of the aircraft cabin, the temperature of air entering the cabin and the like. Referring to fig. 1 to 5, the device mainly comprises an air inlet grille 1, a phase change material filling area 2 and a drainage housing 3, wherein the air inlet grille 1 is used for flattening air charging/discharging flow, and simultaneously increasing the effective heat exchange area of high-temperature gas and the air charging/discharging device, and the air charging/discharging flow enters from one axial end of the air charging/discharging device; the phase-change material filling area 2 is circumferentially arranged on the lateral side of the periphery of the air inlet grille 1 in a surrounding manner, and the phase-change material is filled in the phase-change material filling area to absorb the heat of high-temperature gas and reduce the temperature of backflow air; the drainage cover 3 is arranged at the other end of the air inlet grille 1 (namely above the phase-change material filling area 2) and used for bending the gas flow path, prolonging the retention time of air in the device and improving the heat exchange performance of the device. The phase-change material filling area 2 and the drainage cover 3 can be fixedly connected through a plurality of fixing lugs 4.
The inventive air intake grill 1 may be cylindrical, one preferred size: the inner diameter is 108.2mm, the outer diameter is 110.6mm, the height is 39.8mm, a plurality of regularly arranged holes with the cross sections of 14mm multiplied by 14mm are arranged in the middle, and the thickness of the metal partition plate between the holes is 0.8 mm.
The phase-change material filling area 2 of the invention is a ring column structure, and one of the preferable sizes is as follows: the inner diameter of the ring is 110.6mm, the outer diameter of the ring is 148.0mm, the height of the ring is 40.8mm, and the ring is flush with the air inlet end of the air inlet grille 1.
The drainage housing 3 consists of a flat cover plate 3-1 and a side plate which is connected with the edge of the flat cover plate 3-1 and extends towards the direction of the air inlet grid 1, an axial distance is reserved between the flat cover plate 3-1 and the air inlet grid 1 and between the flat cover plate 3-1 and the phase change material filling area 2, the side plate comprises a wide opening part 3-2 and an equal diameter part 3-3, the necking end of the wide opening part 3-2 is connected with the edge of the flat cover plate 3-1, the wide opening end is connected with one end of the equal diameter part 3-3, and the other end of the equal diameter part 3-3 is open. One preferred size of the drainage housing 3: the maximum outer diameter is 186.0mm, the minimum outer diameter is 158.0mm, the thickness of the shell is 1mm, and the shell is connected with the phase change material filling area 2 through a fixing lug 4.
The invention integrates the rectification heat conduction of the air inlet grille 1 and the drainage function of the drainage cover 3, further strengthens the heat absorption capacity of a heat absorption area, can effectively reduce the pressure difference between the inside and the outside of the cabin in the flying process of the aircraft, and simultaneously obviously reduces the temperature of the backflow high-temperature gas entering the cabin, thereby ensuring the safety of the aircraft. The device not only has good comprehensive performance of pressure relief and temperature reduction, but also has simple structure and convenient application, and shows great application prospect in the aerospace field.
The comprehensive performance of the phase change heat absorption type air charging and discharging device of the invention is evaluated by a numerical simulation method. The numerical simulation method is a mature method for researching the flow and heat transfer of multiple physical fields, and many research institutions analyze the surface aerodynamic heat condition of the near space aircraft and the pressure balance performance of the air charging and discharging device through numerical simulation. In the examples of the present invention, numerical simulations of the charging and discharging processes were performed for cylindrical and pyramid-like enclosures, respectively.
Example 1
Referring to fig. 6, in the present embodiment, the cabin adjacent to the spacecraft is a cylindrical aircraft cabin 5, which has a diameter of 0.75m and a height of 7.6 m. The air charging and discharging device is arranged at the center of the bottom of the cylindrical aircraft cabin body.
The phase-change material filling area 2 of the phase-change heat absorption type air charging and discharging device is filled with acetanilide heat absorption materials, the phase-change temperature is 120 +/-2 ℃, and the phase-change latent heat is 200 +/-20 kJ.kg-1And GH4169 is the rest structural material of the device. In the flying process of the aircraft, the change conditions of the air temperature and the air pressure at the inlet of the air inlet grille of the phase-change heat absorption type air charging and discharging device are shown in figure 7; the wall surface of the cabin body is a heat insulation wall surface.
FIG. 8 is a graph of the pressure difference between the outside air and the inside air during flight of the aircraft. From the figure, it can be found that under the pressure relief effect of the phase-change heat absorption type air charging and discharging device, the pressure difference between the inside and the outside of the cabin body is less than 10Pa, which shows that the air charging and discharging device has good pressure relief effect and can effectively ensure the pressure balance between the inside and the outside of the cabin body.
FIG. 9 is a graph of the average temperature change of the air mass in the cabin and the inlet and outlet surfaces of the phase change heat absorption type air charging and discharging device during the flight of the aircraft. From the figure, it can be found that under the heat absorption action of the phase-change material, even if the inlet air temperature reaches 2000K at most, the average temperature of the outlet surface of the air charging and discharging device is always kept below 500K, and the temperature reduction performance of the air charging and discharging device is good. It is noted that the average temperature at the inlet face of the 200-300s apparatus suddenly dropped because the inlet pressure at this stage suddenly dropped so that the pressure outside the chamber was lower than the pressure inside the chamber, and the exhaust occurred and the cold fluid inside the chamber returned to the outlet face, causing a sudden change in the average temperature at the inlet face.
Example 2
Referring to fig. 10, in the embodiment, the cabin body adjacent to the spacecraft is pyramid-like, and comprises a pyramid-like aircraft nose cone cabin 6 and a pyramid-like aircraft rear cabin 7, the cabin body has a length of about 1.1m and a volume of 0.54m3The thickness of the wall was 0.015 m. The air charging and discharging device is arranged at the central position of the bottom of the cabin body of the pyramid-like aircraft
The phase-change material filling area 2 of the phase-change heat absorption type air charging and discharging device is filled with acetanilide heat absorption materials, the phase-change temperature is 120 +/-2 ℃, and the phase-change latent heat is 200 +/-20 kJ.kg-1And GH4169 is the rest structural material of the device. The aerodynamic heat flux density and the surface pressure change of the surface of the cabin are respectively shown in fig. 11 and fig. 12 during the flight of the aircraft.
FIG. 13 is a graph of the pressure difference between the outside air and the inside air during flight of an aircraft. From the figure, it can be found that under the pressure relief effect of the phase-change heat absorption type air charging and discharging device, the pressure difference between the inside and the outside of the cabin body is less than 50Pa, which shows that the air charging and discharging device has good pressure relief effect and can effectively ensure the pressure balance between the inside and the outside of the cabin body.
FIG. 14 is a graph showing the temperature change of the outlet face (i.e., the air flowing back into the cabin) of the phase change endothermic inflator during flight of the aircraft. From the figure, it can be found that under the heat absorption effect of the phase-change material, the average temperature of the outlet surface of the air charging and discharging device is always kept below 350K, and the air charging and discharging device has good temperature reduction performance.
In conclusion, the phase change heat absorption type air charging and exhausting device designed by the invention can effectively reduce the pressure difference between the inside and the outside of the cabin in the flying process of the aircraft, and meanwhile, the temperature of the backflow high-temperature gas entering the cabin is obviously reduced, so that the safety of the aircraft is ensured. The device not only has good comprehensive performance of pressure relief and temperature reduction, but also has simple structure and convenient application, and shows great application prospect in the aerospace field.
Claims (10)
1. A phase change endothermic charging and discharging device for a passive charging and discharging system for a near space vehicle, comprising:
the air inlet grille (1) is used for flattening air charging/discharging airflow and increasing the effective heat exchange area of high-temperature gas and an air charging/discharging device, and the air charging/discharging airflow enters from one axial end of the air charging/discharging airflow;
the phase-change material filling area (2) is circumferentially arranged on the side of the periphery of the air inlet grille (1) in a surrounding manner and is filled with a phase-change heat absorbing material so as to absorb the heat of high-temperature gas and reduce the temperature of backflow air;
the drainage cover shell (3) is used for bending an airflow path, prolonging the retention time of air in the device and improving the heat exchange performance of the device, is arranged at the other axial end of the air inlet grille (1), and consists of a flat cover plate (3-1) and a side plate which is connected to the edge of the flat cover plate (3-1) and extends towards the air inlet grille (1), and axial intervals are reserved among the flat cover plate (3-1), the air inlet grille (1) and the phase change material filling area (2).
2. The phase-change endothermic charging and discharging device for a passive charging and discharging system for an adjacent space vehicle as claimed in claim 1, characterized in that the height of the intake grille (1), i.e. the axial distance, is 30 to 50mm, and the phase-change material filling area (2) is flush with the intake grille (1) at one axial end of the intake grille (1) and is 1 to 3mm higher than the intake grille (1) at the other axial end.
3. The phase-change heat absorption type air charging and discharging device for the passive air charging and discharging system close to the spacecraft as claimed in claim 1 or 2, wherein the air inlet grille (1) is of a cylindrical structure, the inner diameter is 100-110 mm, the outer diameter is 102-112 mm, a plurality of regularly arranged holes with the cross sections of 14-15 mm x 14-15 mm are arranged in the middle, and the thickness of a metal partition plate between every two holes is 0.8-0.9 mm.
4. The phase-change heat absorption type air charging and discharging device for the passive air charging and discharging system of the near space vehicle as claimed in claim 1, wherein the phase-change material filling area (2) is of an annular cylindrical structure, has an inner diameter of 102-112 mm and an outer diameter of 140-150 mm, is hollow inside and is filled with the phase-change heat absorption material.
5. The phase-change endothermic charging and discharging device for a passive charging and discharging system of an adjacent space vehicle as claimed in claim 1, characterized in that the side plate of the flow guiding casing (3) comprises a wide mouth portion (3-2) and an equal diameter portion (3-3), the throat end of the wide mouth portion (3-2) is connected with the edge of the flat cover plate (3-1), the wide mouth end is connected with one end of the equal diameter portion (3-3), and the other end of the equal diameter portion (3-3) is open.
6. The phase-change heat absorption type air charging and discharging device for the passive air charging and discharging system close to the spacecraft as claimed in claim 1 or 5, wherein the maximum outer diameter of the flow-guiding enclosure (3) is 180-190 mm, the minimum outer diameter is 150-160 mm, and the shell thickness is 1 mm.
7. The phase-change endothermic charging and discharging device for a passive charging and discharging system of a near space vehicle as claimed in claim 1, characterized in that the phase-change material filling area (2) and the drainage casing (3) are fixedly connected by a plurality of fixing lugs (4).
8. A near space vehicle, wherein the cabin is provided with the phase change heat absorption type air charging and discharging device of any one of claims 1 to 7.
9. The near space vehicle as claimed in claim 8, wherein the body is cylindrical, and the phase change heat absorption type air charging and discharging device is installed at the center of the bottom of the cylindrical body.
10. The close-space vehicle as claimed in claim 8, wherein the chamber is pyramid-like, and the phase-change heat-absorbing charging and discharging device is installed at the center of the bottom of the pyramid-like chamber.
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| CN202110651261.XA CN113335534B (en) | 2021-06-10 | 2021-06-10 | Phase-change heat-absorbing type air charging and discharging device of passive air charging and discharging system of near space vehicle |
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| CN202110651261.XA CN113335534B (en) | 2021-06-10 | 2021-06-10 | Phase-change heat-absorbing type air charging and discharging device of passive air charging and discharging system of near space vehicle |
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| CN113335534B CN113335534B (en) | 2024-03-12 |
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| 吴亚东;朱广生;蒋平;李强;宁雷;高波;: "先进的热防护方法及在飞行器的应用前景初探", 宇航总体技术, vol. 1, no. 01, pages 60 - 65 * |
| 郭鹏飞;刘杰平;陈龙;: "高超声速飞行器舱内压力预测", 宇航学报, vol. 37, no. 01, pages 55 - 60 * |
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