A spacecraft fairing environment control system

Abstract

The present invention discloses a spacecraft fairing environment control system, which belongs to the technical field of ventilation systems. A spacecraft fairing environment control system includes a gas flow control unit, which is arranged in the fairing, and also includes: an air environment detection unit, which detects the temperature and humidity inside the fairing; a circulating wind driving unit, which controls the circulation of the airflow inside the fairing; an air conditioning unit, which humidifies, dehumidifies, heats and cools the circulating airflow according to the data detected by the air environment detection unit; a rapid cooling unit, which discharges low-temperature gas when the fairing heats up rapidly; the present invention can monitor the environmental parameters inside the fairing in real time, and perform humidification, dehumidification, heating, cooling and other operations as needed, so as to maintain the stability of the internal environment of the fairing and provide reliable protection for the equipment inside the spacecraft.

Description

Technical Field

[0001] The invention relates to the technical field of ventilation systems, and in particular to a spacecraft fairing environment control system. Background Art

[0002] The fairing environmental control system is a ventilation system specifically designed to monitor and control the internal environment of the fairing.

[0003] At present, the temperature and humidity of the air inside the fairing may fluctuate due to various factors such as changes in the external environment, heat conduction of the fairing material, and heating of internal equipment, causing the temperature and humidity to exceed the appropriate range, which will have an adverse effect on the satellites or other payloads on board. In addition, due to the lack of an effective airflow circulation and distribution system, local overheating or overhumidity may occur inside the fairing, resulting in performance degradation or damage to the equipment. In some extreme cases, the inside of the fairing may heat up rapidly due to the high external temperature environment or overheating of the internal equipment. If there are no effective rapid cooling measures, it will cause serious damage to the sensitive equipment on board. For this reason, a spacecraft fairing environment control system is proposed herein. Summary of the invention

[0004] The present invention is to solve the problem of unstable internal environment of the fairing in the prior art, and proposes a spacecraft fairing environment control system.

[0005] In order to achieve the above-mentioned purpose, the present invention adopts the following technical scheme: a spacecraft fairing environment control system, including a gas flow control unit, which is arranged in the fairing, and also includes: an air environment detection unit, which detects the temperature and humidity inside the fairing; a circulating wind drive unit, which controls the circulation of airflow inside the fairing; an air conditioning unit, which humidifies, dehumidifies, heats and cools the circulating airflow according to the data detected by the air environment detection unit; and a rapid cooling unit, which discharges low-temperature gas when the fairing is rapidly heated.

[0006] As a preferred embodiment of the present invention, a fairing is fixedly connected with a guide cover, a guide cavity is arranged between the guide cover and the fairing, and an air injection hole connecting the inner and outer sides of the guide cover is arranged on the bottom side wall of the guide cover.

[0007] As a preferred embodiment of the present invention: a mounting rod is fixedly installed in the air deflector, a mounting ring is fixedly connected to the mounting rod, a mounting sphere is coupled to the mounting ring, an annular groove is provided on the mounting ring, a ball is provided in the annular groove, and the ball is in contact with the mounting sphere.

[0008] As a preferred embodiment of the present invention: a mounting plate is fixedly installed in the mounting sphere, a mounting box is fixedly installed on the mounting plate, a mounting cavity, a heating cavity and a cooling cavity are arranged in the mounting box, a water storage cavity is arranged at the bottom of the cooling cavity, an air inlet cavity is arranged at the bottom of the mounting cavity, and an air inlet hole connected to the air inlet cavity is arranged at the bottom of the mounting sphere.

[0009] As a preferred embodiment of the present invention: the circulating air driving unit includes a motor fixedly connected to the bottom of the mounting plate, and the output shaft of the motor extends to the fan blades in the air inlet cavity.

[0010] As a preferred embodiment of the present invention: the air conditioning unit includes a semiconductor refrigerator fixedly installed in the installation cavity, a heat storage block fixedly installed in the heating cavity and a heat conductive network fixedly connected in the cooling cavity, the heat conductive network is connected to the heat absorption end of the semiconductor refrigerator, the heat discharge end of the semiconductor refrigerator is connected to the heat storage block, and the heat storage block is provided with air vents connecting the upper and lower ends of the heat storage block.

[0011] As a preferred embodiment of the present invention: a drain outlet is arranged between the cooling chamber and the water storage chamber, a right-angled triangle plate is fixedly installed in the cooling chamber, the right-angled triangle plate is arranged at the bottom of the heat-conducting net, and the condensed water on the heat-conducting net enters the water storage chamber along the right-angled triangle plate and the drain outlet.

[0012] As a preferred embodiment of the present invention: the gas flow control unit includes a controller fixedly installed in the air inlet chamber, and also includes: a first air pipe fixedly connected to the installation box, the two ends of the first air pipe respectively extend to the air inlet chamber and the water storage chamber, one end of the first air pipe extending into the water storage chamber is fixedly connected with a first control valve, the output end at the bottom of the first control valve is fixedly connected with a second air pipe extending into the condensed water, the top of the first control valve is fixedly connected with a third air pipe, and the third air pipe is connected to the cooling chamber; a fourth air pipe fixedly connected to the installation box, the fourth air pipe connects the heating chamber and the air inlet chamber, and one end of the fourth air pipe extending into the air inlet chamber is fixedly installed with the second control valve; a joint, the bottom of which is fixedly connected with a fifth air pipe connected to the water storage chamber, a sixth air pipe connected to the cooling chamber, and a seventh air pipe connected to the heating chamber, the third control valve is fixedly installed on the fifth air pipe, the fourth control valve is fixedly installed on the sixth air pipe, and the top of the joint is fixedly connected with an eighth air pipe connected to the guide chamber.

[0013] As a preferred embodiment of the present invention: the air environment detection unit includes an outlet temperature and humidity sensor fixedly installed on the eighth air pipe and an in-hood temperature and humidity sensor fixedly installed on the inner side of the air guide hood.

[0014] As a preferred embodiment of the present invention: the rapid cooling unit includes a liquid nitrogen bottle fixedly installed on the mounting plate, a fifth control valve is fixedly installed at the output end of the liquid nitrogen bottle, a ninth air pipe is fixedly connected to the output end of the fifth control valve, and the ninth air pipe is connected to the joint.

[0015] Compared with the prior art, the present invention provides a spacecraft fairing environment control system, which has the following beneficial effects:

[0016] 1. The spacecraft fairing environment control system can monitor the environmental parameters inside the fairing in real time, and perform humidification, dehumidification, heating, cooling and other operations as needed, so as to maintain the stability of the internal environment of the fairing and provide reliable protection for the equipment inside the spacecraft;

[0017] 2. The spacecraft fairing environment control system can detect and handle environmental anomalies inside the fairing in a timely manner through intelligent control strategies, avoiding damage to the internal equipment of the spacecraft caused by changes in environmental factors. At the same time, the design of the rapid cooling part can provide effective cooling measures when the fairing temperature rises rapidly, further enhancing the reliability and safety of the fairing;

[0018] 3. The spacecraft fairing environmental control system improves the utilization and efficiency of the internal environment of the fairing through intelligent environmental control strategies, thereby reducing the additional costs caused by environmental factors in space missions. In addition, by optimizing the structure and design of the system, the manufacturing cost and maintenance cost of the system are reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 A schematic diagram of the three-dimensional structure of a spacecraft fairing environment control system proposed by the present invention;

[0020] Figure 2 A schematic diagram of the structure of a fairing environment control system for a spacecraft proposed by the present invention;

[0021] Figure 3 A spacecraft fairing environment control system proposed by the present invention Figure 2 The structural diagram of part A in the figure;

[0022] Figure 4 A cross-sectional view of a mounting sphere of a spacecraft fairing environment control system proposed by the present invention;

[0023] Figure 5 A cross-sectional view of a spacecraft fairing environment control system installation box proposed by the present invention;

[0024] Figure 6 A schematic diagram of the structure of an air conditioning unit of a spacecraft fairing environment control system proposed by the present invention;

[0025] Figure 7 A spacecraft fairing environment control system proposed by the present invention Figure 6 The structural diagram of part B;

[0026] Figure 8 This is a diagram of an airflow circulation system of a spacecraft fairing environment control system proposed by the present invention.

[0027] In the figure: 1, liquid nitrogen bottle; 2, guide cover; 3, guide cavity; 4, jet hole; 5, mounting rod; 6, mounting ring; 7, mounting sphere; 8, annular groove; 9, ball; 10, temperature and humidity sensor in the cover; 11, mounting plate; 12, mounting box; 13, air inlet; 14, motor; 15, fan blade; 16, mounting cavity; 17, heating cavity; 18, cooling cavity; 19, water storage cavity; 20, drain port; 21, first air pipe; 22, first control valve; 23, second air pipe; 2 4. The third air pipe; 25. The fourth air pipe; 26. The second control valve; 27. The fifth air pipe; 28. The sixth air pipe; 29. ​​The seventh air pipe; 30. The third control valve; 31. The fourth control valve; 32. The joint; 33. The eighth air pipe; 34. The semiconductor refrigerator; 35. The heat storage block; 36. The vent hole; 37. The heat conductive net; 38. The spray temperature and humidity sensor; 39. The ninth air pipe; 40. The air inlet chamber; 41. The right-angled triangle plate; 42. The controller; 43. The fifth control valve. DETAILED DESCRIPTION

[0028] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0029] In the description of the present invention, it is necessary to understand that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0030] Example: Refer to Figure 1-Figure 8 A spacecraft fairing environment control system includes a gas flow control unit, which is arranged in the fairing, and also includes: an air environment detection unit, which detects the temperature and humidity inside the fairing; a circulating wind drive unit, which controls the circulation of airflow inside the fairing; an air conditioning unit, which humidifies, dehumidifies, heats and cools the circulating airflow according to the data detected by the air environment detection unit; and a rapid cooling unit, which discharges low-temperature gas when the fairing is rapidly heated.

[0031] like Figure 2 and Figure 3 As shown, in order to facilitate the installation of the entire control system, a guide cover 2 is fixedly connected inside the fairing, a guide cavity 3 is arranged between the guide cover 2 and the fairing, and an injection hole 4 connecting the inside and outside of the guide cover 2 is arranged on the bottom side wall of the guide cover 2. The circulating wind driving unit blows the airflow that has undergone cooling and dehumidification, humidification, heating, or cooling and humidification to the top of the guide cavity 3, and then flows downward under the impetus of the subsequent airflow, and then is evenly sprayed to the inside of the guide cover 2 through the injection hole 4, and then is sucked in by the circulating wind driving unit again.

[0032] The fairing 2 is composed of two semi-cones, which are respectively fixed on two groups of fairings. When the two fairings are combined, the two fairings 2 form a cone.

[0033] Reference Figure 4 and Figure 5 During the use of the fairing, the fairing will tilt with the ground, which will cause the equipment inside the fairing to follow the tilt. In order to prevent the control system from malfunctioning due to the tilt, a mounting rod 5 is fixedly installed in the fairing 2, and a mounting ring 6 is fixedly connected to the mounting rod 5. A mounting sphere 7 is coupled to the mounting ring 6. An annular groove 8 is provided on the mounting ring 6, and a ball 9 is provided in the annular groove 8. The ball 9 is in contact with the mounting sphere 7, and the bottom weight of the mounting sphere 7 is greater than the weight of the upper part. Through the above structure, when the fairing tilts, under the action of gravity, the bottom of the mounting sphere 7 moves vertically downward. When the fairing tilts with the ground, the mounting sphere 7 rotates relative to the mounting ring 6 through the ball 9, and keeps the bottom vertically downward when the weight of the bottom is greater than the weight of the upper part, thereby preventing the environmental control system from tilting relative to each other and preventing the environmental control system from malfunctioning.

[0034] Reference Figure 5 In order to further install the environmental system, a mounting plate 11 is fixedly installed in the mounting sphere 7, and a mounting box 12 is fixedly installed on the mounting plate 11. The mounting box 12 is provided with an mounting cavity 16, a heating cavity 17 and a cooling cavity 18. A water storage cavity 19 is provided at the bottom of the cooling cavity 18, an air inlet cavity 40 is provided at the bottom of the mounting cavity 16, and an air inlet hole 13 connected to the air inlet cavity 40 is provided at the bottom of the mounting sphere 7.

[0035] It first enters the air inlet chamber 40, and then controls the airflow to enter the cooling chamber 18, the heating chamber 17, or the water storage chamber 19 according to the data detected by the air environment detection unit, and finally changes the humidity and temperature of the exhaust gas, so as to make the environment inside the fairing more stable.

[0036] Reference Figure 5The circulating air driving unit includes a motor 14 fixedly connected to the bottom of the mounting plate 11, and the output shaft of the motor 14 extends to the fan blades 15 in the air inlet chamber 40. In this embodiment, the fan blades 15 are driven to rotate by the motor 14, and the rotating fan blades 15 are used to drive the gas inside the fairing to flow, and then the airflow is guided through the pipes and chambers to circulate the airflow. In addition, a piston pump can also be used to drive the gas flow.

[0037] Reference Figure 5-Figure 7 In this embodiment, the air conditioning unit includes a semiconductor refrigerator 34 fixedly installed in the installation cavity 16, a heat storage block 35 fixedly installed in the heating cavity 17 and a heat conductive network 37 fixedly connected in the cooling cavity 18. The heat conductive network 37 is connected to the heat absorption end of the semiconductor refrigerator 34, and the heat discharge end of the semiconductor refrigerator 34 is connected to the heat storage block 35. The heat storage block 35 is provided with a vent hole 36 connecting the upper and lower ends of the heat storage block 35.

[0038] The semiconductor refrigerator 34 is a core component in the air conditioning unit, which can realize one-way heat transfer. Specifically, the semiconductor refrigerator 34 has two main end surfaces: a heat absorption end and a heat discharge end. The heat absorbing end can absorb heat, while the heat dissipating end can release heat. The heat-conducting net 37 is connected to the heat-absorbing end of the semiconductor refrigerator 34, so that the heat-conducting net 37 can transfer the absorbed heat to the heat-absorbing end of the semiconductor refrigerator 34, thereby realizing the heat transfer. The design of the heat-conducting net 37 can make the heat inside the air be evenly absorbed when the air passes through the cooling chamber 18; the heat dissipating end of the semiconductor refrigerator 34 is connected to the heat storage block 35, so that when the semiconductor refrigerator 34 generates heat during the cooling process, the heat will be transferred to the heat storage block 35. The design of the heat storage block 35 can ensure the storage and release of heat, thereby providing a heating function when needed; when the circulating wind driving unit and the gas flow control unit control the airflow to enter the heating chamber 17, it then passes through the heat storage block 35 through the vent 36 and absorbs the heat on the heat storage block 35, thereby providing heat for the inside of the fairing to prevent the temperature inside the fairing from being too low.

[0039] Among them, the heat storage block 35 can adopt heat storage materials such as silicon carbide ceramic heat storage body and high-temperature molten salt. These heat storage materials can cooperate with the semiconductor refrigerator 34 to continuously store heat when not in use, so as to quickly heat the inside of the air duct after the temperature inside the air duct drops.

[0040] Reference Figure 5 and Figure 6In order to discharge the condensed water in the cooling chamber 18 in time, a drain port 20 is provided between the cooling chamber 18 and the water storage chamber 19. A right-angled triangular plate 41 is fixedly installed in the cooling chamber 18. The right-angled triangular plate 41 is provided at the bottom of the heat-conducting net 37. The condensed water on the heat-conducting net 37 enters the water storage chamber 19 along the right-angled triangular plate 41 and the drain port 20. When the semiconductor refrigerator 34 absorbs the heat on the heat-conducting net 37, the temperature on the heat-conducting net 37 is reduced. When the circulating airflow passes through the heat-conducting net 37, the airflow is fully in contact with the heat-conducting net 37, and the heat in the airflow is absorbed by the heat-conducting net 37. Therefore, the temperature of the airflow is reduced. After the temperature of the airflow is reduced, the water molecules inside the airflow condense into condensed water, and then the condensed water drips down along the heat-conducting net 37, and is finally guided by the inclined surface of the right-angled triangular plate 41, and then discharged into the water storage chamber 19 through the drain port 20.

[0041] Reference Figure 1-Figure 8 In order to facilitate the control of the gas flow direction, the gas flow control unit includes a controller 42 fixedly installed in the air inlet chamber 40, and also includes: a first air pipe 21 fixedly connected to the installation box 12, the two ends of the first air pipe 21 extend to the air inlet chamber 40 and the water storage chamber 19 respectively, one end of the first air pipe 21 extending into the water storage chamber 19 is fixedly connected to a first control valve 22, the output end at the bottom of the first control valve 22 is fixedly connected to a second air pipe 23 extending into the condensed water, the top of the first control valve 22 is fixedly connected to a third air pipe 24, the third air pipe 24 is connected to the cooling chamber 18; a fourth air pipe 25 fixedly connected to the installation box 12, the fourth air pipe 25 is connected to the heating chamber 17 and the air inlet chamber 40, and the fourth air pipe 25 extends to one end of the air inlet chamber 40 and is fixedly installed with a second control valve 26; the bottom of the joint 32 is fixedly connected with a fifth air pipe 27 connected with the water storage chamber 19, a sixth air pipe 28 connected with the cooling chamber 18 and a seventh air pipe 29 connected with the heating chamber 17, the fifth air pipe 27 is fixedly installed with a third control valve 30, the sixth air pipe 28 is fixedly installed with a fourth control valve 31, the top of the joint 32 is fixedly connected with an eighth air pipe 33 connected with the guide chamber 3, and the air environment detection unit includes an ejection temperature and humidity sensor 38 fixedly installed on the eighth air pipe 33 and an in-hood temperature and humidity sensor 10 fixedly installed on the inner side of the guide cover 2.

[0042] In this embodiment, the temperature and humidity of the circulating airflow ejected by the ejection temperature and humidity sensor 38 are detected by the temperature and humidity sensor 10 inside the fairing, and then the five groups of control gas flow directions from the first control valve 22 to the fifth control valve 43 are controlled according to the two sets of data combined with the preset temperature and humidity thresholds, specifically:

[0043] When the internal ambient temperature of the fairing is high and the humidity is high: open the first control valve 22 and the fourth control valve 31, and close the other control valves, the airflow passes through the heat-conducting net 37, and enters the joint 32 after being cooled and dehumidified by the heat-conducting net 37, and then enters the top of the guide cavity 3 through the eighth air pipe 33, and then the low-temperature airflow moves downward along the guide cavity 3, and the temperature on the inner wall of the guide hood can be neutralized during the movement, and then enters the inner side of the guide hood 2 to neutralize the temperature of the rest of the inner side of the guide hood;

[0044] When the ambient temperature inside the fairing is high and the humidity is low: open the first control valve 22, the third control valve 30 and the fourth control valve 31, and the other valves are closed, wherein the first control valve 22 controls the air flow wall entering between the second air pipe 23 and the third air pipe 24, and the air flow is discharged into the water through the second air pipe 23, and then bubbles are formed in the water and rise, and the air flow is humidified in this process, and then enters the joint 32 through the fifth air pipe 27 to mix with the low-temperature air flow to lower the temperature, and then the mixed air flow enters the top of the guide cavity 3 through the eighth air pipe 33, and then the low-temperature and humid air flow moves downward along the guide cavity 3, and the temperature on the inner wall of the guide hood can be neutralized and the guide hood can be humidified during the movement, and then enters the inner side of the guide hood 2 to neutralize the temperature and humidity of the rest of the inner side of the guide hood.

[0045] When the ambient temperature inside the fairing is low: open the second control valve 26, close the remaining valves, the circulating airflow enters the heating chamber 17, and then passes through the vent hole 36 on the heat storage block 35 to absorb the heat on the heat storage block 35 to form a hot air flow, and then enters the joint 32, and then enters the top of the guide chamber 3 through the eighth air pipe 33, and then the low-temperature and humid airflow moves downward along the guide chamber 3. During the movement, the temperature on the inner wall of the guide chamber can be neutralized and the guide chamber can be heated, and then it enters the inner side of the guide chamber 2 to neutralize the temperature of the rest of the inner side of the guide chamber.

[0046] In addition, all valves except the fifth control valve 43 can be opened, and the airflow ratio of the circulating airflow entering the second air pipe 23, the third air pipe 24 and the fourth air pipe 25 can be controlled by the first control valve 22 and the second control valve 26. Finally, the airflow that has been humidified, cooled and heated is moderated to form the required airflow with corresponding temperature and humidity.

[0047] Reference Figure 4 The rapid cooling unit includes a liquid nitrogen bottle 1 fixedly mounted on a mounting plate 11 , a fifth control valve 43 is fixedly mounted on an output end of the liquid nitrogen bottle 1 , a ninth air pipe 39 is fixedly connected to an output end of the fifth control valve 43 , and the ninth air pipe 39 is connected to a joint 32 .

[0048] When the temperature of the shroud rises rapidly and the cooperation between the semiconductor refrigerator 34 and the heat-conducting network 37 is insufficient to achieve rapid cooling, the fifth control valve 43 is opened to discharge the liquid nitrogen in the liquid nitrogen bottle 1, and the low temperature of the liquid nitrogen is used to quickly neutralize the heat in the shroud.

[0049] When the deflector shroud separates from the rocket and falls, and the friction with the air generates high temperature, the fifth control valve 43 is opened to allow liquid nitrogen to enter the deflector cavity 3, and the liquid nitrogen is used to cool the deflector shroud, thereby reducing the loss of the deflector shroud caused by the high temperature when it falls.

[0050] In summary, the system can monitor the environmental parameters inside the fairing in real time, and perform humidification, dehumidification, heating, cooling and other operations as needed, so as to maintain the stability of the internal environment of the fairing and provide reliable protection for the equipment inside the spacecraft.

[0051] Through intelligent control strategies, the system can detect and handle environmental anomalies inside the fairing in a timely manner, preventing changes in environmental factors from causing damage to the internal equipment of the spacecraft. At the same time, the design of the rapid cooling unit can provide effective cooling measures when the temperature of the fairing rises rapidly, further enhancing the reliability and safety of the fairing.

[0052] The system improves the utilization and efficiency of the internal environment of the fairing through intelligent environmental control strategies, thereby reducing the additional costs caused by environmental factors in space missions. In addition, by optimizing the system's structure and design, the system's manufacturing and maintenance costs are reduced.

[0053] A stable internal environment of the fairing helps improve the performance and stability of the spacecraft, and good environmental control helps protect the equipment inside the spacecraft from harsh environments such as high temperature and high pressure.

[0054] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A spacecraft fairing environment control system, comprising a gas flow direction control unit, arranged in the fairing, characterized in that: Also includes: Air environment detection unit, which detects the temperature and humidity inside the fairing; A circulating air drive unit controls the circulating flow of air inside the fairing; The air conditioning unit humidifies, dehumidifies, heats and cools the circulating air flow according to the data detected by the air environment detection unit; Rapid cooling section, which discharges low-temperature gas when the fairing heats up rapidly; A fairing (2) is fixedly connected inside the fairing, a fairing cavity (3) is provided between the fairing (2), and a jet hole (4) communicating with the inner and outer sides of the fairing (2) is provided on the bottom side wall of the fairing (2); A mounting rod (5) is fixedly mounted in the air deflector (2), a mounting ring (6) is fixedly connected to the mounting rod (5), a mounting sphere (7) is coupled to the mounting ring (6), an annular groove (8) is provided on the mounting ring (6), a ball (9) is provided in the annular groove (8), and the ball (9) is in contact with the mounting sphere (7); A mounting plate (11) is fixedly mounted inside the mounting sphere (7), a mounting box (12) is fixedly mounted on the mounting plate (11), a mounting chamber (16), a heating chamber (17) and a cooling chamber (18) are arranged inside the mounting box (12), a water storage chamber (19) is arranged at the bottom of the cooling chamber (18), an air inlet chamber (40) is arranged at the bottom of the mounting chamber (16), and an air inlet hole (13) communicating with the air inlet chamber (40) is arranged at the bottom of the mounting sphere (7); The gas flow direction control unit comprises a controller (42) fixedly mounted in the air inlet chamber (40), and further comprises: A first air pipe (21) fixedly connected to the installation box (12), the two ends of the first air pipe (21) respectively extending into the air inlet chamber (40) and the water storage chamber (19), one end of the first air pipe (21) extending into the water storage chamber (19) is fixedly connected to a first control valve (22), the output end at the bottom of the first control valve (22) is fixedly connected to a second air pipe (23) extending into condensed water, the top of the first control valve (22) is fixedly connected to a third air pipe (24), and the third air pipe (24) is connected to the cooling chamber (18); a fourth air pipe (25) fixedly connected to the installation box (12), the fourth air pipe (25) communicating with the heating chamber (17) and the air inlet chamber (40), and a second control valve (26) fixedly mounted on one end of the fourth air pipe (25) extending into the air inlet chamber (40); A joint (32) is fixedly connected at its bottom with a fifth air pipe (27) communicating with the water storage chamber (19), a sixth air pipe (28) communicating with the cooling chamber (18), and a seventh air pipe (29) communicating with the heating chamber (17); a third control valve (30) is fixedly mounted on the fifth air pipe (27); a fourth control valve (31) is fixedly mounted on the sixth air pipe (28); and an eighth air pipe (33) communicating with the flow guide chamber (3) is fixedly connected at its top.

2. A spacecraft fairing environment control system according to claim 1, characterized in that: The circulating air driving unit comprises a motor (14) fixedly connected to the bottom of the mounting plate (11), and an output shaft of the motor (14) extends to a fan blade (15) in the air inlet cavity (40).

3. A spacecraft fairing environment control system according to claim 1, characterized in that: The air conditioning unit comprises a semiconductor refrigerator (34) fixedly mounted in the mounting cavity (16), a heat storage block (35) fixedly mounted in the heating cavity (17), and a heat conduction network (37) fixedly connected in the cooling cavity (18); the heat conduction network (37) is connected to a heat absorption end of the semiconductor refrigerator (34); a heat discharge end of the semiconductor refrigerator (34) is connected to the heat storage block (35); and the heat storage block (35) is provided with an air vent (36) communicating with the upper and lower ends of the heat storage block (35).

4. A spacecraft fairing environment control system according to claim 3, characterized in that: A drain port (20) is provided between the cooling chamber (18) and the water storage chamber (19); a right-angled triangular plate (41) is fixedly installed in the cooling chamber (18); the right-angled triangular plate (41) is provided at the bottom of the heat-conducting net (37); condensed water on the heat-conducting net (37) flows into the water storage chamber (19) along the right-angled triangular plate (41) and the drain port (20).

5. A spacecraft fairing environment control system according to claim 1, characterized in that: The air environment detection unit comprises an outlet temperature and humidity sensor (38) fixedly mounted on the eighth air pipe (33) and an in-hood temperature and humidity sensor (10) fixedly mounted on the inner side of the air guide hood (2).

6. A spacecraft fairing environment control system according to claim 1, characterized in that: The rapid cooling unit comprises a liquid nitrogen bottle (1) fixedly mounted on the mounting plate (11); a fifth control valve (43) is fixedly mounted on the output end of the liquid nitrogen bottle (1); the output end of the fifth control valve (43) is fixedly connected to a ninth air pipe (39); and the ninth air pipe (39) is connected to a joint (32).

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