Thermal protection equipment suitable for spacecraft outboard high-power equipment

Abstract

The invention discloses thermal protection equipment suitable for spacecraft outboard high-power equipment. The thermal protection equipment comprises a metal shell, a high-power circuit and a thermal control circuit, the high-power circuit and the thermal control circuit are arranged in the metal shell and mounted on the inner bottom surface of the metal shell; the outer surfaces of the four side walls of the metal shell are coated with heat insulation materials in a multi-layer mode. The inner bottom surface of the metal shell is coated with black paint, and the outer surface of a top plate of the metal shell is coated with white thermal control paint. According to the thermal protection equipment, the temperature outside an in-orbit high-power aircraft cabin can be stable, and long-term stable operation of high-power equipment outside the spacecraft cabin is guaranteed.

Description

Technical Field

[0001] The invention belongs to the field of thermal control technology, and in particular relates to a thermal protection device suitable for high-power equipment outside a spacecraft cabin. Background Art

[0002] With the in-depth development of aerospace technology, the types and functions of space vehicles are increasing. Therefore, some stand-alone space vehicle products need to complete related functions outside the cabin. However, the environment in space is rather special, with temperatures reaching -270°C. The temperature on the side of the product that is not exposed to the sun is lower, while the temperature on the side exposed to the sun is higher. However, heat cannot be dissipated into space by heat conduction and convection in space, and can only be radiated into space by thermal radiation. Therefore, the thermal insulation design of the product itself and the high emissivity and low absorptivity of the surface material are particularly important. Summary of the invention

[0003] The technology of the present invention solves the problem: overcomes the shortcomings of the prior art and provides a thermal protection device suitable for high-power equipment outside the cabin of a spacecraft, which can achieve temperature stability outside the cabin of an on-orbit high-power aircraft and ensure long-term stable operation of high-power equipment outside the cabin of the spacecraft.

[0004] In order to solve the above technical problems, the present invention discloses a thermal protection device suitable for high-power equipment outside the spacecraft cabin, comprising: a metal shell, a high-power circuit and a thermal control circuit;

[0005] The high-power circuit and the thermal control circuit are arranged inside the metal shell and mounted on the inner bottom surface of the metal shell;

[0006] The outer surfaces of the four side walls of the metal shell are covered with multiple layers of insulation material to achieve thermal isolation from the outside world;

[0007] The inner bottom surface of the metal shell is coated with black paint, and the outer surface of the top plate of the metal shell is coated with white thermal control paint.

[0008] In the above-mentioned thermal protection device suitable for high-power equipment outside the spacecraft cabin, a plurality of thermal control circuits are arranged in a horizontal array on the inner bottom surface of the metal shell.

[0009] In the above-mentioned thermal protection equipment suitable for high-power equipment outside the spacecraft cabin, the number of thermal control circuits is 2N, including: N main thermal control circuits and N backup thermal control circuits; wherein the main thermal control circuits and the backup thermal control circuits are alternately arranged and installed on the inner bottom surface of the metal shell; N≥1.

[0010] In the above-mentioned thermal protection equipment suitable for high-power equipment outside the spacecraft cabin, the power supply and control of each thermal control circuit are provided by different power channels, and the strategy of automatic judgment and hysteresis heating is adopted.

[0011] In the above-mentioned thermal protection equipment suitable for high-power equipment outside the spacecraft cabin, when the temperature control sensor detects that the product temperature is lower than the set temperature A, the main thermal control circuit starts heating; when the temperature control sensor detects that the product temperature is higher than the set temperature B, the main thermal control circuit turns off heating; wherein BA>5℃.

[0012] In the above-mentioned thermal protection equipment suitable for high-power equipment outside the spacecraft cabin, when the temperature control sensor detects that the product temperature is lower than the set temperature A', or the main thermal control circuit fails, the backup thermal control circuit starts heating; when the temperature control sensor detects that the product temperature is higher than the set temperature B', the backup thermal control circuit turns off heating; wherein, A'=A-5, B'=B-5.

[0013] In the above-mentioned thermal protection device suitable for high-power equipment outside the spacecraft cabin, a plurality of high-power circuits are arranged in a longitudinal array on the inner bottom surface of the metal shell.

[0014] In the above-mentioned thermal protection device suitable for high-power equipment outside the spacecraft cabin, the thermal protection device is connected to the cabin body through a metal shell to achieve heat transfer with the cabin body surface.

[0015] The present invention has the following advantages:

[0016] The present invention discloses a thermal protection device suitable for high-power equipment outside the cabin of a spacecraft, which meets the heat preservation requirements of high-power products outside the cabin of a spacecraft under high and low temperature conditions. The cooling operation under high temperature conditions is achieved by coating the surface of the metal shell with materials of different emissivity and absorptivity; the heating function under low temperature conditions can be achieved by using a thermal control circuit. The above measures can avoid the situation where the components in the high-power equipment fail to work properly under high and low temperature conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the external structure of a thermal protection device suitable for high-power equipment outside a spacecraft cabin in an embodiment of the present invention;

[0018] Figure 2 is an outer surface view of a metal shell in an embodiment of the present invention;

[0019] Figure 3 This is a view showing the distribution of circuit components on the front, inner and bottom surfaces of a metal housing in an embodiment of the present invention;

[0020] Figure 4 is a schematic diagram of the layout of a thermal control circuit in an embodiment of the present invention;

[0021] Figure 5 It is a schematic diagram of the layout of a high-power circuit in an embodiment of the present invention. DETAILED DESCRIPTION

[0022] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments disclosed in the present invention will be further described in detail below with reference to the accompanying drawings.

[0023] One of the core ideas of the present invention is that: in view of the problem that the high-power heating equipment on orbit currently lacks thermal control scheme design, is greatly affected by the space temperature when working on orbit, and the working life and stability of the equipment are difficult to guarantee, a thermal protection device suitable for high-power equipment outside the cabin of a spacecraft is proposed. The bottom surface of the inner bottom of the metal shell is coated with black paint, which is conducive to radiation heat absorption, and the outer surface of the top plate is coated with white paint, which is conducive to radiation heat dissipation. The absorption and dissipation ensure the stability of the high-temperature environment temperature; the layout of the components (high-power circuit and thermal control circuit) on the bottom surface of the equipment is conducive to thermal control, which makes it easy for the thermal control circuit to evenly heat the high-power circuit and ensure normal operation in a low-temperature environment; the main and backup designs of the thermal control circuit can realize the control of different temperature gradients.

[0024] Reference Figures 1 to 5 In this embodiment, the thermal protection device suitable for high-power equipment outside the spacecraft cabin includes: a metal shell 1, a high-power circuit 2 and a thermal control circuit 3. Among them, the high-power circuit 2 and the thermal control circuit 3 are arranged inside the metal shell 1 and installed on the inner bottom surface of the metal shell 1; the outer surfaces of the four side walls of the metal shell 1 are coated with multiple layers of insulation material 4 to achieve thermal isolation from the outside; the inner bottom surface of the metal shell 1 is coated with black paint 11, and its high absorption rate and low emissivity characteristics can quickly radiate the heat generated by the high-power circuit to the metal shell; the outer surface of the top plate of the metal shell 1 is coated with white thermal control paint 12, and its low absorption rate and high emissivity can quickly radiate the heat on the metal shell to the space environment. In this way, the high-power circuit inside the high-power equipment can be cooled in a high-temperature environment, so that the equipment can work normally.

[0025] In this embodiment, the inner bottom surface of the metal shell 1 is a large flat structure, and the large power circuits 2 and thermal control circuits 3 are installed on the large flat surface of the inner bottom surface of the metal shell, distributed in an array and placed at intervals to facilitate heat conduction of components and heating of the thermal control circuit.

[0026] In this embodiment, a plurality of thermal control circuits 3 are arranged in a horizontal array on the inner bottom surface of the metal shell 1, and the high-power circuit 2 is evenly divided to achieve temperature rise in a low-temperature environment and ensure normal operation of the device at low temperatures. Figure 4 As shown, the number of thermal control circuits 3 is 2N, including: N main thermal control circuits 31 and N backup thermal control circuits 32. The main thermal control circuits 31 and the backup thermal control circuits 32 are alternately arranged and installed on the inner bottom surface of the metal shell 1; N≥1.

[0027] Preferably, the power supply and control of each thermal control circuit are provided by different power channels, and an automatic judgment and hysteresis heating strategy is adopted. When the main thermal control circuit fails / is repaired or the temperature control is insufficient, the backup thermal control circuit can be used for heating and insulation to avoid the product function being unable to be realized due to the product temperature being too low in the shadow area. Specifically: when the temperature control sensor detects that the product temperature is lower than the set temperature A, the main thermal control circuit 31 starts heating; when the temperature control sensor detects that the product temperature is higher than the set temperature B, the main thermal control circuit 31 turns off heating. Further, when the temperature control sensor detects that the product temperature is lower than the set temperature A', or the main thermal control circuit 31 fails, the backup thermal control circuit 32 starts heating; when the temperature control sensor detects that the product temperature is higher than the set temperature B', the backup thermal control circuit 32 turns off heating. Wherein, BA>5℃, A'=A-5, B'=B-5.

[0028] In this embodiment, a plurality of high-power circuits 2 are arranged in a longitudinal array on the inner bottom surface of the metal housing 1, such as Figure 5 It should be noted that the present invention does not impose any specific restrictions on the number of high-power circuits 2 and thermal control circuits 3, and an appropriate number of high-power circuits 2 and thermal control circuits 3 can be selected and installed on the inner bottom surface of the metal shell 1 according to the situation.

[0029] In this embodiment, the thermal protection device is connected to the cabin through the metal shell 1 to achieve heat transfer with the surface of the cabin.

[0030] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

[0031] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. A thermal protection device suitable for high-power equipment outside the spacecraft cabin, characterized in that: include: Metal casing (1), high-power circuit (2) and thermal control circuit (3); The high-power circuit (2) and the thermal control circuit (3) are arranged inside the metal shell (1) and installed on the inner bottom surface of the metal shell (1); The outer surfaces of the four side walls of the metal shell (1) are coated with multiple layers of heat insulating material (4) to achieve thermal isolation from the outside; The inner bottom surface of the metal shell (1) is coated with black paint (11), and the outer surface of the top plate of the metal shell (1) is coated with white thermal control paint (12).

2. The thermal protection device for high-power equipment outside the spacecraft according to claim 1, characterized in that: A plurality of thermal control circuits (3) are arranged in a horizontal array on the inner bottom surface of the metal shell (1).

3. The thermal protection device for high-power equipment outside the spacecraft according to claim 2, characterized in that: The number of thermal control circuits (3) is 2N, including: N main thermal control circuits (31) and N backup thermal control circuits (32); wherein the main thermal control circuits (31) and the backup thermal control circuits (32) are alternately arranged and installed on the inner bottom surface of the metal shell (1); N≥1.

4. The thermal protection device for high-power equipment outside the spacecraft according to claim 3 is characterized in that: The power supply and control of each thermal control circuit (3) are provided by different power channels, and an automatic judgment and hysteresis heating strategy is adopted.

5. The thermal protection device for high-power equipment outside the spacecraft according to claim 4, characterized in that: When the temperature control sensor detects that the product temperature is lower than the set temperature A, the main thermal control circuit (31) starts heating; when the temperature control sensor detects that the product temperature is higher than the set temperature B, the main thermal control circuit (31) turns off heating; wherein BA>5°C.

6. The thermal protection device for high-power equipment outside the spacecraft according to claim 4, characterized in that: When the temperature control sensor detects that the product temperature is lower than the set temperature A', or the main thermal control circuit (31) fails, the backup thermal control circuit (32) starts heating; when the temperature control sensor detects that the product temperature is higher than the set temperature B', the backup thermal control circuit (32) turns off heating; wherein A'=A-5, B'=B-5.

7. The thermal protection device for high-power equipment outside the spacecraft according to claim 1, characterized in that: A plurality of high-power circuits (2) are arranged in a longitudinal array on the inner bottom surface of the metal housing (1).

8. The thermal protection device for high-power equipment outside the spacecraft according to claim 1, characterized in that: The thermal protection device is connected to the cabin body through the metal shell (1) to achieve heat transfer with the cabin body surface.

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