Heat pipe and folding and unfolding truss integrated device for thermal protection of spacecraft and thermal protection method of heat pipe and folding and unfolding truss integrated device

Abstract

The invention relates to the technical field of power electronics, and discloses a heat pipe and folding and unfolding truss integrated device for spacecraft thermal protection, which comprises a pair of chassis, the pair of chassis is connected through a symmetrical connecting plate, sliding chute seats are fixed on the pair of chassis, and limiting grooves are formed in the sliding chute seats; the device further comprises a folding and unfolding deformation mechanism, one end of the folding and unfolding deformation mechanism is fixed to one end of the limiting groove, the other end of the folding and unfolding deformation mechanism slides in the limiting groove, the two ends of the folding and unfolding deformation mechanism are connected through a base reset spring made of SMA, and in the sliding process of the folding and unfolding deformation mechanism, the folding and unfolding deformation mechanism can be unfolded and folded. The base plate, the symmetrical connecting plates, the sliding groove bases and the folding and unfolding deformation mechanisms are all designed to be of heat pipe cavity structures, liquid absorption cores are sintered on the surfaces of the inner walls of the heat pipe cavity structures, and the heat pipe cavity structures are filled with liquid heat exchange working media. Compared with the prior art, the heat pipe and the folding and unfolding truss are integrally designed, so that the unification of structural bearing and thermal control functions is realized.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of spacecraft vapor-liquid phase change heat transfer, and in particular to a heat pipe and foldable truss integrated device for spacecraft thermal protection and a thermal protection method thereof. BACKGROUND

[0002] During the on-orbit flight of a spacecraft, it is long-term exposed to complex thermal environments such as solar radiation, earth albedo and deep space cold source, and its external structure and load will be subjected to frequent thermal cycles. In particular, in the unfolded truss mechanism, the large-area lightweight rods and connecting hinges are exposed to the space environment, which is prone to problems such as large temperature gradient and significant thermal deformation. Such temperature difference not only affects the mechanical properties and deployment reliability of the truss, but also may reduce the accuracy and stability of the load-carrying equipment such as antennas, optical instruments and infrared detectors.

[0003] To solve the thermal environment problem of the spacecraft, high-efficiency heat transfer elements such as heat pipes, flat plate heat pipes and ring heat pipes are generally used in the prior art to construct a passive thermal control system. These heat pipe devices can quickly transfer heat and equalize temperature without consuming additional energy, and are widely used in the heat dissipation of satellite electronic devices, infrared sensors and power modules. However, the current heat pipes are mostly installed in the form of independent accessories on the surface or inside of the spacecraft structure, and are designed separately from the foldable truss mechanism. This approach has the following disadvantages: 1. Insufficient thermal control capability — traditional trusses are purely mechanical structures that lack effective heat conduction and dissipation paths, making it difficult to meet the requirements of sensors, antennas or optical elements for an isothermal environment; 2. Low integration level: current foldable trusses are mostly purely mechanical load-bearing structures, and the thermal control system is usually installed on the truss using independent thermal insulation structures or thermal insulation coatings, resulting in low system integration level and additional weight and volume of the spacecraft. 3. Discontinuous thermal control: most existing heat pipe-based heat management devices are applied to electronic devices or internal panels of the spacecraft, and lack the ability to be deployed synchronously with the foldable member, resulting in interrupted or inefficient heat transfer paths after the truss is deployed; 4. Poor thermal-mechanical coupling: the rods and hinges of the truss are prone to temperature difference stress under space thermal cycling, and traditional separate thermal control means are difficult to solve problems such as hinge jamming and uneven thermal expansion and contraction.

[0004] Therefore, heat pipes or heat sinks are attached to the foldable truss of the spacecraft to provide limited heat dissipation function after the truss is deployed. Although this scheme can improve the thermal environment to some extent, the thermal control system and the structure system are still independent of each other, making it difficult to achieve true integrated design, and there are still obvious deficiencies in weight, volume and reliability. SUMMARY

[0005] Invention purposes: In view of the problems in the prior art, the application provides a heat pipe and folding truss integrated device for spacecraft thermal protection and a thermal protection method thereof. The heat pipe and folding truss are integrated designed, the related structure of the folding truss is designed in the form of a heat pipe, the folding deformation mechanism can form a continuous and efficient heat transfer channel while being unfolded, the unity of structure bearing and thermal control functions is realized, the installation of additional thermal control components is reduced, and the system integration is improved.

[0006] Technical scheme: The application provides a heat pipe and folding truss integrated device for spacecraft thermal protection, which comprises a pair of chassis, a pair of chassis is connected through a symmetrical connecting plate, a pair of the chassis is fixed with a sliding groove seat, and the sliding groove seat is provided with a limiting groove; the device further comprises a folding deformation mechanism, one end of the folding deformation mechanism is fixed to one end of the limiting groove, the other end of the folding deformation mechanism slides in the limiting groove, the two ends of the folding deformation mechanism are connected through a base reset spring made of SMA shape memory alloy, and the folding deformation mechanism can be unfolded and contracted during the sliding process; the chassis, the symmetrical connecting plate, the sliding groove seat and the related components of the folding deformation mechanism are all heat pipe cavity structures, the inner wall surface of the heat pipe cavity structure is sintered with a liquid absorbing core, and the heat pipe cavity structure is filled with a liquid heat exchange working medium.

[0007] Further, the lower surface of the chassis is fixed with an adhesive, the chassis and the high-heat wall surface are fixed through the adhesive, and the chassis and the high-heat surface are coated with a heat-conducting silicone grease.

[0008] Further, the device further comprises a response reset mechanism, the response reset mechanism comprises a front base, a contact top rod, a rotary transmission rod, and a contact reset spring, the front base is connected to the chassis through a connecting rod, a transmission support rod is further connected between the base and the chassis, the rotary transmission rod is rotationally connected to the transmission support rod, the contact top rod is fixed to one end of the rotary transmission rod, and the other end of the rotary transmission rod is connected to the front base through the contact reset spring.

[0009] Further, the front base, the contact top rod, the rotary transmission rod, the connecting rod, and the transmission support rod are all designed as heat pipe cavity structures.

[0010] Further, the folding deformation mechanism comprises a fixed base, a groove reciprocating base, a space motion base, a base connecting rod, and a heat dissipation unfolding surface, the fixed base is fixed to one end of the limiting groove, the groove reciprocating base slides in the limiting groove, and the fixed base and the groove reciprocating base are connected through the base reset spring; a pair of the base connecting rods are rotationally connected between the fixed base and the groove reciprocating base, between the groove reciprocating base and the space motion base, and between the fixed base and the space motion base, a pair of the base connecting rods are rotationally connected between them, and the heat dissipation unfolding surface is fixed on the triangular space formed by a plurality of the base connecting rods.

[0011] Further, one end of the pair of base connecting rods close to each other is provided with a rotating base, and the lower ends of the pair of rotating bases are rotationally connected, and the upper ends of the pair of rotating bases are oppositely arranged.

[0012] Further, a spherical groove is arranged in the rotating base, a space connecting rod with a ball head is rotationally connected in the spherical groove, the other end of the space connecting rod is rotationally connected with the other end of an adjacent space connecting rod, and a plurality of space connecting rods divide the triangular space into four small triangular spaces.

[0013] Further, the base connecting rod, the space connecting rod, the fixed base, the channel reciprocating base, the space moving base and the rotating base are designed as heat pipe cavity structures, and the contact surfaces of the sliding groove seat and the fixed base, the channel reciprocating base and the lower surface of the space moving base are coated with heat-conducting silicone grease.

[0014] Further, the heat pipe cavity structure comprises an internally hollow cavity, a liquid absorbing core is arranged on the inner wall of the cavity, and a heat exchange working medium is arranged in the liquid absorbing core.

[0015] The application also discloses a heat protection method of the heat pipe and the foldable truss integrated device for spacecraft heat protection. Step 1: the bottom plate of the space heat dissipation heat protection device is fixed to the high-heat wall surface through adhesive glue, the heat exchange working medium in the heat pipe cavity structure of the bottom plate is accumulated at the bottom of the bottom plate, heat is conducted through the shell of the bottom plate and reaches the steam cavity, the liquid working medium is converted into gaseous state, and the heat is taken away and transferred to the sliding groove seat position; Step 2: after the bottom end of the sliding groove seat is heated, heat is transferred to the base reset spring position under the action of the heat pipe cavity structure of the sliding groove seat, and after the base reset spring is heated, the foldable deformation mechanism is driven to slide and expand in the limiting groove. Step 3: heat passes through the heat pipe cavity structure of the foldable deformation mechanism, reaches the heat dissipation expansion surface, and is transferred to the environment by radiation heat exchange.

[0016] Advantages:

[0017] 1. The heat pipe and foldable truss integrated design of the present application: the heat pipe is directly used as a component of the truss rod or truss panel, rather than being attached, which has the functions of bearing and heat conduction. The foldable deformation mechanism designed in the present application completes the expansion and contraction of the foldable truss. During expansion and contraction, the base reset spring made of SMA shape memory alloy is used to achieve expansion and contraction. The base reset spring expands under heat, driving the foldable deformation mechanism to slide and expand in the sliding groove seat. After heat dissipation, the base reset spring returns to its original state when it is cooled, and the foldable deformation mechanism slides and contracts in the sliding groove seat. By designing the chassis, symmetrical connecting plate, sliding groove seat and foldable deformation mechanism as heat pipe cavity structures, the excellent isothermal performance and heat dissipation capacity of the heat pipe are used to improve the temperature uniformity of the truss in complex space environments, reduce the influence of thermal gradient on the structural stability and deployment reliability, reduce the installation of additional thermal control components, and improve the system integration, thereby realizing the lightweight, modular and high-reliability spacecraft thermal protection and structure collaborative design scheme.

[0018] 2. The foldable deformation mechanism designed in the present application can expand and contract, and form a large-area, continuous heat dissipation network when expanded. In the contracted state, it occupies a small volume and does not affect the functional stability of the heat pipe. In the process of application in spacecraft, in the strong radiation and alternating cold and hot orbital environment, the temperature uniformity of the truss itself and the thermal protection of sensitive components are realized.

[0019] 3. The lower surface of the chassis designed in the present application can be fixed to a high-temperature hot surface by adhesion, and in order to reduce the contact thermal resistance, a heat-conducting silicone grease is applied between them. It can realize heat dissipation while facilitating the disassembly and installation of the integrated device.

[0020] 4. The present application designs a response reset mechanism based on the integrated device. In the process of thermal protection, the ball-shaped structure of the contact top rod is lower than the chassis in the initial state. When the ball-shaped structure of the contact top rod touches the wall, the rotary transmission rod starts to rotate, and the contact reset spring is gradually compressed. At this time, the integrated device and the high-temperature wall surface are fixed to the surface by adhesion, and the contact reset spring is always in a compressed state. When it is necessary to remove the integrated device, the adhesion between the chassis and the high-temperature wall surface is removed, and the chassis and the front base structure are separated from the high-temperature wall surface under the action of the contact reset spring, and the removal is completed.

[0021] 5. The components of the response reset mechanism designed in the present application are also designed as heat pipe cavity structures to improve the heat transfer efficiency.

[0022] 6、The folding and unfolding deformation mechanism designed in the application realizes the unfolding and folding of the mechanism through the mode of "elongation of the base reset spring caused by heating and contraction of the base reset spring caused by cooling". The unfolding process is realized through six base connecting rods, and the six base connecting rods form a triangular structure during unfolding. The heat dissipation unfolding surface arranged between the mechanisms can change the heat dissipation area from "the local hot spot of the contact surface between the chassis and the high-heat wall surface" to "the heat dissipation unfolding surface" when completely unfolded, thereby realizing the purpose of increasing the heat dissipation area.

[0023] 7、The base connecting rod in the application is connected, and the connecting end between the two base connecting rods rotates when the base reset spring contracts, the two sides gradually approach to change from the unfolded state to the folded state, and a spherical groove is arranged in the rotating base connected by the two, a space connecting rod with a ball head is arranged to be rotationally connected in the spherical groove, a spherical hinge is formed, and the space formed by the base connecting rod is converted into multiple small triangles, so that the heat dissipation unfolding surface is arranged. Moreover, the parts of the folding and unfolding deformation mechanism are designed as heat pipe cavity structures, which do not affect the heat protection of the overall equipment.

[0024] 8、The heat pipe cavity structure designed in the application is under the action of gravity, the heat exchange working medium in the heat pipe cavity accumulates at the bottom, the heat is conducted to the steam cavity through the shell, the liquid working medium is converted into gaseous state, and the heat is taken away and transferred to the upper position, so that rapid heat dissipation is realized. The liquid working medium in different heat pipe cavities flows back to the initial position under the action of the wick, and the overall heat exchange process of the device is a dynamic heat exchange process. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1 It is a schematic view of the heat pipe and folding and unfolding truss integrated device of the folding and unfolding deformation mechanism in the application in the folded state. Figure 2 It is a schematic view of the heat pipe and folding and unfolding truss integrated device of the folding and unfolding deformation mechanism in the application in the unfolded state. Figure 3 It is a schematic view of the heat pipe and folding and unfolding truss integrated device of the folding and unfolding deformation mechanism in the application in the unfolded state. Figure 2 It is a schematic view of the heat pipe and folding and unfolding truss integrated device of the folding and unfolding deformation mechanism in the application in the unfolded state. Figure 4 It is a schematic view of the heat pipe and folding and unfolding truss integrated device of the folding and unfolding deformation mechanism in the application in the unfolded state. Figure 5 It is a schematic view of the heat pipe and folding and unfolding truss integrated device of the folding and unfolding deformation mechanism in the unfolded state.

[0026] Wherein, 1-contact top rod, 2-convolution transmission rod, 3-contact reset spring, 4-front base, 5-transmission support rod, 6-connecting rod, 7-chassis, 8-limiting groove, 9-symmetrical connecting plate, 10-slotted seat, 11-fixed base, 12-slotted reciprocating base, 13-space movement base, 14-base connecting rod, 15-space connecting rod, 16-heat dissipation unfolding surface, 17-base reset spring, 18-cavity, 19-liquid absorbing core, 20-heat exchange working medium, 21-rotary base. DETAILED DESCRIPTION

[0027] The application will be further described below with reference to the drawings. The following examples are only used to more clearly illustrate the technical solutions of the application, and cannot be used to limit the protection scope of the application.

[0028] The application discloses a heat pipe and folding truss integrated device for thermal protection of a spacecraft, which is shown in Figures 1-5 , and includes a pair of chassis 7, the pair of chassis 7 are connected through a symmetrical connecting plate 9, the pair of chassis 7 are both fixed with a slotted seat 10, and the slotted seat 10 is provided with a limiting groove 8; the device also includes a folding deformation mechanism, one end of the folding deformation mechanism is fixed to one end of the limiting groove 8, and the other end of the folding deformation mechanism slides in the limiting groove 8, the two ends of the folding deformation mechanism are connected through a base reset spring 17 made of SMA shape memory alloy, and the folding deformation mechanism realizes unfolding and contraction in the sliding process; the chassis 7, the symmetrical connecting plate 9, the slotted seat 10 and the folding deformation mechanism are all designed as heat pipe cavity structures. In actual use, the lower surface of the chassis 7 is fixed with an adhesive, the chassis 7 and a high-heat wall surface are fixed through the adhesive, and the chassis 7 and the high-heat wall surface are also coated with a heat-conducting silicone grease.

[0029] The heat pipe and folding truss integrated device also includes a response reset mechanism, the response reset mechanism includes a front base 4, a contact top rod 1, a convolution transmission rod 2 and a contact reset spring 3, the front base 4 is connected with the chassis 7 through a connecting rod 6, and a transmission support rod 5 is further connected between the front base 4 and the chassis 7, the convolution transmission rod 2 is rotationally connected to the transmission support rod 5, the contact top rod 1 is fixed to one end of the convolution transmission rod 2, and the other end of the convolution transmission rod 2 is connected to the front base 4 through the contact reset spring 3. The front base 4, the contact top rod 1, the convolution transmission rod 2, the connecting rod 6 and the transmission support rod 5 are all designed as heat pipe cavity structures.

[0030] In this embodiment, the response reset mechanism is designed. When the integrated device is used, the chassis 7 is pressed and fixed on the high-temperature wall surface together with the front base 4. When the front base 4 is pressed, the contact top rod 1 contacts the wall surface, and after being stressed, it drives the rotary transmission rod 2 to rotate on the transmission support rod 5, and the contact reset spring 3 is deformed, and the complete adhesion of the front base 4 and the chassis 7 is completed. When the device needs to be removed, after the adhesive of the chassis 7 is removed, under the restoring force of the contact reset spring 3, the contact top rod 1 extrudes the high-temperature wall surface, so that the front base 4 is lifted, and the device is removed.

[0031] Referring to Figure 1 and Figure 2 , the folding and unfolding deformation mechanism includes a fixed base 11, a channel reciprocating base 12, a space movement base 13, a base connecting rod 14, and a heat dissipation unfolding surface 16. The fixed base 11 is fixed to one end of the limiting groove 8, the channel reciprocating base 12 is located in the limiting groove 8 and slides, and the fixed base 11 and the channel reciprocating base 12 are connected by a base reset spring 17. Between the fixed base 11 and the channel reciprocating base 12, between the channel reciprocating base 12 and the space movement base 13, and between the fixed base 11 and the space movement base 13, a pair of base connecting rods 14 are rotatably connected. A pair of base connecting rods 14 are rotatably connected between them, and a plurality of base connecting rods 14 form a triangular space on which the heat dissipation unfolding surface 16 is fixed. Referring to Figure 2 , Figure 2 In order to make the image clear and explicit, only the heat dissipation unfolding surface 16 in one side of the folding and unfolding deformation mechanism is drawn, and the heat dissipation unfolding surface 16 in the other side of the folding and unfolding deformation mechanism is also arranged.

[0032] One end of the pair of base connecting rods 14 close to each other is provided with a rotating base 21, and the lower end of the pair of rotating bases 21 is rotatably connected, and the upper end is arranged opposite to each other, thereby forming a limiting hinge. The design of the limiting hinge makes the pair of base connecting rods 14 only rotate upward to form an inverted triangle. A spherical groove is arranged in the rotating base 21, and a space connecting rod 15 with a ball head is rotatably connected in the spherical groove. The other end of the space connecting rod 15 is rotatably connected with the other end of the adjacent space connecting rod 15, and a plurality of space connecting rods 15 divide the triangular space into four small triangular spaces. When the rotating base 21 drives the pair of base connecting rods 14 to rotate, the space connecting rod 15 with a ball head in the rotating base 21 also rotates in the rotating base 21. The base connecting rod 14, the space connecting rod 15, the fixed base 11, the channel reciprocating base 12, the space movement base 13, and the rotating base 21 are all designed as heat pipe cavity structures, and the contact surface of the sliding groove seat 10 and the fixed base 11, the channel reciprocating base 12, and the lower surface of the space movement base 13 are coated with thermal conductive silicone grease.

[0033] In actual use, because the chassis 7 and the front base 4 are adhered to the high-temperature wall surface, the temperature is transmitted to the base reset spring 17, because the base reset spring 17 is made of SMA shape memory alloy, which expands under the action of high temperature, the base reset spring 17 drives the groove reciprocating base 12 to slide in the limiting groove 8 to the direction close to the front base 4, in the sliding process, the two base connecting rods 14 between the groove reciprocating base 12 and the fixed base 11 slowly change into a straight line state, the length of the two base connecting rods 14 is just matched with the length of the limiting groove 8, the groove reciprocating base 12 slides to the end of the limiting groove 8, and the two base connecting rods 14 are just fully expanded. In the expansion process, the two base connecting rods 14 between the groove reciprocating base 12 and the space motion base 13 and between the fixed base 11 and the space motion base 13 are also expanded into a straight line state, and the six base connecting rods 14 form a triangular structure, so that the folding and unfolding deformation mechanism is in an expanded state, and in the expansion process, the plurality of space connecting rods 15 are also in an expanded state, see Figure 2 .

[0034] When the high-temperature wall surface temperature decreases, the base reset spring 17 is not in a high-temperature state, and then returns to the original state, the groove reciprocating base 12 slides in the limiting groove 8 to the direction close to the fixed base 11, and the three pairs of base connecting rods 14 are rotated under the rotation of the rotating base 21, so that the folding and unfolding deformation mechanism is in a folded state.

[0035] The above heat pipe cavity structure includes an internal hollow cavity 18, the inner wall of the cavity 18 is provided with a liquid absorption core 19, and the liquid absorption core 19 is provided with a heat exchange working medium 20.

[0036] In actual use, the heat pipe cavity structure can make the liquid absorption core 19 maintain a wet state under low heat load. Under high heat power, the heat pipe cavity may have a dry-out phenomenon due to too high heat flux, which can be solved by optimizing the arrangement of the liquid absorption core 19 and the filling amount of the heat exchange working medium 20.

[0037] Based on the above integrated device, the heat protection method includes the following steps: a. The integrated device is used as a passive opening device for aviation high-heat flux surface heat dissipation. When the contact top rod 1 contacts the high-temperature wall surface, the chassis 7 contacts the high-temperature wall surface, the inside of the chassis 7 is a heat pipe cavity structure, and under the action of gravity, the heat exchange working medium 20 in the heat pipe cavity accumulates at the bottom of the chassis 7. After heat conduction through the shell of the chassis 7, the liquid working medium is converted into a gaseous state, and the heat is taken away and transferred to the limiting groove 8 position of the chute seat 10.

[0038] b. The device is fully opened, and the heat exchange device works stably: when the contact top rod 1 reaches the limit position, the front base 4 and the chassis 7 are fully contacted with the high-temperature wall surface, and under high-temperature conditions, the base reset spring 17 is heated, and the folding and unfolding deformation mechanism is fully opened as shown inFigure 2 The bottom plate 7 and the high-temperature wall are fixed by adhesive. The bottom plate 7 and the high-temperature wall are coated with thermal conductive silicone grease to reduce the contact thermal resistance therebetween. When the heat exchange is stable, the gaseous working medium accumulates in the heat pipe cavity near the limiting groove 8. The limiting groove 8 and the fixed base 11 and the groove reciprocating base 12 are coated with thermal conductive silicone grease to reduce the thermal resistance. After the heat reaches the heat dissipation development surface 16, it is transferred to the environment by radiation heat exchange. The radiation heat exchange causes the overall temperature of the device to decrease, and the gaseous working medium becomes liquid due to cooling. The liquid working medium in different heat pipe cavities returns to the initial position under the action of the wick 19 and repeats the heat exchange, and the overall heat exchange process is a dynamic heat exchange process.

[0039] c. A plurality of temperature measuring thermocouples are arranged on the high-temperature wall and the bottom plate 7 to detect the temperature. When the detection temperatures of all the thermocouples are lower than the set early warning temperature, the prompter connected with the thermocouples gives a prompt of the completion of heat dissipation. This facilitates the removal of the integrated device by the staff in the later stage or by the automatic mechanical way, which is not the focus of the protection of the present application and is not described here. The heat exchange process stops, and the working medium in the heat pipe cavities of different components returns to the original state, and the components of the fold and expansion deformation mechanism return to the original state under the action of the base resetting spring 17.

[0040] The above embodiments are only for illustrating the technical concept and characteristics of the present application, the purpose of which is to enable those skilled in the art to understand the content of the present application and implement it, and cannot limit the protection scope of the present application. Any equivalent transformation or modification made according to the spirit and essence of the present application should be covered within the protection scope of the present application.

Claims

1. A heat pipe and deployable truss integrated device for thermal protection of a spacecraft, characterized by, The application relates to a heat pipe cavity structure, which comprises a pair of bottom plates (7) connected through symmetrical connecting plates (9), a sliding groove seat (10) fixed on each of the pair of bottom plates (7), and a limiting groove (8) arranged on the sliding groove seat (10); the heat pipe cavity structure further comprises a folding and unfolding deformation mechanism, one end of the folding and unfolding deformation mechanism is fixed to one end of the limiting groove (8), the other end of the folding and unfolding deformation mechanism slides in the limiting groove (8), the two ends of the folding and unfolding deformation mechanism are connected through a base reset spring (17) made of SMA shape memory alloy, and the folding and unfolding deformation mechanism realizes unfolding and contraction during the sliding process; the bottom plate (7), the symmetrical connecting plate (9), the sliding groove seat (10) and the relevant components of the folding and unfolding deformation mechanism are all heat pipe cavity structures, the inner wall surface of the heat pipe cavity structure is sintered with a liquid absorbing core (19), and the heat pipe cavity structure is filled with liquid heat exchange working medium (20).

2. The integrated heat pipe and deployable truss system for thermal protection of a spacecraft of claim 1, wherein, The lower surface of the bottom plate (7) is fixed with adhesive glue, the bottom plate (7) is fixed with a high-heat wall surface through the adhesive glue, and the bottom plate (7) and the high-heat wall surface are further coated with heat-conducting silicone grease.

3. The integrated heat pipe and deployable truss system for thermal protection of spacecraft of claim 1, wherein, The heat pipe cavity structure further comprises a response reset mechanism, the response reset mechanism comprises a front base (4), a contact top rod (1), a rotary transmission rod (2) and a contact reset spring (3), the front base (4) is connected with the bottom plate (7) through a connecting rod (6), a transmission support rod (5) is further connected between the front base (4) and the bottom plate (7), the rotary transmission rod (2) is rotationally connected to the transmission support rod (5), the contact top rod (1) is fixed to one end of the rotary transmission rod (2), and the other end of the rotary transmission rod (2) is connected to the front base (4) through the contact reset spring (3).

4. The integrated heat pipe and deployable truss system for thermal protection of a spacecraft of claim 3, wherein, The front base (4), the contact top rod (1), the rotary transmission rod (2), the connecting rod (6) and the transmission support rod (5) are all designed as heat pipe cavity structures.

5. The integrated heat pipe and deployable truss system for thermal protection of spacecraft of claim 1, wherein, The folding and unfolding deformation mechanism comprises a fixed base (11), a groove reciprocating base (12), a space movement base (13), a base connecting rod (14) and a heat dissipation unfolding surface (16), the fixed base (11) is fixed to one end of the limiting groove (8), the groove reciprocating base (12) slides in the limiting groove (8), and the fixed base (11) and the groove reciprocating base (12) are connected through the base reset spring (17); a pair of the base connecting rods (14) are rotationally connected between the fixed base (11) and the groove reciprocating base (12), between the groove reciprocating base (12) and the space movement base (13) and between the fixed base (11) and the space movement base (13), a pair of the base connecting rods (14) are rotationally connected between them, and the heat dissipation unfolding surface (16) is fixed on the triangular space formed by the plurality of base connecting rods (14).

6. The integrated heat pipe and deployable truss system for thermal protection of a spacecraft of claim 5, wherein, One end of each of the pair of base connecting rods (14) close to each other is provided with a rotating base (21), and the lower ends of the pair of rotating bases (21) are rotationally connected, and the upper ends thereof are oppositely arranged, so as to form a limiting hinge.

7. The integrated heat pipe and deployable truss for thermal protection of a spacecraft of claim 6, wherein, The rotating base (21) is provided with a spherical recess, the spherical recess is rotatably connected with a space connecting rod (15) with a ball head, the other end of the space connecting rod (15) is rotatably connected with the other end of the adjacent space connecting rod (15), and the plurality of space connecting rods (15) divide the triangular space into four small triangular spaces.

8. The integrated heat pipe and deployable truss for thermal protection of a spacecraft of claim 7, wherein, The base connecting rod (14), the space connecting rod (15), the fixed base (11), the channel reciprocating base (12), the space movement base (13) and the rotating base (21) are designed as heat pipe cavity structures, and the contact surface of the sliding groove seat (10) and the fixed base (11), the channel reciprocating base (12) and the lower surface of the space movement base (13) are coated with heat-conducting silicone grease.

9. The integrated heat pipe and deployable truss system for thermal protection of spacecraft of any of claims 1-8, wherein, The heat pipe cavity structure comprises an internally hollow cavity (18), the inner wall of the cavity (18) is provided with a liquid absorbing core (19), and the liquid absorbing core (19) is provided with a heat exchange working medium (20).

10. A method of thermal protection based on the integrated device of claim 1, characterized in that, The method comprises the following steps: Step 1: The bottom plate (7) of the space heat dissipation heat protection device is fixed with the high heat wall surface through adhesive, the heat exchange working medium (20) in the heat pipe cavity structure of the bottom plate (7) is accumulated at the bottom of the bottom plate (7), heat is conducted through the shell of the bottom plate (7) to reach the steam cavity, the liquid working medium is changed into gaseous state, and the heat is taken away and transferred to the sliding groove seat (10) position; Step 2: After the bottom end of the sliding groove seat (10) is heated, the heat is transferred to the base reset spring (17) position under the action of the heat pipe cavity structure of the sliding groove seat (10), after the base reset spring (17) is heated, the folding and unfolding deformation mechanism is driven to slide and unfold in the limiting groove (8); Step 3: After the heat passes through the heat pipe cavity structure of the folding and unfolding deformation mechanism, reaches the heat dissipation unfolding surface (16) and is transferred to the environment by the way of radiation heat exchange.

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