Self-recognition heat radiator for panel satellite and assembling and using method of self-recognition heat radiator

Abstract

The invention provides a self-recognition heat radiator for a panel satellite and an assembling and using method of the self-recognition heat radiator, and belongs to the technical field of thermal control of space products. The problem that an existing panel satellite is poor in heat dissipation capacity is solved. The radiation cooling device comprises a plurality of radiation cooling plates which are sequentially connected through hinge assemblies, in the folded state, the adjacent radiation cooling plates are perpendicularly arranged, the radiation cooling plates are curled inwards layer by layer, the adjacent radiation cooling plates are connected through heat conduction films, and the radiation cooling plates comprise the first radiation cooling plate, the second radiation cooling plates and the third radiation cooling plate; one end of the first radiation cooling plate is connected with the side edge of the flat plate satellite, the other end of the first radiation cooling plate is connected with the second radiation cooling plates, the multiple second radiation cooling plates are connected in sequence, the third radiation cooling plate is connected with the second radiation cooling plates, an expansion breaking device is arranged between the first radiation cooling plate and the second radiation cooling plates, the first radiation cooling plate is connected with a surface-mounted heat pipe, and the surface-mounted heat pipe is connected with the flat plate satellite. And the surface-mounted heat pipe is connected with the cabin plate embedded heat pipe. The heat dissipation device is mainly used for heat dissipation of flat satellites.

Description

Technical Field

[0001] The invention belongs to the technical field of thermal control of space products, and in particular relates to a self-identifying thermal radiator for a flat-panel satellite and an assembly and use method thereof. Background Art

[0002] In recent years, flat-panel satellites have gradually become an important configuration choice for communication satellites and synthetic aperture radar satellites due to their advantages such as light weight, large installation surface, and stackable launch. This type of satellite greatly reduces the weight and volume of the entire satellite while meeting the installation requirements of large-size payloads.

[0003] As the heat consumption of the payload continues to increase, the heat dissipation of flat-panel satellites has gradually become a problem. Traditional satellites usually use their own cabin panels as radiators to achieve heat exchange with the space environment. However, flat-panel satellites have a compact layout and can be roughly regarded as two-dimensional satellites. The number and size of cabin panels that can be used for heat dissipation are limited. Therefore, when the heat consumption of the payload increases to a certain extent, it is necessary to meet its thermal control needs through new thermal control measures.

[0004] At present, alternative measures include deployable radiators and fluid loop radiators. The deployable radiator is folded on the surface of the satellite during the launch phase, and is unfolded after the satellite enters orbit to increase the heat dissipation surface to meet thermal control requirements. However, for two-dimensional flat-panel satellites, it is difficult to have enough space for the two cabin panels to be used for the folding and fixing of the deployable radiator while meeting the requirements of the payload, solar wing and platform equipment layout. The fluid loop radiator adopts active thermal control. The working fluid circulates under the drive of the pump, while absorbing and dissipating heat to dissipate and distribute heat. However, the fluid loop radiator has a complex composition, high cost, and low reliability. It will also increase the weight and power consumption of the satellite, and will produce micro-vibrations when the pump is working, affecting the accuracy of satellite attitude control. Summary of the invention

[0005] In view of this, the present invention aims to propose a self-identifying thermal radiator for a flat-panel satellite and an assembly and use method thereof, so as to solve the problem of poor heat dissipation capacity of existing flat-panel satellites.

[0006] To achieve the above-mentioned purpose, the present invention adopts the following technical scheme: a self-identifying heat radiator for a flat-panel satellite, comprising a plurality of radiant cooling plates connected in sequence by a hinge assembly, wherein in a folded state, adjacent radiant cooling plates are arranged vertically, and the plurality of radiant cooling plates are curled inward layer by layer, and the adjacent radiant cooling plates are connected by a heat-conducting film, and the plurality of radiant cooling plates comprise a first radiant cooling plate, a plurality of second radiant cooling plates and a third radiant cooling plate, wherein one end of the first radiant cooling plate is connected to the side of the flat-panel satellite, and the other end is connected to the second radiant cooling plate, and the plurality of second radiant cooling plates are connected in sequence, and the third radiant cooling plate is connected to the second radiant cooling plate, and an expander is arranged on the side of the flat-panel satellite, and the expander connects the first radiant cooling plate and the second radiant cooling plate, and the first A surface-mounted heat pipe is connected to the radiation cooling plate, and the surface-mounted heat pipe is connected to the heat pipe buried in the cabin plate, and the heat pipe buried in the cabin plate is arranged in the cabin plate of the flat-panel satellite. The hinge assembly includes a vortex spring, a first hinge arm, a second hinge arm and a rotating shaft. The first hinge arm and the second hinge arm are respectively connected to two adjacent radiation cooling plates, and the first hinge arm and the second hinge arm are respectively connected on both sides by a rotating shaft, the rotating shaft is rotatably connected to the first hinge arm, the rotating shaft is clamped and connected to the second hinge arm, the rotating shaft is connected to the inner vortex spring arm of the vortex spring, and the outer vortex spring arm of the vortex spring is connected to the radiation cooling plate connected to the first hinge arm. The vortex spring is formed by winding a bimetallic sheet, and the thermal expansion coefficient of the inner metal sheet along the winding direction is greater than the thermal expansion coefficient of the outer metal sheet.

[0007] Furthermore, the first radiant cooling plate has a satellite end mounting surface and a heat dissipation surface which are perpendicular to each other, the satellite end mounting surface is connected to the side of the flat-panel satellite, and the heat dissipation surface is connected to the second radiant cooling plate.

[0008] Furthermore, the satellite end mounting surface is provided with an expander mounting hole, and the second radiant cooling plate close to the satellite end mounting surface is provided with an expander fixing hole, and the expander passes through the expander mounting hole and the expander fixing hole and is fixed by a gasket and a nut.

[0009] Furthermore, the expander is a connection and separation device triggered by a shape memory alloy, and a slotted bolt is provided on the expander. The expander locks the radiant cooling plate through the slotted bolt. The expander is connected to an electric drive heater, and the memory alloy expands and breaks the slotted bolt through electric heating.

[0010] Furthermore, the first hinge arm and the second hinge arm are both provided with a radiation cooling plate mounting hole and a shaft hole, the first hinge arm and the second hinge arm are connected to the radiation cooling plate through the radiation cooling plate mounting hole, the shaft holes on the first hinge arm and the second hinge arm are aligned, and the shaft passes through the shaft hole.

[0011] Furthermore, the first hinge arm is provided with a vertical limiter and a horizontal limiter.

[0012] Furthermore, one end of the rotating shaft is a hinge end rotating shaft, and the other end is a vortex spring end rotating shaft. The ends of the hinge end rotating shaft and the vortex spring end rotating shaft are both provided with external threads, and the external threads are connected with nuts. A boss is provided between the hinge end rotating shaft and the vortex spring end rotating shaft, and the boss and the second hinge arm are both provided with teeth, and the teeth are embedded with each other. A vortex spring fixing groove is provided on the vortex spring end rotating shaft, and the inner vortex spring arm is embedded in the vortex spring fixing groove. The surface of the hinge end rotating shaft is coated with molybdenum disulfide.

[0013] Furthermore, the radiation cooling plate is an aluminum plate with heat dissipation white paint sprayed on the surface, the inner metal sheet of the vortex spring is a copper alloy sheet, and the outer metal sheet is a steel sheet, and the surface mounted heat pipe, vortex spring, first hinge arm and second hinge arm are all coated with thermal grease.

[0014] The present invention also provides an assembly method for a self-identifying thermal radiator for a flat-panel satellite, which specifically comprises: installing a first radiant cooling plate on the side surface of the flat-panel satellite, passing two expanders through the first radiant cooling plate and installing them on the side surface of the flat-panel satellite, connecting the heat pipe buried in the cabin plate with the surface-mounted heat pipe, connecting the surface-mounted heat pipe to the first radiant cooling plate, connecting all the radiant cooling plates through a hinge assembly, pasting a heat-conductive film between adjacent radiant cooling plates, and connecting the two expanders to the second radiant cooling plate.

[0015] The present invention also provides a method for using a self-identifying thermal radiator for a flat-panel satellite, the method for using the self-identifying thermal radiator comprising the following four working conditions: Working condition 1: before the flat-panel satellite enters orbit, the self-identifying thermal radiator is in a curled and folded state under the fixing action of the first radiant cooling plate and the expander. At this time, several radiant cooling plates form a closed rectangular frame, and the adjacent radiant cooling plates are perpendicular to each other. The self-identifying thermal radiator is in a locked state. After the flat-panel satellite enters orbit, the expander is broken and fixed, and the self-identifying thermal radiator is in an unlocked state. Working condition 2: When the flat-panel satellite enters the high heat consumption working mode from the orbiting mode or the low heat consumption working mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin board and unfolds. At this time, the internal heat of the flat-panel satellite is transferred to the surface heat pipe through the heat pipe buried in the cabin board, and then transferred to the vortex spring through the first radial cooling plate. The vortex spring shows an unfolding trend, and the angle between the first hinge arm and the second hinge arm gradually increases. The second radial cooling plate unfolds, and the heat is transferred to all the radial cooling plates in turn through the thermal conductive film, driving the radial cooling plates to gradually unfold in turn. After unfolding, the radial cooling plates are in the same plane. Under the action of the thermal conductive film, the radial cooling plates dissipate heat together; Working condition 3: When the flat-panel satellite enters the low heat consumption working mode from the high heat consumption working mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin plate and shrinks. At this time, the internal heat consumption of the flat-panel satellite decreases, the heat transferred to the self-identifying heat radiator decreases, and the temperature of each vortex spring decreases. Since the heat is transferred between the radiant cooling plates, the temperature of the vortex spring farther away from the flat-panel satellite decreases faster, so it curls and shrinks earlier, thereby driving the third radiant cooling plate to shrink first. The temperature continues to drop, and each vortex spring begins to shrink step by step until the adjacent radiant cooling plates are perpendicular to each other. The self-identifying heat radiator is in an overall curled and folded state. After the self-identifying heat radiator is folded, only the first radiant cooling plate and part of the outer surface of the second radiant cooling plate effectively dissipate heat; Working condition 4: When the flat-panel satellite enters the non-full-power working mode and the heat consumption is moderate, the self-identification thermal radiator automatically identifies the temperature change of the cabin and is in a semi-expanded state. The deployment process is the same as working condition 2, but due to insufficient heat, it cannot drive all the radiation cooling plates to deploy and is in a semi-expanded state. When the self-identification thermal radiator is semi-expanded, it is in a dynamic equilibrium state of heat transfer.

[0016] Compared with the prior art, the beneficial effects of the present invention are as follows: the present invention provides a self-identifying thermal radiator for a flat-panel satellite and an assembly and use method thereof, which can be compactly folded to the side of the flat-panel satellite without occupying the satellite cabin layout space while ensuring that a sufficiently large heat dissipation surface is provided after deployment, and can achieve automatic deployment and folding effects as the satellite temperature changes, and the heat dissipation surface area can be adjusted in orbit to adapt to different satellite operating conditions.

[0017] The specific advantages are as follows: (1) After being deployed, the self-identifying thermal radiator of the present invention can provide a larger area for radiation heat dissipation, which is beneficial to the heat dissipation of high-power satellites such as communication satellites and synthetic aperture radar satellites.

[0018] (2) The self-identifying thermal radiator of the present invention can be compactly folded into the narrow side of the flat-panel satellite during the launch phase, occupying a small space, thereby improving the space utilization rate of the carrier fairing.

[0019] (3) The self-identifying thermal radiator described in the present invention can self-identify the cabin temperature, thereby autonomously unfolding and retracting. When the satellite is in orbit, the state of the self-identifying thermal radiator can be automatically adjusted according to the change of the working mode to meet the heat dissipation demand.

[0020] (4) The self-identifying thermal radiator described in the present invention has a semi-expanded state. When the satellite is not working at full power, it can self-identify the temperature and adjust the expanded heat dissipation area to meet the heat dissipation demand.

[0021] (5) The self-identifying thermal radiator of the present invention can be adjusted to meet the thermal control design requirements of different satellites by selecting materials with different expansion coefficients and changing the thickness of the metal sheets on both sides to adjust the change in temperature when it is unfolded and retracted.

[0022] (6) The self-identifying thermal radiator described in the present invention is a passive thermal control measure. Except for the need to electrically drive the expander to unlock during entry into orbit, the rest of the working process does not require an increase in the power consumption of the entire satellite.

[0023] (7) The self-identifying thermal radiator of the present invention has a simple structure and high reliability, does not use a fluid circuit, and will not affect the satellite attitude control.

[0024] (8) The self-identifying thermal radiator of the present invention is locked by means of an expander and its own limiter, and the impact of unlocking is small, which has little impact on the satellite and onboard equipment.

[0025] (9) The components of the self-identifying heat radiator described in the present invention are simple in design and have low precision requirements, which can reduce processing costs, shorten processing cycles, and have low costs.

[0026] (10) The components of the self-identifying thermal radiator described in the present invention are independent of each other and can be redesigned / selected according to the specific requirements of the satellite, and the device has strong adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings: Figure 1 This is a schematic diagram of the structure of a self-identifying thermal radiator for a flat-panel satellite according to the present invention; Figure 2 This is a schematic diagram of the structure of the first radiant cooling plate of the present invention; Figure 3 This is a schematic structural diagram of the second radiant cooling plate of the present invention; Figure 4 This is a schematic diagram of the structure of the third radiant cooling plate of the present invention; Figure 5 It is a schematic diagram of the three-dimensional structure of the hinge assembly of the present invention; Figure 6 is a schematic diagram of the cross-sectional structure of the hinge assembly of the present invention; Figure 7 It is a schematic diagram of the vortex spring structure of the present invention; Figure 8 This is a schematic diagram of the structure of the first hinge arm of the present invention; Fig. 9 This is a schematic diagram of the structure of the second hinge arm of the present invention; Fig.10 This is a schematic diagram of the rotating shaft structure of the present invention; Fig.11 A schematic diagram of the hinge assembly assembly process of the present invention; Fig.12The schematic diagram of the assembly process of the self-identifying thermal radiator for flat-panel satellites according to the present invention is as follows: Figure 1 ; Fig.13 The schematic diagram of the assembly process of the self-identifying thermal radiator for flat-panel satellites according to the present invention is as follows: Figure 2 ; Fig.14 The schematic diagram of the assembly process of the self-identifying thermal radiator for flat-panel satellites according to the present invention is as follows: Figure 3 ; Fig.15 The schematic diagram of the assembly process of the self-identifying thermal radiator for flat-panel satellites according to the present invention is as follows: Figure 4 ; Fig.16 Schematic diagram of the deployment process of a self-identifying thermal radiator for a flat-panel satellite according to the present invention Figure 1 ; Fig.17 Schematic diagram of the deployment process of a self-identifying thermal radiator for a flat-panel satellite according to the present invention Figure 2 ; Fig.18 A schematic diagram of the folding process of a self-identifying thermal radiator for a flat-panel satellite according to the present invention Figure 1 ; Fig.19 A schematic diagram of the folding process of a self-identifying thermal radiator for a flat-panel satellite according to the present invention Figure 2 ; Fig. 20 This is a schematic diagram of a semi-expanded state of a self-identifying thermal radiator for a flat-panel satellite according to the present invention.

[0028] In the figure: 1-first radial cooling plate, 2-second radial cooling plate, 3-third radial cooling plate, 4-hinge assembly, 5-thermal conductive film, 6-surface mounted heat pipe, 7-expander, 8-satellite end mounting surface, 9-heat dissipation surface, 10-satellite end mounting hole, 11-expander mounting hole, 12-first hinge arm mounting hole, 13-vortex spring mounting hole, 14-heat pipe mounting hole, 15-second hinge arm mounting hole, 16-vortex spring, 17-first hinge arm, 18-second hinge arm, 19-rotating shaft, 20-outer vortex spring arm, 21-inner vortex spring arm, 22-radiative cooling plate mounting hole, 23-rotating shaft hole, 24-vertical limit, 25-horizontal limit, 26-tooth plate, 27-hinge end rotating shaft, 28-vortex spring end rotating shaft, 29-vortex spring fixing groove, 30-boss, 31-flat satellite, 32-side, 33-cabin plate. DETAILED DESCRIPTION

[0029] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely explain the technical solutions in the embodiments of the present invention. It should be noted that the embodiments of the present invention and the features in the embodiments can be combined with each other without conflict, and the described embodiments are only part of the embodiments of the present invention, not all of the embodiments.

[0030] See also Figure 1-20 The present embodiment is described, a self-identifying heat radiator for a flat-panel satellite, comprising a plurality of radiant cooling plates connected in sequence by a hinge assembly 4, wherein in a folded state, adjacent radiant cooling plates are arranged vertically, and the plurality of radiant cooling plates are curled inward layer by layer, and the adjacent radiant cooling plates are connected by a heat-conducting film 5, wherein the plurality of radiant cooling plates comprise a first radiant cooling plate 1, a plurality of second radiant cooling plates 2, and a third radiant cooling plate 3, wherein one end of the first radiant cooling plate 1 is connected to a side edge 32 of a flat-panel satellite 31, and the other end is connected to the second radiant cooling plate 2, a plurality of second radiant cooling plates 2 are connected in sequence, and the third radiant cooling plate 3 is connected to the second radiant cooling plate 2, and an expander 7 is arranged on the side edge 32 of the flat-panel satellite 31, and the expander 7 connects the first radiant cooling plate 1 and the second radiant cooling plate 2, and a surface-mounted heat pipe 6 is connected to the first radiant cooling plate 1, and the surface-mounted heat pipe 6 is connected to the first radiant cooling plate 1. The tube 6 is connected to the heat pipe buried in the cabin, and the heat pipe buried in the cabin is arranged in the cabin 33 of the flat-panel satellite 31. The hinge assembly 4 includes a vortex spring 16, a first hinge arm 17, a second hinge arm 18 and a rotating shaft 19. The first hinge arm 17 and the second hinge arm 18 are respectively connected to two adjacent radial cooling plates. The first hinge arm 17 and the second hinge arm 18 are respectively connected on both sides by the rotating shaft 19. The rotating shaft 19 is rotatably connected to the first hinge arm 17, and the rotating shaft 19 is connected to the second hinge arm 18 by clamping. The rotating shaft 19 is connected to the inner vortex spring arm 21 of the vortex spring 16, and the outer vortex spring arm 20 of the vortex spring 16 is connected to the radial cooling plate connected to the first hinge arm 17. The vortex spring 16 is formed by winding a bimetallic sheet, and the thermal expansion coefficient of the inner metal sheet along the winding direction is greater than the thermal expansion coefficient of the outer metal sheet.

[0031] The assembly method of this embodiment is as follows: the first radiant cooling plate 1 is installed on the side 32 surface of the flat-panel satellite 31, two expanders 7 are installed on the side 32 surface of the flat-panel satellite 31 through the first radiant cooling plate 1, the heat pipe buried in the cabin plate is connected to the surface heat pipe 6, the surface heat pipe 6 is connected to the first radiant cooling plate 1, all the radiant cooling plates are connected by the hinge assembly 4, the heat conductive film 5 is pasted between adjacent radiant cooling plates, and the two expanders 7 are connected to the second radiant cooling plate 2.

[0032] The method for using the self-identifying heat radiator in this embodiment includes the following four working conditions: Working condition 1: before the flat-panel satellite 31 enters orbit, the self-identifying thermal radiator is in a curled and folded state under the fixing action of the first radiant cooling plate 1 and the expander 7. At this time, a number of radiant cooling plates form a closed rectangular frame, and the adjacent radiant cooling plates are perpendicular to each other. The self-identifying thermal radiator is in a locked state. After the flat-panel satellite 31 enters orbit, the expander 7 is broken and released, and the self-identifying thermal radiator is in an unlocked state. Working condition 2: When the flat-panel satellite 31 enters the high heat consumption working mode from the orbiting mode or the low heat consumption working mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin board 33 and unfolds. At this time, the internal heat of the flat-panel satellite 31 is transferred to the surface mounted heat pipe 6 through the heat pipe buried in the cabin board, and then transferred to the vortex spring 16 through the first radial cooling plate 1. The vortex spring 16 shows an unfolding trend, and the angle between the first hinge arm 17 and the second hinge arm 18 gradually increases. The second radial cooling plate 2 unfolds, and the heat is transferred to all the radial cooling plates in turn through the heat conductive film 5, driving the radial cooling plates to gradually unfold in turn. After unfolding, the radial cooling plates are in the same plane. Under the action of the heat conductive film 5, the radial cooling plates dissipate heat together; Working condition 3: When the flat-panel satellite 31 enters the low heat consumption working mode from the high heat consumption working mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin plate 33 and shrinks. At this time, the internal heat consumption of the flat-panel satellite 31 decreases, the heat transferred to the self-identifying heat radiator decreases, and the temperature of each vortex spring 16 decreases. Since the heat is transferred between the radiant cooling plates, the temperature of the vortex spring 16 that is farther away from the flat-panel satellite 31 decreases faster, and therefore curls and shrinks earlier, thereby driving the third radiant cooling plate 3 to shrink first, and the temperature continues to drop. Each vortex spring 16 begins to shrink step by step until the adjacent radiant cooling plates are perpendicular to each other, and the self-identifying heat radiator presents an overall curled and folded state. After the self-identifying heat radiator is folded, only the outer surface of the first radiant cooling plate 1 and part of the second radiant cooling plate 2 effectively dissipates heat; Working condition 4: When the flat-panel satellite 31 enters the non-full-power working mode and the heat consumption is moderate, the self-identification thermal radiator automatically identifies the temperature change of the cabin board 33 and is in a semi-expanded state. The expansion process is the same as that of working condition 2, but due to insufficient heat, all the radiation cooling plates cannot be driven to expand and are in a semi-expanded state. When the self-identification thermal radiator is semi-expanded, it is in a dynamic equilibrium state of heat transfer.

[0033] The present embodiment will be described in detail below with reference to the accompanying drawings: like Figure 1As shown, a self-identifying heat radiator for a flat-panel satellite comprises a plurality of radiant cooling plates connected in sequence by a hinge assembly 4. In a folded state, adjacent radiant cooling plates are arranged vertically, and the plurality of radiant cooling plates are curled inward layer by layer. The adjacent radiant cooling plates are connected by a heat-conducting film 5. The plurality of radiant cooling plates comprise a first radiant cooling plate 1, a plurality of second radiant cooling plates 2 and a third radiant cooling plate 3. One end of the first radiant cooling plate 1 is connected to a side edge 32 of a flat-panel satellite 31, and the other end is connected to the second radiant cooling plate 2. The plurality of second radiant cooling plates 2 are connected in sequence, and the third radiant cooling plate 3 is connected to the second radiant cooling plate 2. An expander 7 is arranged on the side edge 32 of the flat-panel satellite 31, and the expander 7 connects the first radiant cooling plate 1 and the second radiant cooling plate 2. The first radiant cooling plate 1 is connected to a surface mounted heat pipe 6, and the surface mounted heat pipe 6 is connected to a heat pipe buried in a cabin plate.

[0034] like Figure 2 As shown, the first radiant cooling plate 1 has a satellite end mounting surface 8 and a heat dissipation surface 9 which are perpendicular to each other. The satellite end mounting surface 8 is provided with a satellite end mounting hole 10 and a breaker mounting hole 11. The satellite end mounting hole 10 is used to mount the first radiant cooling plate 1 on the side 32 surface of the flat satellite 31 through standard parts to ensure the firmness and stability of its connection. The breaker mounting hole 11 is used to connect the breaker 7. The heat dissipation surface 9 is provided with a first hinge arm mounting hole 12, a vortex spring mounting hole 13 and a heat pipe mounting hole 14. The first hinge arm mounting hole 12 is used to connect with the first hinge arm 17 to ensure that the first hinge arm 17 is accurately installed on the first radiant cooling plate 1. The vortex spring 16 is relatively fixed to the first radiant cooling plate 1 by the cooperation of its outer vortex spring arm 20 and the vortex spring mounting hole 13, and can be unfolded or curled with this point as support when the temperature changes. The heat pipe installation hole 14 is used for installing the surface mounted heat pipe 6 , and the surface mounted heat pipe 6 can transfer the heat transmitted from the heat pipe buried in the cabin plate to the first radiant cooling plate 1 .

[0035] like Figure 3 As shown, the second radiant cooling plate 2 is provided with a first hinge arm mounting hole 12, a vortex spring mounting hole 13 and a second hinge arm mounting hole 15. The functions of the first hinge arm mounting hole 12 and the vortex spring mounting hole 13 are the same as those on the first radiant cooling plate 1, and are used to connect the first hinge arm 17 and the vortex spring 16 respectively, to ensure that the second radiant cooling plate 2 can work with adjacent components during the expansion and retraction of the self-identifying thermal radiator. The second hinge arm mounting hole 15 is used to connect with the second hinge arm 18, and the first hinge arm 17 and the second hinge arm 18 are connected by the rotating shaft 19 to realize the rotatable connection between adjacent radiant cooling plates. In particular, two additional expansion device fixing holes are provided on the second radiant cooling plate 2 close to the satellite end mounting surface 8, and the expansion device 7 is fixed by a gasket and a nut after passing through the expansion device mounting hole 11 and the expansion device fixing hole. Prevent the self-identifying thermal radiator from accidentally expanding during the satellite launch process.

[0036] like Figure 4 As shown, the third radiant cooling plate 3 is provided with a second hinge arm mounting hole 15. The second hinge arm mounting hole 15 is connected to the second hinge arm 18, so that the third radiant cooling plate 3 can form a complete self-identifying heat radiator structure with other radiant cooling plates and hinge components. During the operation of the self-identifying heat radiator, the third radiant cooling plate 3, driven by the vortex spring 16 and the hinge component 4, completes the expansion and contraction actions together with other radiant cooling plates, and jointly realizes the heat dissipation function to ensure the normal operation of the self-identifying heat radiator.

[0037] All the radiant cooling plates are made of aluminum plates, among which the first radiant cooling plate 1 is formed by sheet metal from aluminum plates. Afterwards, all the radiant cooling plates are heat treated to increase their hardness. Finally, except for the contact areas and installation areas, the remaining surfaces are sprayed with heat-dissipating white paint to improve their heat dissipation efficiency. The length and thickness of all the second radiant cooling plates 2 are consistent, but the widths are slightly different. Specifically, after curling and folding, the closer the second radiant cooling plate 2 is to the inside, the narrower the width is to meet the space requirements for curling inside, so that in the folded state, each radiant cooling plate can be compactly curled layer by layer, which saves space without affecting its heat dissipation performance.

[0038] like Figure 5 and Figure 6 As shown, the hinge assembly 4 includes a vortex spring 16, a first hinge arm 17, a second hinge arm 18 and a rotating shaft 19. The first hinge arm 17 and the second hinge arm 18 are respectively connected to two adjacent radiant cooling plates. The first hinge arm 17 and the second hinge arm 18 are respectively connected on both sides by the rotating shaft 19. The rotating shaft 19 is rotatably connected to the first hinge arm 17. The rotating shaft 19 is connected to the second hinge arm 18 by snapping. The rotating shaft 19 is connected to the inner vortex spring arm 21 of the vortex spring 16. The outer vortex spring arm 20 of the vortex spring 16 is connected to the radiant cooling plate connected to the first hinge arm 17.

[0039] like Figure 7As shown, the vortex spring 16 is formed by winding a bimetallic sheet, and the thermal expansion coefficient of the inner metal sheet along the winding direction is greater than the thermal expansion coefficient of the outer metal sheet. One option is that the inner metal sheet of the vortex spring 16 is a copper alloy sheet, and the outer metal sheet is a steel sheet. The characteristics of the bimetallic sheet are: the thermal expansion coefficients of the steel sheet and the copper alloy sheet are different. When the temperature rises, the expansion of the copper alloy sheet is greater than the expansion of the steel sheet, and the bimetallic sheet as a whole will bend to the side of the steel sheet; when the temperature decreases, the contraction of the copper alloy sheet is greater than the contraction of the steel sheet, and the bimetallic sheet as a whole will bend to the side of the copper alloy sheet. Therefore, the vortex spring 16 specifically manifests as follows: when the temperature rises, the vortex spring 16 shows an expansion trend, and the angle between the outer vortex spring arm 20 and the inner vortex spring arm 21 gradually increases; when the temperature decreases, the vortex spring 16 shows a curling trend, and the angle between the outer vortex spring arm 20 and the inner vortex spring arm 21 gradually decreases. By selecting materials with different expansion coefficients and changing the thickness of the metal sheets on both sides, the change temperature and change angle of the vortex spring 16 when it is unfolded and curled can be adjusted.

[0040] like Figure 8 As shown, the first hinge arm 17 is provided with a radiation cooling plate mounting hole 22 and a shaft hole 23 , the first hinge arm 17 is connected to the radiation cooling plate through the radiation cooling plate mounting hole 22 , and the first hinge arm 17 is provided with a vertical limit 24 and a horizontal limit 25 .

[0041] like Fig. 9 As shown, the second hinge arm 18 is also provided with a radiation cooling plate mounting hole 22 and a shaft hole 23. The second hinge arm 18 is connected to the radiation cooling plate through the radiation cooling plate mounting hole 22. The second hinge arm 18 is provided with a tooth plate 26. The shaft holes 23 on the first hinge arm 17 and the second hinge arm 18 are aligned, and the shaft 19 passes through the shaft hole 23.

[0042] like Fig.10 As shown, one end of the rotating shaft 19 is a hinge end rotating shaft 27, and the other end is a vortex spring end rotating shaft 28. The ends of the hinge end rotating shaft 27 and the vortex spring end rotating shaft 28 are both provided with external threads, and the external threads are connected with nuts. A boss 30 is provided between the hinge end rotating shaft 27 and the vortex spring end rotating shaft 28, and a tooth piece 26 is provided on the boss 30. The boss 30 and the tooth piece 26 on the second hinge arm 18 are interlocked. A vortex spring fixing groove 29 is provided on the vortex spring end rotating shaft 28, and the inner vortex spring arm 21 is embedded in the vortex spring fixing groove 29, so that the vortex spring 16 can be firmly connected to the rotating shaft 19, and when the vortex spring 16 is deformed, it can drive the rotating shaft 19 to rotate. The surface of the hinge end rotating shaft 27 is coated with molybdenum disulfide to reduce friction and avoid vacuum cold welding.

[0043] The cooperation between the rotating shaft hole 23 and the rotating shaft 19 realizes the relative rotation between the first hinge arm 17 and the second hinge arm 18. The vertical limit 24 and the horizontal limit 25 play the role of motion limit in the working process of the self-identifying thermal radiator. In the folded state, the vertical limit 24 ensures that the angle between adjacent radiant cooling plates is not less than 90°, so that the self-identifying thermal radiator maintains a compact structure, which is convenient for withstanding the mechanical environment during the satellite launch stage; in the unfolding process, when the angle between the first hinge arm 17 and the second hinge arm 18 reaches 180°, the horizontal limit 25 prevents the radiant cooling plate from further unfolding, thereby locking the adjacent radiant cooling plates.

[0044] like Fig.11 As shown, the assembly process of the hinge assembly 4 is as follows: first, insert the first hinge arm 17 into the second hinge arm 18 so that the shaft hole 23 is aligned; second, the shaft 19 is passed through the shaft hole 23 from both sides in sequence, the teeth 26 are interlocked with each other, and then a nut is used to fix one side of the hinge end shaft 27; third, the vortex spring 16 is installed on the outside of the shaft 19, the inner vortex spring arm 21 is embedded in the vortex spring fixing groove 29, and then a nut is screwed into the outside of the shaft 23 to fix it. The first hinge arm 17 can rotate around the shaft 19.

[0045] In the embodiment, the thermally conductive film 5 is a flexible film of high thermal conductivity material, which has good thermal conductivity and can withstand many bending times, and can realize the heat transfer between the radiant cooling plates. The expander 7 is a type of miniature connection and separation device triggered by a shape memory alloy. The expander 7 is provided with a slotted bolt. The expander 7 locks the radiant cooling plate through the slotted bolt. The expander 7 is connected to the electric drive heater. The tubular memory alloy is expanded and the slotted bolt is broken by electric heating to achieve unlocking and separation. The surface mounted heat pipe 6, the vortex spring 16, the first hinge arm 17, and the second hinge arm 18 are all coated with thermal conductive silicone grease.

[0046] The specific assembly method of this embodiment is: The first step, such as Fig.12 As shown, the first radiant cooling plate 1 is installed on the surface of the side 32 of the flat-panel satellite 31, and two expanders 7 are installed on the surface of the side 32 through the expander mounting holes 11, and then nuts and gaskets are installed on the slotted bolts of the expanders 7. After the mounting surfaces of the embedded heat pipes in the cabin 33 of the flat-panel satellite 31 and the led-out surface-mounted heat pipes 6 are coated with thermal grease, the surface-mounted heat pipes 6 are fixed to the heat dissipation surface 9 of the first radiant cooling plate 1 through standard parts.

[0047] The second step is, Fig.13As shown, the third radial cooling plate 3 and the last second radial cooling plate 2 are connected by the hinge assembly 4, the spiral spring 16, the first hinge arm 17, the second hinge arm 18 and the structures in contact with the radial cooling plate are all coated with thermal conductive silicone grease and fixed to achieve sufficient heat conduction between each other, and the thermal conductive film 5 is pasted between the third radial cooling plate 3 and the last second radial cooling plate 2 to achieve sufficient heat conduction between the radial cooling plates; according to the above operations, the assembly between all the second radial cooling plates 2 is completed, and the assembly after completion is as shown Fig.14 shown.

[0048] The third step is Fig.15 As shown, the second-step assembly and the first-step assembly are connected by a hinge assembly 4, and then the thermal conductive film 5 is pasted between the first radiant cooling plate 1 and the first second radiant cooling plate 2 to achieve sufficient heat conduction between the radiant cooling plates; at the same time, the slotted bolts of the expander 7 pass through the expander fixing hole of the second radiant cooling plate 2 close to the satellite end mounting surface 8, and finally fixed by gaskets and nuts.

[0049] The method for using the self-identifying heat radiator described in this embodiment includes the following four working conditions: Working condition 1: Before the flat-panel satellite 31 enters orbit, the self-identifying thermal radiator is in a curled state under the fixing action of the first radiant cooling plate 1 and the expander 7. At this time, several radiant cooling plates form a closed rectangular frame. Under the action of the vertical limit 24, the angle between the first hinge arm 17 and the second hinge arm 18 cannot be less than 90°. Therefore, the adjacent radiant cooling plates are perpendicular to each other, and the self-identifying thermal radiator is in a locked state with high rigidity, which can withstand the mechanical environment of the satellite launch stage. After the flat-panel satellite 31 enters orbit, the electric drive heating causes the tubular memory alloy of the expander 7 to expand and break the slotted bolts, the self-identifying thermal radiator is unlocked, and the slotted bolts are fixed to the second radiant cooling plate 2 through gaskets and nuts to achieve a recovery effect.

[0050] Working condition 2: When the flat-panel satellite 31 enters the high heat consumption working mode from the orbiting mode or the low heat consumption working mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin plate 33 and starts to unfold. The specific process of unfolding is as follows: Fig.16 As shown, the internal heat of the flat-panel satellite 31 is transferred to the surface-mounted heat pipe 6 through the heat pipe buried in the cabin, and then transferred to the vortex spring 16 through the first radiant cooling plate 1. The vortex spring 16 shows an expansion trend, and the angle between the first hinge arm 17 and the second hinge arm 18 gradually increases from 90°, driving the radiant cooling plate to gradually expand. When the angle between the first hinge arm 17 and the second hinge arm 18 is 180°, the horizontal limit 25 prevents the hinge from further expanding, thereby locking the adjacent radiant cooling plates. At the same time, the heat is transferred to the first second radiant cooling plate 2 through the thermal conductive film 5, and the second radiant cooling plate 2 transfers the heat to the vortex spring 16 on the other side, thereby driving the next radiant cooling plate to expand. All radiant cooling plates are expanded in this way, and after expansion, the self-identification heat radiator state is as follows Fig.17After the self-identifying heat radiator is unfolded, each radiant cooling plate is in the same plane, and under the action of the heat conductive film 5, each radiant cooling plate fully conducts heat and dissipates heat together, thereby realizing a fast heat dissipation mode.

[0051] Working condition 3: When the flat-panel satellite 31 enters the low heat consumption working mode from the high heat consumption working mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin plate 33 and retracts. The specific retracting process is as follows: the internal heat consumption of the flat-panel satellite 31 decreases, the heat transferred to the self-identifying heat radiator decreases, and the temperature of each vortex spring 16 decreases; since heat is gradually lost when transferred between the radiant cooling plates, the temperature of the vortex spring 16 that is farther away from the flat-panel satellite 31 decreases faster, and therefore curls and retracts earlier, thereby driving the third radiant cooling plate 3 to retract first, such as Fig.18 As the temperature continues to drop, each vortex spring 16 begins to shrink step by step until the adjacent radiant cooling plates are perpendicular to each other. At this time, the vertical limiter 24 prevents the hinge from shrinking further, and the heat radiator is in a curled and folded state as a whole, as shown in FIG. Fig.19 After the self-identifying heat radiator is folded, only the outer surfaces of the first radiant cooling plate 1 and the first two second radiant cooling plates 2 effectively dissipate heat, and the self-identifying heat radiator is in a slow heat dissipation mode.

[0052] Working condition 4: When the flat panel satellite 31 enters the non-full power working mode and the heat consumption is moderate, the self-identification heat radiator automatically identifies the temperature change of the cabin board and is in a semi-expanded state. The expansion process is the same as that of working condition 2. However, due to insufficient heat, all the radiant cooling plates cannot be driven to expand and are in a semi-expanded state. Fig. 20 When the self-identifying heat radiator is half-expanded, it is in a dynamic equilibrium state of heat transfer, that is, the heat dissipated by the expanded part is consistent with the heat transferred by the flat-panel satellite 31. At this time, the self-identifying heat radiator automatically adjusts to the required heat dissipation area according to the heat consumption demand.

[0053] The embodiments of the present invention disclosed above are only used to help illustrate the present invention. The embodiments do not describe all the details in detail, nor do they limit the invention to the specific implementation methods described. According to the content of this specification, many modifications and changes can be made. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well.

Claims

1. A self-identifying thermal radiator for a flat-panel satellite, characterized in that: It comprises a plurality of radiant cooling plates connected in sequence by a hinge assembly (4); in a folded state, adjacent radiant cooling plates are arranged vertically, and the plurality of radiant cooling plates are curled inward layer by layer; the adjacent radiant cooling plates are connected by a heat-conducting film (5); the plurality of radiant cooling plates comprise a first radiant cooling plate (1), a plurality of second radiant cooling plates (2) and a third radiant cooling plate (3); one end of the first radiant cooling plate (1) is connected to a side edge (32) of a flat-panel satellite (31), and the other end is connected to the second radiant cooling plate (2); the plurality of second radiant cooling plates (2) are connected in sequence; the third radiant cooling plate (3) is connected to the second radiant cooling plate (2); an expansion device (7) is arranged on the side edge (32) of the flat-panel satellite (31); the expansion device (7) connects the first radiant cooling plate (1) and a second radiant cooling plate (2); the first radiant cooling plate (1) is connected to a surface-mounted heat pipe (6); the surface-mounted heat pipe (6) is connected to a heat pipe buried in a cabin plate; the cabin plate The plate-embedded heat pipe is arranged in a cabin plate (33) of a flat-panel satellite (31); the hinge assembly (4) comprises a vortex spring (16), a first hinge arm (17), a second hinge arm (18) and a rotating shaft (19); the first hinge arm (17) and the second hinge arm (18) are respectively connected to two adjacent radiant cooling plates; the first hinge arm (17) and the second hinge arm (18) are respectively connected at both sides by the rotating shaft (19); the rotating shaft (19) is rotatably connected to the first hinge arm (17); the rotating shaft (19) is connected to the second hinge arm (18) by snapping; the rotating shaft (19) is connected to an inner vortex spring arm (21) of the vortex spring (16); the outer vortex spring arm (20) of the vortex spring (16) is connected to the radiant cooling plate connected to the first hinge arm (17); the vortex spring (16) is formed by winding a bimetallic sheet; the thermal expansion coefficient of the inner metal sheet along the winding direction is greater than the thermal expansion coefficient of the outer metal sheet.

2. A self-identifying thermal radiator for a flat-panel satellite according to claim 1, characterized in that: The first radiant cooling plate (1) has a satellite end mounting surface (8) and a heat dissipation surface (9) which are perpendicular to each other, the satellite end mounting surface (8) is connected to a side edge (32) of a flat-panel satellite (31), and the heat dissipation surface (9) is connected to the second radiant cooling plate (2).

3. A self-identifying thermal radiator for a flat-panel satellite according to claim 2, characterized in that: The satellite end mounting surface (8) is provided with an expander mounting hole (11), and the second radiant cooling plate (2) close to the satellite end mounting surface (8) is provided with an expander fixing hole, and the expander (7) passes through the expander mounting hole (11) and the expander fixing hole and is fixed by a gasket and a nut.

4. A self-identifying thermal radiator for a flat-panel satellite according to claim 3, characterized in that: The expander (7) is a connection and separation device triggered by a shape memory alloy. A slotted bolt is provided on the expander (7). The expander (7) locks the radiant cooling plate by means of the slotted bolt. The expander (7) is connected to an electric drive heater, and the slotted bolt is expanded and broken by the shape memory alloy through electric drive heating.

5. The self-identifying thermal radiator for a flat-panel satellite according to claim 1, characterized in that: The first hinge arm (17) and the second hinge arm (18) are both provided with a radiant cooling plate mounting hole (22) and a rotation shaft hole (23); the first hinge arm (17) and the second hinge arm (18) are connected to the radiant cooling plate via the radiant cooling plate mounting hole (22); the rotation shaft holes (23) on the first hinge arm (17) and the second hinge arm (18) are aligned; and the rotation shaft (19) passes through the rotation shaft hole (23).

6. A self-identifying thermal radiator for a flat-panel satellite according to claim 1, characterized in that: The first hinge arm (17) is provided with a vertical limiter (24) and a horizontal limiter (25).

7. The self-identifying thermal radiator for a flat-panel satellite according to claim 1, characterized in that: One end of the rotating shaft (19) is a hinge end rotating shaft (27), and the other end is a vortex spring end rotating shaft (28). The ends of the hinge end rotating shaft (27) and the vortex spring end rotating shaft (28) are both provided with external threads, and the external threads are connected with nuts. A boss (30) is provided between the hinge end rotating shaft (27) and the vortex spring end rotating shaft (28). The boss (30) and the second hinge arm (18) are both provided with tooth plates (26), and the tooth plates (26) are interlocked. A vortex spring fixing groove (29) is provided on the vortex spring end rotating shaft (28), and the inner vortex spring arm (21) is embedded in the vortex spring fixing groove (29). The surface of the hinge end rotating shaft (27) is coated with molybdenum disulfide.

8. The self-identifying thermal radiator for a flat-panel satellite according to claim 1, characterized in that: The radiation cooling plate is an aluminum plate with heat dissipation white paint sprayed on the surface; the inner metal sheet of the vortex spring (16) is a copper alloy sheet and the outer metal sheet is a steel sheet; the surface mounted heat pipe (6), the vortex spring (16), the first hinge arm (17) and the second hinge arm (18) are all coated with thermal conductive silicone grease.

9. A method for assembling a self-identifying thermal radiator for a flat-panel satellite as claimed in claim 1, characterized in that: The first radiant cooling plate (1) is mounted on the side (32) surface of the flat-panel satellite (31), two expanders (7) are passed through the first radiant cooling plate (1) and mounted on the side (32) surface of the flat-panel satellite (31), the heat pipe buried in the cabin plate is connected to the surface-mounted heat pipe (6), the surface-mounted heat pipe (6) is connected to the first radiant cooling plate (1), all radiant cooling plates are connected via a hinge assembly (4), a heat-conducting film (5) is pasted between adjacent radiant cooling plates, and the two expanders (7) are connected to the second radiant cooling plate (2).

10. A method for using the self-identifying thermal radiator for a flat-panel satellite as claimed in claim 1, characterized in that: The method of using the self-identifying heat radiator includes the following four working conditions: Working condition 1: before the flat-panel satellite (31) enters orbit, the self-identifying thermal radiator is in a curled and folded state under the fixing action of the first radiant cooling plate (1) and the expander (7). At this time, a plurality of radiant cooling plates form a closed rectangular frame, and adjacent radiant cooling plates are in a mutually perpendicular state. The self-identifying thermal radiator is in a locked state. After the flat-panel satellite (31) enters orbit, the expander (7) is expanded and released, and the self-identifying thermal radiator is in an unlocked state. Working condition 2: when the flat-panel satellite (31) enters the high heat consumption working mode from the orbiting mode or the low heat consumption working mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin (33) and unfolds. At this time, the internal heat of the flat-panel satellite (31) is transferred to the surface-mounted heat pipe (6) through the heat pipe buried in the cabin, and then transferred to the vortex spring (16) through the first radiant cooling plate (1). The vortex spring (16) shows an unfolding trend, and the angle between the first hinge arm (17) and the second hinge arm (18) gradually increases. The second radiant cooling plate (2) unfolds, and the heat is sequentially transferred to all the radiant cooling plates through the heat conductive film (5), driving the radiant cooling plates to gradually unfold in sequence. After unfolding, the radiant cooling plates are in the same plane. Under the action of the heat conductive film (5), the radiant cooling plates dissipate heat together. Working condition 3: when the flat-panel satellite (31) enters the low heat consumption working mode from the high heat consumption working mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin plate (33) and retracts. At this time, the internal heat consumption of the flat-panel satellite (31) decreases, the heat transferred to the self-identifying heat radiator decreases, and the temperature of each vortex spring (16) decreases. Since heat is gradually lost when transferred between the radiant cooling plates, the vortex spring (16) farther away from the flat-panel satellite (31) decreases faster in temperature, and thus curls and retracts earlier, thereby driving the third radiant cooling plate (3) to retract first, the temperature continues to decrease, and each vortex spring (16) begins to retract step by step until adjacent radiant cooling plates are perpendicular to each other, and the self-identifying heat radiator presents an overall curled and retracted state. After the self-identifying heat radiator is retracted, only the outer surfaces of the first radiant cooling plate (1) and part of the second radiant cooling plate (2) effectively dissipate heat; Working condition 4: When the flat-panel satellite (31) enters a non-full power working mode and the heat consumption is moderate, the self-identifying thermal radiator automatically identifies that the temperature change of the cabin plate (33) is in a semi-expanded state. The expansion process is the same as that of working condition 2, but due to insufficient heat, all the radiation cooling plates cannot be driven to expand and are in a semi-expanded state. When the self-identifying thermal radiator is semi-expanded, it is in a dynamic equilibrium state of heat transfer.

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