Self-identifying heat radiator for flat panel satellite and method of assembly and use thereof

Abstract

The application provides a self-identifying heat radiator for a flat plate satellite and an assembling and using method thereof, and belongs to the technical field of thermal control of space products. The application solves the problem of poor heat dissipation capacity of the existing flat plate satellite. The heat radiator comprises a plurality of radiating cold plates connected in sequence through hinge assemblies, wherein the adjacent radiating cold plates are vertically arranged in a folded state, the plurality of radiating cold plates are curled in layers inward, the adjacent radiating cold plates are connected through a heat conduction film, the plurality of radiating cold plates comprise a first radiating cold plate, a plurality of second radiating cold plates and a third radiating cold plate, one end of the first radiating cold plate is connected with the side edge of the flat plate satellite, the other end of the first radiating cold plate is connected with the second radiating cold plate, the plurality of second radiating cold plates are connected in sequence, the third radiating cold plate is connected with the second radiating cold plate, an expansion breaker is arranged between the first radiating cold plate and the second radiating cold plate, a surface-mounted heat pipe is connected to the first radiating cold plate, and the surface-mounted heat pipe is connected with an embedded heat pipe in a cabin plate. The heat radiator is mainly used for heat dissipation of the flat plate satellite.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of space product thermal control, in particular relates to a self-identifying heat radiator for a flat panel satellite and an assembling and using method thereof. BACKGROUND

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

[0003] As the heat consumption of the load continues to increase, the heat dissipation of the flat panel satellite has gradually become a problem. Traditional satellites usually use their own cabin panels as radiators to exchange heat with the space environment. However, flat panel satellites are compact in layout and can be approximated as two-dimensional satellites. The number and size of cabin panels available for heat dissipation are limited, so when the heat consumption of the load increases to a certain extent, additional thermal control measures are needed to meet the thermal control requirements.

[0004] Currently, the alternative measures include deployable radiators and fluid loop radiators. Deployable radiators are folded on the surface of the satellite during the launch phase, and are unfolded to increase the heat dissipation area after the satellite is launched into orbit to meet the thermal control requirements. However, for two-dimensional flat panel satellites, it is difficult to have enough space for the folding and fixing of deployable radiators under the premise of meeting the layout of loads, solar wings, and platform equipment. Fluid loop radiators use active thermal control, with the working fluid circulating under the drive of a pump, absorbing and dissipating heat, and dispersing and distributing heat. However, fluid loop radiators are complex, high in cost, and low in reliability, and will increase the weight and power consumption of the satellite. When the pump is working, it will produce micro-vibrations, affecting the attitude control accuracy of the satellite. SUMMARY

[0005] Therefore, the present application aims to provide a self-identifying heat radiator for a flat panel satellite and an assembling and using method thereof to solve the problem of poor heat dissipation of existing flat panel satellites.

[0006] In order to achieve the above object, the application adopts the following technical scheme: a self-identification heat radiator for flat plate satellite, which comprises a plurality of radiative cold plates connected in sequence through hinge assemblies, in the folded state, adjacent radiative cold plates are arranged vertically, and the plurality of radiative cold plates are curled in layers inward, the adjacent radiative cold plates are connected through a heat conduction film, the plurality of radiative cold plates comprise a first radiative cold plate, a plurality of second radiative cold plates and a third radiative cold plate, one end of the first radiative cold plate is connected with the side edge of the flat plate satellite, the other end is connected with the second radiative cold plate, the plurality of second radiative cold plates are connected in sequence, the third radiative cold plate is connected with the second radiative cold plate, the side edge of the flat plate satellite is provided with an expansion breaker, the expansion breaker is connected with the first radiative cold plate and a second radiative cold plate, the first radiative cold plate is connected with a surface-mounted heat pipe, the surface-mounted heat pipe is connected with an in-cabin heat pipe, the in-cabin heat pipe is arranged in the cabin plate of the flat plate satellite, the hinge assembly comprises a watch 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 with two adjacent radiative cold plates, the two sides of the first hinge arm and the second hinge arm are respectively connected through the rotating shaft, the rotating shaft is rotatably connected with the first hinge arm, the rotating shaft is connected with the second hinge arm through clamping, the rotating shaft is connected with the inner watch spring arm of the watch spring, the outer watch spring arm of the watch spring is connected with the radiative cold plate connected with the first hinge arm, the watch spring is formed by winding a bimetallic strip, the thermal expansion coefficient of the inner side metal sheet in the winding direction is greater than that of the outer side metal sheet.

[0007] Further, the first radiative cold plate has a satellite end mounting surface and a heat dissipation surface perpendicular to each other, the satellite end mounting surface is connected with the side edge of the flat plate satellite, and the heat dissipation surface is connected with the second radiative cold plate.

[0008] Further, the satellite end mounting surface is provided with an expansion breaker mounting hole, and the second radiative cold plate close to the satellite end mounting surface is provided with an expansion breaker fixing hole, the expansion breaker is fixed through the gasket and the nut after passing through the expansion breaker mounting hole and the expansion breaker fixing hole.

[0009] Further, the expansion breaker is a connection and separation device triggered by shape memory alloy, the expansion breaker is provided with a slotted bolt, the expansion breaker locks the radiative cold plate through the slotted bolt, the expansion breaker is connected with an electric drive heater, and the memory alloy expansion breaks the slotted bolt through electric drive heating.

[0010] Further, the first hinge arm and the second hinge arm are both provided with a radiative cold plate mounting hole and a rotating shaft hole, the first hinge arm and the second hinge arm are connected with the radiative cold plate through the radiative cold plate mounting hole, the rotating shaft holes on the first hinge arm and the second hinge arm are aligned, and the rotating shaft passes through the rotating shaft holes.

[0011] Further, the first hinge arm is provided with vertical and horizontal limit positions.

[0012] Further, one end of the rotating shaft is a hinge end rotating shaft, the other end is a volute end rotating shaft, the hinge end rotating shaft and the volute end rotating shaft are provided with external threads at the ends, the external threads are connected with nuts, a boss is arranged between the hinge end rotating shaft and the volute end rotating shaft, toothed pieces are arranged on the boss and the second hinge arm, the toothed pieces are mutually embedded, a volute fixing groove is arranged on the volute end rotating shaft, the inner volute arm is embedded in the volute fixing groove, and the surface of the hinge end rotating shaft is coated with molybdenum disulfide.

[0013] Further, the radiating plate is an aluminum plate, the surface is sprayed with heat dissipation white paint, the inner metal sheet of the volute is a copper alloy sheet, and the outer metal sheet is a steel sheet, and the surface-mounted heat pipe, the volute, the first hinge arm and the second hinge arm are all coated with heat-conducting silicone grease.

[0014] The application also provides an assembling method of the self-identifying heat radiator for the flat plate satellite, specifically comprising the following steps: installing the first radiating plate on the side surface of the flat plate satellite, installing the two expansion breakers through the first radiating plate on the side surface of the flat plate satellite, connecting the surface-mounted heat pipe with the in-embedded heat pipe of the cabin plate, connecting the surface-mounted heat pipe with the first radiating plate, connecting all the radiating plates through the hinge assembly, pasting the heat-conducting film between the adjacent radiating plates, and connecting the two expansion breakers with the second radiating plate.

[0015] The application also provides a use method of the self-identifying heat radiator for the flat plate satellite, which comprises the following four working conditions.

[0016] Working condition 1: before the flat plate satellite is launched into orbit, the self-identifying heat radiator is in a curled and folded state under the fixation of the first radiating plate and the expansion breakers, at this time, the plurality of radiating plates form a closed rectangular frame, the adjacent radiating plates are in a mutually perpendicular state, the self-identifying heat radiator is in a locked state, after the flat plate satellite is launched into orbit, the expansion breakers are expanded to be released from the fixation, and the self-identifying heat radiator is in an unlocked state.

[0017] Working condition 2: when the flat plate satellite enters a high heat consumption working mode from a launch mode or a low heat consumption working mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin plate and expands, at this time, the heat inside the flat plate satellite is transmitted to the surface-mounted heat pipe through the in-embedded heat pipe of the cabin plate, and then transmitted to the volute through the first radiating plate, the volute shows an expanding trend, the angle between the first hinge arm and the second hinge arm gradually increases, the second radiating plate expands, and the heat is sequentially transmitted to all the radiating plates through the heat-conducting film, so as to drive the radiating plates to gradually and sequentially expand, after the expansion, the radiating plates are in the same plane, and the radiating plates collectively dissipate heat under the action of the heat-conducting film.

[0018] Condition 3: When the flat panel satellite enters a low heat dissipation mode from a high heat dissipation mode, the self-identifying heat radiator automatically identifies the change of the cabin plate temperature and retracts, at this time, the internal heat dissipation of the flat panel satellite decreases, the heat transferred to the self-identifying heat radiator decreases, and the temperature of each spiral spring decreases, and since the heat is gradually lost in the process of transferring between the radiation cold plates, the spiral spring far away from the flat panel satellite decreases faster, thus the third radiation cold plate retracts preferentially, the temperature continues to decrease, and each spiral spring starts to retract gradually until the adjacent radiation cold plates are perpendicular to each other, and the self-identifying heat radiator is in a whole retracted state, and after the self-identifying heat radiator is retracted, only the first radiation cold plate and part of the second radiation cold plate can effectively dissipate heat.

[0019] Condition 4: When the flat panel satellite enters a non-full power working mode with moderate heat dissipation, the self-identifying heat radiator automatically identifies the change of the cabin plate temperature and is in a half-expanded state, and the expansion process is the same as that in condition 2, but since the heat is insufficient, all the radiation cold plates cannot be expanded and are in a half-expanded state, and the self-identifying heat radiator is in a dynamic balance state of heat transfer when it is half expanded.

[0020] Compared with the prior art, the self-identifying heat radiator for the flat panel satellite and the assembling and using method thereof have the advantages that: under the premise of ensuring that a large enough heat dissipation surface is provided after expansion, the self-identifying heat radiator can be compactly retracted at the side edge of the flat panel satellite and does not occupy the layout space of the satellite cabin plate, and the self-identifying heat radiator can automatically expand and retract with the change of the temperature of the satellite, and the area of the heat dissipation surface can be adjusted in orbit, so as to adapt to different working conditions of the satellite.

[0021] Specific advantages are as follows:

[0022] (1) The self-identifying heat radiator can provide a large radiation heat dissipation area after expansion, which is beneficial to the heat dissipation of high-power satellites such as communication satellites and synthetic aperture radar satellites.

[0023] (2) The self-identifying heat radiator can be compactly retracted at the narrow edge of the flat panel satellite during the launch phase, so as to occupy a small space and improve the utilization rate of the launch fairing space.

[0024] (3) The self-identifying heat radiator can identify the temperature of the cabin plate and thus autonomously expand and retract, and when the satellite is in orbit, the state of the self-identifying heat radiator can be automatically adjusted according to the change of the working mode to meet the heat dissipation requirement.

[0025] (4) The self-identifying heat radiator has a half-expanded state, and when the satellite works in a non-full power mode, the expansion area of the self-identifying heat radiator can be adjusted according to the temperature to meet the heat dissipation requirement.

[0026] (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 temperature change of its expansion and contraction.

[0027] (6) The self-identifying thermal radiator described in the present invention is a passive thermal control measure. Except for the electrically driven expander unlocking when entering orbit, the rest of the working process does not require increasing the power consumption of the entire satellite.

[0028] (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.

[0029] (8) The self-identifying thermal radiator of the present invention is locked by the expansion device and its own limit, and the unlocking impact is small, which has little impact on the satellite and onboard equipment.

[0030] (9) The components of the self-identifying heat radiator of the present invention are simple in design and have low precision requirements, which can reduce processing costs, shorten processing cycles, and have low costs.

[0031] (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 needs of the satellite, and the device has strong adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The accompanying drawings, which constitute part of the present invention, are provided to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are provided to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0033] Figure 1 This is a schematic structural diagram of a self-identifying thermal radiator for a flat-panel satellite according to the present invention;

[0034] Figure 2 This is a schematic structural diagram of the first radiant cooling plate of the present invention;

[0035] Figure 3 This is a schematic structural diagram of the second radial cooling plate according to the present invention;

[0036] Figure 4 This is a schematic structural diagram of the third radial cooling plate of the present invention;

[0037] Figure 5 This is a schematic diagram of the three-dimensional structure of the hinge assembly of the present invention;

[0038] Figure 6 Schematic diagram of the cross-sectional structure of the hinge assembly of the present invention;

[0039] Figure 7 Schematic diagram of the vortex spring structure of the present invention;

[0040] Figure 8 Schematic diagram of the first hinge arm structure according to the present application;

[0041] Figure 9 Schematic diagram of the second hinge arm structure according to the present application;

[0042] Figure 10 Schematic diagram of the hinge assembly according to the present application;

[0043] Figure 11 Schematic diagram of the hinge assembly assembly process according to the present application;

[0044] Figure 12 Schematic diagram of the self-identifying heat radiator assembly process for a flat panel satellite according to the present application Figure 1 ;

[0045] Figure 13 Schematic diagram of the self-identifying heat radiator assembly process for a flat panel satellite according to the present application Figure 2 ;

[0046] Figure 14 Schematic diagram of the self-identifying heat radiator assembly process for a flat panel satellite according to the present application Figure 3 ;

[0047] Figure 15 Schematic diagram of the self-identifying heat radiator assembly process for a flat panel satellite according to the present application Figure 4 ;

[0048] Figure 16 Schematic diagram of the self-identifying heat radiator deployment process for a flat panel satellite according to the present application Figure 1 ;

[0049] Figure 17 Schematic diagram of the self-identifying heat radiator deployment process for a flat panel satellite according to the present application Figure 2 ;

[0050] Figure 18 Schematic diagram of the self-identifying heat radiator retraction process for a flat panel satellite according to the present application Figure 1 ;

[0051] Figure 19 Schematic diagram of the self-identifying heat radiator retraction process for a flat panel satellite according to the present application Figure 2 ;

[0052] Figure 20 Schematic diagram of the self-identifying heat radiator semi-deployment state for a flat panel satellite according to the present application.

[0053] In the figure:

[0054] 1-first radiating plate, 2-second radiating plate, 3-third radiating plate, 4-hinge assembly, 5-heat-conducting film, 6-surface-mounted heat pipe, 7-expansion breaker, 8-satellite end mounting surface, 9-radiating surface, 10-satellite end mounting hole, 11-expansion breaker mounting hole, 12-first hinge arm mounting hole, 13-volute spring mounting hole, 14-heat pipe mounting hole, 15-second hinge arm mounting hole, 16-volute spring, 17-first hinge arm, 18-second hinge arm, 19-rotation shaft, 20-outer volute spring arm, 21-inner volute spring arm, 22-radiating plate mounting hole, 23-rotation shaft hole, 24-vertical limit, 25-horizontal limit, 26-toothed plate, 27-hinge end rotation shaft, 28-volute spring end rotation shaft, 29-volute spring fixing groove, 30-convex platform, 31-flat satellite, 32-side edge, 33-cabin plate. DETAILED DESCRIPTION

[0055] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict, and the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments.

[0056] Reference is made to Figures 1-20 The present embodiment is described as a self-identifying heat radiator for a flat satellite, which comprises a plurality of radiating plates connected in sequence through a hinge assembly 4. In a folded state, adjacent radiating plates are arranged vertically, and the plurality of radiating plates are curled in layers inwardly. The adjacent radiating plates are connected through a heat-conducting film 5. The plurality of radiating plates comprise a first radiating plate 1, a plurality of second radiating plates 2 and a third radiating plate 3. One end of the first radiating plate 1 is connected to a side edge 32 of a flat satellite 31, and the other end is connected to a second radiating plate 2. The plurality of second radiating plates 2 are connected in sequence. The third radiating plate 3 is connected to a second radiating plate 2. The side edge 32 of the flat satellite 31 is provided with an expansion breaker 7. The expansion breaker 7 is connected to the first radiating plate 1 and a second radiating plate 2. The first radiating plate 1 is connected to a surface-mounted heat pipe 6. The surface-mounted heat pipe 6 is connected to an in-cabin heat pipe. The in-cabin heat pipe is arranged in a cabin plate 33 of the flat satellite 31. The hinge assembly 4 comprises a volute spring 16, a first hinge arm 17, a second hinge arm 18 and a rotation shaft 19. The first hinge arm 17 and the second hinge arm 18 are respectively connected to two adjacent radiating plates. The two sides of the first hinge arm 17 and the second hinge arm 18 are respectively connected through the rotation shaft 19. The rotation shaft 19 is rotatably connected to the first hinge arm 17. The rotation shaft 19 is connected to the second hinge arm 18 in a clamping manner. The rotation shaft 19 is connected to an inner volute spring arm 21 of the volute spring 16. An outer volute spring arm 20 of the volute spring 16 is connected to a radiating plate connected to the first hinge arm 17. The volute spring 16 is formed by winding a bimetallic strip. The thermal expansion coefficient of the inner metal strip along the winding direction is greater than that of the outer metal strip.

[0057] The assembly method of the embodiment is to install the first radiating plate 1 on the surface of the side edge 32 of the flat satellite 31, install the two expanders 7 through the first radiating plate 1 on the surface of the side edge 32 of the flat satellite 31, connect the embedded heat pipes in the cabin plate with the surface-mounted heat pipes 6, connect the surface-mounted heat pipes 6 with the first radiating plate 1, connect all the radiating plates through the hinge assembly 4, paste the heat-conducting film 5 between the adjacent radiating plates, and connect the two expanders 7 with the second radiating plate 2.

[0058] The use method of the self-identifying heat radiator in the embodiment includes the following four working conditions:

[0059] Working condition 1: Before the flat satellite 31 is launched into orbit, the self-identifying heat radiator is in a curled and folded state under the fixation of the first radiating plate 1 and the expander 7, at this time, the several radiating plates form a closed rectangular frame, the adjacent radiating plates are in a perpendicular state to each other, the self-identifying heat radiator is in a locked state, after the flat satellite 31 is launched into orbit, the expander 7 is expanded to be released from the fixation, and the self-identifying heat radiator is in an unlocked state.

[0060] Working condition 2: When the flat satellite 31 enters a high heat consumption working mode from a launch mode or a low heat consumption working mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin plate 33 and expands, at this time, the heat inside the flat satellite 31 is transmitted to the surface-mounted heat pipes 6 through the embedded heat pipes in the cabin plate, and then transmitted to the watch spring 16 through the first radiating plate 1, the watch spring 16 shows an expanding trend, the angle between the first hinge arm 17 and the second hinge arm 18 gradually increases, the second radiating plate 2 expands, the heat is transmitted to all the radiating plates in turn through the heat-conducting film 5, the radiating plates are gradually and sequentially driven to expand, after the expansion, the radiating plates are in the same plane, and the radiating plates collectively dissipate heat under the action of the heat-conducting film 5.

[0061] Working condition 3: When the flat satellite 31 enters a low heat consumption working mode from a high heat consumption working mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin plate 33 and folds, at this time, the heat consumption inside the flat satellite 31 decreases, the heat transmitted to the self-identifying heat radiator decreases, and the temperature of each watch spring 16 decreases, since the heat transmission between the radiating plates will be gradually lost, the farther the watch spring 16 from the flat satellite 31, the faster the temperature of the watch spring 16 decreases, and thus the watch spring 16 is curled and folded earlier, thereby driving the third radiating plate 3 to be preferentially curled and folded, the temperature continues to decrease, each watch spring 16 begins to be curled and folded in stages, until the adjacent radiating plates are perpendicular to each other, and the self-identifying heat radiator presents a curled and folded state as a whole, after the self-identifying heat radiator is curled and folded, only the first radiating plate 1 and part of the second radiating plate 2 effectively dissipate heat on the outer surface.

[0062] 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 recognizes the temperature change of the cabin 33 and is in a semi-expanded state. The deployment process is the same as that of working condition 2, but due to insufficient heat, it cannot drive all the radiant 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.

[0063] The present embodiment will be described in detail below with reference to the accompanying drawings:

[0064] like Figure 1 As shown, a self-identifying thermal radiator for a flat-panel satellite includes a plurality of radial cooling plates connected in sequence by a hinge assembly 4. In a retracted state, adjacent radial cooling plates are arranged vertically, and the plurality of radial cooling plates are curled inward layer by layer. The adjacent radial cooling plates are connected by a thermally conductive film 5. The plurality of radial cooling plates include a first radial cooling plate 1, a plurality of second radial cooling plates 2, and a third radial cooling plate 3. One end of the first radial cooling plate 1 is connected to a side 32 of a flat-panel satellite 31, and the other end is connected to the second radial cooling plate 2. The plurality of second radial cooling plates 2 are connected in sequence, and the third radial cooling plate 3 is connected to the second radial cooling plate 2. An expander 7 is provided on the side 32 of the flat-panel satellite 31, and the expander 7 connects the first radial cooling plate 1 and the second radial cooling plate 2. A surface-mounted heat pipe 6 is connected to the first radial cooling plate 1, and the surface-mounted heat pipe 6 is connected to the heat pipe buried in the cabin.

[0065] like Figure 2 As shown, the first radial cooling plate 1 has a satellite mounting surface 8 and a heat dissipation surface 9 that are perpendicular to each other. The satellite mounting surface 8 is provided with a satellite mounting hole 10 and a breaker mounting hole 11. The satellite mounting hole 10 is used to mount the first radial cooling plate 1 on the side 32 surface of the flat-panel satellite 31 using 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 to the first hinge arm 17 to ensure that the first hinge arm 17 is accurately installed on the first radial cooling plate 1. The vortex spring 16 is relatively fixed to the first radial cooling plate 1 by the cooperation of its outer vortex spring arm 20 with the vortex spring mounting hole 13, and can be expanded or curled with this point as a support when the temperature changes. The heat pipe mounting hole 14 is used for mounting the surface mounted heat pipe 6 , which can transfer the heat from the heat pipe embedded in the cabin to the first radiant cooling plate 1 .

[0066] like Figure 3As shown, the second radial 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 first hinge arm mounting hole 12 and the vortex spring mounting hole 13 function similarly to their counterparts on the first radial cooling plate 1, connecting to a first hinge arm 17 and a vortex spring 16, respectively, to ensure that the second radial cooling plate 2 can coordinate with adjacent components during the deployment and retraction of the self-identifying heat radiator. The second hinge arm mounting hole 15 is used to connect to a second hinge arm 18. The first and second hinge arms 17 and 18 are connected by a rotating shaft 19 to achieve a rotatable connection between adjacent radial cooling plates. Specifically, two additional expansion device fixing holes are provided on the second radial cooling plate 2 near the satellite mounting surface 8. The expansion device 7 passes through the expansion device mounting hole 11 and the expansion device fixing hole and is secured with a gasket and nut. This prevents the self-identifying heat radiator from accidentally deploying during satellite launch and other processes.

[0067] like Figure 4 As shown, the third radial cooling plate 3 is provided with a second hinge arm mounting hole 15. This second hinge arm mounting hole 15 connects to the second hinge arm 18, allowing the third radial cooling plate 3 to form a complete self-identifying heat radiator structure with other radial cooling plates and the hinge assembly. During operation, the self-identifying heat radiator, driven by the vortex spring 16 and hinge assembly 4, unfolds and retracts in conjunction with the other radial cooling plates, achieving heat dissipation and ensuring proper operation of the self-identifying heat radiator.

[0068] All radial cold plates are machined from aluminum sheet metal. The first radial cold plate 1 is formed from aluminum sheet metal. Subsequently, all radial cold plates undergo heat treatment to increase their hardness. Finally, except for the contact and mounting areas, the remaining surfaces are sprayed with heat-dissipating white paint to improve their heat dissipation efficiency. All second radial cold plates 2 are consistent in length and thickness, but vary slightly in width. Specifically, after curling and folding, the width of the second radial cold plate 2 closer to the inside decreases to meet the space required for the curling. This allows each radial cold plate to be compactly curled layer by layer in the folded state, saving space without affecting its heat dissipation performance.

[0069] 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 radial cooling plates. The first hinge arm 17 and the second hinge arm 18 are connected on both sides by a rotating shaft 19. The rotating shaft 19 is rotatably connected to the first hinge arm 17, and the rotating shaft 19 is clamped and connected to the second hinge arm 18. 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.

[0070] like Figure 7As shown, the coil spring 16 is formed by winding a bimetallic strip, the thermal expansion coefficient of the inner metal strip in the winding direction is greater than that of the outer metal strip. One option is that the inner metal strip of the coil spring 16 is a copper alloy strip, and the outer metal strip is a steel strip. The bimetallic strip has the following characteristics: the thermal expansion coefficients of the steel strip and the copper alloy strip are different, when the temperature rises, the expansion of the copper alloy strip is greater than that of the steel strip, and the whole bimetallic strip will bend to the side of the steel strip; when the temperature decreases, the contraction of the copper alloy strip is greater than that of the steel strip, and the whole bimetallic strip will bend to the side of the copper alloy strip. Therefore, the coil spring 16 specifically shows that when the temperature rises, the coil spring 16 shows an unfolding trend, and the angle between the outer coil spring arm 20 and the inner coil spring arm 21 gradually increases; when the temperature decreases, the coil spring 16 shows a curling trend, and the angle between the outer coil spring arm 20 and the inner coil spring arm 21 gradually decreases. By selecting materials with different expansion coefficients and changing the thickness of the two metal strips, the change temperature and angle of the coil spring 16 can be adjusted.

[0071] As shown in Figure 8 , the first hinge arm 17 is provided with a radial plate mounting hole 22 and a rotating shaft hole 23, the first hinge arm 17 is connected with the radial plate through the radial plate mounting hole 22, and the first hinge arm 17 is provided with a vertical limit 24 and a horizontal limit 25.

[0072] As shown in Figure 9 , the second hinge arm 18 is also provided with a radial plate mounting hole 22 and a rotating shaft hole 23, the second hinge arm 18 is connected with the radial plate through the radial plate mounting hole 22, and the second hinge arm 18 is provided with a toothed plate 26, the rotating shaft hole 23 on the first hinge arm 17 and the second hinge arm 18 is aligned, and the rotating shaft 19 passes through the rotating shaft hole 23.

[0073] As shown in Figure 10 , one end of the rotating shaft 19 is a hinge end rotating shaft 27, and the other end is a coil spring end rotating shaft 28, the hinge end rotating shaft 27 and the coil spring end rotating shaft 28 are both provided with external threads at the ends, the external threads are connected with nuts, the hinge end rotating shaft 27 and the coil spring end rotating shaft 28 are provided with a boss 30 therebetween, the boss 30 is provided with a toothed plate 26, the boss 30 and the toothed plate 26 on the second hinge arm 18 are embedded with each other, the coil spring end rotating shaft 28 is provided with a coil spring fixing groove 29, and the inner coil spring arm 21 is embedded in the coil spring fixing groove 29, so that the coil spring 16 can be firmly connected with the rotating shaft 19, and when the coil spring 16 deforms, the rotating shaft 19 can be driven to rotate. The surface of the hinge end rotating shaft 27 is coated with molybdenum disulfide to reduce friction and avoid vacuum cold welding.

[0074] The coupling of the pivot hole 23 and the pivot 19 enables relative rotation between the first hinge arm 17 and the second hinge arm 18. The vertical limiter 24 and the horizontal limiter 25 act as motion limits during the operation of the self-identifying thermal radiator. In the retracted state, the vertical limiter 24 ensures that the angle between adjacent radiant cooling plates is no less than 90°, allowing the self-identifying thermal radiator to maintain a compact structure and withstand the mechanical environment during the satellite launch phase. During deployment, when the angle between the first hinge arm 17 and the second hinge arm 18 reaches 180°, the horizontal limiter 25 prevents the radiant cooling plates from further deployment, locking the adjacent radiant cooling plates.

[0075] like Figure 11 As shown, the assembly process of hinge assembly 4 is as follows: First, insert first hinge arm 17 into second hinge arm 18, aligning shaft hole 23. Second, insert shaft 19 through shaft hole 23 from both sides, interlocking teeth 26, and then secure one side of hinge end shaft 27 with a nut. Third, install vortex spring 16 on the outside of shaft 19, insert inner vortex spring arm 21 into vortex spring securing groove 29, and then secure it with a nut screwed into the outside of shaft 23. First hinge arm 17 can rotate around shaft 19.

[0076] In this embodiment, the thermally conductive film 5 is made of a flexible, highly thermally conductive material with excellent thermal conductivity and high bending resistance, enabling heat transfer between the radiant cooling plates. The expander 7 is a miniature connection and separation device triggered by a shape memory alloy. It is equipped with a slotted bolt that locks the radiant cooling plate. The expander 7 is connected to an electrically driven heater, which uses electric heating to expand the tubular shape memory alloy and break the slotted bolt, achieving unlocking and separation. The surface-mounted heat pipe 6, vortex spring 16, first hinge arm 17, and second hinge arm 18 are all coated with thermal grease.

[0077] The specific assembly method of this embodiment is:

[0078] The first step, such as Figure 12 As shown, the first radiant cooling plate 1 is mounted on the side 32 surface of the flat-panel satellite 31, and two expanders 7 are installed on the side 32 surface through the expander mounting holes 11. Then, nuts and washers are installed on the slotted bolts of the expanders 7. After applying thermal grease on the mounting surfaces of the embedded heat pipe in the cabin 33 of the flat-panel satellite 31 and the led surface-mounted heat pipe 6, the surface-mounted heat pipe 6 is fixed to the heat dissipation surface 9 of the first radiant cooling plate 1 using standard parts.

[0079] The second step is Figure 13As shown, the third radial cold plate 3 and the last second radial cold plate 2 are connected by the hinge assembly 4, and the structures of the vortex spring 16, the first hinge arm 17, the second hinge arm 18 and the radial cold plate in contact are fixed after being smeared with heat-conducting silicone grease to achieve sufficient heat conduction between each other. The heat-conducting film 5 is pasted between the third radial cold plate 3 and the last second radial cold plate 2 to achieve sufficient heat conduction between the radial cold plates. The assembly of all the second radial cold plates 2 is completed according to the above operation, and the assembly is as shown in Figure 14 .

[0080] The third step is shown in Figure 15 As shown, the second step assembly and the first step assembly are connected by the hinge assembly 4, and then the heat-conducting film 5 is pasted between the first radial cold plate 1 and the first second radial cold plate 2 to achieve sufficient heat conduction between the radial cold plates. At the same time, the expansion breaker 7 cuts the slot bolt through the expansion breaker fixing hole of the second radial cold plate 2 close to the satellite end mounting surface 8, and finally the fixing is completed through the gasket and the nut.

[0081] The use method of the self-identifying heat radiator described in the embodiment includes the following four working conditions, which are specifically:

[0082] Working condition 1: Before the flat plate satellite 31 is launched into orbit, the self-identifying heat radiator is in a folded and curled state under the fixing of the first radial cold plate 1 and the expansion breaker 7, at this time, the radial cold plates form a closed rectangular frame. Under the action of the vertical limiting portion 24, the angle between the first hinge arm 17 and the second hinge arm 18 cannot be less than 90°, so that the adjacent radial cold plates are in a mutually perpendicular state, and the self-identifying heat radiator is in a high stiffness locked state and can withstand the mechanical environment in the satellite launch stage. After the flat plate satellite 31 is launched into orbit, the electric drive heating makes the tubular memory alloy of the expansion breaker 7 expand and break the slot bolt, the self-identifying heat radiator is unlocked, the slot bolt is fixed on the second radial cold plate 2 through the gasket and the nut, and the recycling effect is achieved.

[0083] Working condition 2: When the flat plate satellite 31 enters the high heat consumption working mode from the launch mode or the low heat consumption working mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin plate 33 and expands. The expansion process is specifically as shown in Figure 16 As shown, the heat inside the flat plate satellite 31 is transferred to the surface-mounted heat pipe 6 through the in-buried heat pipe in the cabin plate, and then to the vortex spring 16 through the first radial cold 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 radial cold plates to gradually expand, until the angle between the first hinge arm 17 and the second hinge arm 18 is 180°, at which time the horizontal limiting portion 25 hinders the hinge from further expanding, thereby realizing the locking of the adjacent radial cold plates. At the same time, the heat is transferred to the first second radial cold plate 2 through the heat-conducting film 5, and the second radial cold plate 2 transfers the heat to the vortex spring 16 on the other side, thereby driving the next radial cold plate to expand. The expansion of all the radial cold plates is completed in turn, and the state of the self-identifying heat radiator after expansion is as shown inFigure 17 As shown in Fig. 6, after the self-identifying heat radiator is unfolded, each radiating plate is in the same plane, and under the action of the heat-conducting film 5, each radiating plate is fully heat-conducted and cools down, thereby realizing the mode of rapid cooling.

[0084] Case 3: When the flat panel satellite 31 enters a low heat consumption mode from a high heat consumption mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin plate 33 and is retracted. The specific process is as follows: the heat consumption inside the flat panel satellite 31 decreases, and the heat transferred to the self-identifying heat radiator decreases, and the temperature of each spiral spring 16 decreases. Since the heat transfer between the radiating plates will be gradually lost, the spiral spring 16 far from the flat panel satellite 31 decreases faster, and thus retracts earlier, thereby driving the third radiating plate 3 to retract preferentially, as shown in Fig. 5. Figure 18 As shown in Fig. 6, after the self-identifying heat radiator is unfolded, each radiating plate is in the same plane, and under the action of the heat-conducting film 5, each radiating plate is fully heat-conducted and cools down, thereby realizing the mode of rapid cooling. Figure 19 As shown in Fig. 6, after the self-identifying heat radiator is unfolded, each radiating plate is in the same plane, and under the action of the heat-conducting film 5, each radiating plate is fully heat-conducted and cools down, thereby realizing the mode of rapid cooling.

[0085] Case 4: When the flat panel satellite 31 enters a non-full power mode with moderate heat consumption, the self-identifying heat radiator automatically identifies the temperature change of the cabin plate and is in a half-unfolded state. The unfolding process is the same as that in case 2, but due to insufficient heat, it cannot drive all the radiating plates to unfold and is in a half-unfolded state, as shown in Fig. 5. Figure 20 As shown in Fig. 6, after the self-identifying heat radiator is unfolded, each radiating plate is in the same plane, and under the action of the heat-conducting film 5, each radiating plate is fully heat-conducted and cools down, thereby realizing the mode of rapid cooling.

[0086] The above disclosed embodiments of the present application are only used to help explain the present application. The embodiments do not describe all the details, nor limit the present application to the specific embodiments described. According to the content of the present specification, many modifications and changes can be made. The present specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present application, so that those skilled in the art can well understand and utilize the present application.

Claims

1. A self-identifying heat radiator for flat panel satellites, characterized by: It includes several radial cold plates connected in turn through hinge assembly (4), in the state of folding, the adjacent radial cold plates are vertically arranged, and the several radial cold plates are curled in layers inward, the adjacent radial cold plates are connected through heat-conducting film (5), the several radial cold plates include a first radial cold plate (1), a plurality of second radial cold plates (2) and a third radial cold plate (3), one end of the first radial cold plate (1) is connected with the side edge (32) of the flat plate satellite (31), the other end is connected with the second radial cold plate (2), the plurality of second radial cold plates (2) are connected in turn, the third radial cold plate (3) is connected with the second radial cold plate (2), the side edge (32) of the flat plate satellite (31) is provided with an expansion breaker (7), the expansion breaker (7) is connected with the first radial cold plate (1) and a second radial cold plate (2), the first radial cold plate (1) is connected with a surface-mounted heat pipe (6), the surface-mounted heat pipe (6) is connected with a cabin plate embedded heat pipe, the cabin plate embedded heat pipe is arranged in the cabin plate (33) of the flat plate satellite (31), the hinge assembly (4) includes a spiral 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 connected with the adjacent two radial cold plates respectively, the two sides of the first hinge arm (17) and the second hinge arm (18) are connected through the rotating shaft (19) respectively, the rotating shaft (19) is rotatably connected with the first hinge arm (17), the rotating shaft (19) is connected with the second hinge arm (18) through clamping, the rotating shaft (19) is connected with the inner spiral spring arm (21) of the spiral spring (16), the outer spiral spring arm (20) of the spiral spring (16) is connected with the radial cold plate connected with the first hinge arm (17), the spiral spring (16) is formed by winding a bimetallic strip, the thermal expansion coefficient of the inner side metal sheet in the winding direction is greater than that of the outer side metal sheet.

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

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

4. A self-identifying heat radiator for flat panel satellite according to claim 3, characterized in that: The expansion breaker (7) is a connection and separation device triggered by shape memory alloy, the expansion breaker (7) is provided with a notched bolt, the expansion breaker (7) locks the radial cold plate through the notched bolt, the expansion breaker (7) is connected with an electric drive heater, and the notched bolt of the memory alloy is expanded and broken through electric drive heating.

5. A self-identifying heat radiator for flat panel satellite according to claim 1, characterized in that: The first hinge arm (17) and the second hinge arm (18) are provided with a radiating plate mounting hole (22) and a rotating shaft hole (23), the first hinge arm (17) and the second hinge arm (18) are connected with the radiating plate through the radiating plate mounting hole (22), the rotating shaft holes (23) on the first hinge arm (17) and the second hinge arm (18) are aligned, and the rotating shaft (19) penetrates through the rotating shaft holes (23).

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

7. A self-identifying heat radiator for flat panel satellite according to claim 1, characterized in that: The rotating shaft (19) has a hinge end rotating shaft (27) at one end and a volute spring end rotating shaft (28) at the other end, the hinge end rotating shaft (27) and the volute spring end rotating shaft (28) are provided with external threads at the ends, the external threads are connected with nuts in a matched mode, a boss (30) is arranged between the hinge end rotating shaft (27) and the volute spring end rotating shaft (28), the boss (30) and the second hinge arm (18) are provided with toothed sheets (26), the toothed sheets (26) are embedded with each other, the volute spring end rotating shaft (28) is provided with a volute spring fixing groove (29), the inner volute spring arm (21) is embedded in the volute spring fixing groove (29), and the surface of the hinge end rotating shaft (27) is coated with molybdenum disulfide.

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

9. A method of assembling a self-identifying heat radiator for flat panel satellites as claimed in claim 1, characterized in that: The first radiating plate (1) is mounted on the surface of the side edge (32) of the flat plate satellite (31), the two expansion breakers (7) are mounted on the surface of the side edge (32) of the flat plate satellite (31) through the first radiating plate (1), the surface-mounted heat pipe (6) is connected with the in-surface heat pipe, the surface-mounted heat pipe (6) is connected with the first radiating plate (1), all the radiating plates are connected through the hinge assembly (4), the heat-conducting film (5) is pasted between adjacent radiating plates, and the two expansion breakers (7) are connected with the second radiating plate (2).

10. A method of using a self-identifying heat radiator for flat panel satellites as claimed in claim 1, characterized by: The use method of the self-identifying heat radiator includes the following four working conditions. In working condition 1, before the flat plate satellite (31) is launched into orbit, the self-identifying heat radiator is in a curled and folded state under the fixing action of the first radiating plate (1) and the expansion breaker (7), at this time, the radiating plates form a closed rectangular frame, the adjacent radiating plates are in a perpendicular state, the self-identifying heat radiator is in a locked state, after the flat plate satellite (31) is launched into orbit, the expansion breaker (7) is expanded and broken to release the fixing, and the self-identifying heat radiator is in an unlocked state. Working condition 2: when the flat panel satellite (31) enters the high heat dissipation mode from the orbiting mode or the low heat dissipation mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin panel (33) and expands, at this time, the heat inside the flat panel satellite (31) is transmitted to the surface-mounted heat pipe (6) through the embedded heat pipe in the cabin panel, and then transmitted to the coil spring (16) through the first radiating panel (1), the coil spring (16) shows an expanding trend, the angle between the first hinge arm (17) and the second hinge arm (18) gradually increases, the second radiating panel (2) expands, and the heat is transmitted to all radiating panels in turn through the heat-conducting film (5), which drives the radiating panels to gradually and sequentially expand, and after expansion, each radiating panel is in the same plane, and under the action of the heat-conducting film (5), each radiating panel collectively dissipates heat; Working condition 3: when the flat panel satellite (31) enters the low heat dissipation mode from the high heat dissipation mode, the self-identifying heat radiator automatically identifies the temperature change of the cabin panel (33) and contracts, at this time, the internal heat dissipation of the flat panel satellite (31) decreases, the heat transmitted to the self-identifying heat radiator decreases, and the temperature of each coil spring (16) decreases, since the heat is transmitted between the radiating panels and is gradually lost, the coil spring (16) far away from the flat panel satellite (31) decreases faster and thus curls and contracts earlier, thereby driving the third radiating panel (3) to contract preferentially, and the temperature continues to decrease, each coil spring (16) starts to contract step by step until the adjacent radiating panels are perpendicular to each other, and the self-identifying heat radiator presents a whole curling and contracting state, after the self-identifying heat radiator contracts, only the first radiating panel (1) and part of the second radiating panel (2) effectively dissipate heat on the outer surface; Working condition 4: when the flat panel satellite (31) enters the non-full power working mode with moderate heat dissipation, the self-identifying heat radiator automatically identifies the temperature change of the cabin panel (33) and is in a semi-expanded state, the expansion process is the same as that in working condition 2, but since the heat is insufficient, it cannot drive all the radiating panels to expand and is in a semi-expanded state, and the self-identifying heat radiator is in a dynamic balance state of heat transmission when it is semi-expanded.

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