A laminated machine-thermal integrated deployable sun-shading and temperature-regulating device

Abstract

The application discloses a laminated spacecraft thermal integration deployable sun-shading and temperature-regulating device, which comprises a driving device fixedly connected with a spacecraft cabin plate, a deployment structure hingedly connected with the driving device, and the driving device is used for driving the deployment structure to rotate around a rotating shaft; a pressing and releasing device is used for pressing and fixing the deployment structure and the spacecraft cabin plate; a position switch device is used for indicating whether the deployment structure is closed to position; a sun-shading and temperature-regulating device is installed on one side of the deployment structure, which is directed to the inside of the spacecraft, and is used for sun-shading protection and temperature regulation of a heat-sensitive load in the spacecraft. The application has the flexible thermal control and temperature-regulating characteristics of being deployable and retractable, and can improve the energy utilization rate and the effective load capacity of the spacecraft.

Description

Technical Field

[0001] This invention belongs to the field of interdisciplinary technology of aerospace mechanisms and thermal control, and in particular, it is a stacked, thermo-mechanical integrated, deployable, retractable sunshade and temperature-regulating device. Background Technology

[0002] Aerospace technology is developing rapidly, its forms are becoming increasingly diversified, its functions and structures are becoming increasingly complex, and the types and numbers of payload equipment that need to be installed are increasing.

[0003] On the one hand, spacecraft need to use thermal control technology to ensure that the equipment inside the spacecraft is always within a suitable operating temperature range. Traditionally, heat sinks are usually installed on the spacecraft. Depending on the temperature regulation requirements, the heat sinks sometimes need to face the deep cold space for heat dissipation and sometimes need to face the heat source for heating. This function requires a lot of energy to adjust the attitude of the entire spacecraft, which is not conducive to increasing the effective payload capacity of the spacecraft and reducing the launch cost.

[0004] On the other hand, some optical equipment sometimes requires shielding and insulation, and sometimes requires unobstructed observation, with different requirements for ambient temperature in different operating modes. Existing solutions typically implement thermal control and shielding devices separately. Thermal control uses conventional heat pipes and heat dissipation surfaces, while shielding devices are made of lightweight aluminum / titanium alloys or fiber materials. This approach occupies a significant amount of effective layout space and weight resources, resulting in low system efficiency and limiting its use for optical equipment that requires flexible adjustment of temperature and observation field of view.

[0005] Currently, the traditional approach of using whole-device movement and heat pipe conduction to meet heat dissipation and thermal control requirements, as well as flexibility in response to environmental temperature requirements, and the separate implementation of thermal and shading devices, has the following drawbacks: 1) It involves multiple mechanical interfaces with the entire satellite, requiring the satellite platform to provide radiating plates, adapter plates, and heat pipe installation support, which occupies a lot of space resources in the entire satellite, and the heat pipe layout is complex, making overall assembly difficult; 2) The shading movement mechanism and temperature control device are implemented separately, resulting in greater weight and power consumption, reducing the overall energy utilization efficiency of the satellite; 3) It cannot meet the usage requirements of optical equipment that requires flexible adjustment of both temperature and observation field of view. Summary of the Invention

[0006] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a stacked, thermo-mechanical integrated deployable sunshade and temperature regulation device. This overcomes the problem that some spacecraft payloads need to simultaneously achieve both heat preservation and open observation functions, and solves the technical problem of the coordinated operation of spacecraft motion mechanisms and thermal control components.

[0007] The technical solution of this invention is:

[0008] A stacked, thermo-mechanical integrated, retractable sunshade and temperature-regulating device includes: a drive unit, a pressing and releasing device, a positioning switch device, a retractable structure, and a sunshade and temperature-regulating device.

[0009] The drive unit is fixedly connected to the spacecraft cabin panel, and the deployment and retraction structure is hinged to the drive unit. The drive unit is used to drive the deployment and retraction structure to rotate around the rotation axis.

[0010] The clamping and releasing device is fixedly connected to the deployment and retraction structure and is used to clamp and fix the deployment and retraction structure to the spacecraft cabin panel;

[0011] The positioning switch is fixedly connected to the retractable structure and is used to indicate whether the retractable structure is closed in place.

[0012] The sunshade and temperature regulation device is installed on the side of the deployable structure facing the inside of the spacecraft to provide sunshade protection and temperature regulation for heat-sensitive payloads inside the spacecraft.

[0013] Preferably, polyimide or fiberglass heat insulation pads are provided at the installation positions between the drive device and the unfolding structure, between the pressing and releasing device and the unfolding structure, and between the sunshade and temperature regulation device and the unfolding structure to achieve heat-insulated installation.

[0014] Preferably, the compression release device and the drive device are symmetrical about the center of the unfolding structure.

[0015] Preferably, during the launch phase, the deployment and recovery structure is pressed against the spacecraft cabin panel;

[0016] After the spacecraft enters orbit, the clamping release device is powered on, and the internal pyrotechnics ignite to unlock the mechanism. This then drives the retractable structure to open or close.

[0017] Preferably, the deployable drive device includes: a mounting base plate, a drive assembly, an active hinge, and a driven hinge;

[0018] An active hinge and a passive hinge are hinged mounting base plates, and the free ends of the active hinge and the passive hinge are fixedly connected to an extension and retraction structure.

[0019] The drive assembly is mounted on the mounting base plate, and the drive assembly, the active hinge, and the driven hinge are all located on the same side of the mounting base plate.

[0020] The mounting base plate is installed on the spacecraft cabin panel;

[0021] The active hinge and the output shaft of the drive assembly are connected by a pin to achieve power transmission; the driven hinge, active hinge and drive assembly are all coaxially mounted.

[0022] Preferably, the positioning switch device includes: a trigger head, a switch assembly, and a switch bracket;

[0023] The trigger head is mounted on the deployment and retraction structure, the switch assembly is mounted on the switch bracket, and the switch bracket is mounted on the spacecraft cabin panel.

[0024] The trigger head contacts the switching assembly and applies pressure, causing the switching assembly to conduct and generate a trigger signal.

[0025] Preferably, both the trigger head and the switch bracket are made of insulating material;

[0026] The switch assembly is made of any one of beryllium bronze, aluminum alloy, or conductive plastic.

[0027] Preferably, the shading and temperature regulating device includes: mounting feet, a phase change cavity, a thin aluminum plate, a heat-conducting cavity, and a supporting shell;

[0028] Multiple mounting feet are evenly distributed around the edge of the supporting shell, and the mounting feet are connected to the unfolding structure through connectors.

[0029] The supporting shell contains a phase change cavity and a heat conduction cavity;

[0030] The phase change cavity and the heat conduction cavity are stacked and installed, separated by a thin aluminum plate. The phase change cavity is located on the side closer to the unfolding structure, and the heat conduction cavity is located on the side farther away from the unfolding structure.

[0031] Preferably, the phase change cavity is formed by an additively manufactured cell lattice, and the pores of the cell lattice are filled with a phase change working fluid; the heat conduction cavity is composed of a heat pipe array for heat conduction.

[0032] Preferably, it further includes: a temperature measuring and heating device;

[0033] The temperature measuring and heating device is used to measure the surface temperature of the sunshade and temperature regulating device, and to perform heating treatment when the sunshade and temperature regulating device is below the temperature index.

[0034] The temperature measuring and heating device includes: a temperature probe and a heating element;

[0035] There are multiple temperature probes and heating elements, which are installed on the end face of the sunshade and temperature control device facing the inside of the spacecraft cabin.

[0036] Compared with the prior art, the advantages of the present invention are mainly reflected in the following aspects:

[0037] 1. This invention, through the stacked mechanical-thermal integration technology, enables the spatial position of the thermal control implementation device to be changed, increasing the flexibility of thermal control implementation and effectively improving the energy utilization efficiency of spacecraft; at the same time, the stacked installation method of the shielding mechanism and the thermal control device improves the compactness of the equipment, reduces the impact on the spacecraft envelope size, and increases the flexibility of the equipment's spatial layout.

[0038] 2. The present invention forms a cavity with energy storage and thermal management functions through additive manufacturing integrated forming technology, cooperates with a heat-conducting cavity, and uses a heater and a temperature measuring sensor to ensure the required light and heat environmental conditions on the sun-shading side of the sun-shading flipping mechanism, solving the problems of low temperature control accuracy and poor uniformity in the prior art.

[0039] 3. The present invention provides a ring-shaped unfolding and folding structure on the outside of the sun-shading temperature control device and provides reinforcing ribs. Compared with directly installing the sun-shading temperature control device on the driving device, the structural strength and load capacity of the present invention are effectively improved, and the application scenario range of the present invention is expanded. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 is a schematic diagram of the front structural composition of the present invention;

[0041] Figure 2 is a bottom view of the present invention;

[0042] Figure 3 is a schematic diagram of the side structure of the present invention;

[0043] Figure 4 is a schematic diagram of the structural composition of the deployable drive device in the present invention;

[0044] Figure 5 is a schematic diagram of the position switch structure of the present invention;

[0045] Figure 6 is a schematic diagram of the position of the reed protrusion structure of the switch component and the switch bracket of the present invention;

[0046] FIG. 7(a) is a structural diagram of the "rice" character ribs of the unfolding and folding structure of the present invention;

[0047] FIG. 7(b) is a cross-sectional schematic diagram of the unfolding and folding structure of the present invention; <*

[0048] Figure 8 is a schematic diagram of the structural composition of the sun-shading temperature control device of the present invention;

[0049] Figure 9 is a typical case diagram of the phase change cavity lattice structure in the sun-shading temperature control device of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0050] To better describe the present invention, the present invention will be described in detail below in conjunction with the schematic diagrams and examples. The embodiment of the present invention provides a stacked machine-heat integrated deployable sun-shading temperature control device, which solves the realization of a thermal control temperature control device with variable spatial positions, has flexible thermal control temperature control characteristics of being deployable and retractable, and can improve the energy utilization rate and effective payload capacity of spacecraft.

[0051] To facilitate understanding of this embodiment, a detailed description of a stacked, thermo-mechanical integrated, expandable and retractable sunshade and temperature-regulating device disclosed in this embodiment of the invention will be provided first. (See [link to relevant documentation]). Figure 1 The diagram shows a stacked, thermo-mechanical integrated, retractable sunshade and temperature-regulating device. The device includes: a drive unit 1, a pressing and releasing device 2, a position switch device 3, a retractable structure 4, and a sunshade and temperature-regulating device 5.

[0052] The drive unit 1 is fixedly connected to the spacecraft cabin panel, and the deployment and retraction structure 4 is hinged to the drive unit 1. The drive unit 1 is used to drive the deployment and retraction structure 4 to rotate around the rotation axis.

[0053] The clamping and releasing device 2 is fixedly connected to the deploying and retracting structure 4 and is used to clamp and fix the deploying and retracting structure 4 to the spacecraft cabin panel;

[0054] The positioning switch device 3 is fixedly connected to the retractable structure 4 and is used to indicate whether the retractable structure 4 is closed in place.

[0055] In the compressed state of a stacked thermo-mechanical integrated retractable sunshade and temperature-regulating device, the retractable structure 4 is closed in place, triggering the position switch of the position switch device 3. In the unfolded state, the retractable structure 4 moves around the rotation axis to open, and the position switch is disconnected with no signal.

[0056] like Figure 3 As shown, the sunshade and temperature regulation device 5 is installed on the side of the retractable structure 4 facing the inside of the spacecraft, and is used to provide sunshade protection and temperature regulation for heat-sensitive payloads inside the spacecraft. The various components work together to realize a layered, thermo-mechanical integrated retractable sunshade and temperature regulation device that can achieve temperature preservation and regulation in the retracted state and establish an observation channel in the deployed state.

[0057] Polyimide or fiberglass heat insulation pads are installed at the installation positions between the drive device 1 and the unfolding structure 4, between the pressing and releasing device 2 and the unfolding structure 4, and between the sunshade and temperature regulation device 5 and the unfolding structure 4 to achieve heat insulation installation.

[0058] Preferably, the compression release device 2 is installed at a position symmetrical to the drive device 1 about the center of the unfolding structure 4.

[0059] During the launch phase, the deployable structure 4 can be reliably pressed against the spacecraft's cabin panel. After the spacecraft enters orbit, the pressing release device 2 is energized, and the internal pyrotechnics ignite, unlocking the stacked thermo-mechanical integrated deployable sunshade and temperature-regulating device. The drive device 1 then drives the deployable structure 4 to move, opening or closing it.

[0060] Preferably, it also includes a temperature measuring and heating device 6; the temperature measuring and heating device 6 is used to measure the surface temperature of the sunshade and temperature regulating device 5, and to perform heating treatment when the sunshade and temperature regulating device 5 is below the temperature index.

[0061] like Figure 4 As shown, the extendable drive device 1 includes: a mounting base plate 11, a drive assembly 12, an active hinge 13, a driven hinge 14, and a connector mounting bracket 15.

[0062] Active hinge 13 and passive hinge 14 are hinged to mounting base plate 11, and the free ends of active hinge 13 and passive hinge 14 are fixedly connected to retractable structure 4.

[0063] The drive assembly 12 is mounted on the mounting base plate 11, and the drive assembly 12, the active hinge 13, and the driven hinge 14 are all located on the same side of the mounting base plate 11.

[0064] Mounting base plate 11 is mounted on the spacecraft cabin panel;

[0065] The active hinge 13 is connected to the output shaft of the drive assembly 12 by a pin to realize power transmission; the driven hinge 14, the active hinge 13 and the drive assembly 12 are all coaxially mounted, so that the three have the same rotation axis, ensuring the stability and consistency of rotational motion.

[0066] The connector mounting bracket 15 is mounted on the mounting base plate 11. The connector mounting bracket 15 is used to bundle the cables of the drive assembly 12 and the switch assembly 32, and to provide a mounting interface for the electrical connector. The connector mounting bracket 15 should be as close as possible to the output port of the drive assembly 12 while ensuring the installation space for the connector.

[0067] like Figure 5 As shown, the position switch device 3 includes: a trigger head 31, a switch assembly 32, and a switch bracket 33;

[0068] The trigger head 31 is mounted on the deployment and retraction structure 4, the switch assembly 32 is mounted in the slit on the switch bracket 33, and the switch bracket 33 is mounted on the spacecraft cabin panel.

[0069] In the retracted state of a stacked thermo-mechanical integrated retractable sunshade and temperature-regulating device, the installation position of the switch bracket 33 needs to be adjusted so that the trigger head 31 contacts the straight spring 321 in the switch assembly 32 and applies pressure, so that the straight spring 321 and the bent spring 322 in the switch assembly 32 contact each other, and the switch 3 generates a trigger signal.

[0070] Both the trigger head 31 and the switch bracket 33 are made of insulating materials. Polyimide (PI) can be used directly or the surface of the metal material can be treated with insulation such as oxidation or electroplating.

[0071] The switch assembly 32 is made of a material with good conductivity. For metals, beryllium bronze, aluminum alloy, etc. can be selected, and for non-metals, conductive plastics can be selected.

[0072] like Figure 6 As shown, the switch bracket 33 has two slits machined on its side. The switch assembly 32 consists of a straight spring 321 and a bent spring 322. Grooves are provided in the two slits of the switch bracket 33 as positioning structures. Both the straight spring 321 and the bent spring 322 have protrusions at their bottoms that mate with the grooves. In this embodiment, the height of the protrusions on the straight spring 321 and the bent spring 322 is designed to be 0.5mm. The straight spring 321 and the bent spring 322 can be inserted from the side of the switch bracket 33 and fixed in the spring mounting window of the switch bracket using a cover plate, ensuring that the relative positions of the straight spring 321 and the bent spring 322 remain unchanged during repeated use.

[0073] The retractable structure 4 adopts a ring structure. The inner ring is reinforced with "rice" shaped ribs of different cross sections. The cross section of the "rice" ribs adopts a "T" shaped structure, which is used to increase the load capacity and structural strength. The periphery of the retractable structure 4 is provided with uniform or non-uniform threaded holes to achieve fixed connection with the sunshade and temperature regulation device 5, as shown in Figure 7.

[0074] The sunshade and temperature regulation device 5 includes: mounting feet 51, phase change cavity 52, thin aluminum plate, heat conduction cavity 53, and supporting shell 54;

[0075] Multiple mounting feet 51 are evenly distributed around the edge of the supporting shell 54. The mounting feet 51 are connected to the unfolding structure 4 via connectors.

[0076] The supporting shell 54 is provided with a phase change cavity 52 and a heat conduction cavity 53 inside;

[0077] The supporting shell 54 has an aluminum skin structure and is used to provide mechanical support for the phase change cavity 52 and the heat conduction cavity 53;

[0078] like Figure 8 As shown, the phase change cavity 52 and the heat conduction cavity 53 are stacked and installed, separated by a thin aluminum plate. The phase change cavity 52 is located on the side closer to the unfolding structure 4, and the heat conduction cavity 53 is located on the side away from the unfolding structure 4 (i.e., the side closer to the spacecraft cabin).

[0079] The supporting shell 54, phase change cavity 52, and heat conduction cavity 53 are manufactured using an integrated additive manufacturing process.

[0080] like Figure 9 As shown, the interior of the phase change cavity 52 is composed of additively manufactured cell lattices. The cell lattices are mainly used to enhance the structural rigidity, and the lattice pores are filled with phase change working fluid.

[0081] The heat-conducting cavity 53 is composed of a heat pipe array for heat conduction;

[0082] The phase change cavity 52 is provided with at least two filling holes. The filling holes are used to fill the phase change working medium into the phase change cavity 52. ​​The filling holes appear in pairs. One is used to fill the working medium, and the other is used to determine whether the working medium is full. Before filling the medium, the phase change cavity 52 needs to be leak-tested.

[0083] like Figure 2 As shown, the temperature measuring and heating device 6 includes: a temperature measuring probe 61 and a heating element 62; there are multiple temperature measuring probes 61 and heating elements 62, which are installed on the end face of the sunshade and temperature regulating device 5 facing the inside of the spacecraft cabin, and are used to obtain and regulate the surface temperature of the sunshade and temperature regulating device 5. The temperature measuring probes 61 are distributed in a dispersed manner, and the spacing should take into account the requirements of phase change heat transfer efficiency, temperature control accuracy and temperature uniformity.

[0084] The temperature probe 61 and the heating element 62 should be used in combination and spaced as close as possible.

[0085] Preferably, in the embodiments of the present invention Figure 1 The position switch device 3 shown is used to provide a retracted position signal. Depending on the application requirements, this type of position switch device can also be used to indicate the unfolded position.

[0086] Preferably, the retractable structure adopts a ring structure, and the strength is enhanced by structural ribs inside the ring. Figures 7(a) and (b) illustrate the "rice" shaped rib structure diagram and cross-sectional schematic diagram, which can increase the load capacity. Uniform or non-uniform threaded interfaces are set around the ring to realize the stacked mechanical installation connection of the load.

[0087] Example

[0088] In one embodiment, the sunshade and temperature regulation device 5 is provided with multiple mounting feet in the circumference. The sunshade and temperature regulation device is provided with a phase change cavity 52 and a heat conduction cavity 53 inside. The phase change cavity and the heat conduction cavity are stacked and installed. The supporting shell of the sunshade and temperature regulation device is made with the phase change cavity and the heat conduction cavity using an additive manufacturing integrated process. The material can be selected as AlSi10Mg aluminum alloy powder.

[0089] In one embodiment, the phase change cavity 52 is filled with a lattice of cell elements. Figure 9 A pyramid-structured lattice cell with a rod diameter of 0.5 mm and a cell size of 3.75 mm is provided to ensure that the pore volume and filling mass of the phase change cavity meet the temperature control requirements; the liquid filling the phase change cavity can be selected from liquid-solid phase change working fluids such as n-tetradecane and ethylene glycol.

[0090] Preferably, the outer surface of the phase change cavity 52 is coated with a high-emissivity paint to radiate the heat stored in the phase change material to the external space, thereby restoring the heat storage capacity of the phase change material.

[0091] Preferably, the phase change cavity 52 should have at least one filling hole and one powder outlet hole, and the phase change cavity 52 should be leak-tested before filling.

[0092] In one embodiment, a stacked, thermo-mechanical integrated, retractable sunshade and temperature-regulating device further includes a temperature-measuring and heating device 6. Multiple temperature probes 61 and heating elements 62 are present and installed on the lower side or shaded side of the sunshade and temperature-regulating device 5. These are used to acquire and regulate the main body temperature of the sunshade and temperature-regulating device 5. The temperature probes 61 should be distributed, with the spacing determined by considering phase change heat transfer efficiency, temperature control accuracy, and temperature uniformity requirements; for example, the spacing should be designed within the range of Φ200mm to Φ250mm. Simultaneously, the temperature probes and heating elements 62 should be used in combination and arranged as close as possible to each other.

[0093] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any person skilled in the art can make possible variations and modifications to the technical solutions of the present invention using the disclosed methods and techniques without departing from the spirit and scope of the invention. Therefore, any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the content of the technical solutions of the present invention, shall fall within the protection scope of the present invention. Where there is no conflict, the embodiments of this application and the technical features thereof can be combined with each other.

[0094] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A layered machine-thermal integrated deployable sun-shading and temperature-regulating device, characterized in that, The application relates to a deployable and retractable drive device for a spacecraft. The drive device (1), the compression and release device (2), the in-place switch device (3), the deployable and retractable structure (4) and the sunshade and temperature adjusting device (5) are connected with each other; The drive device (1) is fixedly connected with a spacecraft cabin plate, the deployable and retractable structure (4) is hingedly connected with the drive device (1), and the drive device (1) is used for driving the deployable and retractable structure (4) to rotate around a rotating shaft; The compression and release device (2) is fixedly connected with the deployable and retractable structure (4) and is used for compressing and fixing the deployable and retractable structure (4) to the spacecraft cabin plate; The in-place switch device (3) is fixedly connected with the deployable and retractable structure (4) and is used for indicating whether the deployable and retractable structure (4) is closed in place; The sunshade and temperature adjusting device (5) is installed on one side of the deployable and retractable structure (4) and faces the inside of the spacecraft and is used for sunshade protection and temperature adjustment of a heat-sensitive load in the spacecraft; Heat insulation pads made of polyimide or glass steel are arranged at the installation positions between the drive device (1) and the deployable and retractable structure (4), between the compression and release device (2) and the deployable and retractable structure (4) and between the sunshade and temperature adjusting device (5) and the deployable and retractable structure (4) to realize heat insulation installation; The compression and release device (2) and the drive device (1) are symmetrically arranged about the center of the deployable and retractable structure (4); In the launching stage, the deployable and retractable structure (4) is compressed on the spacecraft cabin plate; After the spacecraft is put into orbit, the compression and release device (2) is electrified, the internal explosive is ignited, unlocking is realized, the drive device (1) drives the deployable and retractable structure (4) to move, opening or closing is realized; The sunshade and temperature adjusting device (5) comprises installation feet (51), a phase change cavity (52), a thin aluminum plate, a heat conduction cavity (53) and a supporting shell (54). A plurality of installation feet (51) are circumferentially and evenly arranged at the edges of the supporting shell (54), the installation feet (51) are installed and connected with the deployable and retractable structure (4) through connecting pieces. The supporting shell (54) is internally provided with the phase change cavity (52) and the heat conduction cavity (53). The phase change cavity (52) and the heat conduction cavity (53) are installed in layers, are separated by the thin aluminum plate in the middle, the phase change cavity (52) is located on the side close to the deployable and retractable structure (4), and the heat conduction cavity (53) is located on the side away from the deployable and retractable structure (4). The phase change cavity (52) is internally formed by a cell point array manufactured by additive manufacturing, and a phase change working medium is filled in the pores of the cell point array; the heat conduction cavity (53) is composed of a heat pipe array and is used for heat conduction. The application further comprises a temperature measuring and heating device (6). The temperature measuring and heating device (6) is used for measuring the surface temperature of the sunshade and temperature adjusting device (5) and performing heating treatment when the sunshade and temperature adjusting device (5) is lower than a temperature index. The temperature measuring and heating device (6) comprises a temperature measuring probe (61) and a heating sheet (62). The temperature measuring probe (61) and the heating sheet (62) are both provided in plurality and are installed on the end face of the sunshade and temperature adjusting device (5) and face the inside of the spacecraft cabin.

2. The integrated solar energy and heat device according to claim 1, wherein, The deployable and retractable drive device (1) comprises an installation base plate (11), a drive assembly (12), a driving hinge (13) and a driven hinge (14). The driving hinge (13) and the driven hinge (14) are hingedly connected with the installation base plate (11), and the free ends of the driving hinge (13) and the driven hinge (14) are fixedly connected with the deployable and retractable structure (4). The driving assembly (12) is mounted on the mounting base plate (11), and the driving assembly (12), the driving hinge (13) and the driven hinge (14) are located on the same side of the mounting base plate (11); The mounting base plate (11) is mounted on a spacecraft cabin plate; The driving hinge (13) is connected with the output shaft of the driving assembly (12) through a pin, so as to realize power transmission; the driving hinge (13), the driven hinge (14) and the driving assembly (12) are coaxially mounted.

3. The integrated solar energy and heat device according to claim 2, wherein the device is characterized by: The in-place switch device (3) comprises a trigger head (31), a switch assembly (32) and a switch bracket (33); The trigger head (31) is mounted on the unfolding and folding structure (4), the switch assembly (32) is mounted on the switch bracket (33), and the switch bracket (33) is mounted on the spacecraft cabin plate; The trigger head (31) is in contact with the switch assembly (32) and applies pressure, so that the switch assembly (32) is turned on to generate a trigger signal.

4. The integrated solar energy and heat device according to claim 3, wherein the device is characterized by: The trigger head (31) and the switch bracket (33) are both made of insulating materials; The switch assembly (32) is made of any one of beryllium bronze, aluminum alloy or conductive plastic.

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