Stacked mechanical-thermal integrated foldable sun-shading and temperature-adjusting device

Abstract

A stacked mechanical-thermal integrated foldable sunshade temperature adjusting device is characterized in that a driving device is fixedly connected with a spacecraft deck, a foldable structural body is hinged to the driving device, and the driving device is used for driving the foldable structural body to rotate around a rotating shaft; the pressing and releasing device is used for pressing and fixing the unfolding and folding structural body and the spacecraft deck; the in-place switch device is used for indicating whether the unfolding and folding structure body is closed in place or not; the sunshade temperature adjusting device is installed on the side, facing the inner side of the spacecraft, of the unfolding and folding structural body and used for conducting sunshade protection and temperature adjustment on heat-sensitive loads in the spacecraft. The flexible thermal control temperature adjusting device has the flexible thermal control temperature adjusting characteristic of being capable of being unfolded and folded, and the energy utilization rate and the effective load capacity of the spacecraft can be improved.

Description

Technical Field

[0001] The present invention belongs to the field of the intersection of aerospace mechanism and thermal control technology, and in particular to a stacked mechanical and thermal integrated retractable sunshade and temperature regulating device. Background Art

[0002] With the rapid development of aerospace technology, its forms are becoming more diverse, its functions and structures are becoming more complex, and the types and quantities of payload equipment required 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 an appropriate operating temperature range. The traditional method usually requires installing a heat sink on the spacecraft. Depending on the temperature regulation requirements, the heat sink sometimes needs to face the deep cold space to dissipate heat, and sometimes needs to face the heat source to heat. This function requires a lot of energy to adjust the position of the entire device to achieve it, which is not conducive to increasing the spacecraft's payload capacity and reducing launch costs.

[0004] On the other hand, some optical devices sometimes need to be shielded for heat preservation, and sometimes need to be observed without shielding, and different working modes have different requirements for ambient temperature. The existing scheme usually implements the heat implementation and shielding device separately. The thermal control adopts the conventional heat pipe heat conduction and heat dissipation surface plus heat dissipation. The shielding device is implemented with lightweight aluminum alloy / titanium alloy or fiber materials, which will occupy more effective layout space and weight resources, and the system efficiency is low, which puts forward restrictions on the use of optical equipment that needs flexible adjustment of temperature and observation field.

[0005] At present, the traditional method of using the whole device maneuverability and heat pipe heat conduction to meet the heat dissipation surface and thermal control requirements, as well as the flexibility required for ambient temperature, is achieved by the traditional use of thermal implementation and shielding devices. This method has the following disadvantages: 1) There are many mechanical interfaces with the entire satellite, and the satellite platform needs to provide radiation panels, adapter plates and heat pipe installation supports, which occupy a lot of space resources of the entire satellite, and the heat pipe layout is complex, making the assembly implementation difficult; 2) The sunshade movement mechanism and temperature control device are implemented separately, which are heavier and consume more power, reducing the energy utilization efficiency of the entire satellite; 3) It cannot meet the use requirements of optical equipment that have flexible adjustment requirements for both temperature and observation field of view. Summary of the invention

[0006] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art and provide a stacked mechanical and thermal integrated retractable sunshade and temperature regulating device, which overcomes the difficulty that some spacecraft payloads need to achieve both shielding and heat preservation and open observation functions at the same time, and solves the technical problem of the coordination between the spacecraft motion mechanism and the thermal control component.

[0007] The technical solution of the present invention is:

[0008] A stacked mechanical and thermal integrated retractable sunshade and temperature regulating device, comprising: a driving device, a pressing and releasing device, an in-position switch device, a retractable structure and a sunshade and temperature regulating device;

[0009] The driving device is fixedly connected to the spacecraft cabin plate, the stowage structure is hinged to the driving device, and the driving device is used to drive the stowage structure to rotate around the rotation axis;

[0010] The compression release device is fixedly connected to the stowage structure and is used to compress and fix the stowage structure to the spacecraft cabin panel;

[0011] The in-place switch device is fixedly connected to the unfolding and retracting structure and is used to indicate whether the unfolding and retracting structure is in full closure;

[0012] The sunshade and temperature regulating device is installed on the side of the deployment structure facing the inner side of the spacecraft, and is used to provide sunshade protection and temperature regulation for heat-sensitive loads inside the spacecraft.

[0013] Preferably, thermal insulation pads made of polyimide or fiberglass are provided at the installation positions between the driving device and the stowage structure, between the compression and release device and the stowage structure, and between the sunshade and temperature regulating device and the stowage structure to achieve thermal insulation installation.

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

[0015] Preferably, during the launch phase, the stowed structure is pressed against the spacecraft deck;

[0016] After the spacecraft enters orbit, the compression release device is energized, the internal pyrotechnics ignite to unlock, and the drive device drives the deployment structure to move to open or close.

[0017] Preferably, the retractable driving device comprises: a mounting base, a driving assembly, an active hinge and a driven hinge;

[0018] The active hinge and the passive hinge are hingedly mounted on a base plate, and the free ends of the active hinge and the passive hinge are fixedly connected to the expansion and contraction structure;

[0019] The driving assembly is mounted on the mounting base plate, and the driving 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 mounted on the spacecraft cabin panel;

[0021] The active hinge is connected to the output shaft of the driving assembly through a pin to achieve power transmission; the driven hinge, the active hinge and the driving assembly are all coaxially installed.

[0022] Preferably, the in-place switch device comprises: a trigger head, a switch assembly and a switch bracket;

[0023] The trigger head is mounted on the stowage 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 switch component and applies pressure, so that the switch component is turned on and generates a trigger signal.

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

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

[0027] Preferably, the sunshade and temperature regulating device comprises: a mounting foot, a phase change cavity, a thin aluminum plate, a heat conduction cavity and a supporting shell;

[0028] A plurality of mounting feet are evenly distributed around the edge of the supporting shell, and the mounting feet are connected to the unfolding and retracting structure through connecting pieces;

[0029] A phase change cavity and a heat conduction cavity are arranged inside the supporting shell;

[0030] The phase change cavity and the heat conduction cavity are stacked and separated by a thin aluminum plate in the middle. The phase change cavity is located on the side close to the expansion and retraction structure, and the heat conduction cavity is located on the side away from the expansion and retraction structure.

[0031] Preferably, the interior of the phase change cavity is composed of a cell lattice manufactured by additive manufacturing, and the pores of the cell lattice are filled with a phase change working medium; the heat conduction cavity is composed of a heat pipe array for heat conduction.

[0032] Preferably, it also 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 lower than the temperature index;

[0034] The temperature measuring and heating device comprises: a temperature measuring probe and a heating plate;

[0035] There are multiple temperature measuring probes and heating plates, which are installed on the end surface of the sunshade and temperature regulating device facing the inner side 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. The present invention uses stacked mechanical and thermal integration technology to achieve the change of the spatial position of the thermal control implementation device, increase the flexibility of thermal control implementation, and effectively improve the energy utilization efficiency of the 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 envelope size of the spacecraft, and increases the flexibility of the spatial layout of the equipment.

[0038] 2. The present invention uses additive manufacturing integrated molding technology to form a cavity with energy storage and thermal management functions, cooperates with a heat-conducting cavity, and uses a heater and a temperature sensor to ensure the required light and heat environment conditions on the back side of the sunshade flip mechanism, thereby solving the problems of low temperature control accuracy and poor uniformity in the prior art.

[0039] 3. The present invention sets an annular expansion and contraction structure on the outside of the sunshade and temperature regulating device, and sets reinforcing ribs. Compared with directly installing the sunshade and temperature regulating 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 It is a schematic diagram of the front structure of the present invention;

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

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

[0043] Figure 4 It is a schematic diagram of the structure of the retractable driving device in the present invention;

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

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

[0046] FIG. 7( a ) is a diagram showing the structure of the "M"-shaped ribs of the unfolding and stowing structure of the present invention;

[0047] FIG7( b ) is a cross-sectional schematic diagram of the unfolding and stowing structure of the present invention;

[0048] Figure 8 It is a schematic diagram of the structure of the sunshade and temperature regulating device of the present invention;

[0049] Fig. 9 This is a typical example diagram of the phase change cavity lattice structure in the sunshade and temperature control device of the present invention. DETAILED DESCRIPTION

[0050] To better describe the present invention, the present invention is described in detail with schematic diagrams and examples. The present invention provides a stacked mechanical and thermal integrated retractable sunshade and temperature control device, which solves the problem of realizing a thermal control and temperature control device with variable spatial position, has a flexible thermal control and temperature control feature that can be deployed and retracted, and can improve the energy utilization rate and payload capacity of spacecraft.

[0051] To facilitate understanding of this embodiment, firstly, a stacked mechanical and thermal integrated retractable sunshade and temperature regulating device disclosed in an embodiment of the present invention is described in detail, see Figure 1 The structure diagram of a stacked mechanical and thermal integrated retractable sunshade and temperature regulating device is shown, and the device includes: a driving device 1, a compression and release device 2, an in-position switch device 3, an expansion and retracting structure 4 and a sunshade and temperature regulating device 5.

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

[0053] The compression and release device 2 is fixedly connected to the stowage structure 4, and is used to compress and fix the stowage structure 4 to the spacecraft cabin panel;

[0054] The in-position switch device 3 is fixedly connected to the stowable structure 4 and is used to indicate whether the stowable structure 4 is in-position.

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

[0056] like Figure 3 As shown, the sunshade and temperature regulating device 5 is installed on the side of the stowage structure 4 facing the inner side of the spacecraft, and is used to provide sunshade protection and temperature regulation for the heat-sensitive loads inside the spacecraft. The various components work together to realize a stacked mechanical and thermal integrated stowage sunshade and temperature regulating device that can achieve the functions of heat preservation and temperature regulation in the stowed state and establishment of an observation channel in the deployed state.

[0057] Insulation pads made of polyimide or fiberglass are provided at the installation positions between the driving device 1 and the stowage structure 4, between the compression and release device 2 and the stowage structure 4, and between the sunshade and temperature regulating device 5 and the stowage structure 4 to achieve heat insulation installation.

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

[0059] During the launch phase, the stowage structure 4 can be reliably pressed against the spacecraft cabin board. After the spacecraft enters orbit, the pressing release device 2 is energized, the internal pyrotechnics are ignited, and the stacked mechanical and thermal integrated stowageable sunshade and temperature regulating device is unlocked, and the driving device 1 drives the stowage structure 4 to move and open or close.

[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 perform heating treatment on the sunshade and temperature regulating device 5 when the temperature is lower than the temperature index.

[0061] like Figure 4 As shown, the retractable driving device 1 comprises: a mounting base 11, a driving assembly 12, an active hinge 13, a driven hinge 14 and a connector mounting frame 15;

[0062] The active hinge 13 and the passive hinge 14 are hingedly mounted on the base plate 11, and the free ends of the active hinge 13 and the passive hinge 14 are fixedly connected to the unfolding and retracting structure 4;

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

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

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

[0066] The connector mounting frame 15 is installed on the mounting substrate 11. The connector mounting frame 15 is used to bundle the cables of the drive component 12 and the switch component 32, and provide an installation interface for the electrical connector. The connector mounting frame 15 should be as close as possible to the outlet port of the drive component 12 while ensuring the installation space of the connector.

[0067] like Figure 5 As shown, the in-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 stowage 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 board;

[0069] When a stacked mechanical and thermal integrated retractable sunshade and temperature control device is in a folded state, it is necessary to adjust the installation position of the switch bracket 33 so that the trigger head 31 contacts and applies pressure to the straight spring piece 321 in the switch assembly 32, so that the straight spring piece 321 and the bent spring piece 322 in the switch assembly 32 contact, and the switch 3 is in place to generate a trigger signal.

[0070] The trigger head 31 and the switch bracket 33 are both made of insulating materials, and polyimide PI can be directly used or an insulating treatment such as oxidation or electroplating can be performed on the surface of the metal material;

[0071] The switch assembly 32 is made of a material with good electrical conductivity. The metal may be beryllium bronze, aluminum alloy, etc., and the non-metal may be conductive plastic.

[0072] like Figure 6 As shown, the switch bracket 33 has two slits on its side, and the switch assembly 32 is composed of a straight spring piece 321 and a bent spring piece 322. The two slits of the switch bracket 33 are respectively provided with grooves as positioning structures, and the bottoms of the straight spring piece 321 and the bent spring piece 322 are both provided with protrusions that match the groove structures. In the embodiment of the present invention, the height of the protrusions of the straight spring piece 321 and the bent spring piece 322 is designed to be 0.5 mm. The straight spring piece 321 and the bent spring piece 322 can be inserted from the side of the switch bracket 33 and fixed in the spring piece installation window of the switch bracket by a cover plate, ensuring that the relative positions of the straight spring piece 321 and the bent spring piece 322 remain unchanged during repeated use.

[0073] The expansion and retracting structure 4 adopts a ring-shaped structure, and "M"-shaped ribs with different cross-sections are used inside the ring to enhance the structural strength. The cross-section of the "M"-shaped rib adopts a "T"-shaped structure, both of which are used to increase the load capacity and structural strength. Uniform or uneven threaded holes are provided on the edge of the circumference of the expansion and retracting structure 4 to achieve fixed connection with the sunshade and temperature regulating device 5, as shown in Figure 7.

[0074] The sunshade and temperature regulating device 5 comprises: a mounting foot 51, a phase change cavity 52, a thin aluminum plate, a heat conduction cavity 53 and a supporting shell 54;

[0075] A plurality of mounting feet 51 are evenly distributed around the edge of the supporting shell 54, and the mounting feet 51 are mounted and connected to the stowage structure 4 through a connecting piece;

[0076] A phase change cavity 52 and a heat conduction cavity 53 are provided inside the supporting shell 54;

[0077] The supporting shell 54 is an aluminum skin structure, which 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 separated by a thin aluminum plate. The phase change cavity 52 is located on the side close to the expansion and retraction structure 4, and the heat conduction cavity 53 is located on the side away from the expansion and retraction structure 4 (i.e., the side close to the spacecraft cabin).

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

[0080] like Fig. 9 As shown, the interior of the phase change cavity 52 is formed by a cell lattice manufactured by additive manufacturing. The cell lattice is mainly used to enhance the structural rigidity, and the lattice pores are filled with a phase change medium.

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

[0082] The phase change cavity 52 is provided with at least two filling holes, which are used to fill the phase change working fluid into the phase change cavity 52. ​​The filling holes appear in pairs, one for filling the working fluid and the other for determining whether the working fluid is full. Before filling, 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 plate 62; there are multiple temperature measuring probes 61 and heating plates 62, and they are installed on the end surface of the sunshade and temperature regulating device 5 facing the inner side of the spacecraft cabin, and are used to obtain and adjust the surface temperature of the sunshade and temperature regulating device 5. The temperature measuring probes 61 are arranged in a dispersed manner, and the spacing setting should comprehensively consider the phase change heat transfer efficiency, temperature control accuracy and temperature uniformity requirements.

[0084] The temperature measuring probe 61 and the heating plate 62 should be used in combination, and the distance between them should be as close as possible.

[0085] Preferably, in the embodiment of the present invention Figure 1 The function of the in-position switch device 3 shown is to provide a folded in-position signal. According to application requirements, this type of in-position switch device can also be used to indicate the deployed in-position.

[0086] Preferably, the expansion and contraction structure adopts an annular structure, and structural ribs are used inside the ring to enhance strength. Figure 7 (a) (b) shows an example of the "M"-shaped rib structure diagram and cross-sectional schematic diagram, which can increase the load capacity. Uniform or uneven threaded interfaces are arranged around the ring to realize a stacked mechanical installation connection of the load.

[0087] Example

[0088] In one embodiment, a plurality of mounting feet are provided around the sunshade and temperature regulating device 5, a phase change cavity 52 and a heat conduction cavity 53 are provided inside the sunshade and temperature regulating device, and the phase change cavity and the heat conduction cavity are installed in a stacked manner; the supporting shell of the sunshade and temperature regulating device and the phase change cavity and the heat conduction cavity are manufactured by an integrated additive manufacturing process, and the material can be AlSi10Mg aluminum alloy powder.

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

[0090] Preferably, the outer surface of the shell of the phase change cavity 52 is coated with high-radiation paint to radiate the heat stored in the phase change material to the external space and restore the heat storage capacity of the phase change material.

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

[0092] In one embodiment, a stacked mechanical and thermal integrated retractable sunshade and temperature regulating device further includes a temperature measuring and heating device 6, wherein there are multiple temperature measuring probes 61 and heating plates 62, which are installed on the lower side or the back side of the sunshade and temperature regulating device 5, and are used to obtain and adjust the main body temperature of the sunshade and temperature regulating device 5. The temperature measuring probes 61 should be dispersedly arranged, and the spacing setting comprehensively considers the phase change heat transfer efficiency, temperature control accuracy and temperature uniformity requirements, such as the design spacing within the range of Φ200mm to Φ250mm. At the same time, the temperature measuring probes and heating plates 62 should be used in combination, and the layout should be as close as possible.

[0093] Although the present invention has been disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention by using the above disclosed methods and technical contents without departing from the spirit and scope of the present invention. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall belong to the protection scope of the technical solution of the present invention. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other.

[0094] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A stacked mechanical and thermal integrated retractable sunshade and temperature regulating device, characterized in that: include: A driving device (1), a pressing and releasing device (2), an in-position switch device (3), an unfolding and retracting structure (4) and a sunshade and temperature regulating device (5); The driving device (1) is fixedly connected to the spacecraft cabin panel, the stowage structure (4) is hinged to the driving device (1), and the driving device (1) is used to drive the stowage structure (4) to rotate around the rotation axis; The pressing and releasing device (2) is fixedly connected to the stowing and unfolding structure (4) and is used to press and fix the stowing and unfolding structure (4) and the spacecraft cabin panel; The in-place switch device (3) is fixedly connected to the unfolding and retracting structure (4) and is used to indicate whether the unfolding and retracting structure (4) is in a closed position; The sunshade and temperature regulating device (5) is installed on the side of the unfolding and stowing structure (4) facing the inner side of the spacecraft, and is used for sunshade protection and temperature regulation of heat-sensitive loads inside the spacecraft.

2. A stacked mechanical and thermal integrated retractable sunshade and temperature regulating device according to claim 1, characterized in that: Thermal insulation pads made of polyimide or fiberglass are provided at the installation positions between the driving device (1) and the stowable structure (4), between the pressing and releasing device (2) and the stowable structure (4), and between the sunshade and temperature regulating device (5) and the stowable structure (4) to achieve thermal insulation installation.

3. The stacked mechanical and thermal integrated retractable sunshade and temperature regulating device according to claim 1, characterized in that: The pressing and releasing device (2) and the driving device (1) are symmetrical about the center of the unfolding and retracting structure (4).

4. The stacked mechanical and thermal integrated retractable sunshade and temperature regulating device according to claim 1, characterized in that: During the launch phase, the unfolding and stowing structure (4) is pressed against the spacecraft cabin panel; After the spacecraft enters orbit, the clamping release device (2) is energized, the internal pyrotechnics ignite, unlocking is achieved, and the driving device (1) drives the deployment structure (4) to move, opening or closing.

5. A stacked mechanical and thermal integrated retractable sunshade and temperature regulating device according to any one of claims 1 to 4, characterized in that: The retractable driving device (1) comprises: a mounting base (11), a driving assembly (12), an active hinge (13) and a driven hinge (14); The active hinge (13) and the passive hinge (14) are hingedly mounted on the base plate (11), and the free ends of the active hinge (13) and the passive hinge (14) are fixedly connected to the unfolding and retracting structure (4); The driving assembly (12) is mounted on the mounting base (11), and the driving assembly (12), the active hinge (13), and the driven hinge (14) are all located on the same side of the mounting base (11); The mounting base plate (11) is mounted on a spacecraft cabin panel; The active hinge (13) is connected to the output shaft of the driving assembly (12) via a pin to achieve power transmission; the driven hinge (14), the active hinge (13) and the driving assembly (12) are all coaxially mounted.

6. The stacked mechanical and thermal integrated retractable sunshade and temperature regulating device according to claim 5, characterized in that: The in-position 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 stowage structure (4), the switch assembly (32) is mounted on the switch bracket (33), and the switch bracket (33) is mounted on the spacecraft cabin panel; The trigger head (31) contacts the switch component (32) and applies pressure, so that the switch component (32) is turned on to generate a trigger signal.

7. The stacked mechanical and thermal integrated retractable sunshade and temperature regulating device according to claim 6, characterized in that: The trigger head (31) and the switch bracket (33) are both made of insulating materials; The switch component (32) is made of any one of beryllium copper, aluminum alloy or conductive plastic.

8. The stacked mechanical and thermal integrated retractable sunshade and temperature regulating device according to claim 5, characterized in that: The sunshade and temperature regulating device (5) comprises: a mounting foot (51), a phase change cavity (52), a thin aluminum plate, a heat conduction cavity (53) and a supporting shell (54); A plurality of mounting feet (51) are evenly distributed in the circumferential direction at the edge of the supporting shell (54), and the mounting feet (51) are mounted and connected to the unfolding and retracting structure (4) via a connecting piece; A phase change cavity (52) and a heat conduction cavity (53) are provided inside the supporting shell (54); The phase change cavity (52) and the heat conduction cavity (53) are stacked and separated by a thin aluminum plate in the middle; the phase change cavity (52) is located on a side close to the expansion and contraction structure (4), and the heat conduction cavity (53) is located on a side away from the expansion and contraction structure (4).

9. The stacked mechanical and thermal integrated retractable sunshade and temperature regulating device according to claim 8, characterized in that: The interior of the phase change cavity (52) is formed by a cell lattice manufactured by additive manufacturing, and the pores of the cell lattice are filled with a phase change working fluid; The heat conduction cavity (53) is composed of a heat pipe array and is used for heat conduction.

10. The stacked mechanical and thermal integrated retractable sunshade and temperature regulating device according to claim 9, characterized in that: Also includes: 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 on the sunshade and temperature regulating device (5) when the temperature is lower than the temperature index; The temperature measuring and heating device (6) comprises: a temperature measuring probe (61) and a heating plate (62); There are multiple temperature measuring probes (61) and heating plates (62), which are installed on the end surface of the sunshade and temperature regulating device (5) facing the inner side of the spacecraft cabin.

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