A thermal control method for a deployable star sensor assembly with high thermal stability and low thermal control power consumption

Abstract

A thermal control method for deployable star sensor assemblies with high thermal stability and low thermal control power consumption, belonging to the field of satellite thermal control technology, solves the problem that existing technologies cannot achieve high thermal stability of deployable star sensor assemblies under complex and variable external heat flow conditions with fewer resources. The method includes the following steps: deploying the star sensor; applying thin films to the outer surface of the multi-segment light shield of the star sensor and the upper surface of the top cover of the star sensor's electronics box; retracting the deployed star sensor; thermal control treatment of the star sensor; closed-loop temperature control treatment by attaching heating elements to the star sensor bracket; thermally insulating the star sensor and the star sensor bracket to obtain the star sensor assembly; thermally insulating the star sensor assembly to the main load-bearing substrate of the remote sensing camera; and bonding the upper outer circle of the top cover of the star sensor's electronics box in the star sensor assembly to the multi-layer thermal insulation assembly on the outside of the satellite using pressure-sensitive adhesive.

Description

Technical Field

[0001] This invention relates to the field of satellite thermal control technology, specifically to a thermal control method for deployable star sensor components with high thermal stability and low thermal control power consumption. Background Technology

[0002] The accuracy of uncontrolled positioning of remote sensing satellites largely determines the effectiveness of remote sensing image applications. As a high-precision attitude measurement instrument, the star sensor plays an important role in the attitude measurement and control system of the satellite. Its attitude determination accuracy and repeatability directly determine the uncontrolled positioning accuracy of the satellite, which in turn affects the high-precision geometric processing and application of remote sensing images without ground control.

[0003] Unlike traditional star sensors, deployable star sensors have their sunshades retracted before orbital insertion. By retracting their multiple sunshade segments, the volume of the star sensor in the launch state is reduced, which facilitates satellite layout and reduces the launch envelope. This has high practical value for microsatellites that pursue integration and miniaturization. However, due to its special structure, thermal design is difficult and implementation is risky. In particular, it is difficult to cover the pop-out part of the sunshade with multiple layers of heat insulation components, resulting in more drastic temperature fluctuations and poor thermal stability of the deployable star sensor assembly in orbit. Thermal stability directly affects the measurement accuracy of the star sensor and restricts further improvement of its accuracy, affecting the uncontrolled positioning accuracy of the satellite. Improving the thermal stability of the star sensor assembly requires ensuring not only the temperature of the star sensor support but also the temperature of the star sensor electronics box.

[0004] Based on a comprehensive consideration of the characteristics of the satellite platform and space environment factors, the traditional thermal control scheme for star sensor components takes the reduction of the influence of external heat flow and active heating compensation as its design principles. It adopts a combination of active and passive thermal control methods. By selecting materials such as thermal control coatings, thin film heating elements, heat pipes and multi-layer thermal insulation components, the star sensor components are designed with reasonable and effective thermal control to ensure that the star sensor components have a stable and suitable on-orbit temperature.

[0005] However, these methods are not entirely applicable to deployable star sensors, and the thermal control parameters in related studies mostly consider the star sensor bracket or mounting flange, with less consideration for the star sensor electronics enclosure, and even when requirements are placed, they are often not high. Therefore, for microsatellites, how to achieve high thermal stability of deployable star sensor components under complex and variable external space heat flow conditions with limited resources remains to be solved. Summary of the Invention

[0006] This invention solves the problem that existing technologies cannot achieve high thermal stability of deployable star sensor components under complex and variable external heat flow conditions with fewer resources.

[0007] The present invention discloses a thermal control method for a deployable star sensor assembly with high thermal stability and low thermal control power consumption, comprising the following steps:

[0008] Step S1: Unfold the star sensor, apply a thin film to the outer surface of the multi-segment light shield of the unfolded star sensor and the upper surface of the electronic box cover of the star sensor, and then fold up the unfolded star sensor.

[0009] Step S2: Perform thermal control treatment on the star sensor that was gathered in step S1.

[0010] Step S3: Perform closed-loop temperature control on the star sensor bracket and perform thermal control treatment on the inner and outer surfaces of the star sensor bracket respectively.

[0011] Step S4: Heat-insulate the star sensor that has been thermally controlled in step S2 with the star sensor bracket obtained in step S3 to obtain the star sensor assembly.

[0012] Step S5: Heat-insulate the star sensor assembly obtained in step S4 and the main load-bearing substrate of the remote sensing camera.

[0013] Step S6: Adhere the upper outer circle of the star sensor electronics box cover of the star sensor assembly that has been heat-insulated and installed in step S5 to the multi-layer heat insulation assembly on the outside of the satellite using pressure-sensitive adhesive.

[0014] Furthermore, in one embodiment of the present invention, in step S1, the thin film includes an F46 thin film.

[0015] Furthermore, in one embodiment of the present invention, step S2, which involves thermally controlling the star sensor that has been gathered in step S1, includes the following steps:

[0016] Step S201: The upper cover and lower cover of the star sensor electronics box are integrally coated with a thermally conductive graphite film.

[0017] Step S202: One end of the graphene flexible heat-conducting cable is attached to the thermally conductive graphite film on the lower cover of the star sensor electronics box, and the other end of the graphene flexible heat-conducting cable is connected to the main load-bearing structure plate of the satellite.

[0018] Step S203: Cover the lower cover of the star sensor electronics box with a multi-layer heat insulation component.

[0019] Furthermore, in one embodiment of the present invention, step S3, which involves performing closed-loop temperature control on the star sensor holder, specifically includes:

[0020] Thin film heating elements are attached to the inner surface of the star sensor bracket;

[0021] The inner surface of the star sensor bracket includes the inner side of the opposite side of the star sensor bracket mounting surface and the inner sides of both sides of the star sensor bracket.

[0022] Furthermore, in one embodiment of the present invention, step S3, which involves thermally controlling the inner and outer surfaces of the star sensor bracket, specifically includes:

[0023] Apply thermally conductive graphite film to all surfaces inside the star sensor bracket where the thin-film heating element has been attached;

[0024] In addition to the star sensor mounting hole, double-sided aluminized polyester film and single-sided acrylic pressure-sensitive adhesive are pasted on the star sensor mounting surface of the star sensor bracket, and a multi-layer heat insulation component is wrapped around the outer surface of the star sensor bracket except for the star sensor mounting surface.

[0025] Furthermore, in one embodiment of the present invention, in step S4, the thermally controlled star sensor from step S2 and the star sensor bracket from step S3, which has undergone closed-loop temperature control, are thermally insulated and installed together.

[0026] The star sensor and its bracket are installed with multiple polyimide heat insulation pads for thermal insulation.

[0027] The multiple polyimide heat insulation pads mentioned refer to four polyimide heat insulation pads.

[0028] Furthermore, in one embodiment of the present invention, step S5, specifically the thermal insulation installation of the star sensor assembly obtained in step S4 with the main load-bearing substrate of the remote sensing camera, specifically involves:

[0029] The star sensor assembly and the main load-bearing substrate of the remote sensing camera are installed with multiple polyimide thermal pads for thermal insulation.

[0030] The multiple polyimide heat insulation pads mentioned refer to four polyimide heat insulation pads.

[0031] Furthermore, in one embodiment of the present invention, in step S6, the upper outer circle of the star sensor electronics box cover in the star sensor assembly that has been thermally insulated in step S5 is bonded to the satellite's external multi-layer thermal insulation assembly using pressure-sensitive adhesive, specifically as follows:

[0032] In the star sensor assembly, one half of multiple strips of polyimide film single-sided acrylic pressure-sensitive adhesive is pasted on the upper outer circle of the star sensor electronics box cover, and the other half of the multiple strips of polyimide film single-sided acrylic pressure-sensitive adhesive is bonded to the satellite's external multi-layer heat insulation components.

[0033] The aforementioned multi-layer polyimide film single-sided acrylic pressure-sensitive adhesive consists of 8 polyimide film single-sided acrylic pressure-sensitive adhesives.

[0034] This invention solves the problem that existing technologies cannot achieve high thermal stability of deployable star sensor components under complex and variable external heat flux conditions with limited resources. Specific beneficial effects include:

[0035] 1. The thermal control method of the deployable star sensor assembly with high thermal stability and low thermal control power consumption described in this invention effectively utilizes the large mass characteristics of the satellite's main load-bearing structural plate as a structural heat sink, which fully weakens the adverse effects of alternating external heat flow on the deployable star sensor assembly. Without the need for additional heat dissipation surfaces, a balance is achieved between internal heat source, heat dissipation capacity and external heat flow, and high thermal stability of the deployable star sensor assembly under complex and variable external heat flow conditions is achieved with fewer resources.

[0036] 2. The thermal control method for a deployable star sensor assembly with high thermal stability and low thermal control power consumption described in this invention involves heat-insulating the star sensor bracket to the main load-bearing substrate of the remote sensing camera and the star sensor, respectively, attaching an aluminized polyester film single-sided acrylic pressure-sensitive adhesive to the mounting surface of the star sensor, setting a multi-layer heat insulation component between the star sensor and the star sensor, attaching a thin film heating plate and a thermally conductive graphite film to the inner surface of the star sensor bracket, and covering the outer surface of the star sensor bracket with a multi-layer heat insulation component, effectively isolating external influences, and achieving active temperature control of the star sensor bracket better than ±0.15℃ with low power consumption;

[0037] 3. The thermal control method for a deployable star sensor assembly with high thermal stability and low thermal power consumption described in this invention establishes a connection between the temperature of the star sensor electronics box and the satellite's main load-bearing structure plate through a graphene flexible heat-conducting cable. By attaching multiple strips of polyimide film single-sided acrylic pressure-sensitive adhesive in a ring-shaped distribution to the electronics box, the problem of difficulty in sealing the multi-layer heat insulation components outside the satellite when using a deployable star sensor assembly is solved, greatly reducing the impact of external space heat flow on the star sensor assembly. In addition, the upper and lower covers of the star sensor electronics box are integrally covered with a thermally conductive graphite film, effectively ensuring the uniform and stable temperature of the star sensor electronics box shell. With multiple measures combined, the on-orbit temperature fluctuation of the star sensor electronics box imaging sensor under purely passive thermal control is better than ±1.5℃. Attached Figure Description

[0038] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the following description of the embodiments taken in conjunction with the accompanying drawings, wherein:

[0039] Figure 1 This is a schematic diagram of the structural state of the deployable star sensor before and after deployment, as described in Embodiment 2.

[0040] Figure 2 This is a schematic diagram of the single-unit thermal control implementation of the star sensor as described in Embodiment 3;

[0041] Figure 3 This is a schematic diagram of the star sensor bracket structure and the adhesive position of the temperature control film heating element described in Embodiment 4;

[0042] Figure 4 This is a schematic diagram of the external thermal control implementation of the star sensor bracket as described in Embodiment 5;

[0043] Figure 5 This is a schematic diagram showing the structure and connection of the star sensor assembly described in Embodiment Six;

[0044] Figure 6 This is a schematic diagram of the layout of the star sensor assembly described in Embodiment 7 within the remote sensing satellite cabin;

[0045] Figure 7 This is a schematic diagram of the adhesive connection between the star sensor and the external multilayer heat insulation assembly of the satellite as described in Embodiment 8.

[0046] Figure 8 The following are on-orbit telemetry data diagrams of the star sensor assembly described in Embodiment 1: (a) temperature curve of the star sensor imaging sensor, (b) temperature curve of the star sensor support, and (c) on / off state diagram of the heater of the star sensor support. Detailed Implementation

[0047] Various embodiments of the present invention will now be clearly and completely described with reference to the accompanying drawings. The embodiments described with reference to the drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0048] Implementation Method 1: The thermal control method for a deployable star sensor assembly with high thermal stability and low thermal power consumption, as described in this implementation method, includes the following steps:

[0049] Step S1: Unfold the star sensor, apply a thin film to the outer surface of the multi-segment light shield of the unfolded star sensor and the upper surface of the electronic box cover of the star sensor, and then fold up the unfolded star sensor.

[0050] Step S2: Perform thermal control treatment on the star sensor that was gathered in step S1.

[0051] Step S3: Perform closed-loop temperature control on the star sensor bracket and perform thermal control treatment on the inner and outer surfaces of the star sensor bracket respectively.

[0052] Step S4: Heat-insulate the star sensor that has been thermally controlled in step S2 with the star sensor bracket that has been closed-loop temperature controlled in step S3 to obtain the star sensor assembly.

[0053] Step S5: Heat-insulate the star sensor assembly obtained in step S4 and the main load-bearing substrate of the remote sensing camera.

[0054] Step S6: Adhere the upper outer circle of the star sensor electronics box cover of the star sensor assembly that has been heat-insulated and installed in step S5 to the multi-layer heat insulation assembly on the outside of the satellite using pressure-sensitive adhesive.

[0055] In the existing technology, for microsatellites, it is not possible to achieve high thermal stability of deployable star sensor components with fewer resources under complex and variable external space heat flow conditions.

[0056] This application achieves a balance between internal heat source, heat dissipation capacity, and external heat flow without the need for additional heat dissipation surfaces, thus realizing high thermal stability of the deployable star sensor component under complex and variable external heat flow conditions with fewer resources.

[0057] like Figure 8 The image shown is a diagram of the on-orbit telemetry data (within 8 hours) of the star sensor component in this embodiment: Figure 8 As shown in (a), the on-orbit temperature fluctuation of the star sensor imaging sensor is better than ±1.5℃; Figure 8 As shown in (b), the on-orbit temperature fluctuation of the star sensor holder is better than ±0.15℃; Figure 8 As shown in (c), the duty cycle of the star sensor bracket heater is 0.34, and the average power consumption is about 0.27W.

[0058] Based on the above results, this embodiment achieves the thermal control objective of high thermal stability and low thermal control power consumption for the deployable star sensor component.

[0059] Implementation Method 2: This implementation method further defines the thermal control method for a deployable star sensor assembly with high thermal stability and low thermal control power consumption described in Implementation Method 1. In step S1, the thin film includes an F46 thin film.

[0060] In this embodiment, such as Figure 1 As shown, the star sensor needs to undergo surface thermo-optical property modification treatment in the unfolded state. F46 film is applied to the outer surface of each level of the light shield of the unfolded star sensor and the upper surface of the star sensor's electronics box (near the light shield). After the application is completed, the unfolded star sensor is folded up to prepare for the next step of processing.

[0061] Implementation Method 3: This implementation method further defines the thermal control method for a deployable star sensor assembly with high thermal stability and low thermal power consumption described in Implementation Method 1. In step S2, the thermal control treatment of the star sensor that was folded up in step S1 includes the following steps:

[0062] Step S201: The upper cover and lower cover of the star sensor electronics box are integrally coated with a thermally conductive graphite film.

[0063] Step S202: One end of the graphene flexible heat-conducting cable is attached to the thermally conductive graphite film on the lower cover of the star sensor electronics box, and the other end of the graphene flexible heat-conducting cable is connected to the main load-bearing structure plate of the satellite.

[0064] Step S203: Cover the lower cover of the star sensor electronics box with a multi-layer heat insulation component.

[0065] In this embodiment, such as Figure 2 As shown, thermal control processing is applied to the star sensor, specifically as follows:

[0066] First, the upper cover and lower cover of the star sensor electronics box are integrally bonded together using a thermally conductive graphite film.

[0067] Secondly, one end of a graphene flexible thermal conductive cable is attached to the thermally conductive graphene film on the lower cover of the star sensor electronics box, and the other end of the graphene flexible thermal conductive cable is connected and adhered to it. Figure 6 The satellite main load-bearing structure plate below the star sensor assembly is shown; the satellite main load-bearing structure plate acts as a structural heat sink.

[0068] Finally, a 10-unit multilayer thermal insulation assembly is wrapped around the lower cover of the star sensor electronics box, with the outer surface of the multilayer being a double-sided aluminum-coated polyester film.

[0069] By using graphene flexible heat-conducting cables, the temperature of the star sensor electronics box is linked to the satellite's main load-bearing structural plate. By attaching multiple strips of polyimide film with single-sided acrylic pressure-sensitive adhesive in a ring-shaped distribution within the electronics box, the problem of sealing the multi-layered external heat insulation components of the satellite when using deployable star sensor components is solved, greatly reducing the impact of external heat flow on the star sensor components. In addition, the upper and lower covers of the star sensor electronics box are integrally covered with thermally conductive graphite film, effectively ensuring the uniform and stable temperature of the star sensor electronics box shell. With these multiple measures combined, the on-orbit temperature fluctuation of the star sensor electronics box imaging sensor under purely passive thermal control is better than ±1.5℃.

[0070] Implementation Method Four: This implementation method further defines the thermal control method for a deployable star sensor assembly with high thermal stability and low thermal power consumption described in Implementation Method One. In step S3, the closed-loop temperature control treatment of the star sensor bracket specifically involves:

[0071] Thin film heating elements are attached to the inner surface of the star sensor bracket;

[0072] The inner surface of the star sensor bracket includes the inner side of the opposite side of the star sensor bracket mounting surface and the inner sides of both sides of the star sensor bracket.

[0073] In this embodiment, such as Figure 3 As shown, the star sensor bracket is made of TC4 titanium alloy, a material with a low coefficient of thermal expansion. Thin film heating elements are attached to the inside of the star sensor bracket and to all surfaces except the mounting side of the bracket to achieve closed-loop temperature control of the star sensor bracket. The temperature control loop power of the star sensor bracket is 0.8W.

[0074] Implementation Method 5: This implementation method further defines the thermal control method for a deployable star sensor assembly with high thermal stability and low thermal control power consumption described in Implementation Method 1. In step S3, the thermal control treatment of the inner and outer surfaces of the star sensor bracket is specifically as follows:

[0075] Apply thermally conductive graphite film to all surfaces inside the star sensor bracket where the thin-film heating element has been attached;

[0076] In addition to the star sensor mounting hole, double-sided aluminized polyester film and single-sided acrylic pressure-sensitive adhesive are pasted on the star sensor mounting surface of the star sensor bracket, and a multi-layer heat insulation component is wrapped around the outer surface of the star sensor bracket except for the star sensor mounting surface.

[0077] In this embodiment, such as Figure 4 As shown, a double-sided aluminized polyester film and a single-sided acrylic pressure-sensitive adhesive are pasted on the star sensor mounting surface of the star sensor bracket. It is worth noting that the star sensor mounting hole must be exposed. The remaining surface is covered with a 10-unit multi-layer heat insulation component, and the outer surface of the multi-layer is a double-sided aluminized polyester film.

[0078] Implementation Method Six: This implementation method further defines the thermal control method for a deployable star sensor assembly with high thermal stability and low thermal control power consumption described in Implementation Method One. Specifically, in step S4, the thermally controlled star sensor from step S2 and the star sensor support from step S3, which has undergone closed-loop temperature control, are thermally insulated during installation.

[0079] The star sensor and its bracket are installed with multiple polyimide heat insulation pads for thermal insulation.

[0080] The multiple polyimide heat insulation pads mentioned refer to four polyimide heat insulation pads.

[0081] In this embodiment, such as Figure 5 As shown, the star sensor and the star sensor bracket are installed with thermal insulation by four polyimide thermal pads.

[0082] Implementation Method Seven: This implementation method further defines the thermal control method for a deployable star sensor assembly with high thermal stability and low thermal control power consumption described in Implementation Method One. Specifically, in step S5, the thermal insulation installation of the star sensor assembly obtained in step S4 with the main load-bearing substrate of the remote sensing camera is as follows:

[0083] The star sensor assembly and the main load-bearing substrate of the remote sensing camera are installed with multiple polyimide thermal pads for thermal insulation.

[0084] The multiple polyimide heat insulation pads mentioned refer to four polyimide heat insulation pads.

[0085] In this embodiment, such as Figure 6As shown, the star sensor assembly is thermally insulated and mounted on the main load-bearing base plate of the remote sensing camera using four polyimide thermal pads.

[0086] Considering the target temperature of the main load-bearing substrate of the remote sensing camera, in order to reduce the mutual influence between the star sensor assembly and the main load-bearing substrate of the remote sensing camera, the target temperature of the star sensor bracket is set to be the same as the target temperature of the main load-bearing substrate of the remote sensing camera.

[0087] By heat-insulating the star sensor bracket to the main load-bearing substrate of the remote sensing camera and the star sensor respectively, aluminized polyester film single-sided acrylic pressure-sensitive adhesive is pasted on the mounting surface of the star sensor, and a multi-layer heat insulation component is set between the star sensor and the mounting surface. A thin film heating plate and a thermally conductive graphite film are pasted on the inner surface of the star sensor bracket, and the outer surface of the star sensor bracket is covered with a multi-layer heat insulation component, external influences are effectively isolated. The active temperature control of the star sensor bracket is better than ±0.15℃ with low power consumption.

[0088] Implementation Method Eight: This implementation method further defines the thermal control method for a deployable star sensor assembly with high thermal stability and low thermal control power consumption described in Implementation Method One. In step S6, the upper outer circle of the star sensor electronics box cover in the star sensor assembly (already thermally insulated in step S5) is adhered to the satellite's external multi-layer thermal insulation assembly using pressure-sensitive adhesive.

[0089] In the star sensor assembly, one half of multiple strips of polyimide film single-sided acrylic pressure-sensitive adhesive is pasted on the upper outer circle of the star sensor electronics box cover, and the other half of the multiple strips of polyimide film single-sided acrylic pressure-sensitive adhesive is bonded to the satellite's external multi-layer heat insulation components.

[0090] The aforementioned multi-layer polyimide film single-sided acrylic pressure-sensitive adhesive consists of 8 polyimide film single-sided acrylic pressure-sensitive adhesives.

[0091] In this embodiment, such as Figure 7 As shown, eight strips of polyimide film with single-sided acrylic pressure-sensitive adhesive are annularly distributed on the upper outer circumference of the star sensor electronics box cover, leaving half the length unattached. Holes are cut and forked in the multi-layer heat insulation component on the outside of the satellite, and after passing through the star sensor's light shield, it is further bonded with the aforementioned polyimide film with single-sided acrylic pressure-sensitive adhesive leaving half the length unattached. The outer surface of the multi-layer heat insulation component on the outside of the satellite near the star sensor's light shield is an F46 film.

[0092] In summary, this invention provides a thermal control method for deployable star sensor components that achieves high thermal stability and low thermal control power consumption. It utilizes thermal control materials such as F46 thin film, thin film heating element, thermally conductive graphite film, aluminized polyester film with single-sided acrylic pressure-sensitive adhesive, multilayer thermal insulation components, graphene flexible thermal conductive cable, polyimide thermal insulation pad, and polyimide film with single-sided acrylic pressure-sensitive adhesive to achieve the thermal control objectives of high thermal stability and low thermal control power consumption for the deployable star sensor components.

[0093] The above provides a detailed description of a thermal control method for a deployable star sensor assembly with high thermal stability and low thermal power consumption. Specific examples have been used to illustrate the principles and implementation methods of the invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the invention. At the same time, those skilled in the art will recognize that there will be changes in the specific implementation methods and application scope based on the ideas of the invention. Therefore, the content of this specification should not be construed as a limitation of the invention.

Claims

1. A thermal control method for a deployable star sensor assembly with high thermal stability and low thermal control power consumption, characterized in that, Includes the following steps: Step S1: Unfold the star sensor, apply a thin film to the outer surface of the multi-segment light shield of the unfolded star sensor and the upper surface of the electronic box cover of the star sensor, and then fold up the unfolded star sensor. Step S2: Perform thermal control treatment on the star sensor that was gathered in step S1; The thermal control treatment of the star sensor that has been gathered in step S1 includes the following steps: Step S201: The upper cover and lower cover of the star sensor electronics box are integrally coated with a thermally conductive graphite film. Step S202: One end of the graphene flexible heat-conducting cable is attached to the thermally conductive graphite film on the lower cover of the star sensor electronics box, and the other end of the graphene flexible heat-conducting cable is connected to the main load-bearing structure plate of the satellite. Step S203: Cover the lower cover of the star sensor electronics box with a multi-layer heat insulation component; Step S3: Perform closed-loop temperature control on the star sensor bracket and perform thermal control treatment on the inner and outer surfaces of the star sensor bracket respectively. Step S4: Heat-insulate the star sensor that has undergone thermal control treatment in step S2 with the star sensor bracket obtained in step S3 to obtain the star sensor assembly; Step S5: Heat-insulate the star sensor assembly obtained in step S4 and the main load-bearing substrate of the remote sensing camera. Step S6: Adhere the upper outer circle of the star sensor electronics box cover of the star sensor assembly that has been thermally insulated in step S5 to the external multi-layer thermal insulation assembly of the satellite using pressure-sensitive adhesive.

2. The thermal control method for a deployable star sensor assembly with high thermal stability and low thermal power consumption according to claim 1, characterized in that, In step S1, the thin film includes an F46 thin film.

3. The thermal control method for a deployable star sensor assembly with high thermal stability and low thermal control power consumption according to claim 1, characterized in that, In step S3, the closed-loop temperature control process for the star sensor holder specifically involves: Thin film heating elements are attached to the inner surface of the star sensor bracket; The inner surface of the star sensor bracket includes the inner side of the opposite side of the star sensor bracket mounting surface and the inner sides of both sides of the star sensor bracket.

4. The thermal control method for a deployable star sensor assembly with high thermal stability and low thermal control power consumption according to claim 1, characterized in that, In step S3, the thermal control treatment of the inner and outer surfaces of the star sensor bracket is specifically as follows: Apply thermally conductive graphite film to all surfaces inside the star sensor bracket where the thin-film heating element has been attached; In addition to the star sensor mounting hole, double-sided aluminized polyester film and single-sided acrylic pressure-sensitive adhesive are pasted on the star sensor mounting surface of the star sensor bracket, and a multi-layer heat insulation component is wrapped around the outer surface of the star sensor bracket except for the star sensor mounting surface.

5. The thermal control method for a deployable star sensor assembly with high thermal stability and low thermal control power consumption according to claim 1, characterized in that, In step S4, the thermally controlled star sensor from step S2 and the star sensor bracket from step S3, which has undergone closed-loop temperature control, are thermally insulated and installed together. The star sensor and its bracket are installed with multiple polyimide heat insulation pads for thermal insulation. The plurality of polyimide heat insulation pads are four polyimide heat insulation pads.

6. The thermal control method for a deployable star sensor assembly with high thermal stability and low thermal control power consumption according to claim 1, characterized in that, In step S5, the thermal insulation installation of the star sensor assembly obtained in step S4 with the main load-bearing substrate of the remote sensing camera specifically involves: The star sensor assembly and the main load-bearing substrate of the remote sensing camera are installed with multiple polyimide thermal pads for thermal insulation. The plurality of polyimide heat insulation pads are four polyimide heat insulation pads.

7. The thermal control method for a deployable star sensor assembly with high thermal stability and low thermal control power consumption according to claim 1, characterized in that, In step S6, the step of attaching the upper outer circumference of the star sensor electronics box cover of the star sensor assembly (which was heat-insulated and installed in step S5) to the multi-layer heat insulation assembly on the outside of the satellite using pressure-sensitive adhesive specifically involves: In the star sensor assembly, one half of multiple strips of polyimide film single-sided acrylic pressure-sensitive adhesive is pasted on the upper outer circle of the star sensor electronics box cover, and the other half of the multiple strips of polyimide film single-sided acrylic pressure-sensitive adhesive is bonded to the satellite's external multi-layer heat insulation components. The aforementioned multi-layer polyimide film single-sided acrylic pressure-sensitive adhesive consists of 8 polyimide film single-sided acrylic pressure-sensitive adhesives.

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