A high-precision temperature control device for a star sensor of a space optical remote sensing satellite

Abstract

The present application relates to the technical field of space heat control, and especially relates to a high-efficiency and high-precision temperature control device for a star sensor of a space optical remote sensing satellite, which effectively solves the temperature stability problem of a high-precision star sensor carried on a space optical remote sensing load. A star sensor assembly support can be connected with a main frame of the space optical remote sensing load. A plurality of star sensor bases are connected on the star sensor assembly support and their extension directions are determined according to the optical axis directions of the star sensors. Each star sensor base is mechanically connected with a star sensor support through heat insulation, so as to reduce the thermal disturbance of the star sensor support temperature change on the star sensor base. The high-precision control of the star sensor flange greatly simplifies the complexity of the thermal control system and is safe and reliable.

Description

Technical Field

[0001] This invention relates to the field of aerospace thermal control technology, and in particular to a high-efficiency and high-precision temperature control device for a space optical remote sensing satellite star sensor. Background Technology

[0002] In current methods, the star sensor is a key component for satellite attitude control, providing crucial data for attitude correction. During on-orbit operation, the star sensor faces drastic changes in external heat flux. Thermal deformation of the optical system causes variations in defocus, affecting the pointing stability of the star sensor. For high-precision star sensors, effective measures must be taken to control thermal deformation.

[0003] The pointing and attitude stability of space optical remote sensing satellites have a crucial impact on imaging quality. Currently, the performance indicators of space optical remote sensing payloads are constantly improving, and the requirements for attitude control precision are becoming increasingly stringent. Star sensors are gradually shifting from being mounted on satellite platforms to being directly mounted on space optical remote sensing payloads. Because space optical remote sensing payloads themselves require very high temperature control precision, it is necessary to effectively control the temperature level of the star sensor itself, as well as the thermal disturbance of the star sensor's temperature level and temperature changes on the optical remote sensor.

[0004] In addition, the energy supply capacity of small and medium-sized satellite payloads is limited. The thermal control system is a system that operates in orbit for a long time and requires a continuous and stable energy supply. Especially when the satellite is in the shadow area, there is no energy input to the satellite solar panels, and the power consumption required by the thermal control system will increase significantly. Therefore, it is of great significance to achieve efficient and low-energy thermal control.

[0005] In summary, the high-efficiency and high-precision thermal control of star sensor components has significant application value. Summary of the Invention

[0006] The technical problem solved by this invention is to significantly differentiate itself from existing common design methods such as radiators and heat pipes, and the use of light shields to create heat dissipation surfaces. It proposes a safer, more reliable, and highly integrated thermal control method to effectively solve the temperature stability problem of high-precision star sensors mounted on space optical remote sensing payloads. The key focus is on solving the temperature control problem of the star sensor flange, while simultaneously meeting the requirements for low thermal control energy consumption. Therefore, this invention proposes a high-efficiency, high-precision temperature control device for space optical remote sensing satellite star sensors.

[0007] To solve the above-mentioned technical problems, the technical solution of the present invention is as follows:

[0008] A high-precision temperature control device for a star sensor of a space optical remote sensing satellite includes:

[0009] Star sensor component bracket 11, which can be connected to the main frame of the space optical remote sensing payload;

[0010] Multiple star sensor bases 12 are connected to the star sensor assembly bracket 11, and their extension direction is determined according to the optical axis of each star sensor 10.

[0011] Each of the star sensor bases 12 is mechanically connected to a star sensor support 13 by means of heat insulation, so as to reduce the thermal disturbance of the star sensor base 12 caused by the temperature change of the star sensor support 13.

[0012] Each star sensor 10 is mounted on a corresponding star sensor support 13, and a mounting surface is formed between the star sensor 10 and the corresponding star sensor support 13. The mounting surface is processed with a preset precision and coated with thermal grease.

[0013] Preferably, the heat insulation method is as follows: an annular titanium alloy heat insulation pad 14 is provided between the star sensor support 13 and the star sensor base 12 for heat insulation, and the annular titanium alloy heat insulation pad 14 has a mechanical connection mounting point.

[0014] Preferably, the heat insulation method is as follows: a multi-layer heat insulation component 17 is laid outside the position between the star sensor support 13 and the star sensor base 12 at the installation point, so as to further prevent the temperature change of the star sensor support 13 from causing thermal disturbance to the star sensor base 12.

[0015] The multi-layer heat insulation component 17 is composed of a double-sided aluminized polyester film and a polyester mesh.

[0016] Furthermore, each star sensor 10 is connected to the star sensor support 13 via a flange.

[0017] Furthermore, the star sensor support 13 is a hollow thin-walled cylinder with an internal crossbeam;

[0018] The top and bottom surfaces of the crossbeam and the mounting surface of the star sensor support 13 are processed according to a second preset machining accuracy requirement.

[0019] Furthermore, the outer surface of the star sensor support 13 is coated with white paint so that the outer surface of the star sensor support 13 can serve as a heat dissipation surface.

[0020] Furthermore, the star sensor 10 includes:

[0021] The star sensor circuit box 24 has a reserved gap between itself and the crossbeam, and the reserved gap is filled with an insulating thermally conductive pad.

[0022] Furthermore, the outer surface of the star sensor circuit box 24 and the inner surface of the star sensor support 13 are subjected to black anodizing treatment to enhance mutual radiative heat transfer.

[0023] Furthermore, the star sensor 10 includes:

[0024] An electric heater 15 is disposed on the bottom surface of the crossbeam inside the star sensor support 13;

[0025] A temperature control point thermistor 16 is connected to the electric heater 15, and the temperature control point thermistor 16 is arranged around the flange 23 of the star sensor 10.

[0026] Furthermore, the star sensor 10 includes:

[0027] The front section 21 and the rear section 22 of the star sensor light shield are connected in sequence.

[0028] The rear section 22 of the star sensor light shield is connected to the flange 23.

[0029] Polyimide heat insulation pads 25 are respectively provided between the front section 21 and the rear section 22 of the star sensor light shield, and between the rear section 22 of the star sensor light shield and the flange 23.

[0030] The present invention has the following beneficial effects:

[0031] This technical solution enables high-precision control of the star sensor flange temperature variation range of 10±2℃. Compared with existing technical solutions, the heat dissipation surface can be effectively reduced, and the heat compensation power consumption is reduced. Especially in the shadow area, the heat dissipation of the star sensor circuit box can be guided to the flange for use as heat compensation power consumption, thereby further reducing heat compensation power consumption and saving satellite energy. The star sensor support integrates structural support, heat dissipation, and heat compensation functions, which greatly simplifies the complexity of the thermal control system and ensures safety and reliability. Attached Figure Description

[0032] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0033] Figure 1 This is a schematic diagram of the high-precision temperature control device for star sensors provided by the present invention;

[0034] Figure 2 This is a schematic diagram of the star sensor assembly;

[0035] Figure 3 This is a schematic diagram of the star sensor support structure;

[0036] Figure 4 This is a schematic diagram of the internal structure configuration of the star sensor support.

[0037] The reference numerals in the figure are:

[0038] Star sensor assembly bracket 11, star sensor base 12, star sensor 10, star sensor support 13;

[0039] 14. Annular titanium alloy heat insulation pad; 17. Multi-layer heat insulation component; 18. Crossbeam;

[0040] Star sensor circuit box 24;

[0041] Electric heater 15, temperature control point thermistor 16;

[0042] Star sensor light shield front section 21, star sensor light shield rear section 22, flange 23, polyimide heat insulation pad 25. Detailed Implementation

[0043] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention. It should be noted that, for ease of description, in this application, "left side" is referred to as "first end", "right side" as "second end", "upper side" as "first end", and "lower side" as "second end" in the current view. The purpose of such description is to clearly express the technical solution and should not be construed as an improper limitation of the technical solution of this application.

[0044] The purpose is to significantly differentiate from existing common design methods such as radiators and heat pipes, and the use of light shields to create heat dissipation surfaces, and to propose a safer, more reliable, and highly integrated thermal control device to effectively solve the temperature stability problem of high-precision star sensors mounted on space optical remote sensing payloads. The key is to solve the temperature control problem of the star sensor flange, while meeting the requirements of low thermal control energy consumption. To this end, this invention proposes a high-efficiency and high-precision temperature control device for star sensors of space optical remote sensing satellites.

[0045] Specifically, please refer to Figure 1 As shown, the high-precision temperature control device for the star sensor of the space optical remote sensing satellite includes:

[0046] The star sensor assembly bracket 11 can be connected to the main frame of the space optical remote sensing payload; multiple star sensor bases 12 are connected to the star sensor assembly bracket 11, and their extension direction is determined according to the optical axis of each star sensor 10; each star sensor base 12 is mechanically connected to a star sensor support 13 through heat insulation to reduce the thermal disturbance of the star sensor base 12 caused by the temperature change of the star sensor support 13; each star sensor 10 is installed on the corresponding star sensor support 13, and a mounting surface is formed between the star sensor 10 and the corresponding star sensor support 13, and the mounting surface is processed with a preset precision and coated with thermal grease.

[0047] In this technical solution, the star sensor assembly bracket 11 is directly mechanically connected to the main frame of the space optical remote sensing payload. The star sensor base 12 is a transition component, which is determined according to the optical axis direction of each star sensor. The star sensor support 13 is mechanically connected to the star sensor base through a titanium alloy heat insulation pad. Each star sensor is installed on the corresponding support through a flange. The mounting surface is a high-precision machined surface and is coated with thermally conductive silicone grease.

[0048] To reduce the impact of external space heat flow and radiative heat flow from satellite and camera components on the star sensor, the surface of the star sensor and related components, except for the light inlet, connection surface, and heat dissipation surface, is covered with a 20-unit multi-layer thermal insulation component 17.

[0049] A ring-shaped titanium alloy heat insulation pad 14 is provided between the star sensor support 13 and the star sensor base 12 for heat insulation. The components on both sides of the heat insulation pad are mechanically connected through the mounting points. Except for the connection points, a 10-unit multi-layer heat insulation component 17 is laid between the star sensor support 13 and the star sensor base 12 to further prevent the temperature change of the star sensor support 13 from causing thermal disturbance to the star sensor base 12.

[0050] A heat dissipation surface is provided on the outer surface of the star sensor support 13 to dissipate the internal working heat dissipation and absorbed external heat flow of the star sensor. A low-absorptivity, high-emissivity white paint is sprayed onto the heat dissipation surface to enhance heat dissipation. The selection of the heat dissipation surface is based on thermal analysis results, prioritizing the minimum overall heat flow absorbed by the star sensor in the sunlit area during on-orbit operation, while also considering the shading relationship between star sensors. This technical solution achieves high-precision control of the star sensor flange temperature variation range of 10±2℃. Compared with existing technical solutions, the heat dissipation surface can be effectively reduced, and the heat compensation power consumption is lowered. Especially in the shaded area, the heat dissipation of the star sensor circuit box can be guided to the flange for use as heat compensation power consumption, thereby further reducing heat compensation power consumption and saving satellite energy. The star sensor support integrates structural support, heat dissipation, and heat compensation functions, greatly simplifying the complexity of the thermal control system and ensuring safety and reliability.

[0051] In an optional embodiment, the specific heat insulation method is as follows: an annular titanium alloy heat insulation pad 14 is provided between the star sensor support 13 and the star sensor base 12 for heat insulation, and the annular titanium alloy heat insulation pad 14 has a mechanically connected mounting point.

[0052] In an optional embodiment, the heat insulation method is as follows: a multi-layer heat insulation component 17 is laid outside the position between the star sensor support 13 and the star sensor base 12 at the mounting point to further prevent the temperature change of the star sensor support 13 from causing thermal disturbance to the star sensor base 12.

[0053] The multi-layer thermal insulation component 17 is composed of a double-sided aluminized polyester film and a polyester mesh.

[0054] Further, please refer to Figure 1-3 As shown, each star sensor 10 is connected to the star sensor support 13 via a flange.

[0055] Please see Figure 1-4 As shown, the star sensor support 13 is a hollow thin-walled cylinder with an internal crossbeam 18.

[0056] The top and bottom surfaces of the crossbeam and the mounting surface of the star sensor support 13 are processed according to a second preset machining accuracy requirement.

[0057] The star sensor support 13 is a hollow, thin-walled cylindrical structure with an internal crossbeam. The top and bottom surfaces of the crossbeam, as well as the mounting surface of the support, are all high-precision machined surfaces. The outer surface of the support is coated with a white paint with high emissivity and low absorptivity. Each support has a portion of its outer surface exposed as a heat dissipation surface. The orientation and size of the heat dissipation surface are determined based on the results of finite element simulation thermal analysis.

[0058] In one specific implementation, please refer to Figure 1-3 As shown, the outer surface of the star sensor support 13 is coated with white paint so that the outer surface of the star sensor support 13 can serve as a heat dissipation surface.

[0059] In one specific embodiment, the star sensor 10 includes a star sensor circuit box 24, which maintains a reserved gap with the crossbeam, and the reserved gap is filled with an insulating thermally conductive pad.

[0060] In one specific embodiment, the outer surface of the star sensor circuit box 24 and the inner surface of the star sensor support 13 are treated with black anodizing to enhance radiative heat transfer between them.

[0061] In the specific configuration, a gap is left between the outer bottom surface of the star sensor circuit box 24 and the crossbeam of the star sensor support 13, and the gap is filled with an insulating thermally conductive pad; the electric heater 15 is set on the bottom surface of the crossbeam inside the star sensor support 13, and the temperature control point thermistor 16 is set on the star sensor flange. Polyimide heat insulation rings are set between the front and rear sections of the star sensor's light shield, and between the rear section of the light shield and the flange. To enhance the heat insulation effect, the polyimide heat insulation rings are thinned by 0.5mm in areas other than the mounting points.

[0062] Please see Figure 1-3 As shown, the star sensor 10 includes: an electric heater 15 disposed on the bottom surface of the crossbeam inside the star sensor support 13; and a temperature control point thermistor 16 connected to the electric heater 15, wherein the temperature control point thermistor 16 is disposed around the flange 23 of the star sensor 10.

[0063] Please see Figure 1-3 As shown, the star sensor 10 includes: a front section 21 and a rear section 22 of the star sensor light shield connected in sequence; a polyimide heat insulation pad 25 is respectively provided between the front section 21 and the rear section 22 of the star sensor light shield and between the rear section 22 of the star sensor light shield and the flange 23.

[0064] The star sensor consists of a front section 21 of a light shield, a rear section 22 of a light shield, a flange 23, a circuit box 24, and a polyimide thermal insulation pad 25. An insulating thermally conductive pad is laid between the star sensor circuit box 24 and the internal crossbeam of the star sensor support 13. An appropriate gap, preferably 0.25 mm, is left between the internal crossbeam of the star sensor support 13 and the star sensor circuit box 24 to accommodate a 10 mil thick insulating thermally conductive pad. The bottom side of the insulating thermally conductive pad is adhered to the internal crossbeam of the star sensor support using thermally conductive silicone rubber, while the top side adheres well to the surface of the star sensor circuit box 24.

[0065] The outer surface of the star sensor circuit box 24 and the inner surface of the star sensor support 13 are treated with black anodizing to enhance mutual radiative heat transfer, and the infrared emissivity ε≥0.8.

[0066] An active thermal control heating zone is provided on the bottom side of the internal crossbeam of each star sensor support. Each heating zone includes a main and a backup electric heater 15 and a thermistor 16. The electric heater 15 is located on the internal crossbeam of the star sensor support 13, and the temperature control point thermistor 16 is located around the star sensor flange 23.

[0067] Three sets of star sensors are mounted on a shared star sensor bracket 11. To prevent thermal disturbance to the space optical remote sensor from the star sensor components, isothermal control is applied to both the star sensor bracket 11 and the space optical remote sensor, meaning the temperature control target is consistent with the space optical remote sensor frame. An active thermal control heating zone is provided on the star sensor bracket, including a main and a backup temperature control loop. Each temperature control loop includes an electric heater 15 and a thermistor 16. The outer surface of the star sensor bracket is covered with a 20-unit multi-layer thermal insulation assembly 17.

[0068] To prevent severe disturbances to the star sensor caused by external heat flow, the entire star sensor assembly is covered with a multi-layered thermal insulation component 17. Since the light inlet of the star sensor 10 is exposed to sunlight for a portion of the time during its orbital operation, most of the heat flow entering the light inlet is absorbed by the front section 21 of the star sensor's sunshade. Therefore, polyimide thermal insulation pads 25, each 5 mm thick, are installed between the front section 21 and the rear section 22 of the star sensor's sunshade, and between the rear section 22 and the flange 23. This significantly reduces the transfer of heat absorbed by the front section 21 to the rear section 22 and the flange 23, thereby significantly reducing thermal disturbances to the flange 23.

[0069] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A high-precision temperature control device for a space optical remote sensing satellite star sensor, characterized in that, include: Star sensor component bracket (11), which can be connected to the main frame of the space optical remote sensing payload; Multiple star sensor bases (12) are connected to the star sensor assembly bracket (11) and their extension direction is determined according to the optical axis of each star sensor (10). Each of the star sensor bases (12) is mechanically connected to a star sensor support (13) by means of heat insulation, so as to reduce the thermal disturbance of the star sensor base (12) caused by the temperature change of the star sensor support (13); Each star sensor (10) is mounted on a corresponding star sensor support (13), and a mounting surface is formed between the star sensor support (13) and the corresponding star sensor support (13). The mounting surface is processed with a preset precision and coated with thermal grease. The heat insulation method is as follows: an annular titanium alloy heat insulation pad (14) is provided between the star sensor support (13) and the star sensor base (12) for heat insulation, and the annular titanium alloy heat insulation pad (14) has a mechanical connection mounting point. A multi-layer heat insulation assembly (17) is laid between the star sensor support (13) and the star sensor base (12) at the installation point to further prevent the temperature change of the star sensor support (13) from causing thermal disturbance to the star sensor base (12). The star sensor (10) is covered with a multi-layer heat insulation component (17) except for the light inlet, the connection surface and the heat dissipation surface; The multilayer thermal insulation component (17) is composed of a double-sided aluminized polyester film and a polyester mesh; Each star sensor (10) is connected to the star sensor support (13) via a flange; The star sensor support (13) is a hollow thin-walled cylinder with an internal crossbeam (18); The top and bottom surfaces of the crossbeam and the mounting surface of the star sensor support (13) are processed according to a second preset processing accuracy requirement; The outer surface of the star sensor support (13) is coated with white paint so that the outer surface of the star sensor support (13) can serve as a heat dissipation surface. The star sensor (10) includes: The star sensor circuit box (24) has a reserved gap between itself and the crossbeam, and the reserved gap is filled with an insulating thermal pad. The outer surface of the star sensor circuit box (24) and the inner surface of the star sensor support (13) are subjected to black anodizing treatment to enhance mutual radiative heat transfer. The star sensor (10) includes: An electric heater (15) is disposed on the bottom surface of the crossbeam inside the star sensor support (13); A temperature control point thermistor (16) is connected to the electric heater (15), and the temperature control point thermistor (16) is arranged around the flange (23) of the star sensor (10); The star sensor (10) includes: The front section (21) and rear section (22) of the star sensor light shield are connected in sequence. The rear section (22) of the star sensor light shield is connected to the flange (23). Polyimide heat insulation pads (25) are respectively provided between the front section (21) and the rear section (22) of the star sensor light shield, and between the rear section (22) of the star sensor light shield and the flange (23).

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