Star sensor mounting device and satellite

Abstract

A star sensor installation device comprises an installation support, a heat dissipation plate and a temperature control system, the installation support comprises at least one installation face, the installation face is provided with a star sensor installation interface, a star sensor is installed on the installation support through the star sensor installation interface, the heat dissipation plate is flexibly connected to the installation face, and the temperature control system is connected to the heat dissipation plate. The temperature control system is arranged on the mounting bracket and is used for carrying out temperature control on the mounting bracket, the star sensor comprises a conduction part, and the conduction part is in contact with the heat dissipation plate, so that heat energy generated in the working process of the star sensor is diffused to the outside through the heat dissipation plate. A satellite is also provided.

Description

Technical Field

[0001] The invention relates to the field of satellite structure design, and in particular to a star sensor mounting bracket. Background Art

[0002] For common star sensor mounting brackets, a single star sensor is usually installed, and the material is aluminum alloy or aluminum-magnesium alloy, which is installed inside the star. Conventional star sensor brackets have problems such as high quality cost, thermal environment sensitivity, and limited installation methods.

[0003] On the other hand, most satellites use dual or multi-star sensors, and there are certain requirements for the relative stability between the optical axes of the dual star sensors. Common star sensor brackets are installed in multiple units, and they are installed on multiple brackets. There is a problem of not achieving common reference installation, which introduces more influences from other structures. At the same time, star sensors need to dissipate heat when working in orbit. In order to avoid the influence on the bracket and star sensors, traditional heat sinks generally adopt an independent heat sink design, and use heat pipes to connect the heat sink and star sensors. There are problems such as heavy weight, low reliability, high assembly process requirements, large space occupation and high cost. Summary of the invention

[0004] An object of the present invention is to provide a star sensor mounting bracket, which can reduce the mass and occupied space of the overall structure of the star sensor bracket and facilitate assembly.

[0005] The above-mentioned star sensor installation device comprises:

[0006] A mounting bracket, comprising at least one mounting surface, wherein a star sensor mounting interface is provided on the mounting surface, and the star sensor is mounted on the mounting bracket through the star sensor mounting interface;

[0007] A heat sink flexibly connected to the mounting surface; and

[0008] A temperature control system, arranged on the mounting bracket, for implementing temperature control on the mounting bracket;

[0009] The star sensor comprises a conducting part, and the conducting part is in contact with the heat sink, so that the heat energy generated by the star sensor during operation can be diffused to the outside through the heat sink.

[0010] In one or more embodiments, the star sensor mounting bracket includes a top surface, a bottom surface, and a plurality of vertical ribs, the top surface and the bottom surface are connected by the plurality of vertical ribs, the top surface provides the mounting surface, a star body interface is provided on the bottom surface, and the star sensor mounting device is mounted on the satellite body through the star body interface.

[0011] In one or more embodiments, the temperature control system includes a heater, a thermistor and a multi-layer thermal insulation material, the heater and the thermistor are arranged on the vertical ribs, the thermistor is located on a side close to the mounting surface, and the multi-layer thermal insulation material is arranged between the mounting bracket and the star sensor, and covers the mounting bracket, a portion of the heat sink, the heater and the thermistor.

[0012] In one or more embodiments, the outermost layer of the multi-layer insulation material is a secondary surface mirror material.

[0013] In one or more embodiments, the star sensor includes a star sensor flange, and the star sensor flange has the conducting portion;

[0014] The heat sink is flexibly connected to the mounting surface through a plurality of fastening components, each of the fastening components comprises a flexible connection gasket and a connecting screw, a plurality of first through holes are provided on the heat sink, a plurality of second through holes are provided on the star sensor flange, a plurality of mounting holes are provided on the mounting bracket, and the connecting screws pass through the flexible connection gasket, the first through holes, the second through holes in sequence and are threadedly connected to the mounting holes;

[0015] Wherein, there is a gap between the connecting screw and the inner wall surface of the first through hole.

[0016] In one or more embodiments, thermal conductive silicone grease is applied between the star sensor flange and the heat sink.

[0017] In one or more embodiments, the heat sink is made of an aluminum plate, one side of which is coated with white paint.

[0018] In one or more embodiments, the mounting bracket is formed by molding carbon fiber cloth and curing at high temperature, so that the equivalent thermal expansion coefficient of the mounting bracket in all directions is 0.7×10 -6 ~2×10 -6 m / K.

[0019] In one or more embodiments, the mounting bracket includes a plurality of mounting surfaces, and angles are formed between the plurality of mounting surfaces. The plurality of heat sinks are flexibly connected to the plurality of mounting surfaces, respectively, to dissipate heat for the plurality of star sensors.

[0020] Another object of the present invention is to provide a satellite that can reduce the mass and occupied space of the overall structure of the star sensor and facilitate assembly.

[0021] The satellite comprises a satellite body, a star sensor and the star sensor mounting device as described above, wherein the star sensor is mounted on the satellite body through the star sensor mounting device.

[0022] Compared with the prior art, this application has at least the following beneficial effects:

[0023] By adopting a design in which the heat sink is flexibly connected to the mounting bracket, compared with a design in which the heat sink is rigidly connected to the mounting bracket, the heat deformation of the heat sink due to drastic temperature changes on the star sensor and the mounting bracket can be avoided to the greatest extent. At the same time, compared with the traditional external heat sink design, the design in which the heat sink is integrally connected to the mounting bracket adopted in the present application can reduce the constraints on the installation position of the star sensor, make it easier to arrange the position of the star sensor outside the satellite cabin, and improve the applicability of the star sensor installation device.

[0024] At the same time, the star sensor mounting device can control the temperature of the mounting bracket through a temperature control system to stabilize the temperature of the mounting bracket, thereby ensuring that the relative accuracy relationship between the multiple star sensors is stable when multiple star sensors are mounted on the mounting bracket. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0026] Figure 1 It is a schematic diagram of a star sensor mounting bracket in the prior art.

[0027] Figure 2 Schematic diagram of a star sensor installation device and a star sensor according to an embodiment of the present application.

[0028] Figure 3 is an exploded view of a star sensor mounting device according to an embodiment of the present application.

[0029] Figure 4 is a schematic diagram of a star sensor installation device according to an embodiment of the present application.

[0030] Figure 5 is a top view of a star sensor mounting device according to an embodiment of the present application.

[0031] Figure 6 yes Figure 5 A partial enlarged view of area A.

[0032] Figure 7 is a schematic diagram of a fastening assembly according to an embodiment of the present application.

[0033] Figure 8 is a schematic diagram of a heat dissipation plate according to an embodiment of the present application.

[0034] Fig. 9 Schematic diagram of the layering of the bracket body according to an embodiment of the present application. DETAILED DESCRIPTION

[0035] The present invention is further described below in conjunction with specific embodiments and drawings. More details are described in the following description to facilitate a full understanding of the present invention, but the present invention can obviously be implemented in a variety of other ways different from the description. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment. It should be noted that these and other subsequent drawings are only examples, which are not drawn according to the conditions of equal proportions, and should not be used as a limitation on the protection scope of the actual requirements of the present invention.

[0036] like Figure 1 As shown, the current star sensor mounting bracket 1' can usually only mount one star sensor, and the star sensor is mounted on the mounting bracket 1' through the star sensor mounting interface 111' thereon. For satellites with dual star sensors or multi-star sensors, multiple star sensors need to be mounted on multiple mounting brackets respectively, and the common reference installation of multiple star sensors cannot be achieved, which affects the relative stability between the optical axes of the star sensors. At the same time, the introduction of a large number of other structures will lead to problems such as large mass, large occupied space, and high cost.

[0037] On the other hand, in order to avoid the heat sink affecting the mounting bracket and the star sensor, the traditional star sensor heat dissipation method usually guides the heat energy generated by the star sensor to an external heat sink independent of the mounting bracket and the star sensor through a heat pipe. This will further increase the overall mass and occupied space, and there are also problems such as low reliability and high requirements for assembly process.

[0038] In order to solve the problems existing in one or more of the above-mentioned traditional star sensor mounting brackets, the present application provides a satellite and a star sensor mounting device thereof. The satellite includes a satellite body, a star sensor 5 and a star sensor mounting device. The star sensor 5 is mounted on the satellite body through the star sensor mounting device.

[0039] like Figure 2 As shown, the star sensor mounting device includes a mounting bracket 1, a heat sink 4 and a temperature control system 2, the mounting bracket 1 includes at least one mounting surface 11, the mounting surface 11 is provided with a star sensor mounting interface 111, the star sensor 5 is mounted on the mounting bracket 1 through the star sensor mounting interface 111, the heat sink 4 is flexibly connected to the mounting surface 11, the temperature control system 2 is arranged on the mounting bracket 1, and is used to implement temperature control on the mounting bracket 1, wherein the star sensor 5 includes a conduction part 51, and the conduction part 51 is in contact with the heat sink 4, so that the heat energy generated by the star sensor 5 during operation is diffused to the outside through the heat sink 4.

[0040] When the star sensor 5 is working on-orbit, its main heat-generating component is an imaging component, such as a star-sensing imaging CCD (charge coupled device) component. From the observation direction of the star sensor 5, the heat dissipation environment of the heat sink 4 in the optical axis direction is optimal. The optical axis direction refers to the axial direction of the incident light path designed in the optical system. The star sensor needs to avoid sunlight and ground light during operation. Therefore, when the heat dissipation surface of the heat sink 4 faces the optical axis direction (the heat dissipation surface is perpendicular to the optical axis direction), the heat dissipation environment of the star sensor is optimal and can naturally avoid sunlight. The internal heat conduction structure design of the star sensor 5 can be used to introduce the heat energy generated by its heat-generating components into the conduction part 51. The conduction part 51 can be a contact plane where the star sensor 5 contacts the heat sink 4, so that the heat sink 4 and the conduction part 51 are in direct contact to achieve heat dissipation. The heat dissipation method is simple and reliable. The star sensor mounting device can complete the mechanical and thermal coupling design on the same mounting bracket 1, avoiding the need to use external heat sinks and heat pipes in traditional heat dissipation methods, maximizing the use of existing structures and space, and not requiring the use of additional resources.

[0041] By adopting a design in which the heat sink 4 is flexibly connected to the mounting bracket 1, compared with a design in which the heat sink 4 is rigidly connected to the mounting bracket, the heat deformation of the heat sink 4 on the star sensor 5 and the mounting bracket 1 due to drastic temperature changes can be avoided to the greatest extent. At the same time, compared with the traditional external heat sink design, the design in which the heat sink 4 is integrally connected to the mounting bracket 1 adopted in the present application can reduce the constraints on the installation position of the star sensor 5, make it easier to arrange the star sensor 5 outside the satellite cabin, and improve the applicability of the star sensor installation device.

[0042] At the same time, the star sensor mounting device can control the temperature of the mounting bracket 1 through the temperature control system 2 to stabilize the temperature of the mounting bracket 1, and further when multiple star sensors 5 are mounted on the mounting bracket 1, the relative accuracy relationship between the multiple star sensors 5 can be ensured to be stable.

[0043] In this article, flexible connection is a connection method different from rigid connection. By designing the connection form, connection interface, connection preload, etc. between components, the flexible connection method can ensure that the connection can withstand the load in the active section of satellite launch and the accuracy of the installed single machine will not change. When there is a drastic temperature change in orbit, the thermal deformation caused by the temperature change can be released through flexible displacement.

[0044] The following combination Figures 2 to 8 Taking a satellite with a dual star sensor configuration as an example, a specific implementation of the star sensor installation device provided by the present application is described. In this implementation, the star sensor installation device can be used to install multiple star sensors 5, which can achieve multi-star sensor common reference installation, ensure that the multi-optical axis has small thermal deformation and high stability on orbit, and realize the mechanical and thermal coupling design, which has the characteristics of small space occupation, low cost, light weight, etc.

[0045] Please refer to Figure 3 The mounting bracket 1 includes two mounting surfaces 11 , and an angle is formed between the two mounting surfaces 11 . The two heat sinks 4 are flexibly connected to the two mounting surfaces 11 , respectively, to dissipate heat for the two star sensors 5 .

[0046] Furthermore, the star sensor mounting bracket 1 includes a top surface 112, a bottom surface 113 and a plurality of vertical ribs 114, the top surface 112 and the bottom surface 113 are connected by the plurality of vertical ribs 114, the top surface 112 provides a mounting surface 11, and a star body interface is provided on the bottom surface 113, and the star sensor mounting device is mounted on the satellite body through the star body interface.

[0047] Mounting bracket 1 adopts Figure 3 In the form of the open shell reinforced structure shown, the overall cross-section of the bracket is roughly "C"-shaped, the bottom surface 113 is used to connect with the satellite body, the top surface 112 is used to fix the star sensor 5 and the heat sink 4, and the vertical ribs 114 can be used to lay the temperature control system 2. The mounting bracket 1 includes a bracket body composed of a top surface 112, a bottom surface 113 and a plurality of vertical ribs 114. The bracket body can be made of a low expansion coefficient material, which provides a basis for realizing a low expansion or zero expansion design of the mounting bracket 1 for multiple star sensors 5.

[0048] Furthermore, the bracket body of the mounting bracket 1 can be formed by molding carbon fiber cloth at high temperature so that the equivalent thermal expansion coefficient of the mounting bracket 1 in all directions is 0.7×10 -6 ~2×10 -6 m / K, Fig. 9 The carbon fiber layer diagram is shown. The layering method is a near-zero expansion layer. Compared with the traditional metal bracket, the bracket body molded by the layering method can achieve a low expansion or near-zero expansion coefficient design, and maximize the optical axis common reference installation of multiple star sensors 5, ensure the optical axis stability of the star sensor 5 and the optical axis angle stability between multiple star sensors 5, and achieve the stability of the optical axis relationship between multiple star sensors on track, which is not affected by the temperature fluctuation of the star sensor mounting bracket. In addition, the mounting bracket 1 body is prepared by molding a high-modulus, high-strength carbon fiber composite material, which can greatly reduce the mass of the mounting bracket 1, and ensure high stiffness and strength, which can effectively reduce the random mechanical response of the star sensor 5.

[0049] According to the star sensor installation device provided in this embodiment, high-modulus carbon fiber with high rigidity and low density is used for molding, which is light in weight and can meet the mechanical environment. The laying method of the bracket body is designed according to the calculation result of the thermal expansion coefficient to obtain a bracket body with a low expansion coefficient. At the same time, the bracket body has a smooth and flat surface without weight-reducing grooves, reinforcing ribs and other designs, which is convenient for implementing thermal control on the bracket body and realizing precise temperature control. The temperature control accuracy can reach ±1°C, realizing the mechanical and thermal coupling integrated design of the installation bracket 1.

[0050] In other embodiments, the bracket body material of the mounting bracket 1 is not limited to carbon fiber, but may also be other low expansion coefficient materials, such as high-component aluminum-based silicon carbide, carbon silicon carbide and other composite materials with low expansion coefficient.

[0051] After the preparation of the bracket body of the mounting bracket 1 is completed, the hole position processing can be performed on the bracket body for subsequent assembly work. Specifically, in this embodiment, the mounting bracket 1 includes a bracket body, a mounting interface precision gasket 12, a support plate nut 13, a countersunk rivet 14 and a load interface precision gasket 15. The star sensor 5 can be fixedly connected to the mounting bracket 1 through the cooperation of the support plate nut 13 and the countersunk rivet 14, and the mounting interface precision gasket 12 and the load interface precision gasket 15 can be pasted on the mounting bracket 1 with an adhesive. The mounting interface precision gasket 12 is used to ensure that the star sensor 5 will not be deformed when it is installed with the mounting bracket 1, and the load interface precision gasket 15 is used to ensure that the mounting bracket 1 will not be deformed when the mounting bracket 1 is installed on the satellite body. After the adhesive is cured, the final precision processing can be further completed according to the design drawings of the mounting bracket 1 to ensure the high precision of the mounting bracket 1.

[0052] Furthermore, the temperature control system 2 includes a heater 21, a thermistor 22 and a multi-layer thermal insulation material 3. The heater 21 and the thermistor 22 are arranged on the vertical rib 114, the thermistor 22 is located on the side close to the mounting surface 11, and the multi-layer thermal insulation material 3 is arranged between the mounting bracket 1 and the star sensor 5, and the mounting bracket 1, part of the heat sink 4, the heater 21 and the thermistor 22 are covered therein, wherein part of the heat sink refers to the heat sink 4 outside the heat sink surface to ensure.

[0053] The thermistor 22 is used as a temperature detector and can be adhered to the side of the vertical rib 114 of the mounting bracket 1 close to the mounting surface 11 by using an adhesive, and the thermistor 22 can be covered with a protective film to prevent the thermistor 22 from being affected by external radiation. The heater 21 is used as an actuator and can be conformally adhered to the vertical rib 114 by using an adhesive such as silicone rubber to control the temperature, and the temperature control of the mounting bracket 1 can be implemented through control methods such as PID.

[0054] The multi-layer thermal insulation material 3 can be composed of polyimide aluminum-plated film and nylon mesh. The polyimide aluminum-plated film can isolate thermal radiation, and the nylon mesh can insulate heat. The multi-layer thermal insulation material 3 can be covered and pasted on the outside of the mounting bracket 1 by nylon fasteners.

[0055] Furthermore, the outermost layer of the multi-layer thermal insulation material 3 may be a secondary surface mirror material, which has low absorptivity and high emissivity and can effectively isolate external heat flow.

[0056] Further, such as Figure 6 As shown, the star sensor 5 includes a star sensor flange 52, the star sensor flange 52 has a conducting portion 51, the heat sink 4 is flexibly connected to the mounting surface 11 through a plurality of fastening components 6, each fastening component includes a flexible connection gasket 61 and a connecting screw 62, the heat sink 4 is provided with a plurality of first through holes 41, the star sensor flange 52 is provided with a plurality of second through holes 53, the mounting bracket 1 is provided with a plurality of mounting holes 12, the connecting screw 62 sequentially passes through the flexible connection gasket 41, the first through hole 41, the second through hole 53 and is threadedly connected to the mounting hole 12, wherein a gap 7 is provided between the connecting screw 62 and the inner wall surface of the first through hole 41.

[0057] The first through hole 41 may be an elliptical through hole. By designing the first through hole 41 to be elliptical, a gap 7 is provided between the connecting screw 62 and the inner wall surface of the first through hole 41. The gap 7 may be used to release the expansion deformation of the heat sink 4, thereby avoiding deformation of the star sensor 5 and the mounting bracket 1 caused by temperature changes of the heat sink 4.

[0058] refer to Figure 6 and Figure 7 In this embodiment, the heat sink is assembled as follows: first, a positioning bushing (not shown in the figure) is installed on the connecting screw 62 to ensure that the connecting screw 62 can pass through the elliptical first through hole 41 in the center, and the gap between the connecting screw 62 and the inner walls on both sides of the first through hole 41 is uniform and consistent. Then, the connecting screw 62 passes through the flat gasket 63 with a lubricating film sprayed on both sides and the flexible connecting gasket 61 to fix the heat sink 4, the star sensor flange 52, and the mounting bracket 1 together. After the connecting screws 62 of all the fastening components 6 are installed, the positioning bushings are removed in turn and the connection is restored. The minimum torque required to be applied to the connecting screw 62 is calculated according to the extension force generated by the temperature change and the working conditions related to the star sensor vibration environment, and applied at a coefficient of 1.5, and the connecting screws 62 are tightened in turn.

[0059] Furthermore, thermal conductive silicone grease is applied between the star sensor flange 52 and the heat sink 4 to fill the contact gap between the two and increase the heat conduction effect.

[0060] Furthermore, the heat sink 4 can be made of an aluminum plate, one side of which is coated with white paint. The size of the heat sink can be designed and processed according to the required heat dissipation area calculated by thermal control. After processing, one side is sprayed with white paint. It has low absorption and high emissivity, and can act as a heat dissipation coating.

[0061] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any 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 fall within the protection scope defined by the claims of the present invention.

Claims

1. A star sensor installation device, characterized in that: include: A mounting bracket, comprising at least one mounting surface, wherein a star sensor mounting interface is provided on the mounting surface, and the star sensor is mounted on the mounting bracket through the star sensor mounting interface; A heat sink flexibly connected to the mounting surface; and A temperature control system, arranged on the mounting bracket, for implementing temperature control on the mounting bracket; The star sensor comprises a conducting part, and the conducting part is in contact with the heat sink, so that the heat energy generated by the star sensor during operation can be diffused to the outside through the heat sink.

2. The star sensor installation device according to claim 1, characterized in that: The star sensor mounting bracket comprises a top surface, a bottom surface and a plurality of vertical ribs, the top surface and the bottom surface are connected by the plurality of vertical ribs, the top surface provides the mounting surface, a star body interface is arranged on the bottom surface, and the star sensor mounting device is mounted on the satellite body through the star body interface.

3. The star sensor mounting device according to claim 2, characterized in that: The temperature control system includes a heater, a thermistor and a multi-layer thermal insulation material. The heater and the thermistor are arranged on the vertical ribs, the thermistor is located on a side close to the mounting surface, and the multi-layer thermal insulation material is arranged between the mounting bracket and the star sensor, and covers the mounting bracket, a portion of the heat sink, the heater and the thermistor.

4. The star sensor mounting device according to claim 3, characterized in that: The outermost layer of the multi-layer thermal insulation material is a secondary surface mirror material.

5. The star sensor mounting device according to claim 1, characterized in that: The star sensor comprises a star sensor flange, and the star sensor flange has the conducting part; The heat sink is flexibly connected to the mounting surface through a plurality of fastening components, each of the fastening components comprises a flexible connection gasket and a connecting screw, a plurality of first through holes are provided on the heat sink, a plurality of second through holes are provided on the star sensor flange, a plurality of mounting holes are provided on the mounting bracket, and the connecting screws pass through the flexible connection gasket, the first through holes, the second through holes in sequence and are threadedly connected to the mounting holes; Wherein, there is a gap between the connecting screw and the inner wall surface of the first through hole.

6. The star sensor mounting device according to claim 5, characterized in that: Thermal conductive silicone grease is applied between the star sensor flange and the heat sink.

7. The star sensor mounting device according to claim 1, characterized in that: The heat sink is made of an aluminum plate, one side of which is coated with white paint.

8. The star sensor mounting device according to claim 1, characterized in that: The mounting bracket is formed by molding carbon fiber cloth and curing at high temperature, so that the equivalent thermal expansion coefficient of the mounting bracket in all directions is 0.7×10 -6 ~2×10 -6 m / K.

9. The star sensor mounting device according to claim 1, characterized in that: The mounting bracket includes a plurality of mounting surfaces, and angles are formed between the plurality of mounting surfaces. The plurality of heat sinks are flexibly connected to the plurality of mounting surfaces, respectively, to dissipate heat for the plurality of star sensors.

10. A satellite, characterized in that: The invention comprises a satellite body, a star sensor and a star sensor mounting device according to any one of claims 1 to 9, wherein the star sensor is mounted on the satellite body through the star sensor mounting device.

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