Star-sensitive load support assembly and satellite

Abstract

The utility model provides a star-sensitive load support assembly and a satellite, and relates to the technical field of satellites. The utility model provides a star-sensitive load bracket assembly and a satellite. The star-sensitive load bracket assembly comprises a load, the carbon fiber bracket is arranged on the surface of the load; and the star-sensitive element is arranged on the carbon fiber bracket, and the star-sensitive element, the load and the carbon fiber bracket are fixedly mounted into a whole. The thermal expansion coefficient of the carbon fiber in the carbon fiber bracket is low, the thermal deformation of the material is small, and the change of the relative position caused by the thermal deformation between the load and the star sensor is reduced. The star-sensitive element is directly connected with the load into a whole through the carbon fiber bracket, so that a transmission path between the star-sensitive element and the load is shortened, random angle change caused by thermal deformation on the transmission path is further reduced, and the reorbit shooting precision and the integrity of the bracket assembly are improved.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of satellites, in particular to a star sensor load support assembly and a satellite. BACKGROUND

[0002] After a satellite is in orbit, the sun irradiation and the earth irradiation will cause the temperature of the satellite to change alternately. The ordinary satellite load is arranged in a cabin, and the star sensor is arranged outside the cabin. The star sensor and the load are transmitted through two or more structural plates. The thermal deformation of the materials on the transmission path will cause the random angle between the load and the star sensor to change, resulting in low in-orbit shooting accuracy, and the influence cannot be eliminated. CONTENT OF THE UTILITY MODEL

[0003] Therefore, the application provides a star sensor load support assembly and a satellite, which can shorten the transmission path of the star sensor and the load, reduce the thermal deformation on the transmission path, and improve the in-orbit shooting accuracy.

[0004] The star sensor load support assembly and the satellite provided by the application comprise:

[0005] a load;

[0006] a carbon fiber support fixed to the surface of the load;

[0007] a star sensor element installed on the carbon fiber support and fixedly installed with the load and the carbon fiber support as a whole.

[0008] Optionally, the application further comprises:

[0009] a structural plate, wherein the structural plate is formed with a load mounting cabin, the load is connected with the structural plate and located in the load mounting cabin.

[0010] Optionally, the structural plate is provided with a through hole, one end of the carbon fiber support extends to the outside of the structural plate through the through hole, and the star sensor element is installed on the end of the carbon fiber support located on the outside of the structural plate.

[0011] Optionally, the carbon fiber support comprises:

[0012] a support body fixed to the surface of the load;

[0013] at least one star sensor mounting groove arranged on the support body and used for accommodating the star sensor element.

[0014] Optionally, the carbon fiber support comprises at least two star sensor mounting grooves, any two adjacent star sensor mounting grooves have an included angle, and the star sensor elements are respectively installed in the star sensor mounting grooves.

[0015] Optionally, the star sensor element is installed on the lateral side of the load through the carbon fiber support.

[0016] Optionally, the application further comprises:

[0017] The heat dissipation part has one end connected with the load and the other end penetrating through the structural plate and fixed to the outer surface of the structural plate.

[0018] Optionally, the heat dissipation part comprises:

[0019] The heat conduction pipe has one end connected with the load and the other end penetrating through the structural plate and extending to the outer side of the structural plate.

[0020] The heat dissipation plate is fixed to the surface of the structural plate and connected with the heat conduction pipe.

[0021] Optionally, the heat dissipation part has a clearance space with the carbon fiber support for spacing the heat dissipation part from the carbon fiber support.

[0022] Optionally, the load is a camera.

[0023] The application also provides a satellite comprising the star sensor load support assembly.

[0024] The carbon fiber support of the star sensor load support assembly and the satellite provided by the application has a low thermal expansion coefficient of carbon fiber and a small thermal deformation of material, reducing the change in relative position caused by thermal deformation between the load and the star sensor element. The star sensor element is directly connected with the load through the carbon fiber support, thereby shortening the transmission path between the star sensor element and the load and reducing the random angle change caused by thermal deformation in the transmission path, improving the re-orbit shooting accuracy and the integrity of the support assembly. BRIEF DESCRIPTION OF DRAWINGS

[0025] In order to more clearly illustrate the technical solutions in the embodiments of the application, the following will briefly introduce the drawings needed to be used in the embodiment description. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can also be obtained by those skilled in the art according to these drawings without exceeding the scope of the application.

[0026] Figure 1 is a structural schematic diagram of the star sensor load support assembly provided by the application;

[0027] Figure 2 is a structural schematic diagram of the star sensor load support assembly provided by the application from another angle;

[0028] Figure 3 is a structural schematic diagram of the carbon fiber support in the star sensor load support assembly provided by the application;

[0029] Figure 4 is a structural schematic bottom view of the star sensor load support assembly provided by the application;

[0030] Figure 5 is a structural schematic diagram of the satellite provided by the application.

[0031] Explanation of reference signs: 1, load; 2, carbon fiber support; 21, support body; 22, star sensor mounting groove; 3, star sensor element; 4, structural plate; 5, heat dissipation part; 51, heat conduction pipe; 52, heat dissipation plate; 6, avoiding space; 100, satellite; 200, support assembly. DETAILED DESCRIPTION

[0032] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are some of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0033] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "straight", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" and the like indicate the orientation or positional relationship shown in the drawings, and are only used to facilitate the description of the present application and simplify the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the present application. In addition, the terms "first", "second" and the like are only used for description purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first", "second" and the like can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "multiple" is two or more, unless otherwise explicitly specified and limited.

[0034] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected or can communicate with each other; it can be directly connected, or indirectly connected through an intermediate medium; it can be the internal connection of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0035] In the present application, unless specifically defined and limited otherwise, the first feature is "on" or "under" the second feature can include that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, the first feature is "on", "above" and "over" the second feature includes that the first feature is directly above and obliquely above the second feature, or only indicates that the first feature is higher in horizontal height than the second feature. The first feature is "under", "below" and "underneath" the second feature includes that the first feature is directly above and obliquely above the second feature, or only indicates that the first feature is lower in horizontal height than the second feature.

[0036] Reference Figure 1 The star sensor payload support assembly provided by the present application comprises a payload 1, a carbon fiber support 2 and a star sensor element 3. The carbon fiber support 2 is fixed to the surface of the payload 1; the star sensor element 3 is installed on the carbon fiber support 2 and fixedly installed with the payload 1 and the carbon fiber support 2 as a whole.

[0037] The carbon fiber support 2 has a low coefficient of thermal expansion of carbon fiber, and the material has a small thermal deformation, thereby reducing the change in relative position between the payload 1 and the star sensor element 3 caused by thermal deformation. The star sensor element 3 is directly connected with the payload 1 through the carbon fiber support 2 as a whole, thereby shortening the transmission path between the star sensor element 3 and the payload 1, and further reducing the random angle change caused by thermal deformation in the transmission path, and improving the re-orbit shooting accuracy and the overall performance of the support assembly.

[0038] Reference Figure 1 As an optional embodiment, the star sensor element 3 is installed on the lateral side of the payload 1 through the carbon fiber support 2.

[0039] As an optional embodiment, the payload 1 is a camera.

[0040] When the payload 1 is a camera, the star sensor element 3 is installed on the lateral side of the payload 1 through the carbon fiber support 2 and integrated with the payload 1, so that the distance between the star sensor element 3 and the payload 1 is the shortest, the integrality and temperature uniformity of the star sensor element 3, the carbon fiber support 2 and the payload 1 are improved, and the transmission path distance between the optical axis of the camera and the optical axis of the star sensor element 3 and the thermal deformation caused by cold and hot alternation are reduced. The camera of the payload 1 can include a shell and a camera body, wherein the shell can be a carbon fiber material consistent with the carbon fiber support 2.

[0041] Reference Figure 2 As an optional embodiment, a structure plate 4 is further included, the structure plate 4 is formed with a payload mounting cabin, the payload 1 is connected with the structure plate 4 and located in the payload mounting cabin, thereby accommodating and protecting the payload 1.

[0042] Reference Figure 1As an optional embodiment, the structural plate 4 is provided with a through hole, one end of the carbon fiber support 2 extends to the outside of the structural plate 4 through the through hole, and the star sensor element 3 is installed at the end of the carbon fiber support 2 located outside the structural plate 4.

[0043] With reference to Figure 3 As an optional embodiment, the carbon fiber support 2 includes a support body 21 and at least one star sensor installation groove 22 fixed to the surface of the load 1; the star sensor installation groove 22 is arranged on the support body 21 and used for accommodating the star sensor element 3.

[0044] As an optional embodiment, the carbon fiber support includes at least two star sensor installation grooves 22, that is, in the case where the number of star sensor installation grooves 22 is more than two, an included angle is formed between any two adjacent star sensor installation grooves 22, and the star sensor elements 3 are respectively installed in the star sensor installation grooves 22.

[0045] The star sensor elements 3 are respectively installed in the star sensor installation grooves 22 corresponding to the number of star sensor installation grooves 22, and the star sensor elements 3 respectively detect the satellite attitude and calibrate each other through the included angle between the two star sensor installation grooves 22, thereby improving the detection accuracy.

[0046] In some embodiments, the included angle between the two star sensor installation grooves 22 is greater than 80° to meet the use of the two star sensor elements 3.

[0047] With reference to Figure 1 As an optional embodiment, the heat dissipation part 5 is further included, one end of the heat dissipation part 5 is connected with the load 1, the other end passes through the structural plate 4 and is fixed to the outer surface of the structural plate 4.

[0048] The heat dissipation part 5 transmits the heat generated by the operation of the load 1 to the outside of the structural plate 4, avoids overheating of the load 1, and reduces the influence of heat on the tracking shooting accuracy.

[0049] With reference to Figure 4 As an optional embodiment, the heat dissipation part 5 includes a heat conduction pipe 51 and a heat dissipation plate 52; one end of the heat conduction pipe 51 is connected with the load 1, the other end passes through the structural plate 4 and extends to the outside of the structural plate 4; the heat dissipation plate 52 is fixed to the surface of the structural plate 4 and connected with the heat conduction pipe 51.

[0050] In some embodiments, the cross section of the heat conduction pipe 51 is circular, circular rectangular or elliptical. The heat conduction pipe 51 with the cross section of circular rectangular or elliptical is more flat and has better heat conduction effect than the heat conduction pipe 51 with the cross section of circle. One end of the heat conduction pipe 51 connected with the heat dissipation plate 52 can be uniformly distributed in a grid shape on the surface of the heat dissipation plate 52 to improve the heat dissipation effect.

[0051] With reference to Figure 4As an optional implementation, the heat dissipation part 5 and the carbon fiber support 2 have a clearance space 6 for spacing the heat dissipation part 5 and the carbon fiber support 2. The influence of the heat conducted by the heat dissipation part 5 on the carbon fiber support 2 is reduced, the thermal deformation is reduced, and the shooting accuracy is improved.

[0052] Reference Figure 5 The application also provides a satellite 100 comprising the above-mentioned star sensor payload support assembly 200.

[0053] The above has introduced the embodiments of the application in detail, and the principles and implementation manners of the application have been described by applying specific examples. The above embodiment descriptions are only used to help understand the method of the application and its core idea. Meanwhile, the changes or deformations made by the person skilled in the art according to the idea of the application, based on the specific implementation manners and application range of the application, all belong to the protection range of the application. In summary, the content of the specification should not be understood as the limitation of the application.

Claims

1. A star sensor payload support assembly, comprising: The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly.

2. The support assembly of claim 1, wherein, The application relates to a star-sensing load support assembly.

3. The support assembly of claim 1, wherein, The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly.

4. The support assembly of claim 3, wherein, The application relates to a star-sensing load support assembly.

5. The support assembly of claim 1, wherein, The application relates to a star-sensing load support assembly.

6. The support assembly of claim 1, wherein, The application relates to a star-sensing load support assembly.

7. A satellite, characterized by The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly. The application relates to a star-sensing load support assembly.

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