Satellite star sensor and accelerometer integrated mounting bracket

Abstract

The invention relates to a satellite star sensor and accelerometer integrated mounting bracket, which comprises an annular frame serving as a main mounting base; the equipment mounting plate is arranged in the annular frame and is used for mounting an accelerometer; the plurality of star sensor mounting parts are arranged on the annular frame and are used for mounting star sensors; the annular frame is connected with a satellite main structure through a plurality of first connecting pieces, and the equipment mounting plate is connected with the annular frame through at least one second connecting piece. According to the invention, through unique structural design and material selection, stable maintenance of a high-precision included angle of the star sensor and a measurement environment of the accelerometer in an on-orbit environment is realized; the problems that in-orbit installation stability of a star sensor and an accelerometer is insufficient, the star sensor and the accelerometer are easily affected by thermal deformation of a satellite main structure, and extra stress is caused by thermal expansion mismatch of different materials are solved.

Description

Technical Field

[0001] This invention relates to the field of satellite structure technology, and in particular to an integrated mounting bracket for satellite star sensors and accelerometers. Background Technology

[0002] The core payload of a high-precision Earth gravity field measurement satellite typically includes multiple star sensors for determining the satellite's attitude and high-precision accelerometers for measuring non-conservative force accelerations. The accuracy of the satellite's gravity field measurement is directly affected by the accuracy of the angles between the star sensors and the stability of the accelerometer measurement environment. These devices are all high-precision sensors, and even minute thermal deformations or mechanical stresses at their mounting interfaces can introduce measurement errors, thus affecting the quality of the final scientific data.

[0003] Traditional installation methods typically involve mounting star sensors and accelerometers independently on the satellite's main structure (such as load-bearing plates or bulkheads). During on-orbit operation, the satellite's main structure generates complex thermal deformation fields due to periodic changes in external heat flux and the influence of internal heat sources. This deformation is directly transmitted to the rigidly connected sensing devices, causing changes in the relative positional relationships between the devices (especially the angles between star sensors) and warping deformation of the accelerometer mounting interface. The required accuracy of the angles between star sensors can reach the arcsecond level; therefore, even minute angular changes caused by thermal deformation of the satellite's main structure cannot be ignored.

[0004] On the other hand, the installation of accelerometer equipment requires consideration of the matching of material thermal expansion coefficients. The accelerometer body is usually made of a specific alloy (such as aluminum alloy). If it is directly installed on the satellite's main structure (such as carbon fiber composite material) with a large difference in thermal expansion coefficient, thermal stress will be generated at the mounting interface due to the inconsistent thermal expansion / contraction of the materials when the on-orbit temperature changes. This will cause undesirable warping deformation of the mounting plate or equipment base, which will be directly coupled into the accelerometer's measurement signal, creating interference.

[0005] Existing technologies lack a solution capable of providing a highly stable installation environment for multiple high-precision star sensors and accelerometers simultaneously. Current solutions often focus on thermal control or vibration reduction for individual devices, failing to address the issues of thermal deformation isolation and matching during integrated installation of multiple devices at the system architecture level. Specifically, existing solutions struggle to maintain high stability of the angle between star sensors and effectively release thermal stress at the accelerometer mounting interface within a compact space.

[0006] Therefore, designing an integrated mounting bracket for satellite star sensors and accelerometers that can isolate thermal deformation of the satellite's main structure, match the thermal properties of equipment materials, and ensure the stability of multi-device installation is crucial for improving the accuracy of satellite gravity field measurements. Summary of the Invention

[0007] To address the technical problems existing in the prior art, the present invention aims to provide an integrated mounting bracket for satellite star sensors and accelerometers. Through structural design and material selection, it achieves stable maintenance of high-precision angles of the star sensors and stable measurement environment of the accelerometers in the on-orbit environment.

[0008] To achieve the above-mentioned objectives, the present invention provides an integrated mounting bracket for a satellite star sensor and accelerometer, comprising:

[0009] The ring-shaped frame serves as the main mounting base;

[0010] The equipment mounting plate is located within the frame of the annular frame and is used to mount the accelerometer.

[0011] Multiple star sensor mounting parts are disposed on the annular frame for mounting star sensors;

[0012] The ring frame is connected to the satellite main structure through multiple first connectors, and the equipment mounting plate is connected to the ring frame through at least one second connector.

[0013] According to one technical solution of the present invention, the annular frame is formed by connecting multiple hollow square tubes, comprising:

[0014] Adjacent right-angled square tubes and second right-angled square tubes;

[0015] Adjacent first and second oblique square tubes;

[0016] The first right-angled square tube, the second right-angled square tube, the first oblique-angled square tube, and the second oblique-angled square tube are used as four corner points arranged sequentially along the clockwise direction of the ring frame;

[0017] Four connecting square tubes are used to connect the first right-angled square tube, the second right-angled square tube, the first oblique-angled square tube, and the second oblique-angled square tube;

[0018] The angle between the beveled square tube and its adjacent side is determined by the angle of the star sensor to be installed.

[0019] According to one technical solution of the present invention, the star-sensor mounting part is a star-sensor mounting corner box made of carbon fiber composite material, which is connected and fixed to the annular frame through a connecting structure, and the number of such boxes is three.

[0020] The three star-sensor mounting corner boxes are respectively located at:

[0021] On the first right-angled square tube, located on the side away from the second oblique-angled square tube;

[0022] On the first angled square tube, located on the upper side perpendicular to the annular frame;

[0023] On the second beveled square tube, located on the outer beveled surface of the second beveled square tube.

[0024] According to one technical solution of the present invention, a positioning adjustment block is provided on the inner side of the connecting square tube between the first right-angled square tube and the second right-angled square tube;

[0025] The device mounting plate is provided with round holes, which are matched and fitted to the positioning adjustment block during installation.

[0026] According to one technical solution of the present invention, the second connector includes:

[0027] Two V-shaped forks are respectively installed on two opposite sides of the equipment mounting plate;

[0028] Two connecting adjustment blocks are respectively fixed on the connecting square tube between the first right-angled square tube and the second oblique-angled square tube and on the connecting square tube between the second right-angled square tube and the first oblique-angled square tube;

[0029] Each of the V-shaped forks has its two ends connected to the equipment mounting plate at the opening, and its tip connected to the corresponding connecting adjustment block.

[0030] According to one technical solution of the present invention, the connecting adjustment block includes a base portion for fixed connection with the connecting square tube and a truncated cone portion for connection with the V-shaped fork.

[0031] According to one technical solution of the present invention, the circular hole and the connecting adjustment block are located in the same plane.

[0032] According to one technical solution of the present invention, the first connecting member is an ear piece, and there are three such ear pieces. The three ear pieces are evenly distributed around the geometric center of the annular frame and fixed to the lower end of the annular frame. The included angle between any two ear pieces is 120°.

[0033] According to one technical solution of the present invention, the annular frame is made of carbon fiber composite material; the equipment mounting plate and the first connecting member are made of aluminum alloy.

[0034] According to one aspect of the present invention, a satellite is provided, including a satellite main structure and an integrated mounting bracket for a satellite star sensor and accelerometer as described in any of the above technical solutions, wherein the bracket is mounted on the satellite main structure via a first connector.

[0035] Compared with the prior art, the present invention has the following advantages:

[0036] This invention proposes an integrated mounting bracket for satellite star sensors and accelerometers. By using a ring frame made of carbon fiber composite material with a low coefficient of thermal expansion, the overall thermal deformation of the bracket body under on-orbit temperature changes is significantly reduced, providing a dimensionally stable master mounting reference for the star sensor and accelerometer.

[0037] In this invention, the annular frame is connected to the main structure of the satellite through three lugs with included angles of 120 degrees to each other, forming a defined and stable statically determinate support. This allows the deformation of the main structure of the satellite to be "decoupled" when it undergoes bending or warping deformation under uneven thermal loads, minimizing the bending moment and torque transmitted to the annular frame, thereby isolating the impact of thermal deformation of the main structure of the satellite on the equipment on the support.

[0038] This invention utilizes a centrally located mounting plate connected to a ring frame via V-shaped forks on both sides. This allows the mounting plate to freely expand or contract under thermal load, with the central point as a reference, along the direction indicated by the V-shaped forks. This avoids the mutual constraint and resulting thermal stress caused by the different coefficients of thermal expansion between the aluminum alloy mounting plate and the carbon fiber ring frame. The V-shaped forks, as a flexible connection structure, effectively release thermal stress, prevent warping deformation of the mounting plate, and ensure the flatness stability of the accelerometer mounting surface.

[0039] In this invention, multiple star sensors are directly mounted on a ring frame via star sensor mounting boxes made of the same low-thermal-expansion-coefficient carbon fiber composite material. Because the ring frame and the mounting boxes are made of the same material and have extremely low thermal expansion coefficients, the three components form a unified whole with coordinated thermal deformation. This ensures that the relative geometric relationship (especially the included angle) between the three star sensor mounting interfaces remains highly stable under temperature changes, meeting the arcsecond-level mounting accuracy requirements.

[0040] The integrated bracket structure of this invention is compact and highly integrated. It unifies the installation requirements of star sensors and accelerometers, reduces the number of components, simplifies the satellite assembly process, and improves the consistency and reliability of installation accuracy. Attached Figure Description

[0041] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly described below. Obviously, the drawings described below are merely some embodiments of the present invention, and those skilled in the art can obtain other drawings based on these drawings without creative effort.

[0042] Figure 1 This schematic diagram illustrates the structure of an integrated mounting bracket for a satellite star sensor and accelerometer, which is equipped with a star sensor and an accelerometer, according to an embodiment of the present invention.

[0043] Figure 2 This schematic diagram illustrates the installation of the star sensor and accelerometer on the integrated mounting bracket for satellite star sensors and accelerometers in an embodiment of the present invention.

[0044] Figure 3 This schematic diagram illustrates the structure of an integrated mounting bracket for a satellite star sensor and accelerometer according to an embodiment of the present invention.

[0045] Figure 4 This schematic diagram shows an exploded view of an integrated mounting bracket for a satellite star sensor and accelerometer according to an embodiment of the present invention.

[0046] Figure 5 This schematic diagram shows an exploded view of the annular frame in an embodiment of the present invention.

[0047] Figure 6 This diagram illustrates the installation of the first connector and the annular frame in an embodiment of the present invention.

[0048] Figure 7 This is a schematic diagram illustrating the installation of the device mounting plate and the second connector in an embodiment of the present invention.

[0049] Figure label:

[0050] 1. Circular frame; 2. Equipment mounting plate; 3. Star sensor mounting part; 4. First connector; 5. Second connector;

[0051] 11. First right-angled square tube; 12. Second right-angled square tube; 13. First oblique-angled square tube; 14. Second oblique-angled square tube; 15. Connecting square tube; 16. Positioning adjustment block;

[0052] 21. Round hole;

[0053] 51. V-shaped fork; 52. Connecting adjustment block. Detailed Implementation

[0054] The description of the embodiments in this specification should be taken in conjunction with the accompanying drawings, which should form part of the complete specification. In the drawings, the shape or thickness of the embodiments may be exaggerated and may be indicated in a simplified or convenient manner. Furthermore, parts of the various structures in the drawings will be described separately; it is worth noting that elements not shown in the figures or not described in words are in a form known to those skilled in the art.

[0055] The descriptions of the embodiments herein, including any references to directions and orientations, are for ease of description only and should not be construed as limiting the scope of the invention. The following description of preferred embodiments involves combinations of features, which may exist independently or in combination; the invention is not particularly limited to the preferred embodiments. The scope of the invention is defined by the claims.

[0056] like Figures 1 to 7 As shown, this invention discloses an integrated mounting bracket for satellite star sensors and accelerometers. As an independent component of the satellite, it aims to provide a highly stable mounting environment for the high-precision star sensors and high-precision accelerometers on the satellite. The bracket mainly includes an annular frame 1 serving as the main mounting base, a device mounting plate 2 for mounting the accelerometer, multiple star sensor mounting parts 3 for mounting the star sensors, multiple first connectors 4 for connecting the bracket to the satellite's main structure, and second connectors 5 for connecting the device mounting plate 2 and the annular frame 1. The device mounting plate 2 has multiple threaded holes for fixing the accelerometer.

[0057] The annular frame 1 serves as the core load-bearing and positioning reference for the entire support system. Its envelope size is determined based on the satellite's internal space and payload layout, and it is typically designed as a square or near-square annular structure. The equipment mounting plate 2 is located within the internal space enclosed by the annular frame 1 and is "suspended" or "connected" to the annular frame 1 in a specific manner via the second connector 5, rather than being directly and rigidly fixed to one side of the frame. Multiple star sensor mounting parts 3 are respectively fixed at specific corner positions of the annular frame 1, and the normal direction of their mounting surfaces is precisely set according to the satellite's field-of-view pointing requirements for the star sensors. The annular frame 1 is connected to the satellite's main load-bearing structure via multiple (preferably three) circumferentially distributed first connectors 4, thereby realizing the installation of the entire support module and the satellite body.

[0058] Typically, the annular frame 1 is made of carbon fiber composite material with a low coefficient of thermal expansion, which ensures low on-orbit thermal deformation of the support. This thermal deformation characteristic provides a local stable environment for the sensitive equipment. Together with the first connector 4 and the second connector 5, it isolates or absorbs thermal deformation and thermal stress generated from the satellite's main structure and the interaction between different materials, thereby ensuring the accuracy of the angle between the star sensors and the stability of the accelerometer's mounting interface.

[0059] The integrated design reduces the cumulative errors and number of interfaces caused by individual equipment installations, and improves installation stiffness and natural frequency at the system level, which helps to suppress vibration response under on-orbit mechanical conditions. As a whole, the bracket provides a carrier and basic framework for implementing subsequent optimization measures such as thermal stability and material matching.

[0060] In some embodiments of the present invention, the annular frame 1 is composed of multiple hollow square tubes joined by adhesive bonding or precision mechanical connection. The hollow square tubes can reduce weight while ensuring strength. The annular frame 1 includes:

[0061] Adjacent right-angled square tubes 11 and 12;

[0062] Adjacent to each other, the first oblique square tube 13 and the second oblique square tube 14;

[0063] The first right-angled square tube 11, the second right-angled square tube 12, the first oblique-angled square tube 13, and the second oblique-angled square tube 14 are used as four corner points arranged sequentially along the clockwise direction of the annular frame 1.

[0064] Four connecting square tubes 15 are used to connect the first right-angle square tube 11, the second right-angle square tube 12, the first oblique square tube 13, and the second oblique square tube 14;

[0065] The angle between the beveled square tube and its adjacent side is determined by the angle of the star sensor to be installed.

[0066] The adjacent faces of the first right-angled square tube 11 and the second right-angled square tube 12 are perpendicular to each other, forming a standard 90-degree interior angle. The first beveled square tube 13 and the second beveled square tube 14 are specially designed according to the pointing requirements of the star sensors to be installed on them. The "beveled angle" of the beveled square tube refers to the fact that its main axis is not perpendicular to the axis of the adjacent connecting square tube 1513, but there is a specific included angle. This included angle α (and the beveled angle β of the beveled square tube used to install the corner box) is obtained by geometric projection and inverse calculation based on the projection angle of the star sensor's optical axis in the satellite body coordinate system (usually, the angle of the star sensor is determined first, and then the angles of the first beveled square tube 13, the second beveled square tube 14, and the star sensor mounting corner box are determined). By customizing the shape of the beveled square tube, a star sensor mounting interface that meets complex pointing requirements can be directly formed on the standard square ring frame, avoiding the need to add complex adapter brackets on the standard frame, reducing assembly steps and sources of error.

[0067] The cross-sectional dimensions of all square tubes can be optimized according to stiffness, weight, and installation interface requirements. The square tubes are nested and glued together using square tube joints to form a well-integrated frame structure.

[0068] By changing the angle parameters of the beveled square tubes, star sensor layouts with different pointing requirements can be quickly adapted, enhancing the flexibility and versatility of the support design. The hollow square tube structure minimizes weight while ensuring sufficient bending and torsional stiffness, meeting the lightweight design requirements of spacecraft. The process of fabricating individual components and then bonding them together reduces the requirements for large-scale processing equipment, improves processing feasibility, and allows for better control over the fiber orientation and properties of the materials in each part, compared to fabricating large and complex frames as a whole.

[0069] For example, taking the center of the ring frame 1 as the origin, establish as follows: Figure 1 , Figures 4 to 6In the three-dimensional coordinate system shown, the four connecting square tubes 15 are respectively the positive X-side, positive Y-side, negative X-side, and negative Y-side square tubes, each with a cross-sectional dimension of 60mm × 60mm and a wall thickness of 1.5mm, molded from carbon fiber composite material. The first right-angle square tube 11, the second right-angle square tube 12, the first oblique-angle square tube 13, and the second oblique-angle square tube 14 are respectively the corner square tubes on the negative X-negative Y-side, positive X-negative Y-side, positive X-positive Y-side, and negative X-positive Y-side, with a wall thickness of 2mm, molded from carbon fiber composite material. After the four connecting square tubes 15 and the four corner square tube joints are nested and glued together, they form a square frame structure, which serves as the main mounting base of the integrated bracket.

[0070] In some embodiments of the present invention, the star-sensor mounting part 3 is a star-sensor mounting corner box made of carbon fiber composite material, which is connected and fixed to the annular frame 1 through a connecting structure, and there are three of them;

[0071] The three star-sensor mounting corner boxes are respectively located at:

[0072] On the first right-angled square tube 11, on the side away from the second oblique-angled square tube 14;

[0073] The first oblique square tube 13 is located on the upper side perpendicular to the annular frame 1;

[0074] On the second beveled square tube 14, located on the outer beveled surface of the second beveled square tube 14.

[0075] One side of the star sensor mounting box is connected and fixed to the outer surface or bevel of the corresponding corner square tube (right-angle square tube or bevel square tube) on the annular frame 1 through four screw holes, while the other side provides a flat mounting flange surface for mounting and fixing a star sensor through four screw holes.

[0076] The use of carbon fiber composite materials to manufacture the star sensor mounting box allows its coefficient of thermal expansion to match that of the annular frame 1, which is also primarily made of carbon fiber composite material. When the on-orbit temperature changes, the annular frame 1 and the star sensor mounting box will undergo coordinated thermal deformation, with an extremely low risk of relative displacement or stress due to material differences. Secondly, the extremely high specific stiffness and dimensional stability of carbon fiber composite material provide an extremely robust mounting interface with minimal deformation for the star sensors. The star sensors are directly and rigidly connected to the star sensor mounting box via screws, and the star sensor mounting box is then rigidly connected to the annular frame 11, effectively unifying the mounting reference of multiple star sensors onto a single low-deformation carbon fiber composite material structure.

[0077] In some embodiments of the present invention, a positioning adjustment block 16 is provided on the inner side of the connecting square tube 15 between the first right-angled square tube 11 and the second right-angled square tube 12;

[0078] The device mounting plate 2 is provided with a circular hole 21. During installation, the circular hole 21 is fitted to the positioning adjustment block 16.

[0079] The positioning adjustment block 16, which can be integrally formed with the connecting square tube 15 or glued later, serves to provide a precise positioning reference for the equipment mounting plate 2 within the frame plane. The engagement of the positioning adjustment block 16 with the circular hole 21 ensures the theoretically designed position of the equipment mounting plate 2 within the annular frame 1, preventing eccentricity or rotation of the equipment mounting plate 2 due to assembly errors. This positioning method is simple, effective, and easy to implement and inspect during assembly.

[0080] like Figure 5 and Figure 6 As shown, the positioning adjustment block 16 of the equipment mounting plate 2 is set on the side of the connecting square tube 15 on the negative Y side facing the positive Y direction. On the negative X side of the positive X side square tube and the positive X side of the negative X side square tube, there are connecting adjustment blocks 52 of the V-shaped fork 51 for positioning and installing the V-shaped fork 51.

[0081] In some embodiments of the present invention, such as Figure 2 , Figure 4 and Figure 7 As shown, the second connector 5 includes:

[0082] Two V-shaped forks 51 are respectively installed on two opposite sides of the equipment mounting plate 2. The V-shaped fork 51 is a V-shaped flexible connecting component that can be precision machined from a thin metal plate (such as titanium alloy) and has a certain degree of in-plane flexibility.

[0083] Two connecting adjustment blocks 52 are respectively fixed on the connecting square tube 15 between the first right-angle square tube 11 and the second oblique square tube 14 and on the connecting square tube 15 between the second right-angle square tube 12 and the first oblique square tube 13;

[0084] The two ends of the opening of each V-shaped fork 51 (i.e. the ends of the two "forks") are connected to the equipment mounting plate 2, and the tip (bottom of the V) of each V-shaped fork 51 is connected to the corresponding connecting adjustment block 52 by screws.

[0085] The V-shaped fork 51 is a key element for relieving thermal stress. When the temperature changes, the aluminum alloy mounting plate 2 and the carbon fiber annular frame 1 have different amounts of thermal expansion. The V-shaped fork 51 allows the mounting plate 2 to undergo slight displacement within the V-plane relative to the connecting adjustment block 52 (i.e., relative to the annular frame 1), thereby absorbing thermal strain caused by the difference in thermal expansion coefficients and preventing the formation of large internal stresses or warping deformation in the mounting plate 2. Simultaneously, the V-shaped fork 51 has high stiffness in the direction perpendicular to its plane, ensuring the normal support stability of the mounting plate 2.

[0086] In some embodiments of the present invention, the connecting adjustment block 52 includes a base portion for fixed connection with the connecting square tube 15 and a truncated cone portion for connection with the V-shaped fork 51. The truncated cone portion extends from the base portion toward the center of the frame, and its end is an interface surface for connection with the tip of the V-shaped fork 51, and is typically designed with a threaded hole.

[0087] The frustum section is designed in a frustum shape, which optimizes stress distribution and reduces stress concentration at the connection with the V-shaped fork 51. Furthermore, its specific geometry and height, coordinated with the height of the positioning adjustment block 16, jointly determine the installation position of the equipment mounting plate 2 in the thickness direction (Z-direction in the diagram) of the annular frame 1. The top connecting surface of the frustum section and the positioning surface of the positioning adjustment block 16 are precision machined to ensure they lie within the same theoretical mounting plane, thus guaranteeing that the equipment mounting plate 2 can sit flat on the plane defined by the positioning adjustment block 16 and the two connecting adjustment blocks 52. Precision machining controls the height of these three support points, ensuring a very high initial flatness of the equipment mounting plate 2 after installation, providing an ideal installation reference for the accelerometer. Simultaneously, the frustum structure enhances local stiffness, ensuring the stability of the hinge point of the V-shaped fork 51, allowing the thermal deformation release mechanism to operate precisely as designed.

[0088] In some embodiments of the present invention, the first connector 4 is an ear piece, and there are three of them. The three ear pieces are evenly distributed around the geometric center of the annular frame 1 and fixed to the lower end of the annular frame 1. The included angle between any two ear pieces is 120°.

[0089] Each lug is typically L-shaped, U-shaped, or T-shaped, with one side securely connected to the bottom or side of the annular frame 1 by multiple screws, and the other side (usually with screw holes) used to connect to the corresponding interface on the satellite main structure. The three lugs constitute the complete mechanical connection between the bracket and the satellite main structure.

[0090] The three-point support forms a stable structure. When the main satellite structure undergoes complex spatial deformations such as bending and warping due to uneven sunlight or heat dissipation in orbit, the deformation of the main structure cannot effectively transfer bending or torque to the support because the support is only connected to it at three points. The ring frame 1 of the integrated support only follows the average displacement and attitude changes of the three connection points, filtering out the higher-order bending components in the deformation of the main structure, and effectively isolating the large-scale, low-frequency thermal deformation of the satellite outside the support. In addition, the 120° uniform distribution provides optimal support stability and isotropy, ensuring that the support stiffness is consistent in all directions and avoiding deformation caused by support asymmetry.

[0091] like Figure 5 As shown, three lugs are installed at three locations on the positive Z side (i.e., the surface of the annular frame 1): the negative Y side, the positive X-positive Y side, and the negative X-positive Y side. The upper surface of the lugs is connected to the annular frame 1, and the lower surface of the lugs is connected to the satellite body. The three aluminum alloy lugs, with an included angle of 120 degrees to each other, are installed on the main structure of the satellite. The vertical surfaces of the lugs intersect at the geometric central axis of the integrated bracket, ensuring that the thermal deformation of the main structure of the satellite in orbit is decoupled from the annular frame.

[0092] According to one aspect of the present invention, a satellite is provided, including a satellite main structure and an integrated mounting bracket for a satellite star sensor and accelerometer as described in any of the above technical solutions, wherein the bracket is mounted on the satellite main structure via the first connector 4.

[0093] In summary, the integrated mounting bracket for satellite star sensors and accelerometers of the present invention significantly reduces the overall thermal deformation of the bracket body under orbital temperature changes by using a ring frame made of carbon fiber composite material with a low coefficient of thermal expansion, thus providing a dimensionally stable master mounting reference for the star sensor and accelerometer.

[0094] In this invention, the annular frame is connected to the main structure of the satellite through three lugs with included angles of 120 degrees to each other, forming a defined and stable statically determinate support. This allows the deformation of the main structure of the satellite to be "decoupled" when it undergoes bending or warping deformation under uneven thermal loads, minimizing the bending moment and torque transmitted to the annular frame, thereby isolating the impact of thermal deformation of the main structure of the satellite on the equipment on the support.

[0095] This invention utilizes a centrally located mounting plate connected to a ring frame via V-shaped forks on both sides. This allows the mounting plate to freely expand or contract under thermal load, with the central point as a reference, along the direction indicated by the V-shaped forks. This avoids the mutual constraint and resulting thermal stress caused by the different coefficients of thermal expansion between the aluminum alloy mounting plate and the carbon fiber ring frame. The V-shaped forks, as a flexible connection structure, effectively release thermal stress, prevent warping deformation of the mounting plate, and ensure the flatness stability of the accelerometer mounting surface.

[0096] In this invention, multiple star sensors are directly mounted on a ring frame via star sensor mounting boxes made of the same low-thermal-expansion-coefficient carbon fiber composite material. Because the ring frame and the mounting boxes are made of the same material and have extremely low thermal expansion coefficients, the three components form a unified whole with coordinated thermal deformation. This ensures that the relative geometric relationship (especially the included angle) between the three star sensor mounting interfaces remains highly stable under temperature changes, meeting the arcsecond-level mounting accuracy requirements.

[0097] The integrated bracket structure of this invention is compact and highly integrated. It unifies the installation requirements of star sensors and accelerometers, reduces the number of components, simplifies the satellite assembly process, and improves the consistency and reliability of installation accuracy.

[0098] It should also be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or terminal device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or terminal device. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or terminal device that includes said element.

[0099] Finally, it should be noted that the above description represents a preferred embodiment of the present invention. It should be pointed out that although preferred embodiments have been described, those skilled in the art, once they understand the basic inventive concept of the present invention, can make various improvements and modifications without departing from the principles described herein. These improvements and modifications should also be considered within the scope of protection of the present invention. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the embodiments of the present invention.

Claims

1. An integrated mounting bracket for satellite star sensors and accelerometers, characterized in that, include: The ring frame (1) serves as the main mounting base; The equipment mounting plate (2) is set inside the frame of the annular frame (1) and is used to install the accelerometer; Multiple star sensor mounting parts (3) are disposed on the annular frame (1) for mounting star sensors; The ring frame (1) is connected to the satellite main structure through multiple first connectors (4), and the equipment mounting plate (2) is connected to the ring frame (1) through at least one second connector (5).

2. The integrated mounting bracket for satellite star sensor and accelerometer according to claim 1, characterized in that, The annular frame (1) is formed by connecting multiple hollow square tubes, including: The first right-angled square tube (11) and the second right-angled square tube (12) are arranged adjacent to each other. The first oblique square tube (13) and the second oblique square tube (14) are arranged adjacent to each other. The first right-angled square tube (11), the second right-angled square tube (12), the first oblique-angled square tube (13) and the second oblique-angled square tube (14) are used as four corner points of the ring frame (1) arranged in a clockwise direction; Four connecting square tubes (15) are used to connect the first right-angle square tube (11), the second right-angle square tube (12), the first oblique square tube (13) and the second oblique square tube (14). The angle between the beveled square tube and its adjacent side is determined by the angle of the star sensor to be installed.

3. The integrated mounting bracket for satellite star sensor and accelerometer according to claim 2, characterized in that, The star sensor mounting part (3) is a star sensor mounting corner box made of carbon fiber composite material, which is connected and fixed to the annular frame (1) through a connecting structure, and there are three of them; The three star-sensor mounting corner boxes are respectively located at: On the first right-angled square tube (11), it is located on the side away from the second oblique-angled square tube (14); The first oblique square tube (13) is located on the upper side perpendicular to the annular frame (1); On the second beveled square tube (14), located on the outer beveled surface of the second beveled square tube (14).

4. The integrated mounting bracket for satellite star sensor and accelerometer according to claim 2, characterized in that, A positioning adjustment block (16) is provided on the inner side of the connecting square tube (15) between the first right-angle square tube (11) and the second right-angle square tube (12). The device mounting plate (2) is provided with a round hole (21). During installation, the round hole (21) is matched and installed with the positioning adjustment block (16).

5. The integrated mounting bracket for satellite star sensor and accelerometer according to claim 4, characterized in that, The second connector (5) includes: Two V-shaped forks (51) are respectively installed on two opposite sides of the equipment mounting plate (2); Two connecting adjustment blocks (52) are respectively fixed on the connecting square tube (15) between the first right-angle square tube (11) and the second oblique square tube (14) and on the connecting square tube (15) between the second right-angle square tube (12) and the first oblique square tube (13); Each of the V-shaped forks (51) has its two ends connected to the equipment mounting plate (2) at the opening, and its tip connected to the corresponding connection adjustment block (52).

6. The integrated mounting bracket for satellite star sensor and accelerometer according to claim 5, characterized in that, The connecting adjustment block (52) includes a base portion for fixed connection with the connecting square tube (15) and a cone portion for connection with the V-shaped fork (51).

7. The integrated mounting bracket for satellite star sensor and accelerometer according to claim 6, characterized in that, The circular hole (21) and the connecting adjustment block (52) are located in the same plane.

8. The integrated mounting bracket for satellite star sensor and accelerometer according to claim 1, characterized in that, The first connector (4) is an ear piece, and there are three of them. The three ear pieces are evenly distributed around the geometric center of the ring frame (1) and fixed to the lower end of the ring frame (1). The included angle between any two ear pieces is 120°.

9. The integrated mounting bracket for satellite star sensor and accelerometer according to claim 1, characterized in that, The ring frame (1) is made of carbon fiber composite material; the equipment mounting plate (2) and the first connector (4) are made of aluminum alloy.

10. A satellite, characterized in that, It includes a satellite main structure and an integrated mounting bracket for the satellite star sensor and accelerometer as described in any one of claims 1 to 9, wherein the bracket is mounted on the satellite main structure via the first connector.

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