A satellite payload cabin with integrated platform and payload design

Abstract

The invention relates to a satellite payload cabin with platform and payload integrated design, belonging to the field of aerospace technology and equipment; a south plate, an east plate, a north plate and a west plate are butted end to end in sequence to form a square cavity structure; a counter floor is horizontally covered on the top of the square cavity structure; an external space camera is arranged at the center of the upper surface of the counter floor; a middle partition is vertically arranged in the inner cavity of the square cavity structure; the east partition is perpendicular to the middle partition, and the axial ends of the east partition are respectively butted with the middle of the east plate and the middle of the middle partition; the west partition is perpendicular to the middle partition; four heat conducting pipes are grouped in pairs, and two groups of heat conducting pipes are butted to form a U-shaped heat conducting pipe group; the payload cabin of the invention has a compact structure, comprehensively considers the structural support and heat dissipation requirements of the space camera and the satellite design, gives full play to the advantages of the whole satellite structure and thermal control, realizes the integrated design of the space camera and the satellite structure and thermal control, and meets the requirements of reliable support and high-precision temperature control of the space camera.

Description

Technical Field

[0001] The invention belongs to the field of aerospace technology and equipment, and relates to a satellite payload cabin with platform and payload integrated design. Background Art

[0002] With the rapid advancement of remote sensing satellite technology and the continuous expansion of its application fields, space optical camera payloads are increasingly developing in the direction of long focal length and large aperture. Optical systems with long focal length and large aperture are more sensitive to changes in the stiffness of the load-bearing structure and internal and external heat sources, making structural stability and temperature field fluctuations important factors affecting the imaging quality of high-resolution cameras on orbit. As the core of the integrated design of platform and payload, the space optical camera payload has a complex coupling relationship with the external space environment and the satellite platform, and requires multidisciplinary optimization design such as optics, mechanics, electricity, and heat. If the platform and the payload have multiple connection points in the structure, the deformation of the platform structure will directly affect the stability of the payload structure. The functional density of the entire satellite is high, and the heat dissipation of the platform instrument cabin equipment will affect the thermal environment of the camera, thereby affecting the imaging quality.

[0003] Remote sensing satellites are generally composed of satellite platforms and payloads, which are relatively independent in structure and function. The platform provides an installation interface for the payload, and the interface relationship is relatively clear. A typical example is the French "SPOT" series of satellites. Traditional satellites are usually based on a parallel design model. After agreeing on the mechanical, electrical, and thermal interfaces, the satellite platform and space camera are independently developed, with little consideration of the mutual coupling between the two. Insufficient consideration is given to the optimization of the mechanical, electrical, and thermal joint design, making it difficult to give full play to the advantages of the entire satellite, resulting in large resource overheads for satellite envelope space, weight, power consumption, and even insurmountable technical difficulties, leading to repeated iterations in the entire design process. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art and propose a satellite payload cabin with integrated platform and payload design. The payload cabin of the present invention has a compact structure, and the structural support and heat dissipation requirements of the space camera are comprehensively considered with the satellite design, and the advantages of the whole satellite structure and thermal control are fully utilized, thereby realizing the integrated design of the space camera and the satellite structure and thermal control, and meeting the requirements of reliable support and high-precision temperature control of the space camera.

[0005] The solution of the present invention is:

[0006] A satellite payload cabin with platform and payload integrated design comprises a counter floor, a middle partition, an east partition, a west partition, a south plate, a north plate, an east plate, a west plate and four heat pipes; wherein the south plate, the east plate, the north plate and the west plate are all placed vertically and connected end to end in sequence to form a square cavity structure; the counter floor covers the top of the square cavity structure horizontally; an external space camera is arranged at the center of the upper surface of the counter floor; the middle partition is arranged vertically in the inner cavity of the square cavity structure; the middle partition is parallel to the east plate, and the axial ends of the middle partition are respectively fixed to the middle part of the south plate and the middle part of the north plate; the east partition is perpendicular to the middle partition, and the axial ends of the east partition are respectively connected to the middle part of the east plate and the middle part of the middle partition; the west partition is perpendicular to the middle partition, and the axial ends of the west partition are respectively connected to the middle part of the west plate and the middle part of the middle partition; the four heat pipes are arranged in groups of two, and the two groups of heat pipes are connected to form a U-shaped heat pipe group, and the U-shaped heat pipe group is installed on the south plate, the north plate and the middle partition.

[0007] In the above platform and payload integrated design satellite payload cabin, a payload cabin coordinate system OXYZ is established, wherein the origin O is the geometric center of the bottom end surface of the payload cabin; the Z axis points vertically to the floor direction; the X axis points vertically to the east board; and the Y axis is determined by the right-hand rule;

[0008] The middle partition is a concave structure located in the YOZ plane; the east partition and the west partition are symmetrical relative to the YOZ plane, and the east partition and the west partition are connected to form a concave structure; the middle partition, the east partition and the west partition are spliced ​​into a cross support structure.

[0009] In the above-mentioned platform and payload integrated design satellite payload cabin, a circular through hole is provided at the center of the counter floor; the external camera extends into the circular through hole of the counter floor and enters the recess of the cross support structure.

[0010] In the above-mentioned platform and payload integrated design satellite payload cabin, the heat pipes are of L-shaped structure; one side of one group of heat pipes is horizontally installed on the inner wall of the north plate, and the other side is horizontally installed on the side wall of the middle partition; one side of another group of heat pipes is horizontally installed on the inner wall of the south plate, and the other side is horizontally installed on the side wall of the middle partition.

[0011] In the above-mentioned platform and payload integrated design satellite payload cabin, the satellite payload cabin also includes 6 middle partition heat pipe brackets, 2 north and south plate heat pipe brackets, and clamps; wherein, the 6 middle partition heat pipe brackets are used to fix the edges of 2 groups of heat pipes arranged on the side walls of the middle partition; the 2 north and south plate heat pipe brackets are used to support the edges of the 2 groups of heat pipes located on the south plate and the north plate; the clamps are arranged on the north and south plate heat pipe brackets to fix the heat pipes.

[0012] In the above-mentioned platform and payload integrated design satellite payload cabin, U-shaped heat pipes are arranged inside the south plate and the north plate, and the U-shaped heat pipes of the south plate and the north plate are symmetrically arranged.

[0013] In the above-mentioned platform and payload integrated design satellite payload cabin, the two ends of the opening of the U-shaped heat pipe group are respectively connected to the two U-shaped heat pipes; after the external camera is extended into the floor, the heat collecting plate of the external camera contacts the middle part of the U-shaped heat pipe group; the heat collecting plate concentrates the heat of the external camera, and exports the heat to the two U-shaped heat pipes through the U-shaped heat pipe group, and realizes radiation heat dissipation of the heat through the two U-shaped heat pipes.

[0014] In the above-mentioned platform and payload integrated design satellite payload cabin, the heat pipe is coated with multiple layers of insulation material before installation, and a heating plate and a thermistor are installed on the outer wall. When the temperature of the external camera is too low, the external camera is heated by the heating plate to maintain the normal working temperature of the external camera; the connection area between the U-shaped heat pipe group and the heat collecting plate of the external camera and the two U-shaped heat pipes is coated with thermal conductive silicone.

[0015] In the above-mentioned platform and payload integrated design satellite payload cabin, the U-shaped heat pipe group and the U-shaped heat pipe form an orthogonal heat pipe network; OSR sheets are pasted on the outer walls of the south plate and the north plate; and the inner walls of the south plate and the north plate where the U-shaped heat pipe is placed are coated with multiple layers of thermal insulation materials.

[0016] In the above-mentioned platform and payload integrated design satellite payload cabin, it is characterized in that: the four notch corner points of the middle partition, east partition and west partition spliced ​​into a cross support structure are respectively provided with an aluminum alloy reinforcement joint; each partition is affixed with two layers of carbon fiber reinforcement plies in the reinforcement joint coverage area to reduce concentrated stress; two threaded holes are provided on the upper end surface of each group of reinforcement joints for installation; the floor, middle partition, east partition, west partition, east plate and west plate are carbon fiber skin honeycomb sandwich panels; the south plate and north plate are aluminum alloy skin honeycomb sandwich panels; the middle partition plate heat pipe bracket, the north and south plate heat pipe brackets and the clamps are made of aluminum alloy materials.

[0017] The beneficial effects of the present invention compared with the prior art are:

[0018] (1) The payload cabin of the present invention is designed as a box-type structure with a notch in the middle. The rear optical part of the space camera is installed inside the cabin. The structural design is compact, which reduces the moment of inertia and Z-axis center of mass offset of the entire satellite, significantly improves the mechanical environment of the active segment space camera, and can also enhance the agile maneuverability of the satellite.

[0019] (2) The payload cabin of the present invention transmits the space camera load to the floor, partition and outer plate through a reasonable main load-bearing structure design. The force transmission path is simple, the load-bearing capacity is high, and the thermal stability is good. The deformation of the cabin plate in the heat flow environment outside the space can avoid affecting the camera structure and thus affecting the imaging quality.

[0020] (3) The payload cabin of the present invention optimizes the structural support and thermal control design of the space camera in a coordinated manner, fully tapping the resource potential of the satellite platform. The payload cabin is designed with a dedicated camera heat dissipation surface. Through reasonable insulation and heat dissipation design, a heat pipe is used to transfer the heat source inside the camera to the satellite surface for heat dissipation, and the heat dissipation surface is precisely temperature-controlled, thereby improving the heat dissipation efficiency of the camera and reducing temperature fluctuations during the imaging process. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is an exploded schematic diagram of the present invention without the camera payload compartment;

[0022] Figure 2 It is a schematic diagram of the assembly of the camera payload cabin of the present invention;

[0023] Figure 3 It is a schematic diagram of the heat pipe of the present invention;

[0024] Figure 4 This is a schematic diagram of the heat pipe installation interface of the present invention;

[0025] Figure 5 This is a schematic diagram of the interface between the payload cabin and the external camera;

[0026] Figure 6 Schematic diagram of the heat pipe bracket and clamp in the payload cabin. DETAILED DESCRIPTION

[0027] The present invention will be further described below in conjunction with the embodiments.

[0028] The present invention proposes a satellite payload cabin with a platform and payload integrated design. The payload cabin has a compact structure, and comprehensively considers the structural support and heat dissipation requirements of a space camera with the satellite design, fully utilizing the advantages of the entire satellite structure and thermal control, and realizes an integrated design of the space camera with the satellite structure and thermal control, meeting the requirements of reliable support and high-precision temperature control of the space camera.

[0029] Platform and payload integrated design satellite payload compartment, such as Figure 1 , Figure 2As shown, it specifically includes a floor panel 1, a middle partition panel 2, an east partition panel 3, a west partition panel 4, a south panel 5, a north panel 6, an east panel 7, a west panel 8 and four heat pipes 9; wherein the south panel 5, the east panel 7, the north panel 6 and the west panel 8 are all placed vertically and connected end to end in sequence to form a square cavity structure; the floor panel 1 is horizontally covered on the top of the square cavity structure; the external space camera is arranged at the center of the upper surface of the floor panel 1; the middle partition panel 2 is vertically arranged in the inner cavity of the square cavity structure; the middle partition panel 2 is parallel to the east panel 7, And the axial ends of the middle partition 2 are respectively fixedly connected to the middle part of the south plate 5 and the middle part of the north plate 6; the east partition 3 is perpendicular to the middle partition 2, and the axial ends of the east partition 3 are respectively connected to the middle part of the east plate 7 and the middle part of the middle partition 2; the west partition 4 is perpendicular to the middle partition 2, and the axial ends of the west partition 4 are respectively connected to the middle part of the west plate 8 and the middle part of the middle partition 2; the four heat pipes 9 are grouped in pairs, and the two groups of heat pipes 9 are connected to form a U-shaped heat pipe group, which is installed on the south plate 5, the north plate 6, and the middle partition 2.

[0030] A load compartment coordinate system OXYZ is established, wherein the origin O is the geometric center of the bottom end face of the load compartment; the Z axis points vertically to the direction of the floor panel 1; the X axis points vertically to the east panel 7; the Y axis is determined by the right-hand rule; the middle partition 2 is a concave structure located in the YOZ plane; the east partition 3 and the west partition 4 are symmetrical with respect to the YOZ plane, and the east partition 3 and the west partition 4 are connected and assembled into a concave structure; the middle partition 2, the east partition 3 and the west partition 4 are assembled into a cross support structure.

[0031] A circular through hole is provided at the center of the base plate 1; the external camera extends into the circular through hole of the base plate 1 and enters the notch of the cross support structure.

[0032] like Figure 3 As shown, the heat conducting pipes 9 are of L-shaped structure; one side of one group of heat conducting pipes 9 is horizontally installed on the inner wall of the north plate 6, and the other side is horizontally installed on the side wall of the middle partition 2; one side of another group of heat conducting pipes 9 is horizontally installed on the inner wall of the south plate 5, and the other side is horizontally installed on the side wall of the middle partition 2.

[0033] like Figure 1 , Figure 4 As shown, the satellite payload cabin also includes 6 middle partition heat pipe brackets 10, 2 north and south plate heat pipe brackets 11, and clamps 12; wherein, the 6 middle partition heat pipe brackets 10 are used to fix the edges of 2 groups of heat pipes 9 arranged on the side walls of the middle partition 2; the 2 north and south plate heat pipe brackets 11 are used to support the edges of the 2 groups of heat pipes 9 located on the south plate 5 and the north plate 6; the clamps 12 are arranged on the north and south plate heat pipe brackets 11 to fix the heat pipes 9 with the clamps 12.

[0034] U-shaped heat pipes 101 are disposed inside the south plate 5 and the north plate 6 , and the U-shaped heat pipes 101 of the south plate 5 and the north plate 6 are symmetrically disposed.

[0035] like Figure 4 As shown, both ends of the opening of the U-shaped heat pipe group are connected to two U-shaped heat pipes 101 respectively; after the external camera is extended into the floor 1, the heat collecting plate of the external camera contacts the middle of the U-shaped heat pipe group; the heat collecting plate concentrates the heat of the external camera, and exports the heat to the two U-shaped heat pipes 101 through the U-shaped heat pipe group, and realizes radiation heat dissipation of the heat through the two U-shaped heat pipes 101.

[0036] Before installation, the heat pipe 9 is coated with multiple layers of insulation material, and a heating plate and a thermistor are installed on the outer wall. When the temperature of the external camera is too low, the external camera is heated by the heating plate to maintain the normal working temperature of the external camera; the connection area between the U-shaped heat pipe group and the heat collecting plate of the external camera and the two U-shaped heat pipes 101 is coated with thermal conductive silicone.

[0037] The U-shaped heat pipe group and the U-shaped heat pipe 101 form an orthogonal heat pipe network; the outer walls of the south plate 5 and the north plate 6 are pasted with OSR sheets; the inner walls of the south plate 5 and the north plate 6 where the U-shaped heat pipe 101 is mounted are coated with multiple layers of thermal insulation materials.

[0038] like Figure 5 As shown, the middle partition 2, the east partition 3 and the west partition 4 are spliced ​​into four notched corner points of the cross support structure, and an aluminum alloy reinforcement joint 102 is provided respectively; each partition is affixed with two layers of carbon fiber reinforcement plies 103 in the area covered by the reinforcement joint 102 to reduce concentrated stress; two threaded holes 104 are provided on the upper end surface of each group of reinforcement joints 102 for installation; the floor panel 1, the middle partition 2, the east partition 3, the west partition 4, the east panel 7 and the west panel 8 are carbon fiber skinned honeycomb sandwich panels; the south panel 5 and the north panel 6 are aluminum alloy skinned honeycomb sandwich panels; the middle partition heat pipe bracket 10, the north and south panel heat pipe brackets 11 and the clamp 12 are made of aluminum alloy material.

[0039] like Figure 6 As shown, waist-shaped holes are designed on the bottom mounting surfaces of the middle partition heat pipe bracket 10, the north and south plate heat pipe brackets 11, and the clamp 12 to ensure that the position of the heat pipe 9 can be finely adjusted in all directions in the cabin.

[0040] When assembling the equipment in the load compartment, it is only necessary to open the east plate 7 and the west plate 8 to form an open operating space without the need for support from a retaining frame tooling.

[0041] Example

[0042] like Figure 1 , 2 As shown, the platform and payload integrated design satellite payload cabin structure of the present invention includes: a floor 1, a middle partition 2, an east partition 3, a west partition 4, a south plate 5, a north plate 6, an east plate 7, a west plate 8, a heat pipe 9, a middle partition heat pipe bracket 10, a north and south plate heat pipe bracket 11, and a clamp 12.

[0043] The middle partition 2 is a "concave" shaped structure and is located in the YOZ plane; the east partition 3 and the west partition 4 are located in the XOY plane, and are half of the "concave" shaped structure symmetrical about the YOZ plane. The two are vertically connected to the middle partition 2 to form a cross support structure with a notch in the middle; a circular opening is provided in the middle of the floor panel 1, and the south plate 5, north plate 6, east plate 7, and west plate 8 are connected to the floor panel 1 around the cross support structure to form a closed cabin body, and the cabin body size is about 2400mm (X) × 2600mm (Y) × 1000mm (Z); the top plate 1, south plate 5, north plate 6 and the cross support structure together constitute the main load-bearing structure of the payload cabin. After the structural parts are installed, they are generally not disassembled and serve as the installation basis for space cameras and electronic equipment in the cabin.

[0044] The rear cover of the space camera passes through the circular opening of the floor panel 1 and enters the recessed space of the cross-support structure in the cabin, and is installed on the floor panel 1 through the camera flange. The compact structural design can improve the space utilization rate of the payload cabin by more than 10%, reduce the rotational inertia and Z-axis center of mass offset of the entire satellite, improve the mechanical environment of the active segment camera, and at the same time enhance the agile maneuverability of the satellite. In addition, the camera is directly connected to the main load-bearing structure of the payload cabin, the load-bearing path is smooth, the mechanical performance of the entire satellite is good, and the mass of the satellite's bearing structure can be effectively saved.

[0045] like Figure 3 As shown, the heat pipe 9 is an approximately right-angle structure in space, connected by arc transition at the corners, and includes four I-shaped single-hole groove heat pipes, and the mounting surfaces at both ends of the heat pipes are parallel to the XOY plane and the XOZ plane respectively.

[0046] like Figure 4 As shown in the figure, a heat collecting plate is installed at the rear cover of the space camera to collect the heat generated by the heat source in the camera. The +X side areas of the south plate 5 and the north plate 6 are respectively provided with a camera heat dissipation surface 101, and the area of ​​a single heat dissipation surface is about 0.4m 2 The heat pipe 9 transfers the heat from the heat collecting plate to the camera heat dissipation surface 101 and radiates heat into the space.

[0047] The middle partition heat pipe bracket 10 is installed on the +X side cabin plate of the middle partition 2 (3 pieces on each ±Y side, a total of 6 pieces); the south and north plate heat pipe brackets 11 are respectively installed on the +X side non-heat dissipation area cabin plates of the south plate 5 and the north plate 6 (3 pieces on each south and north plates, a total of 6 pieces); the 4 heat pipes 9 are supported and fixed on the +X side inside the load cabin through the middle partition heat pipe bracket 10, the south and north plate heat pipe brackets 11 and the clamps 12; one end of the heat pipe 9 is connected to the heat collecting plate, and the other end is connected to the camera heat dissipation surface 101, and the heat pipe 9 is fixed to the heat collecting plate and the camera heat dissipation surface 101 by the clamps 12.

[0048] Before installation, the heat pipe 9 is coated with multiple layers of insulation material, and a heating plate and a thermistor are installed at appropriate positions; the connection area between the heat pipe 9 and the heat collecting plate and the camera heat dissipation surface 101 is coated with thermal conductive silicone to improve the thermal conductivity of the heat pipe 9, the heat collecting plate and the load compartment plate.

[0049] The middle partition heat pipe bracket 10 and the middle partition 2 are insulated by polyimide insulation gaskets; the north and south plate heat pipe brackets 11 and the south plate 5 and the north plate 6 are insulated by polyimide insulation gaskets; the space camera and the floor 1 are insulated by titanium alloy insulation gaskets to minimize the impact of the payload cabin on the camera temperature.

[0050] A pair of U-shaped heat pipes are embedded in the camera heat dissipation surfaces 101 of the south plate 5 and the north plate 6, and the heat pipes 9 and the U-shaped heat pipes form an orthogonal heat pipe network; in order to reduce the influence of the satellite heat dissipation surface on the camera heat dissipation surface 101, the camera heat dissipation surface 101 is expanded outward along the -Z and -X directions within a proper distance range without embedded heat pipes of the whole satellite; in order to prevent the internal temperature of the camera from being too low when the camera is not working or the external heat flow on the camera heat dissipation surface 101 is small, a certain number of compensating heating circuits are pasted on the heat pipes 9 connecting the north and south heat dissipation surfaces.

[0051] OSR sheets are pasted on the outer surfaces of the south plate 5 and the north plate 6 facing the space, and the camera heat dissipation surface 101 facing the cabin is covered with multiple layers of heat insulation materials.

[0052] Through the heat dissipation design and high-precision temperature control of the camera heat dissipation surface 101, a heat dissipation capacity of 130W of the heat source in the camera can be achieved, ensuring that the on-orbit operating temperature of the electronic equipment in the camera meets the requirements.

[0053] like Figure 5 As shown, 4 groups of reinforcing joints 102 are arranged at the corner points of the notch of the cross support structure composed of the middle partition 2, the east partition 3, and the west partition 4. The reinforcing joints 102 are made of high-strength aluminum alloy, which has high strength and is easy to machine. Two layers of carbon fiber reinforcement plies 103 (4 groups in total) are attached to the partition in the area covered by the reinforcing joints 102 to disperse the load transfer to the partition and reduce the concentrated stress. Two threaded holes 104 (8 in total) are provided on the upper end surface of each group of reinforcing joints 102, which together with the outer circle threaded holes of the circular opening on the counter plate 1 constitute a camera installation interface. The camera installation interface on the counter plate 1 is a boss, which is 2mm higher than the cabin plate, which is convenient for overall machining and can achieve a flatness of the camera installation surface of no more than 0.2mm.

[0054] Through structural optimization design, the load compartment's carrying capacity can reach about 400kg.

[0055] like Figure 6As shown in the figure, the middle partition heat pipe support 10 is in a "⊥" shape. There are 3 mounting holes on the docking surface with the heat pipe 9 for installing the clamp 12. There are reinforcing ribs on the opposite side to improve the stiffness. There are 4 waist-shaped holes on the bottom surface for connecting with the middle partition 2; the north-south plate heat pipe support 11 is in a "Ⅱ" shape. There are 3 mounting holes on the top surface for installing the clamp 12. There are 4 waist-shaped holes on the bottom surface for connecting with the south plate 5 and the north plate 6; the clamp 12 is composed of two "ㄥ" shapes connected in series. There are 3 waist-shaped holes for pressing the heat pipe 9.

[0056] The heat pipe 9 can be finely adjusted in position in all directions in the cabin through the waist-shaped holes of the support and the clamp, avoiding the influence of the processing and assembly errors of the cabin plates on the assembly of the heat pipe 9, and ensuring good fit between the heat pipe 9 and the heat collection plate and the camera heat dissipation surface 101.

[0057] When the equipment in the payload cabin is assembled, open the east plate 7 and the west plate 8 to form an open operation space. There is no need to rely on the traditional cage tooling for support. Based on the main load-bearing structure, install the instrument equipment and cables on the inner surfaces of the south plate 5, the north plate 6 and the top plate 1. The operation space of the payload cabin is more than 800 mm, and the structure is open, which is convenient for the assembly operation.

[0058] The payload cabin of the present invention uses mature raw materials. The floor 1, the middle partition 2, the east partition 3, the west partition 4, the east plate 7 and the west plate 8 are carbon fiber skin honeycomb sandwich panels, which have high load-bearing capacity and good thermal stability, and can avoid the influence of the deformation of the cabin plates under the space external heat flux environment on the camera structure, and further affect the imaging quality; the south plate 5 and the north plate 6 are aluminum alloy skin honeycomb sandwich panels, meeting the requirements of equipment installation and heat dissipation; the middle partition heat pipe support 10, the north-south plate heat pipe support 11 and the clamp 12 are made of aluminum alloy materials, which are light in weight and convenient for machining.

[0059] As Figure 4 、 6 shown in the figure, the steps for docking the payload cabin of the present invention with the space camera are as follows:

[0060] Step 1: Remove the east plate 7 of the payload cabin;

[0061] Step 2: Install the middle partition heat pipe supports 10 (3 pieces on each of the ±Y sides) and the north-south plate heat pipe supports 11 (3 pieces on each of the north and south plates) at the specified positions on the middle partition 2, the south plate 5 and the north plate 6. Install polyimide thermal insulation gaskets between the heat pipe supports and the cabin plates;

[0062] Step 3: Install the heat pipes 9 on the middle partition heat pipe supports 10 and the north-south plate heat pipe supports 11 respectively, and preliminarily fix them through the clamps 12;

[0063] Step 4: Fix the heat pipe 9 to the camera heat dissipation surface 101 through the clamp 12, adjust the heat pipe to fit well with the heat dissipation surface, and apply thermal conductive silicone to the connection area;

[0064] Step 5: Arrange the multi-layer insulation material of the heat pipe 9, and weld the heating plate and thermistor leads on the heat pipe to the corresponding cables on the satellite;

[0065] Step six, measuring the distance between the mounting end surface of the heat collecting plate on the heat conducting tube 9 and the mounting surface of the space camera on the base plate 1, so as to adjust the distance between the heat collecting plate of the space camera and the mounting flange;

[0066] Step 7: Install four guide rods at four quadrants on the camera installation surface of the base plate 1;

[0067] Step 8: Lift the camera above the opening to the floor 1, and after passing through the guide rod, slowly lower the camera along the guide rod to below the opening to the floor 1. During the descent, observe the gap between the camera heat collecting plate and the heat pipe 9. The waist-shaped hole of the heat pipe bracket and the adjustable deformation of the heat pipe itself can be used to ensure that the gap between the heat pipe 9 and the heat collecting plate meets the requirements.

[0068] Step nine: After the heat pipe gap meets the requirements, the heat pipe 9 is fixed on the heat collecting plate through the clamp 12, and the connection area between the heat collecting plate and the heat pipe is coated with thermal conductive silicone;

[0069] Step 10, after the space camera is installed, remove the guide rods and the hanger, connect the camera to the external connector onboard cable, use multi-layer insulation material to seal the camera heat pipe installation port and the external connector installation port, and restore the installation of East Plate 7.

[0070] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on 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 of the technical solution of the present invention.

Claims

1. A satellite payload cabin with integrated platform and payload design, characterized in that: The invention comprises a counter floor (1), a middle partition (2), an east partition (3), a west partition (4), a south plate (5), a north plate (6), an east plate (7), a west plate (8) and four heat conducting pipes (9); wherein the south plate (5), the east plate (7), the north plate (6) and the west plate (8) are all placed vertically and connected end to end in sequence to form a square cavity structure; the counter floor (1) is horizontally covered on the top of the square cavity structure; the external space camera is arranged at the center of the upper surface of the counter floor (1); the middle partition (2) is vertically arranged in the inner cavity of the square cavity structure; the middle partition (2) is parallel to the east plate (7), and the middle The axial ends of the partition (2) are respectively fixedly connected to the middle of the south plate (5) and the middle of the north plate (6); the east partition (3) is perpendicular to the middle partition (2), and the axial ends of the east partition (3) are respectively butted against the middle of the east plate (7) and the middle of the middle partition (2); the west partition (4) is perpendicular to the middle partition (2), and the axial ends of the west partition (4) are respectively butted against the middle of the west plate (8) and the middle of the middle partition (2); the four heat conducting pipes (9) are grouped in pairs, and the two groups of heat conducting pipes (9) are butted against each other to form a U-shaped heat conducting pipe group, which is installed on the south plate (5), the north plate (6) and the middle partition (2); Establish a load cabin coordinate system OXYZ, where the origin O is the geometric center of the bottom end surface of the load cabin; the Z axis is perpendicular to the direction of the opposite floor (1); the X axis is perpendicular to the east board (7); and the Y axis is determined by the right-hand rule; The middle partition (2) is a concave-shaped structure located in the YOZ plane; the east partition (3) and the west partition (4) are symmetrical relative to the YOZ plane, and the east partition (3) and the west partition (4) are butt-jointed to form a concave-shaped structure; the middle partition (2), the east partition (3) and the west partition (4) are spliced ​​to form a cross support structure; A circular through hole is arranged at the center of the counter floor (1); the external camera extends into the circular through hole of the counter floor (1) and enters the notch of the cross support structure.

2. The satellite payload cabin with integrated platform and payload design according to claim 1, characterized in that: The heat conducting pipes (9) are of an L-shaped structure; one side of one group of heat conducting pipes (9) is horizontally mounted on the inner wall of the north plate (6), and the other side is horizontally mounted on the side wall of the middle partition plate (2); one side of another group of heat conducting pipes (9) is horizontally mounted on the inner wall of the south plate (5), and the other side is horizontally mounted on the side wall of the middle partition plate (2).

3. The satellite payload cabin with integrated platform and payload design according to claim 2, characterized in that: The satellite payload cabin further comprises six middle partition heat pipe brackets (10), two north and south plate heat pipe brackets (11), and clamps (12); wherein the six middle partition heat pipe brackets (10) are used to fix the edges of two groups of heat conducting pipes (9) arranged on the side walls of the middle partition (2); the two north and south plate heat pipe brackets (11) are used to support the edges of the two groups of heat conducting pipes (9) located on the south plate (5) and the north plate (6); and the clamps (12) are arranged on the north and south plate heat pipe brackets (11) to fix the heat conducting pipes (9) by the clamps (12).

4. The satellite payload cabin with integrated platform and payload design according to claim 3, characterized in that: U-shaped heat pipes (101) are arranged inside the south plate (5) and the north plate (6), and the U-shaped heat pipes (101) of the south plate (5) and the north plate (6) are arranged symmetrically.

5. The satellite payload cabin with integrated platform and payload design according to claim 4, characterized in that: The two ends of the opening of the U-shaped heat-conducting pipe group are respectively connected to the two U-shaped heat pipes (101); after the external camera is extended into the floor (1), the heat collecting plate of the external camera contacts the middle of the U-shaped heat-conducting pipe group; the heat collecting plate concentrates the heat of the external camera, and conducts the heat to the two U-shaped heat pipes (101) through the U-shaped heat-conducting pipe group, and radiates the heat through the two U-shaped heat pipes (101).

6. The satellite payload cabin with integrated platform and payload design according to claim 5, characterized in that: The heat-conducting pipe (9) is coated with multiple layers of heat-insulating material before installation, and a heating plate and a thermistor are installed on the outer wall. When the temperature of the external camera is too low, the external camera is heated by the heating plate to maintain the normal operating temperature of the external camera. The connection area between the U-shaped heat-conducting pipe group and the heat collecting plate of the external camera and the two U-shaped heat pipes (101) is coated with heat-conducting silica gel.

7. The satellite payload cabin with integrated platform and payload design according to claim 6, characterized in that: The U-shaped heat pipe group and the U-shaped heat pipe (101) form an orthogonal heat pipe network; OSR sheets are attached to the outer walls of the south plate (5) and the north plate (6); and the inner walls of the south plate (5) and the north plate (6) where the U-shaped heat pipe (101) is mounted are coated with multiple layers of heat insulation material.

8. The satellite payload cabin with integrated platform and payload design according to claim 7, characterized in that: The middle partition (2), the east partition (3) and the west partition (4) are spliced ​​into four notched corners of a cross support structure, each of which is provided with an aluminum alloy reinforcement joint (102); each partition is affixed with two layers of carbon fiber reinforcement plies (103) in the area covered by the reinforcement joint (102) to reduce concentrated stress; two threaded holes (104) are provided on the upper end surface of each group of reinforcement joints (102) for installation; the floor panel (1), the middle partition (2), the east partition (3), the west partition (4), the east plate (7) and the west plate (8) are carbon fiber skin honeycomb sandwich panels; the south plate (5) and the north plate (6) are aluminum alloy skin honeycomb sandwich panels; the middle partition plate heat pipe bracket (10), the north and south plate heat pipe brackets (11) and the clamp (12) are made of aluminum alloy material.

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