A composite support device applied to an inter-satellite laser communication terminal

Abstract

The application provides a composite support device applied to an inter-satellite laser communication terminal, comprising three central main support frames, the three central main support frames are arranged in an isosceles triangle and are fixedly installed on the top end surface of a main structure, the vertical central axis of the first central main support frame, the vertical central axis of the second central main support frame and the vertical central axis of the third central main support frame are located in the same vertical plane, the vertical central axis of the first central main support frame coincides with the vertical central axis of the longitudinal front end surface of the main structure, and the device further comprises two auxiliary side support frames, the two auxiliary side support frames are symmetrically fixedly installed on the left end surface and the right end surface of the main structure. The flexible joints arranged on the central main support frames in the application can absorb small deformation of the installation area, the auxiliary side support frames are located on the two sides of the main structure, the flexible joints and the flexible grooves arranged on the auxiliary side support frames can absorb large deformation and isolate thermal deformation introduced by the change of the ambient temperature.

Description

Technical Field

[0001] This invention belongs to the field of laser communication technology, and relates to laser communication terminals, specifically to a composite support device for inter-satellite laser communication terminals. Background Technology

[0002] Satellite laser communication technology uses lasers as the information carrier and features high bandwidth, small size, low power consumption, and good security, making it an effective means of achieving high-speed satellite communication. An inter-satellite laser communication terminal consists of an optical head and a control unit. The optical head is the core component of the entire inter-satellite laser communication terminal, responsible for beam transmission and reception, beam shaping, and spatial pointing.

[0003] The optical head comprises the main structure, transceiver channel, coarse pointing mechanism, and telescope. The transceiver channel is typically installed within the main structure. As the core module of the inter-satellite laser communication terminal, the transceiver channel directly impacts the transmission and reception performance of the entire laser communication system. During the launch and on-orbit operation phases, the inter-satellite laser communication terminal is subject to complex external environmental factors, including launch vibrations, gravity release, and temperature variations. These changes alter the relative positions of the optical components within the transceiver channel, affecting the optical axis consistency of the transmitted and received signals, thereby reducing the tracking efficiency and communication quality of the inter-satellite laser communication terminal. Furthermore, the complex environment during launch, orbit insertion, and space operation necessitates that the supporting structure of the inter-satellite laser communication terminal possess excellent structural stability and stress unloading capabilities. Summary of the Invention

[0004] To address the shortcomings of existing technologies, the present invention aims to provide a composite support device for inter-satellite laser communication terminals, thereby solving the technical problem that the consistency of the optical axis of light emission and reception in inter-satellite laser communication terminals under complex temperature-changing environments needs to be further improved.

[0005] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0006] A composite support device for inter-satellite laser communication terminals includes three central main support frames. The first central main support frame is fixedly installed on the top surface of the main structure, and the second and third central main support frames are fixedly installed on the bottom surface of the main structure. The vertical central axes of the first, second, and third central main support frames are all located in the same vertical plane. The vertical central axis of the first central main support frame coincides with the vertical central axis of the longitudinal front face of the main structure, and the vertical central axes of the second and third central main support frames are symmetrically arranged about the vertical central axis of the first central main support frame.

[0007] It also includes two auxiliary side support frames, which are symmetrically fixedly installed on the left and right end faces of the main structure, respectively.

[0008] The central main support frame includes a horizontally arranged main frame fixing plate, which is fixedly connected to the main structure. A left flexible section of the main frame is embedded and fixedly connected to the longitudinal front end of the main frame fixing plate. The left flexible section of the main frame is arranged vertically on the main frame fixing plate. A right flexible section of the main frame is embedded and fixedly connected to the longitudinal front end of the main frame fixing plate. The right flexible section of the main frame is arranged vertically on the main frame fixing plate. The left and right flexible sections of the main frame are symmetrically arranged about the vertical central axis of the first central main support frame.

[0009] The main frame left flexible section and the main frame right flexible section are fixedly connected by a main frame mounting boss. The main frame mounting boss is set vertically, and the longitudinal front end face of the main frame mounting boss contacts the satellite cabin panel. The main frame mounting boss is used to connect with the satellite cabin panel.

[0010] The present invention also has the following technical features:

[0011] Specifically, the main frame fixing plate is an arc-shaped plate. A rectangular main frame mounting hole is provided at the center of the longitudinal front end of the main frame fixing plate. The main frame mounting hole passes through the vertical upper and lower ends of the main frame fixing plate. A left flexible section of the main frame is provided inside the main frame mounting hole. One side of the left flexible section of the main frame is fixedly connected to the main frame fixing plate, and the other side of the left flexible section of the main frame is fixedly connected to one side of the main frame mounting boss.

[0012] The main frame mounting hole is also provided with a right flexible section of the main frame. One side of the right flexible section of the main frame is fixedly connected to the other side of the main frame mounting boss, and the other side of the right flexible section of the main frame is fixedly connected to the main frame fixing plate.

[0013] Specifically, the main frame fixing plate is provided with three vertical through main frame fixing screw holes, which penetrate the main frame fixing plate and are evenly distributed along an arc. The main frame fixing plate and the main structure are fixedly connected by main frame fixing screws installed in the main frame fixing screw holes.

[0014] Around the outer surface of the main frame fixing screw hole located at the middle position of the arc, there is also a main frame U-shaped flexible groove, with the opening of the main frame U-shaped flexible groove facing backward.

[0015] The main frame fixing plate is also provided with a rounded rectangular main frame through hole. The main frame through hole penetrates the main frame fixing plate vertically. The main frame through hole is located at the transverse center of the main frame fixing plate and close to the longitudinal front end. The longitudinal front end of the main frame through hole is in contact with the longitudinal rear end of the main frame left flexible section, the main frame right flexible section and the main frame mounting boss.

[0016] Specifically, the main frame mounting boss is U-shaped with the opening facing inward.

[0017] The main frame mounting boss is also provided with a longitudinally penetrating main frame satellite mounting screw hole at its center. The main frame mounting boss and the satellite compartment plate are fixedly connected by the main frame satellite mounting screw installed in the main frame satellite mounting screw hole.

[0018] Specifically, the auxiliary side support frame includes a vertically arranged auxiliary frame long strip fixing plate, which is connected to the auxiliary frame mounting boss connecting plate through a long flexible section, and the long flexible section is arranged along the longitudinal direction.

[0019] The auxiliary frame mounting boss connecting plate is provided with an upper auxiliary frame mounting boss and a lower auxiliary frame mounting boss. The upper auxiliary frame mounting boss is located vertically above the lower auxiliary frame mounting boss, and the upper auxiliary frame mounting boss and the lower auxiliary frame mounting boss are vertically symmetrical. The upper auxiliary frame mounting boss and the lower auxiliary frame mounting boss are used to connect with the satellite cabin panel.

[0020] Specifically, the auxiliary frame long strip fixing plate has four horizontally penetrating long strip fixing screw holes, which are evenly distributed vertically; the auxiliary frame long strip fixing plate is fixedly connected to the main structure by long strip fixing screws installed in the long strip fixing screw holes.

[0021] On the vertical sides of the two long strip fixing screw holes in the middle of the vertical axis, there are rectangular narrow flexible sections with rounded corners at both ends. The longitudinal rear end of the narrow flexible section is flush with the longitudinal rear end of the long strip fixing plate of the auxiliary frame. The longitudinal extension of the narrow flexible section extends into the auxiliary frame mounting boss connecting plate, and the longitudinal front end of the narrow flexible section is flush with the longitudinal front end of the auxiliary frame mounting boss connecting plate.

[0022] The outer surface of the auxiliary frame long strip fixing plate has two long strip U-shaped flexible grooves, which are arranged in a mirror symmetrical manner; the two long strip U-shaped flexible grooves are respectively located around the two long strip fixing screw holes in the vertical direction.

[0023] The inner surface of the auxiliary frame long strip fixing plate is provided with a long strip fixing boss, which contacts the main structure, and the long strip fixing screw hole passes through the long strip fixing boss.

[0024] Specifically, the auxiliary frame mounting boss connecting plate has two symmetrically arranged fixing screw holes in the vertical middle. The two fixing screw holes are located between two narrow flexible sections and extend horizontally through the auxiliary frame mounting boss connecting plate. The auxiliary frame mounting boss connecting plate is fixedly connected to the main structure by fixing screws installed in the fixing screw holes.

[0025] The outer surface of the auxiliary frame mounting boss connecting plate is also provided with two connecting plate U-shaped flexible grooves. The openings of the two connecting plate U-shaped flexible grooves face backward, and the two connecting plate U-shaped flexible grooves are respectively located around the fixing screw holes of the auxiliary frame boss connecting plate.

[0026] The inner surface of the auxiliary frame mounting boss connecting plate is also provided with a connecting plate fixing boss, which contacts the main structure, and the auxiliary frame boss connecting plate fixing screw hole penetrates the connecting plate fixing boss.

[0027] Specifically, the mounting boss on the auxiliary frame includes a vertically arranged mounting boss plate on the auxiliary frame. The mounting boss plate on the auxiliary frame is fixedly connected to the outer surface of the mounting boss connecting plate on the auxiliary frame. The longitudinal front end face of the mounting boss plate on the auxiliary frame also contacts the satellite cabin panel.

[0028] The upper boss plate of the auxiliary frame is also provided with a satellite connection screw hole at the center position, which passes through the front and rear ends of the upper boss plate of the auxiliary frame; the upper boss plate satellite connection screw installed in the upper boss plate satellite connection screw hole is used to fix the mounting boss on the auxiliary frame and the satellite compartment plate.

[0029] Both the upper and lower ends of the upper boss plate of the auxiliary frame are provided with upper boss transverse fixing plates. The upper boss transverse fixing plates are arranged in the horizontal direction and are right-angled triangles. One right-angled side of the upper boss transverse fixing plate is fixedly connected to the longitudinal rear end face of the upper boss plate of the auxiliary frame, and the other right-angled side of the upper boss transverse fixing plate is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate.

[0030] The upper boss plate of the auxiliary frame is also provided with an upper boss vertical fixing plate. The upper boss vertical fixing plate is arranged vertically. The shape of the upper boss plate of the auxiliary frame is a right triangle. One right-angled side of the upper boss vertical fixing plate is fixedly connected to the upper boss plate of the auxiliary frame, and the other right-angled side of the upper boss vertical fixing plate is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate.

[0031] Specifically, the auxiliary frame lower mounting boss includes a vertically arranged auxiliary frame lower boss plate, which is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate, and the longitudinal front end face of the auxiliary frame lower boss plate is also in contact with the satellite cabin plate.

[0032] The lower boss plate of the auxiliary frame is also provided with a satellite connection screw hole at the center position, which passes through the front and rear ends of the lower boss plate of the auxiliary frame; the lower boss plate satellite connection screw installed in the lower boss plate satellite connection screw hole is used to fix the lower mounting boss of the auxiliary frame and the satellite compartment plate.

[0033] Both the upper and lower ends of the auxiliary frame lower boss plate are provided with a lower boss horizontal fixing plate. The lower boss horizontal fixing plate is arranged horizontally and is shaped as a right triangle. One right-angled side of the lower boss horizontal fixing plate is fixedly connected to the longitudinal rear end face of the auxiliary frame lower boss plate, and the other right-angled side of the lower boss horizontal fixing plate is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate.

[0034] The lower boss plate of the auxiliary frame is also provided with a lower boss vertical fixing plate. The lower boss vertical fixing plate is arranged vertically and is shaped like a right triangle. One right-angled side of the lower boss vertical fixing plate is fixedly connected to the lower boss plate of the auxiliary frame, and the other right-angled side of the lower boss vertical fixing plate is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate.

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

[0036] (I) The device in this invention adopts a central main support frame distributed in an isosceles triangle to ensure the main support rigidity of the main structure in the inter-satellite laser communication terminal. The flexible joints set on the central main support frame absorb the small deformation of the installation area. The auxiliary side support frame is located on both sides of the main structure. The flexible joints and flexible grooves set on the auxiliary side support frame can absorb large deformation and isolate the thermal deformation introduced by the external environment due to changes in ambient temperature.

[0037] (II) The device in this invention consists of a central main support frame and an auxiliary side support frame. While ensuring the support rigidity, it absorbs the thermal deformation caused by the material or temperature mismatch between the inter-satellite laser communication terminal and the satellite cabin through the flexible joint set on the support structure, so that the inter-satellite laser communication terminal has high temperature adaptability, compact structure, easy installation and strong versatility.

[0038] (III) The device in this invention uses high-strength and high-toughness titanium alloy metal material as the support frame material, which ensures the safety margin of large-scale vibration intensity during the launch phase while avoiding metal fatigue under on-orbit cyclic thermal deformation; in addition, the extremely low thermal conductivity of titanium alloy can effectively isolate the contact heat exchange between the inter-satellite laser communication terminal and the satellite compartment, reducing the impact on the temperature uniformity of the inter-satellite laser communication terminal.

[0039] (IV) The device in this invention adopts a split design, which is easy to process and convenient to install and debug. Attached Figure Description

[0040] Figure 1 This is a schematic diagram of the installation structure of the composite support device in the inter-satellite laser communication terminal.

[0041] Figure 2(a) is a schematic diagram of the central main support frame in this invention.

[0042] Figure 2(b) is a bottom view of Figure 2(a).

[0043] Figure 3(a) is a schematic diagram of the auxiliary side support frame in this invention.

[0044] Figure 3(b) is the left view of Figure 3(a).

[0045] Figure 4 The first-order mode shape diagram of an inter-satellite laser communication terminal using the composite support device of the present invention.

[0046] Figure 5 This invention describes the deformation of the main structure of an inter-satellite laser communication terminal under wide temperature variations using the composite support device of this invention.

[0047] Figure 6(a) is a schematic diagram of the thermal deformation of the satellite cabin under high temperature conditions.

[0048] Figure 6(b) is a schematic diagram of the thermal deformation of the satellite cabin under low temperature conditions.

[0049] Figure 7 This is a displacement cloud diagram of the central main support frame in this invention caused by the thermal deformation of the satellite cabin panel.

[0050] Figure 8 This is a displacement cloud diagram of the auxiliary side support frame in this invention caused by the thermal deformation of the satellite cabin panel.

[0051] The meanings of the labels in the diagram are as follows: 1-Central main support frame, 2-Main structure, 3-Auxiliary side support frame, 4-Coarse pointing structure, 5-Telescope.

[0052] 101-Main frame fixing plate, 102-Main frame left flexible section, 103-Main frame right flexible section, 104-Main frame mounting boss, 105-Main frame mounting hole, 106-Main frame satellite mounting screw hole.

[0053] 301-Auxiliary frame long strip fixing plate, 302-Long strip flexible section, 303-Auxiliary frame mounting boss connecting plate, 304-Auxiliary frame upper mounting boss, 305-Auxiliary frame lower mounting boss.

[0054] 10101 - Main frame fixing screw hole, 10102 - Main frame U-shaped flexible groove, 10103 - Main frame through hole.

[0055] 30101-Fixing screw hole for long strip plate, 30102-Narrow flexible section, 30103-U-shaped flexible groove for long strip plate, 30104-Fixing boss for long strip plate.

[0056] 30301 - Auxiliary frame boss connecting plate fixing screw hole, 30302 - Connecting plate U-shaped flexible groove, 30303 - Connecting plate fixing boss.

[0057] 30401 - Upper boss plate of auxiliary frame, 30402 - Satellite connection screw hole of upper boss plate, 30403 - Horizontal fixing plate of upper boss, 30404 - Vertical fixing plate of upper boss.

[0058] 30501 - Lower boss plate of auxiliary frame, 30502 - Satellite connection screw hole of lower boss plate, 30503 - Horizontal fixing plate of lower boss, 30504 - Vertical fixing plate of lower boss.

[0059] The specific content of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Detailed Implementation

[0060] It should be noted that, unless otherwise specified, all components and materials in this invention are known in the prior art. For example, the flexible joint is a known flexible joint, the titanium alloy metal material is a known titanium alloy metal material, the inter-satellite laser communication terminal is a known commonly used inter-satellite laser communication terminal, and the coarse pointing structure is a known commonly used coarse pointing structure.

[0061] In this invention, the main structure 2 refers to the main structure in the optical head of the inter-satellite laser communication terminal, and the main structure is a commonly used known main structure.

[0062] In this invention, the coordinate system OXYZ is a known three-dimensional rectangular coordinate system; the X-axis is horizontal and points to the right; the Y-axis is vertical and points forward; and the Z-axis is vertical and points upward.

[0063] In this invention, the central main support frame 1 is fixedly connected to the long side of the longitudinal front end face of the main structure 2, and the auxiliary side support frame 3 is fixedly connected to the short side of the longitudinal front end face of the main structure 2.

[0064] Following the above technical solutions, specific embodiments of the present invention are given below. It should be noted that the present invention is not limited to the following specific embodiments, and all equivalent modifications made based on the technical solutions of this application fall within the protection scope of the present invention.

[0065] Example:

[0066] This embodiment provides a composite support device for inter-satellite laser communication terminals, such as... Figure 1As shown, it includes three central main support frames 1. The first central main support frame 1 is fixedly installed on the top surface of the main structure 2, and the second and third central main support frames 1 are fixedly installed on the bottom surface of the main structure 2. The vertical central axis of the first central main support frame 1, the vertical central axis of the second central main support frame 1, and the vertical central axis of the third central main support frame 1 are all located in the same vertical plane. The vertical central axis of the first central main support frame 1 coincides with the vertical central axis of the longitudinal front end face of the main structure 2, and the vertical central axes of the second and third central main support frames 1 are symmetrically arranged with the vertical central axis of the first central main support frame 1 as the axis of symmetry.

[0067] like Figure 1 As shown, it also includes two auxiliary side support frames 3, which are symmetrically fixedly installed on the left and right end faces of the main structure 2.

[0068] As shown in Figure 2(a), the central main support frame 1 includes a horizontally arranged main frame fixing plate 101, which is fixedly connected to the main structure 2. The longitudinal front end of the main frame fixing plate 101 is embedded and fixedly connected to the left flexible section 102 of the main frame, which is arranged vertically on the main frame fixing plate 101. The longitudinal front end of the main frame fixing plate 101 is embedded and fixedly connected to the right flexible section 103 of the main frame, which is arranged vertically on the main frame fixing plate 101. The left flexible section 102 and the right flexible section 103 of the main frame are symmetrically arranged with the vertical central axis of the first central main support frame 1 as the axis of symmetry.

[0069] As shown in Figure 2(a), a main frame mounting boss 104 is fixedly connected between the left flexible section 102 and the right flexible section 103 of the main frame. The main frame mounting boss 104 is set vertically, and the longitudinal front end face of the main frame mounting boss 104 contacts the satellite module. The main frame mounting boss 104 is used to connect with the satellite module.

[0070] In this embodiment, both the central main support frame 1 and the auxiliary side support frame 3 are made of high-strength and high-toughness titanium alloy metal material.

[0071] In this embodiment, the central main support frame 1 provides the main support stiffness, and the flexible joints on the central main support frame 1 can absorb small thermal deformations in small areas. The auxiliary side support frame 3 is located on the left and right sides of the front end of the main structure in the inter-satellite laser communication terminal. Since the inter-satellite laser communication terminal has large lateral thermal deformations, the flexible joints and flexible grooves on the auxiliary side support frame 3 can absorb large lateral thermal deformations.

[0072] As a preferred embodiment, as shown in Figure 2(a), the main frame fixing plate 101 is an arc-shaped plate. A rectangular main frame mounting hole 105 is provided at the center of the longitudinal front end of the main frame fixing plate 101. The main frame mounting hole 105 passes through the vertical upper and lower ends of the main frame fixing plate 101. The main frame left flexible section 102 is provided inside the main frame mounting hole 105. One side of the main frame left flexible section 102 is fixedly connected to the main frame fixing plate 101, and the other side of the main frame left flexible section 102 is fixedly connected to one side of the main frame mounting boss 104.

[0073] The main frame mounting hole 105 is also provided with a main frame right flexible section 103. One side of the main frame right flexible section 103 is fixedly connected to the other side of the main frame mounting boss 104, and the other side of the main frame right flexible section 103 is fixedly connected to the main frame fixing plate 101.

[0074] As a preferred embodiment, as shown in Figure 2(a), the main frame fixing plate 101 is provided with three vertically penetrating main frame fixing screw holes 10101. The three main frame fixing screw holes 10101 penetrate the main frame fixing plate 101 and are evenly distributed along the arc. The main frame fixing plate 101 and the main structure 2 are fixedly connected by the main frame fixing screws installed in the main frame fixing screw holes 10101.

[0075] As shown in Figure 2(a), a U-shaped flexible groove 10102 for the main frame is also provided around the outer surface of the main frame fixing screw hole 10101 located at the middle position of the arc. The opening of the U-shaped flexible groove 10102 for the main frame faces backward.

[0076] As shown in Figure 2(b), the main frame fixing plate 101 is also provided with a rounded rectangular main frame through hole 10103. The main frame through hole 10103 penetrates the main frame fixing plate 101 vertically. The main frame through hole 10103 is located at the transverse center of the main frame fixing plate 101 and close to the longitudinal front end. The longitudinal front end of the main frame through hole 10103 is in contact with the longitudinal rear end of the main frame left flexible section 102, the main frame right flexible section 103 and the main frame mounting boss 104.

[0077] As a preferred embodiment, as shown in FIG2(a), the main frame mounting boss 104 is U-shaped with the opening facing inward.

[0078] The main frame mounting boss 104 is also provided with a longitudinally penetrating main frame satellite mounting screw hole 106 at its center. The main frame satellite mounting screw installed in the main frame satellite mounting screw hole 106 is used to fix the main frame mounting boss 104 and the satellite compartment plate.

[0079] As a preferred embodiment, as shown in FIG3(a), the auxiliary side support frame 3 includes a vertically arranged auxiliary frame long strip fixing plate 301. The auxiliary frame long strip fixing plate 301 is connected to the auxiliary frame mounting boss connecting plate 303 through a long strip flexible section 302. The long strip flexible section 302 is arranged along the longitudinal direction.

[0080] As shown in Figure 3(a), the auxiliary frame mounting boss connecting plate 303 is provided with an upper auxiliary frame mounting boss 304 and a lower auxiliary frame mounting boss 305. The upper auxiliary frame mounting boss 304 is located vertically above the lower auxiliary frame mounting boss 305, and the upper auxiliary frame mounting boss 304 and the lower auxiliary frame mounting boss 305 are vertically symmetrical. The upper auxiliary frame mounting boss 304 and the lower auxiliary frame mounting boss 305 are used to connect with the satellite cabin panel.

[0081] As a preferred embodiment, as shown in Figure 3(a), the auxiliary frame long strip fixing plate 301 has four horizontally penetrating long strip fixing screw holes 30101, which are evenly arranged vertically; the auxiliary frame long strip fixing plate 301 and the main structure 2 are fixedly connected by long strip fixing screws installed in the long strip fixing screw holes 30101.

[0082] As shown in Figure 3(a), on the vertical sides of the auxiliary frame long strip fixing plates 301 on the two long strip fixing screw holes 30101 in the middle vertical direction, there are rectangular narrow flexible sections 30102 with rounded corners at both ends. The longitudinal rear end of the narrow flexible section 30102 is flush with the longitudinal rear end of the auxiliary frame long strip fixing plate 301. The longitudinal extension of the narrow flexible section 30102 extends into the auxiliary frame mounting boss connecting plate 303, and the longitudinal front end of the narrow flexible section 30102 is flush with the longitudinal front end of the auxiliary frame mounting boss connecting plate 303.

[0083] As shown in Figure 3(a), two U-shaped flexible grooves 30103 are respectively opened on the outer surface of the auxiliary frame long strip fixing plate 301. The two U-shaped flexible grooves 30103 are arranged in a mirror symmetrical manner. The two U-shaped flexible grooves 30103 are respectively located around the two vertically upward and downward long strip fixing screw holes 30101.

[0084] As shown in Figure 3(b), the inner surface of the auxiliary frame long strip fixing plate 301 is provided with a long strip fixing boss 30104. The long strip fixing boss 30104 contacts the main structure 2, and the long strip fixing screw hole 30101 passes through the long strip fixing boss 30104.

[0085] In this embodiment, the narrow flexible section 30102 and the two long U-shaped flexible grooves 30103 mainly absorb deformation along the Z-axis and rotational deformation around the Y-axis. The narrow flexible section 30102 is used to absorb smaller deformations, and the long U-shaped flexible grooves 30103 are used to absorb larger deformations.

[0086] As a preferred embodiment, as shown in Figure 3(a), the auxiliary frame mounting boss connecting plate 303 has two auxiliary frame boss connecting plate fixing screw holes 30301 arranged symmetrically in the vertical middle. The two auxiliary frame boss connecting plate fixing screw holes 30301 are located between two narrow flexible sections 30102, and the two auxiliary frame boss connecting plate fixing screw holes 30301 penetrate the auxiliary frame mounting boss connecting plate 303 laterally. The auxiliary frame mounting boss connecting plate 303 is fixedly connected to the main structure 2 by the auxiliary frame boss connecting plate fixing screws installed in the auxiliary frame boss connecting plate fixing screw holes 30301.

[0087] As shown in Figure 3(a), two U-shaped flexible grooves 30302 are also provided on the outer surface of the auxiliary frame mounting boss connecting plate 303. The openings of the two U-shaped flexible grooves 30302 face backward, and the two U-shaped flexible grooves 30302 are respectively located around the fixing screw holes 30301 of the auxiliary frame boss connecting plate.

[0088] As shown in Figure 3(b), the inner surface of the auxiliary frame mounting boss connecting plate 303 is also provided with a connecting plate fixing boss 30303. The connecting plate fixing boss 30303 is in contact with the main structure 2, and the auxiliary frame boss connecting plate fixing screw hole 30301 penetrates the connecting plate fixing boss 30303.

[0089] In this embodiment, the long flexible section 302 and the connecting plate U-shaped flexible groove 30302 mainly absorb deformation along the X-axis and rotational deformation around the Z-axis. The long flexible section 302 is used to absorb smaller deformations, and the connecting plate U-shaped flexible groove 30302 is used to absorb larger deformations.

[0090] As a preferred embodiment, as shown in FIG3(a), the auxiliary frame mounting boss 304 includes a vertically arranged auxiliary frame upper boss plate 30401. The auxiliary frame upper boss plate 30401 is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate 303, and the longitudinal front end face of the auxiliary frame upper boss plate 30401 is also in contact with the satellite cabin plate.

[0091] As shown in Figure 3(a), a satellite connection screw hole 30402 is also provided at the center of the upper boss plate 30401 of the auxiliary frame. The upper boss plate satellite connection screw hole 30402 passes through the front and rear ends of the upper boss plate 30401 of the auxiliary frame. The upper boss plate satellite connection screw installed in the upper boss plate satellite connection screw hole 30402 is used to fix the mounting boss 304 on the auxiliary frame to the satellite compartment plate.

[0092] As shown in Figure 3(a), both the upper and lower ends of the upper boss plate 30401 of the auxiliary frame are provided with upper boss transverse fixing plates 30403. The upper boss transverse fixing plates 30403 are arranged in the transverse direction. The shape of the upper boss transverse fixing plates 30403 is a right triangle. One right-angled side of the upper boss transverse fixing plate 30403 is fixedly connected to the longitudinal rear end face of the upper boss plate 30401 of the auxiliary frame, and the other right-angled side of the upper boss transverse fixing plate 30403 is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate 303.

[0093] As shown in Figure 3(a), an upper boss vertical fixing plate 30404 is also provided on the upper boss plate 30401 of the auxiliary frame. The upper boss vertical fixing plate 30404 is arranged vertically. The shape of the upper boss plate 30401 of the auxiliary frame is a right triangle. One right-angled side of the upper boss vertical fixing plate 30404 is fixedly connected to the upper boss plate 30401 of the auxiliary frame, and the other right-angled side of the upper boss vertical fixing plate 30404 is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate 303.

[0094] As a preferred embodiment, as shown in FIG3(a), the auxiliary frame lower mounting boss 305 includes a vertically arranged auxiliary frame lower boss plate 30501. The auxiliary frame lower boss plate 30501 is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate 303, and the longitudinal front end face of the auxiliary frame lower boss plate 30501 is also in contact with the satellite cabin plate.

[0095] As shown in Figure 3(a), a satellite connection screw hole 30502 is also provided at the center of the lower boss plate 30501 of the auxiliary frame. The satellite connection screw hole 30502 of the lower boss plate passes through the front and rear ends of the lower boss plate 30501 of the auxiliary frame. The satellite connection screw of the lower boss plate installed in the satellite connection screw hole 30502 of the lower boss plate is used to fix the lower mounting boss 305 of the auxiliary frame to the satellite compartment plate.

[0096] As shown in Figure 3(a), both the upper and lower ends of the auxiliary frame lower boss plate 30501 are provided with a lower boss transverse fixing plate 30503. The lower boss transverse fixing plate 30503 is arranged in the transverse direction and is a right triangle. One right-angled side of the lower boss transverse fixing plate 30503 is fixedly connected to the longitudinal rear end face of the auxiliary frame lower boss plate 30501, and the other right-angled side of the lower boss transverse fixing plate 30503 is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate 303.

[0097] As shown in Figure 3(a), a lower boss vertical fixing plate 30504 is also provided on the lower boss plate 30501 of the auxiliary frame. The lower boss vertical fixing plate 30504 is arranged vertically and is a right triangle. One right-angled side of the lower boss vertical fixing plate 30504 is fixedly connected to the lower boss plate 30501 of the auxiliary frame, and the other right-angled side of the lower boss vertical fixing plate 30504 is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate 303.

[0098] Figure 4 The coarse pointing mechanism 4 and the telescope 5 are hidden in the first-order mode shape diagram of the inter-satellite laser communication terminal using the composite support device of the present invention. The simulation results show that the first-order frequency of the optical head using the present invention is higher than the common satellite main frequency, indicating that the device in the present invention can provide high support structure stiffness and ensure the stability of the optical head structure.

[0099] Figure 5 To address the deformation of the main structure of the inter-satellite laser communication terminal using the composite support device of this invention under wide temperature variations, Figure 5 It can be seen that when the optical head deforms by 0.05mm at the mounting footprint of the satellite module due to temperature change, the relative deformation of the main structure 2 itself is less than 0.005mm. This indicates that the present invention can effectively isolate the thermal deformation of the satellite module caused by temperature change and ensure the stability of the internal optical path of the optical head.

[0100] Figure 6(a) is a schematic diagram of the thermal deformation of the satellite module under high-temperature conditions, where the high-temperature condition is a temperature rise of ΔT (ΔT is greater than 10℃) in the space environment. As shown in Figure 6(a), when the temperature rises by ΔT, the satellite module usually has a higher temperature, which will cause deformation Δu0~Δu3 at the mounting footprint of the optical head (Δu0 and Δu3 are the deformations of the satellite module at the mounting location of the central main support frame 1, and Δu1 and Δu2 are the deformations of the satellite module at the mounting location of the auxiliary side support frame 3).

[0101] Figure 6(b) is a schematic diagram of the thermal deformation of the satellite module under cryogenic conditions, where cryogenic conditions refer to a temperature drop of ΔT (ΔT is greater than 10℃) in the space environment. As shown in Figure 6(b), when the temperature rises by ΔT, the satellite module typically has a higher temperature, which will cause deformation Δu0~Δu3 at the mounting footprint of the optical head (Δu0 and Δu3 are the deformations of the satellite module at the mounting location of the central main support frame 1, and Δu1 and Δu2 are the deformations of the satellite module at the mounting location of the auxiliary side support frame 3).

[0102] Figure 7 This is a displacement cloud diagram of the central main support frame in this invention caused by the thermal deformation of the satellite cabin panel. Figure 7It can be seen that when the optical head deforms by 0.07mm at the mounting footprint of the satellite module due to temperature change, the main structure 2 itself deforms by about 0.02mm, indicating that the central main support frame 1 can effectively isolate the thermal deformation of the satellite module near the mounting footprint.

[0103] Figure 8 This is a displacement cloud diagram of the auxiliary side support frame in this invention caused by the thermal deformation of the satellite cabin panel. Figure 8 It can be seen that when the optical head deforms by 0.08mm at the mounting footprint of the satellite module due to temperature change, the main structure 2 itself deforms by about 0.01mm, indicating that the auxiliary side support frame 3 can effectively isolate the thermal deformation of the satellite module near the mounting footprint.

Claims

1. A composite support device for inter-satellite laser communication terminals, characterized in that, It includes three central main support frames (1). The first central main support frame (1) is fixedly installed on the top surface of the main structure (2), and the second and third central main support frames (1) are fixedly installed on the bottom surface of the main structure (2). The vertical central axis of the first central main support frame (1), the vertical central axis of the second central main support frame (1), and the vertical central axis of the third central main support frame (1) are all located in the same vertical plane. The vertical central axis of the first central main support frame (1) coincides with the vertical central axis of the longitudinal front end face of the main structure (2). The vertical central axis of the second central main support frame (1) and the vertical central axis of the third central main support frame (1) are symmetrically arranged with the vertical central axis of the first central main support frame (1) as the axis of symmetry. It also includes two auxiliary side support frames (3), which are symmetrically fixed on the left and right end faces of the main structure (2), respectively; the auxiliary side support frame (3) includes a vertically arranged auxiliary frame long strip fixing plate (301), which is connected to the auxiliary frame mounting boss connecting plate (303) through a long strip flexible section (302), and the long strip flexible section (302) is arranged along the longitudinal direction; the auxiliary frame mounting boss connecting plate (303) is provided with an auxiliary frame upper mounting boss (304) and an auxiliary frame lower mounting boss (305). The central main support frame (1) includes a horizontally arranged main frame fixing plate (101), which is fixedly connected to the main structure (2). The longitudinal front end of the main frame fixing plate (101) is embedded and fixedly connected to the left flexible section (102) of the main frame. The left flexible section (102) of the main frame is arranged vertically on the main frame fixing plate (101). The longitudinal front end of the main frame fixing plate (101) is embedded and fixedly connected to the right flexible section (103) of the main frame. The right flexible section (103) of the main frame is arranged vertically on the main frame fixing plate (101). The left flexible section (102) and the right flexible section (103) of the main frame are symmetrically arranged with the vertical central axis of the first central main support frame (1) as the axis of symmetry. The main frame left flexible section (102) and the main frame right flexible section (103) are fixedly connected by a main frame mounting boss (104). The main frame mounting boss (104) is set vertically, and the longitudinal front end face of the main frame mounting boss (104) contacts the satellite cabin plate. The main frame mounting boss (104) is used to connect with the satellite cabin plate. The main frame fixing plate (101) is also provided with a rounded rectangular main frame through hole (10103). The main frame through hole (10103) penetrates the main frame fixing plate (101) vertically. The main frame through hole (10103) is located at the transverse center of the main frame fixing plate (101) and close to the longitudinal front end. The longitudinal front end of the main frame through hole (10103) is in contact with the longitudinal rear end of the main frame left flexible section (102), the main frame right flexible section (103) and the main frame mounting boss (104).

2. The composite support device for inter-satellite laser communication terminals as described in claim 1, characterized in that, The main frame fixing plate (101) is an arc-shaped plate. A rectangular main frame mounting hole (105) is provided at the center of the longitudinal front end of the main frame fixing plate (101). The main frame mounting hole (105) passes through the vertical upper and lower ends of the main frame fixing plate (101). The main frame left flexible section (102) is provided inside the main frame mounting hole (105). One side of the main frame left flexible section (102) is fixedly connected to the main frame fixing plate (101) in the horizontal direction. The other side of the main frame left flexible section (102) is fixedly connected to one side of the main frame mounting boss (104) in the horizontal direction. The main frame mounting hole (105) is also provided with a main frame right flexible section (103). One side of the main frame right flexible section (103) is fixedly connected to the other side of the main frame mounting boss (104), and the other side of the main frame right flexible section (103) is fixedly connected to the main frame fixing plate (101).

3. The composite support device for inter-satellite laser communication terminals as described in claim 2, characterized in that, The main frame fixing plate (101) is provided with three vertically penetrating main frame fixing screw holes (10101). The three main frame fixing screw holes (10101) penetrate the main frame fixing plate (101) and are evenly distributed along the arc line. The main frame fixing plate (101) and the main structure (2) are fixedly connected by the main frame fixing screws installed in the main frame fixing screw holes (10101). The main frame fixing screw hole (10101) located at the middle position of the arc is surrounded by a main frame U-shaped flexible groove (10102), with the opening of the main frame U-shaped flexible groove (10102) facing backward.

4. The composite support device for inter-satellite laser communication terminals as described in claim 1, characterized in that, The main frame mounting boss (104) is U-shaped with the opening facing inward; The main frame mounting boss (104) is also provided with a longitudinally penetrating main frame satellite mounting screw hole (106) at its center. The main frame satellite mounting screw installed in the main frame satellite mounting screw hole (106) is used to fix the main frame mounting boss (104) and the satellite compartment plate.

5. The composite support device for inter-satellite laser communication terminals as described in claim 1, characterized in that, The mounting boss (304) on the auxiliary frame is located vertically above the mounting boss (305) on the auxiliary frame. The mounting boss (304) on the auxiliary frame and the mounting boss (305) on the auxiliary frame are vertically symmetrical. The mounting boss (304) on the auxiliary frame and the mounting boss (305) on the auxiliary frame are used to connect with the satellite cabin panel.

6. The composite support device for inter-satellite laser communication terminals as described in claim 5, characterized in that, The auxiliary frame long strip fixing plate (301) is provided with four horizontally penetrating long strip fixing screw holes (30101), and the four long strip fixing screw holes (30101) are evenly arranged vertically; the auxiliary frame long strip fixing plate (301) and the main structure (2) are fixedly connected by long strip fixing screws installed in the long strip fixing screw holes (30101). On the vertical sides of the auxiliary frame long strip fixing plates (301) of the two long strip fixing screw holes (30101) in the vertical middle, there are rectangular narrow flexible sections (30102) with rounded corners at both ends. The longitudinal rear end of the narrow flexible section (30102) is flush with the longitudinal rear end of the auxiliary frame long strip fixing plate (301). The longitudinal extension of the narrow flexible section (30102) extends into the auxiliary frame mounting boss connecting plate (303), and the longitudinal front end of the narrow flexible section (30102) is flush with the longitudinal front end of the auxiliary frame mounting boss connecting plate (303). The outer surface of the auxiliary frame long strip fixing plate (301) is provided with two long strip U-shaped flexible grooves (30103), and the two long strip U-shaped flexible grooves (30103) are arranged in a mirror symmetrical manner; the two long strip U-shaped flexible grooves (30103) are respectively located around the two long strip fixing screw holes (30101) in the vertical direction. The inner surface of the auxiliary frame long strip fixing plate (301) is provided with a long strip fixing boss (30104), the long strip fixing boss (30104) is in contact with the main structure (2), and the long strip fixing screw hole (30101) passes through the long strip fixing boss (30104).

7. The composite support device for inter-satellite laser communication terminals as described in claim 5, characterized in that, The auxiliary frame mounting boss connecting plate (303) is provided with two auxiliary frame boss connecting plate fixing screw holes (30301) symmetrically arranged in the vertical middle. The two auxiliary frame boss connecting plate fixing screw holes (30301) are located between two narrow flexible sections (30102). The two auxiliary frame boss connecting plate fixing screw holes (30301) penetrate the auxiliary frame mounting boss connecting plate (303) laterally. The auxiliary frame mounting boss connecting plate (303) is fixedly connected to the main structure (2) by the auxiliary frame boss connecting plate fixing screw installed in the auxiliary frame boss connecting plate fixing screw holes (30301). The outer surface of the auxiliary frame mounting boss connecting plate (303) is also provided with two connecting plate U-shaped flexible grooves (30302). The openings of the two connecting plate U-shaped flexible grooves (30302) face backward, and the two connecting plate U-shaped flexible grooves (30302) are respectively located around the fixing screw holes (30301) of the auxiliary frame boss connecting plate. The inner surface of the auxiliary frame mounting boss connecting plate (303) is also provided with a connecting plate fixing boss (30303), the connecting plate fixing boss (30303) is in contact with the main structure (2), and the auxiliary frame boss connecting plate fixing screw hole (30301) passes through the connecting plate fixing boss (30303).

8. The composite support device for inter-satellite laser communication terminals as described in claim 5, characterized in that, The auxiliary frame mounting boss (304) includes a vertically arranged auxiliary frame mounting boss plate (30401), which is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate (303), and the longitudinal front end face of the auxiliary frame mounting boss plate (30401) is also in contact with the satellite cabin plate. The upper boss plate (30401) of the auxiliary frame is also provided with a satellite connection screw hole (30402) at the center position. The satellite connection screw hole (30402) of the upper boss plate passes through the front and rear ends of the upper boss plate (30401) of the auxiliary frame. The satellite connection screw of the upper boss plate installed in the satellite connection screw hole (30402) of the upper boss plate is used to fix the mounting boss (304) on the auxiliary frame and the satellite compartment plate. The upper and lower ends of the auxiliary frame upper boss plate (30401) are provided with upper boss transverse fixing plates (30403). The upper boss transverse fixing plates (30403) are arranged in the transverse direction. The shape of the upper boss transverse fixing plates (30403) is a right triangle. One right-angled side of the upper boss transverse fixing plate (30403) is fixedly connected to the longitudinal rear end face of the auxiliary frame upper boss plate (30401). The other right-angled side of the upper boss transverse fixing plate (30403) is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate (303). The auxiliary frame upper boss plate (30401) is also provided with an upper boss vertical fixing plate (30404). The upper boss vertical fixing plate (30404) is arranged vertically. The shape of the auxiliary frame upper boss plate (30401) is a right triangle. One right-angled side of the upper boss vertical fixing plate (30404) is fixedly connected to the auxiliary frame upper boss plate (30401), and the other right-angled side of the upper boss vertical fixing plate (30404) is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate (303).

9. The composite support device for inter-satellite laser communication terminals as described in claim 5, characterized in that, The auxiliary frame lower mounting boss (305) includes a vertically arranged auxiliary frame lower boss plate (30501), which is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate (303), and the longitudinal front end face of the auxiliary frame lower boss plate (30501) is also in contact with the satellite cabin plate. The lower boss plate (30501) of the auxiliary frame is also provided with a satellite connection screw hole (30502) at the center position. The satellite connection screw hole (30502) of the lower boss plate passes through the front and rear ends of the lower boss plate (30501) of the auxiliary frame. The satellite connection screw of the lower boss plate installed in the satellite connection screw hole (30502) of the lower boss plate is used to fix the lower mounting boss (305) of the auxiliary frame to the satellite compartment plate. The lower boss plate (30501) of the auxiliary frame is provided with a lower boss horizontal fixing plate (30503) at both the upper and lower ends. The lower boss horizontal fixing plate (30503) is arranged horizontally and is a right triangle. One right-angled side of the lower boss horizontal fixing plate (30503) is fixedly connected to the longitudinal rear end face of the lower boss plate (30501) of the auxiliary frame, and the other right-angled side of the lower boss horizontal fixing plate (30503) is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate (303). The lower boss plate (30501) of the auxiliary frame is also provided with a lower boss vertical fixing plate (30504). The lower boss vertical fixing plate (30504) is arranged vertically and is shaped as a right triangle. One right-angled side of the lower boss vertical fixing plate (30504) is fixedly connected to the lower boss plate (30501) of the auxiliary frame, and the other right-angled side of the lower boss vertical fixing plate (30504) is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate (303).

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