Composite supporting device applied to inter-satellite laser communication terminal

Abstract

The invention provides a composite supporting device applied to an inter-satellite laser communication terminal, which comprises three central main supporting frames, and the three central main supporting frames are arranged in an isosceles triangle shape and are fixedly mounted on the top end surface of a main structure; the vertical central axis of the first central main supporting frame, the vertical central axis of the second central main supporting frame and the vertical central axis of the third central main supporting frame are all located in the same vertical plane. The vertical central axis of the first central main supporting frame coincides with the vertical central axis of the longitudinal front end face of the main structure. The device further comprises two auxiliary side supporting frames which are symmetrically and fixedly installed on the left end face and the right end face of the main structure respectively. The flexible joints arranged on the center main supporting frame of the device absorb small deformation of a mounting area; the auxiliary side supporting frames are located on the two sides of the main structure, and the flexible joints and the flexible grooves arranged on the auxiliary side supporting frames can absorb large deformation and isolate external thermal deformation caused by environment temperature changes.

Description

Technical Field

[0001] The present invention belongs to the technical field of laser communication, relates to a laser communication terminal, and specifically relates to a composite supporting device applied to an inter-satellite laser communication terminal. Background Art

[0002] Satellite laser communication technology uses laser as an information carrier, which has the characteristics of high bandwidth, small size, low power consumption and good confidentiality. It is an effective means to achieve high-speed satellite communication. The intersatellite laser communication terminal includes an optical head and a control unit. Among them, the optical head is the core part of the entire intersatellite laser communication terminal, responsible for completing the functions of beam transmission and reception, shaping and space pointing.

[0003] The optical head includes the main structure, transceiver channel, coarse pointing mechanism and telescope. The transceiver channel is usually installed in the main structure. As the core module of the intersatellite laser communication terminal, the transceiver channel directly affects the transceiver performance of the entire laser communication system. The intersatellite laser communication terminal will be affected by the complex external environment during the launch phase and the on-orbit operation phase, including launch vibration, gravity release and temperature changes. These changes will cause the relative positions of the optical elements inside the transceiver channel to change, affecting the consistency of the optical axis of the transceiver signal light, thereby reducing the tracking efficiency and communication quality of the intersatellite laser communication terminal. In addition, the complex environment of the intersatellite laser communication terminal during launch, orbit entry and space operation requires that the support structure of the intersatellite laser communication terminal has good structural stability and stress unloading capabilities. Summary of the invention

[0004] In view of the deficiencies in the prior art, the purpose of the present invention is to provide a composite support device for an intersatellite laser communication terminal, so as to solve the technical problem in the prior art that the optical axis consistency of the intersatellite laser communication terminal transmitting and receiving light under a complex temperature change environment needs to be further improved.

[0005] In order to solve the above technical problems, the present invention adopts the following technical solutions to achieve the above problems:

[0006] A composite support device applied to an intersatellite laser communication terminal comprises three central main support frames, wherein a first central main support frame is fixedly mounted on the top end surface of a main structure, and a second central main support frame and a third central main support frame are fixedly mounted on the bottom end surface of the 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 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 end surface of the main structure, and the vertical central axis of the second central main support frame and the vertical central axis of the third central main support frame are symmetrically arranged with the vertical central axis of the first central main support frame as the axis of symmetry.

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

[0008] The central main support frame includes a transversely arranged main frame fixing plate, the main frame fixing plate is fixedly connected to the main structure, the longitudinal front end of the main frame fixing plate is embedded and fixedly connected with a main frame left flexible section, the main frame left flexible section is vertically arranged on the main frame fixing plate, the longitudinal front end of the main frame fixing plate is embedded and fixedly connected with a main frame right flexible section, the main frame right flexible section is vertically arranged on the main frame fixing plate, the main frame left flexible section and the main frame right flexible section are symmetrically arranged with the vertical center axis of the first central main support frame as the symmetry axis.

[0009] A main frame mounting boss is fixedly connected between the left flexible section of the main frame and the right flexible section of the main frame. The main frame mounting boss is arranged vertically. The longitudinal front end surface 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, and a rectangular main frame mounting hole is arranged 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, and a main frame left flexible section is arranged inside the main frame mounting hole. One transverse side of the main frame left flexible section is fixedly connected to the main frame fixing plate, and the other transverse side of the main frame left flexible section is fixedly connected to one transverse side of the main frame mounting boss.

[0012] A main frame right flexible section is also provided inside the main frame mounting hole, one lateral side of the main frame right flexible section is fixedly connected to the other lateral side of the main frame mounting boss, and the other lateral side of the main frame right flexible section is fixedly connected to the main frame fixing plate.

[0013] Specifically, the main frame fixing plate is provided with three vertically penetrating main frame fixing screw holes, the three main frame fixing screw holes penetrate the main frame fixing plate, and the three main frame fixing screw holes are evenly arranged along the arc line; the main frame fixing plate and the main structure are fixedly connected by the main frame fixing screws installed in the main frame fixing screw holes.

[0014] A main frame U-shaped flexible groove is also arranged around the outer surface of the main frame fixing screw hole arranged at the middle position of the arc line, and the opening of the main frame U-shaped flexible groove faces backwards.

[0015] The main frame fixing plate is also provided with a main frame through hole in the shape of a rounded rectangle. The main frame through hole vertically penetrates the main frame fixing plate. The main frame through hole is located at the horizontal 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 in a U-shape with the opening facing inwards.

[0017] A main frame satellite mounting screw hole which runs longitudinally through the central position of the main frame mounting boss is also provided, and the main frame mounting boss and the satellite cabin 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, the auxiliary frame long strip fixing plate is connected to the auxiliary frame mounting boss connecting plate through a long strip flexible section, and the long strip flexible section is arranged along the longitudinal direction.

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

[0020] Specifically, the auxiliary frame long strip fixing plate is provided with four transversely penetrating long strip fixing screw holes, and the four long strip fixing screw holes are evenly arranged vertically; the auxiliary frame long strip fixing plate and the main structure are fixedly connected by long strip fixing screws installed in the long strip fixing screw holes.

[0021] A rectangular narrow strip flexible section with rounded corners at both ends is arranged on the auxiliary frame long strip fixing plates on both sides of the two vertical middle long strip fixing screw holes, and the longitudinal rear end of the narrow strip flexible section is flush with the longitudinal rear end of the auxiliary frame long strip fixing plate; the narrow strip flexible section extends longitudinally into the auxiliary frame mounting boss connecting plate, and the longitudinal front end of the narrow strip 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 fixed plate is provided with two long plate U-shaped flexible grooves, which are arranged in mirror symmetry; the two long plate U-shaped flexible grooves correspond to the two long plate fixing screw holes located vertically above and below.

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

[0024] Specifically, two auxiliary frame boss connecting plate fixing screw holes are symmetrically arranged in the vertical middle of the auxiliary frame mounting boss connecting plate, the two auxiliary frame boss connecting plate fixing screw holes are located between two narrow flexible joints, and the two auxiliary frame boss connecting plate fixing screw holes penetrate the auxiliary frame mounting boss connecting plate horizontally; the auxiliary frame mounting boss connecting plate is fixedly connected to the main structure by means of auxiliary frame boss connecting plate fixing screws installed in the auxiliary frame boss connecting plate 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 backwards, 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, the connecting plate fixing boss is in contact with the main structure, and the auxiliary frame boss connecting plate fixing screw hole penetrates the connecting plate fixing boss.

[0027] Specifically, the auxiliary frame upper mounting boss includes a vertically arranged auxiliary frame upper boss plate, the auxiliary frame upper boss plate is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate, and the longitudinal front end surface of the auxiliary frame upper boss plate is also in contact with the satellite cabin plate.

[0028] An upper boss plate satellite connection screw hole is also provided at the central position of the upper boss plate of the auxiliary frame, and the upper boss plate satellite connection screw hole 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 fixes the mounting boss on the auxiliary frame and the satellite cabin plate.

[0029] The upper and lower ends of the auxiliary frame upper boss plate are provided with upper boss transverse fixing plates, which are arranged horizontally and are in the shape of a right-angled triangle. One right-angled side of the upper boss transverse fixing plate is fixedly connected to the longitudinal rear end face of the auxiliary frame upper boss plate, 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] An upper boss vertical fixing plate is also provided on the upper boss plate of the auxiliary frame. The upper boss vertical fixing plate is arranged vertically. The shape of the upper boss plate of the auxiliary frame is a right-angled 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 surface of the auxiliary frame lower boss plate is also in contact with the satellite cabin plate.

[0032] A lower boss plate satellite connection screw hole is also provided at the central position on the lower boss plate of the auxiliary frame, and the lower boss plate satellite connection screw hole passes through the front and rear ends of the lower boss plate of the auxiliary frame; the lower mounting boss of the auxiliary frame and the satellite cabin plate are fixedly connected by the lower boss plate satellite connection screw installed in the lower boss plate satellite connection screw hole.

[0033] The upper and lower ends of the auxiliary frame lower boss plate are provided with lower boss transverse fixing plates, which are arranged horizontally and are in the shape of a right-angled triangle. One right-angled side of the lower boss transverse 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 transverse fixing plate is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate.

[0034] A lower boss vertical fixing plate is also provided on the lower boss plate of the auxiliary frame. The lower boss vertical fixing plate is arranged vertically and has a shape of a right-angled 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 of the present invention adopts a central main support frame distributed in an isosceles triangle to ensure the main support stiffness of the main structure in the intersatellite laser communication terminal. The flexible nodes arranged on the central main support frame absorb the smaller deformation of the installation area; the auxiliary side support frames are located on both sides of the main structure. The flexible nodes and flexible grooves arranged on the auxiliary side support frames can absorb larger deformation and isolate the thermal deformation introduced by the external environment due to changes in ambient temperature.

[0037] (II) The device of the present invention is composed of a central main support frame and an auxiliary side support frame. While ensuring the support stiffness, the flexible nodes arranged on the support structure absorb the thermal deformation caused by the mismatch between the intersatellite laser communication terminal and the satellite cabin plate due to the material or temperature mismatch, so that the intersatellite laser communication terminal has high temperature adaptability, compact structure, easy installation and strong versatility.

[0038] (III) The device of the present invention uses high-strength and high-toughness titanium alloy metal material as the material of the support frame, which ensures a large-scale vibration strength safety margin during the launch phase while avoiding the occurrence of 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 intersatellite laser communication terminal and the satellite cabin plate, reducing the impact on the temperature uniformity of the intersatellite laser communication terminal.

[0039] (IV) The device of the present invention adopts a split design, which is easy to process and convenient to install and debug.

[0040] Figure 1 The figure is a schematic diagram of the installation structure of the composite support device in the present invention in the intersatellite laser communication terminal.

[0041] FIG. 2( a ) is a schematic structural diagram of the central main support frame of the present invention.

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

[0043] FIG. 3( a ) is a schematic structural diagram of the auxiliary side support frame in the present invention.

[0044] FIG. 3( b ) is a left side view of FIG. 3( a ).

[0045] Figure 4 The first-order modal vibration diagram of the intersatellite laser communication terminal using the composite support device of the present invention.

[0046] Figure 5 The main structure of the intersatellite laser communication terminal using the composite support device of the present invention is deformed under wide temperature changes.

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

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

[0049] Figure 7 It is a displacement cloud diagram of the central main support frame in the present invention due to thermal deformation of the satellite cabin plate.

[0050] Figure 8 It is a displacement cloud diagram of the auxiliary side support frame in the present invention due to thermal deformation of the satellite cabin plate.

[0051] The meanings of the numbers in the figure are: 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 fixed plate, 302-long flexible joint, 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-strip board fixing screw hole, 30102-narrow strip flexible section, 30103-strip board U-shaped flexible groove, 30104-strip board fixing boss.

[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 holes of upper boss plate, 30403-upper boss horizontal fixing plate, 30404-upper boss vertical fixing plate.

[0058] 30501-auxiliary frame lower boss plate, 30502-lower boss plate satellite connection screw holes, 30503-lower boss horizontal fixing plate, 30504-lower boss vertical fixing plate.

[0059] The specific contents of the present invention are further described in detail below in conjunction with the accompanying drawings and embodiments. DETAILED DESCRIPTION

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

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

[0062] In the present invention, the coordinate system OXYZ coordinate system 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 to the front; and the Z axis is vertical and points to the top.

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

[0064] In accordance with the above technical scheme, 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 changes made on the basis of the technical scheme of this application fall within the protection scope of the present invention.

[0065] Example:

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

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

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

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

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

[0071] In this embodiment, the central main support frame 1 is used to provide the main support stiffness, and the flexible joints arranged on the central main support frame 1 can absorb the small thermal deformation of the small area. The auxiliary side support frame 3 is located on the left and right sides of the front end surface of the main structure in the intersatellite laser communication terminal. Since the lateral thermal deformation of the intersatellite laser communication terminal is large, the flexible joints and flexible grooves arranged on the auxiliary side support frame 3 can absorb the large lateral thermal deformation.

[0072] As a preferred solution of this embodiment, as shown in Figure 2(a), the main frame fixing plate 101 is an arc-shaped plate, and a rectangular main frame mounting hole 105 is arranged 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, and a main frame left flexible section 102 is arranged 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] A main frame right flexible section 103 is also provided inside the main frame mounting hole 105 , one lateral side of the main frame right flexible section 103 is fixedly connected to the other lateral side of the main frame mounting boss 104 , and the other lateral side of the main frame right flexible section 103 is fixedly connected to the main frame fixing plate 101 .

[0074] As a preferred solution of this embodiment, as shown in Figure 2(a), three vertically penetrating main frame fixing screw holes 10101 are provided on the main frame fixing plate 101, and the three main frame fixing screw holes 10101 penetrate the main frame fixing plate 101, and the three main frame fixing screw holes 10101 are evenly arranged 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.

[0075] As shown in FIG. 2( a ), a main frame U-shaped flexible groove 10102 is also provided around the outer surface of the main frame fixing screw hole 10101 provided along the middle position of the arc line, and the opening of the main frame U-shaped flexible groove 10102 faces backwards.

[0076] As shown in Figure 2(b), a main frame through hole 10103 in the shape of a rounded rectangle is also provided on the main frame fixing plate 101. The main frame through hole 10103 vertically penetrates the main frame fixing plate 101. The main frame through hole 10103 is located at the lateral 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 ends 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 solution of this embodiment, as shown in FIG. 2( a ), the main frame mounting boss 104 is in a U-shape with the opening facing inward.

[0078] A main frame satellite mounting screw hole 106 which runs longitudinally through the main frame mounting boss 104 is also provided at the center position thereof. The main frame satellite mounting screw hole 106 is used to fix the main frame mounting boss 104 and the satellite cabin panel.

[0079] As a preferred solution of this embodiment, as shown in Figure 3(a), the auxiliary side support frame 3 includes a vertically arranged auxiliary frame long strip fixing plate 301, and 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, and the long strip flexible section 302 is arranged along the longitudinal direction.

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

[0081] As a preferred solution of this embodiment, as shown in Figure 3(a), four transversely penetrating long plate fixing screw holes 30101 are provided on the auxiliary frame long plate fixing plate 301, and the four long plate fixing screw holes 30101 are evenly arranged in the vertical direction; the auxiliary frame long plate fixing plate 301 is fixedly connected to the main structure 2 by the long plate fixing screws installed in the long plate fixing screw holes 30101.

[0082] As shown in Figure 3(a), a rectangular narrow strip flexible section 30102 with rounded corners at both ends is provided on the auxiliary frame long strip fixing plate 301 on both sides of the two vertical middle long strip fixing screw holes 30101, and the longitudinal rear end of the narrow strip 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 strip flexible section 30102 extends into the auxiliary frame mounting boss connecting plate 303, and the longitudinal front end of the narrow strip 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), the outer surface of the auxiliary frame long fixed plate 301 is provided with two long plate U-shaped flexible grooves 30103, and the two long plate U-shaped flexible grooves 30103 are arranged in mirror symmetry; the two long plate U-shaped flexible grooves 30103 correspond to the two long plate fixing screw holes 30101 located vertically above and below.

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

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

[0086] As a preferred solution of this embodiment, as shown in Figure 3(a), two auxiliary frame boss connecting plate fixing screw holes 30301 are symmetrically arranged in the vertical middle of the auxiliary frame mounting boss connecting plate 303, and the two auxiliary frame boss connecting plate fixing screw holes 30301 are located between the two narrow strip flexible joints 30102. The two auxiliary frame boss connecting plate fixing screw holes 30301 horizontally penetrate the auxiliary frame mounting boss connecting plate 303; 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 FIG. 3( a ), the outer surface of the auxiliary frame mounting boss connecting plate 303 is further provided with two connecting plate U-shaped flexible grooves 30302 , the openings of the two connecting plate U-shaped flexible grooves 30302 are 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;

[0088] As shown in FIG. 3( b ), the inner surface of the auxiliary frame mounting boss connecting plate 303 is further 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 .

[0089] In this embodiment, the long flexible joint 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 joint 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 solution of this embodiment, as shown in Figure 3(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 surface of the auxiliary frame upper boss plate 30401 is also in contact with the satellite cabin plate.

[0091] As shown in Figure 3(a), an upper boss plate satellite connection screw hole 30402 is also provided at the center position on the upper boss plate 30401 of the auxiliary frame, and 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 fixes the auxiliary frame mounting boss 304 and the satellite cabin plate.

[0092] As shown in Figure 3(a), upper boss transverse fixing plates 30403 are provided at the upper and lower ends of the auxiliary frame upper boss plate 30401. The upper boss transverse fixing plates 30403 are arranged horizontally, and the shape of the upper boss transverse fixing plates 30403 is a right-angled 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, 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 auxiliary frame upper boss plate 30401. The upper boss vertical fixing plate 30404 is arranged vertically. The auxiliary frame upper boss plate 30401 is in the shape of 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.

[0094] As a preferred solution of this embodiment, as shown in Figure 3(a), the auxiliary frame lower mounting boss 305 includes a vertically arranged auxiliary frame lower boss plate 30501, and 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 surface 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 lower boss plate satellite connection screw hole 30502 is also provided at the center position on the lower boss plate 30501 of the auxiliary frame, and the lower boss plate satellite connection screw hole 30502 passes through the front and rear ends of the lower boss plate 30501 of the auxiliary frame; the lower mounting boss 305 of the auxiliary frame and the satellite cabin plate are fixedly connected by the lower boss plate satellite connection screw installed in the lower boss plate satellite connection screw hole 30502.

[0096] As shown in Figure 3(a), lower boss transverse fixing plates 30503 are provided at the upper and lower ends of the auxiliary frame lower boss plate 30501. The lower boss transverse fixing plates 30503 are arranged horizontally, and the shape of the lower boss transverse fixing plates 30503 is a right-angled 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 auxiliary frame lower boss plate 30501. The lower boss vertical fixing plate 30504 is arranged vertically, and the shape of the lower boss vertical fixing plate 30504 is a right-angled triangle. One right-angled side of the lower boss vertical fixing plate 30504 is fixedly connected to the auxiliary frame lower boss plate 30501, 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 first-order modal vibration shape diagram of the intersatellite laser communication terminal using the composite support device of the present invention hides the coarse pointing mechanism 4 and the telescope 5. From the simulation results, it can be seen that the first-order frequency of the optical head using the present invention is higher than the common satellite main frequency, which means that the device of the present invention can provide higher support structure stiffness and ensure the structural stability of the optical head.

[0099] Figure 5 The deformation of the main structure of the intersatellite laser communication terminal using the composite support device of the present invention under wide temperature changes is Figure 5 It can be seen that when the optical head is deformed by 0.05 mm due to temperature change at the installation footprint of the satellite cabin panel, the relative deformation of the main structure 2 itself is less than 0.005 mm, which means that the present invention can effectively isolate the thermal deformation of the satellite cabin panel 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 thermal deformation of satellite cabin panels under high temperature conditions, where the space environment temperature rises by ΔT (ΔT is greater than 10°C). As shown in Figure 6(a), when the temperature rises by ΔT, the satellite cabin panels usually have a higher temperature, which will cause deformations of Δu0 to Δu3 at the optical head installation footprint (Δu0 and Δu3 are the deformations of the satellite cabin panels at the installation of the central main support frame 1, and Δu1 and Δu2 are the deformations of the satellite cabin panels at the installation of the auxiliary side support frame 3).

[0101] Figure 6(b) is a schematic diagram of the thermal deformation of the satellite cabin panel under low temperature conditions, where the space environment temperature drops by ΔT (ΔT is greater than 10°C). As shown in Figure 6(b), when the temperature rises by ΔT, the satellite cabin panel usually has a higher temperature, which will cause deformations of Δu0 to Δu3 at the optical head installation footprint (Δu0 and Δu3 are the deformations of the satellite cabin panel at the installation of the central main support frame 1, and Δu1 and Δu2 are the deformations of the satellite cabin panel at the installation of the auxiliary side support frame 3).

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

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

Claims

1. A composite support device for an intersatellite laser communication terminal, characterized in that: The invention comprises three central main support frames (1), wherein the first central main support frame (1) is fixedly mounted on the top end surface of the main structure (2), and the second central main support frame (1) and the third central main support frame (1) are fixedly mounted on the bottom end 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 surface of the main structure (2), and 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 symmetry axis; It also includes two auxiliary side support frames (3), which are symmetrically fixedly mounted on the left end surface and the right end surface of the main structure (2); The central main support frame (1) comprises a main frame fixing plate (101) arranged transversely, the main frame fixing plate (101) is fixedly connected to the main structure (2), the longitudinal front end of the main frame fixing plate (101) is embedded and fixedly connected with a main frame left flexible section (102), the main frame left flexible section (102) 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 with a main frame right flexible section (103), the main frame right flexible section (103) is arranged vertically on the main frame fixing plate (101), the main frame left flexible section (102) and the main frame right flexible section (103) are symmetrically arranged with the vertical central axis of the first central main support frame (1) as the symmetry axis; A main frame mounting boss (104) is fixedly connected between the main frame left flexible section (102) and the main frame right flexible section (103). The main frame mounting boss (104) is arranged vertically. The longitudinal front end surface of the main frame mounting boss (104) contacts the satellite cabin panel. The main frame mounting boss (104) is used to connect with the satellite cabin panel.

2. The composite support device for intersatellite laser communication terminal according to claim 1, characterized in that: The main frame fixing plate (101) is an arc-shaped plate, and a rectangular main frame mounting hole (105) is arranged 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), and a main frame left flexible section (102) is arranged 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) in the transverse direction. A main frame right flexible section (103) is also provided inside the main frame mounting hole (105), one lateral side of the main frame right flexible section (103) is fixedly connected to the other lateral side of the main frame mounting boss (104), and the other lateral 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 intersatellite laser communication terminal according to 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 the three main frame fixing screw holes (10101) are evenly arranged 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); A main frame U-shaped flexible groove (10102) is also provided around the outer surface of the main frame fixing screw hole (10101) provided along the middle position of the arc line, and the opening of the main frame U-shaped flexible groove (10102) faces backwards; The main frame fixing plate (101) is also provided with a main frame through hole (10103) in the shape of a rounded rectangle. The main frame through hole (10103) vertically penetrates the main frame fixing plate (101). The main frame through hole (10103) is located at the lateral 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 ends of the main frame left flexible section (102), the main frame right flexible section (103) and the main frame mounting boss (104).

4. The composite support device for intersatellite laser communication terminal according to claim 1, characterized in that: The main frame mounting boss (104) is in the shape of a U with the opening facing inwards; A main frame satellite mounting screw hole (106) which runs longitudinally through the center of the main frame mounting boss (104) is also provided, and the main frame mounting boss (104) and the satellite cabin plate are fixedly connected by the main frame satellite mounting screw installed in the main frame satellite mounting screw hole (106).

5. The composite support device for intersatellite laser communication terminal according to claim 1, characterized in that: The auxiliary side support frame (3) comprises an auxiliary frame long strip fixing plate (301) arranged vertically, the auxiliary frame long strip fixing plate (301) is connected to the auxiliary frame mounting boss connecting plate (303) via 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 auxiliary frame upper mounting boss (304) is located vertically above the auxiliary frame lower mounting boss (305); the auxiliary frame upper mounting boss (304) and the auxiliary frame lower mounting boss (305) are vertically symmetrical; the auxiliary frame upper mounting boss (304) and the auxiliary frame lower mounting boss (305) are used to be connected to the satellite cabin panel.

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

7. The composite support device for intersatellite laser communication terminal according to 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 of the auxiliary frame mounting boss connecting plate (303), the two auxiliary frame boss connecting plate fixing screw holes (30301) are located between the two narrow strip flexible joints (30102), and the two auxiliary frame boss connecting plate fixing screw holes (30301) penetrate the auxiliary frame mounting boss connecting plate (303) horizontally; 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); 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) are 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 intersatellite laser communication terminal according to claim 5, characterized in that: The auxiliary frame upper mounting boss (304) comprises an auxiliary frame upper boss plate (30401) arranged vertically, 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 surface of the auxiliary frame upper boss plate (30401) is also in contact with the satellite cabin plate; The center position of the auxiliary frame upper boss plate (30401) is also provided with an upper boss plate satellite connection screw hole (30402), and the upper boss plate satellite connection screw hole (30402) runs through the front and rear ends of the auxiliary frame upper boss plate (30401); the upper boss plate satellite connection screw installed in the upper boss plate satellite connection screw hole (30402) fixes the auxiliary frame upper mounting boss (304) and the satellite cabin plate; The upper and lower ends of the auxiliary frame upper boss plate (30401) are both provided with upper boss transverse fixing plates (30403), the upper boss transverse fixing plates (30403) are arranged in the transverse direction, and the shape of the upper boss transverse fixing plates (30403) is a right triangle, one right-angled side of the upper boss transverse fixing plates (30403) is fixedly connected to the longitudinal rear end face of the auxiliary frame upper boss plate (30401), and the other right-angled side of the upper boss transverse fixing plates (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), which is arranged vertically. The auxiliary frame upper boss plate (30401) is in the shape of 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 intersatellite laser communication terminal according to claim 5, characterized in that: The auxiliary frame lower mounting boss (305) comprises an auxiliary frame lower boss plate (30501) arranged vertically, 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 surface of the auxiliary frame lower boss plate (30501) is also in contact with the satellite cabin plate; A lower boss plate satellite connection screw hole (30502) is also provided at the center position of the lower boss plate (30501) of the auxiliary frame. The lower boss plate satellite connection screw hole (30502) passes through the front and rear ends of the lower boss plate (30501) of the auxiliary frame. The lower boss plate satellite connection screw installed in the lower boss plate satellite connection screw hole (30502) fixes the auxiliary frame lower mounting boss (305) and the satellite cabin plate. The lower and upper ends of the auxiliary frame lower boss plate (30501) are both provided with lower boss transverse fixing plates (30503), the lower boss transverse fixing plates (30503) are arranged in the transverse direction, and the shape of the lower boss transverse fixing plates (30503) is a right-angled triangle, one right-angled side of the lower boss transverse fixing plates (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 plates (30503) is fixedly connected to the outer surface of the auxiliary frame mounting boss connecting plate (303); The auxiliary frame lower boss plate (30501) is also provided with a lower boss vertical fixing plate (30504), which is arranged vertically and has a right triangle shape. One right-angled side of the lower boss vertical fixing plate (30504) is fixedly connected to the auxiliary frame lower boss plate (30501), 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).

Images