Variable satellite connection frame damping device

Abstract

This invention discloses a variable satellite connector shock absorption device, belonging to the field of aerospace technology. It includes a fixed outer ring, a middle shock absorption layer, an upper connector, a lower connector, variable support rods, and a bottom fixed washer. The fixed outer ring and the middle shock absorption layer employ a layered inlay design with interlocking contact surfaces. The upper and lower ends of the middle shock absorption layer are connected to the upper and lower connectors, respectively. The outer ends of both the upper and lower connectors are connected to the satellite. The middle shock absorption layer is filled with elastic material and uses a sponge-like loose porous structure design, which can provide cushioning and shock absorption during normal satellite operation. Variable support rods are axially evenly distributed between the fixed outer ring and the upper and lower connectors. The outer ends of the variable support rods are fixed to the fixed outer ring, and their inner sides abut against the upper and lower connectors. The variable support rods are made of shape memory alloy or low-melting-point polymer, which can change stiffness to achieve both fixing and shock absorption functions.

Description

Technical Field

[0001] This invention belongs to the field of aerospace technology, specifically relating to a variable satellite connector shock absorption device. Background Technology

[0002] Modern small satellites, characterized by low cost, powerful functionality, and easy assembly, have become an indispensable part of modern aerospace technology, playing a crucial role in atmospheric detection, communication, academic research, and space exploration. The satellite connector frame, acting as the "skeleton" and "spine" of the satellite, primarily bears and transmits payloads and connects various satellite subsystems. It connects to the launch vehicle via a satellite adapter interface. Currently, the main satellite connector frame structures used in various applications include skin-reinforced structures, biomimetic honeycomb sandwich structures, and truss structures. These structures, while ensuring the overall rigidity of the connector frame, achieve lightweighting through layering, perforation, and frame support. Regarding materials, various high-performance composite materials have been developed, such as carbon fiber reinforced polymer (CFRP) and shape memory alloys, which provide excellent shock absorption and impact resistance, ensuring overall stability.

[0003] Currently, research on variable materials has matured and been applied. Shape memory alloys, as a new type of material, have adjustable phase transition temperatures, excellent mechanical properties, good biocompatibility, and wide environmental adaptability. They have become an important reference for material selection for multifunctional variable structures in industrial production. Low-melting-point polymers, as an easily processed organic non-metallic material, have low processing temperatures, good fluidity and wettability, and can quickly fill gaps in the molten state. They are often used for rapid encapsulation and tight connections. Their characteristics of melting and softening at high temperatures and solidifying and hardening at low temperatures are also widely used in industrial fields where the working environment is constantly changing.

[0004] In summary, this invention aims to combine variable materials with vibration reduction technology and apply them to traditional connecting frames to achieve a lightweight, low-cost, and multi-functional variable satellite connecting frame vibration reduction structure design. This device, applied to small satellite connecting frames, has two application functions depending on the working environment: solving the connection and fixation problem during satellite launch and the vibration reduction problem when the satellite is in orbit and subjected to external interference. It provides a new solution to the current challenge of unifying launch fixation and operational vibration reduction in satellite connecting frame design. Currently, satellite connecting frame design is mature both domestically and internationally, and research on variable materials has made significant progress in application. Variable satellite connecting frames still hold great potential in the future aerospace and precision instrument fields. Summary of the Invention

[0005] The purpose of this invention is to solve the problem of unifying launch fixation and operational vibration damping in current satellite mount designs, and to provide a variable satellite mount vibration damping device. This device addresses the connection and fixation issues during satellite launch and the vibration damping problems caused by external interference during satellite operation in orbit, while simultaneously reducing costs and expanding its application scope and fields.

[0006] A variable satellite connector shock absorption device includes: a fixed outer ring 1, a middle shock absorption layer 2, an upper connector 3, a lower connector 4, a variable support rod 5, and a bottom fixed washer 6;

[0007] The fixed outer ring 1 has a cylindrical structure and is composed of a symmetrical left end 101 and a right end 102 of the fixed outer ring.

[0008] Multiple fixed outer ring layered inlay bosses 106 are axially and equally spaced on the inner ring cylindrical surface of the fixed outer ring 1, with a sawtooth cross section.

[0009] The bottom of the inner cylindrical surface is evenly distributed with holes 104 at 60° intervals to fix the end face of the outer ring.

[0010] The inner ring cylindrical surface top of the fixed outer ring layered inlay boss 106 is evenly distributed with holes 103 at 120° intervals on the inner end face of the fixed outer ring.

[0011] The holes 104 at 60° intervals on the bottom surface of the fixed outer ring and the holes 103 at 120° intervals on the inner end face of the fixed outer ring are countersunk holes, and variable support rods 5 are fixedly connected inside them.

[0012] The intermediate damping layer 2 is composed of a symmetrical intermediate damping layer left end 201 and an intermediate damping layer right end 202;

[0013] The intermediate damping layer 2 has a columnar structure, with axially spaced, equally spaced intermediate damping layer inlaid protrusions 205 on its columnar surface, and the cross-section is sawtooth-shaped.

[0014] The sawtooth boss structure of the inner ring of the fixed outer ring 1 and the sawtooth boss structure of the outer ring of the intermediate damping layer 2 are connected in a cooperative manner.

[0015] The bottom of the intermediate damping layer 2 is evenly provided with 60° through holes 204 on the end face of the intermediate damping layer;

[0016] The intermediate damping layer 2 has 120° through holes 203 evenly distributed in the groove between the intermediate damping layer layer-shaped inlaid bosses 205 at the top of the intermediate damping layer 2.

[0017] The top and bottom of the inner side of the intermediate shock-absorbing layer 2 are connected to the upper connecting frame 3 and the lower connecting frame 4, respectively.

[0018] The intermediate damping layer 2 adopts a sponge-like loose porous structure;

[0019] The variable support rod 5 passes through the through hole 204 on the intermediate damping layer 2 and abuts against the outer wall of the upper connecting frame 3 and the lower connecting frame 4;

[0020] The variable support rod 5 can be heated to change from a rigid rod to a flexible rod.

[0021] The upper connecting frame 3 is composed of a stepped cylindrical frame 301, surface countersunk holes 302, stepped layered inlaid bosses 303, and surface machined holes 304 of the cylindrical frame.

[0022] The stepped cylindrical frame 301 is a multi-step cylindrical structure, and its upper bearing surface is provided with surface countersunk holes 302 to connect with the satellite part;

[0023] The stepped cylindrical frame 301 has multiple stepped layered inlaid bosses 303 axially and evenly fixed in the middle, and the cylindrical frame surface is provided with countersunk holes 304 evenly distributed around the circumference, which are used to connect with the inner end of the variable support rod 5.

[0024] It consists of a 403 surface and a 404 machined hole on the cylindrical sleeve surface;

[0025] The stepped cylindrical sleeve 402 is a multi-step cylindrical structure. Its lower end is provided with a lower surface 403 that connects to the satellite part, and its middle part is fixed with a lower connecting frame layered inlay boss 401.

[0026] The lower connecting frame has layered inlaid bosses 401 with countersunk cylindrical sleeve surface machining holes 404 evenly distributed on them.

[0027] The intermediate damping layer 2 is connected to the upper connecting frame 3 and the lower connecting frame 4 through a gradually changing cavity and a layered inlay structure. A solid layer is provided in the middle to separate the upper connecting frame 3 and the lower connecting frame 4.

[0028] The solid layer inside the intermediate shock-absorbing layer 2 is connected to the lower end of the upper connecting frame 3 and the upper end of the lower connecting frame 4, respectively, and the contact surface is provided with a cavity to unload stress.

[0029] The fixed outer ring 1 has holes 105 evenly distributed at 60° intervals on its bottom circumference, which cooperate with the evenly distributed 60° through holes 601 on the bottom fixed washer 6, and are positioned and fixed by positioning pins 602.

[0030] The bottom fixing washer 6 is a thin circular ring structure, and its outer diameter is equal to the outer diameter of the fixing outer ring 1; the inner diameter of the ring can limit the bottom end of the intermediate shock-absorbing layer 2.

[0031] The fixed outer ring 1 is columnar and is made of boron fiber reinforced aluminum matrix composite material Bf / Al, titanium alloy Ti-6Al-4V or copper-based alloy Cu-Al-Ni, which has high rigidity and high temperature resistance.

[0032] The variable support rod 5 comprises an inner ring fixing surface 501, an outer ring fixing surface 502, and a middle contact surface 503.

[0033] The inner ring fixing surface 501 contacts the countersunk hole on the outer ring of the upper connecting frame 3 and the lower connecting frame 4, the middle contact surface 503 cooperates with the through hole on the middle shock-absorbing layer 2, and the outer ring fixing surface 502 is fixed with the countersunk hole on the inner ring of the fixing outer ring 1.

[0034] The variable support rod 5 is made of shape memory alloy or low melting point polymer.

[0035] The main structure of this invention can be manufactured using 3D printing technology;

[0036] During installation, the variable support rod 5 is fixed to the inner end face of the fixed outer ring at a 120° interval hole 103 and the end face of the fixed outer ring at a 60° interval hole 104 on the left end 101 of the fixed outer ring.

[0037] The intermediate damping layer layer-shaped inlay protrusion 205 at the left end 201 of the intermediate damping layer is matched with the fixed outer ring layer-shaped inlay protrusion 106 of the fixed outer ring 1.

[0038] And it is fixed by connecting the intermediate contact surface 503 of the variable support rod 5 to the 120° through hole 203 on the inner end face of the intermediate damping layer and the 60° through hole 204 on the end face of the intermediate damping layer;

[0039] Then, the stepped cylindrical frame 301 of the upper connecting frame 3, the stepped layered inlay boss 303 and the lower connecting frame layered inlay boss 401 of the lower connecting frame 4 are respectively matched, and the lower connecting frame layered inlay boss 401 is connected to the internal cavity structure processed by the intermediate damping layer 2.

[0040] The inner ring fixing surface 501 of the variable support rod 5 is connected to the machined hole 304 on the cylindrical frame surface of the upper connecting frame 3 and the machined hole 404 on the cylindrical sleeve surface of the lower connecting frame 4 for fixation.

[0041] The right end 202 of the intermediate damping layer, the right end 102 of the fixed outer ring, and the remaining variable support rod 5 are connected in sequence, and the bottom fixing washer 6 is connected to the fixed outer ring 1 and the intermediate damping layer 2 respectively through the positioning pin 602 to realize the installation and fixation of the entire device.

[0042] A method for using a variable satellite connector shock absorber, employing the aforementioned variable satellite connector shock absorber, is as follows:

[0043] The device of this invention has two operating states: satellite launch and satellite in-orbit operation;

[0044] a. The variable support rod 5 is made of shape memory alloy: Ni-Ti-Hf high-temperature nickel-titanium alloy;

[0045] Step a1: Satellite launch

[0046] At room temperature, the variable support rod 5 is rigid and can be fixed by connecting it with the fixed outer ring 1, the intermediate damping layer 2, the upper connecting frame 3, and the lower connecting frame 4.

[0047] After the satellite is launched into space, the variable support rod 5 can be softened by heating and attached to the intermediate damping layer 2, thus losing its fixing function. The entire device is connected by the intermediate damping layer 2, which at this time plays the role of shock absorption and buffering.

[0048] b. The variable support rod 5 is made of a low-melting-point polymer: polyamide hot melt adhesive or polyurethane hot melt adhesive;

[0049] The variable support rod 5 has an internal metal wire 802 at its center. The internal metal wire 802 can be connected to the external circuit 801. The internal metal wire 802 is wrapped with a low melting point polymer material, which together constitutes the low melting point polymer component 8.

[0050] Step b1: Satellite launch

[0051] At room temperature, the low-melting-point polymer component 8 is rigid and can be fixed by connecting it with the fixed outer ring 1, the intermediate damping layer 2, the upper connecting frame 3, and the lower connecting frame 4.

[0052] Step b2: The satellite is operating normally in orbit.

[0053] After the satellite is launched into space, the internal metal wires 802 of the low-melting-point polymer component 8 can be heated by the external circuit 801 to soften them, so that they attach to the intermediate damping layer 2 and lose their fixing function. The entire device is connected by the intermediate damping layer 2, which can also play a role in shock absorption and buffering.

[0054] This invention provides a variable satellite connector shock absorption device, belonging to the field of aerospace technology. It includes a fixed outer ring, a middle shock absorption layer, an upper connector, a lower connector, variable support rods, and a bottom fixed washer. The fixed outer ring and the middle shock absorption layer employ a layered inlay design with interlocking contact surfaces. The upper and lower ends of the middle shock absorption layer are connected to the upper and lower connectors, respectively. The outer ends of both the upper and lower connectors are connected to the satellite. The middle shock absorption layer is filled with elastic material and uses a sponge-like loose porous structure design, which can provide cushioning and shock absorption during normal satellite operation. Variable support rods are axially evenly distributed between the fixed outer ring and the upper and lower connectors. The outer ends of the variable support rods are fixed to the fixed outer ring, and their inner sides abut against the upper and lower connectors. The variable support rods are made of shape memory alloy or low-melting-point polymer, which can change stiffness to achieve both fixing and shock absorption functions.

[0055] The beneficial effects and advantages of this invention compared with the prior art are as follows:

[0056] The variable support rod has two working states and material design schemes. When using a shape memory alloy (Ni-Ti-Hf high-temperature nickel-titanium alloy), it exhibits rigidity at room temperature (during satellite launch). The entire device can be fixed by connecting it to the outer ring, the middle damping layer, the upper connecting frame, and the lower connecting frame. After the satellite is launched into space, the variable support rod can be heated to restore its high-temperature soft state through the shape memory effect of the shape memory alloy. Alternatively, when using low-melting-point polymers (polyamide hot melt adhesive or polyurethane hot melt adhesive), the variable support rod has a metal wire at its center, wrapped with a low-melting-point polymer. After the satellite is launched into space, the internal metal wire of the variable support rod can be heated by an external circuit to soften it, causing it to adhere to the middle damping layer and lose its fixing function. The entire device relies on the middle damping layer for connection, and in this case, it mainly serves as a shock absorber. Attached Figure Description

[0057] Figure 1 This is a schematic diagram of the overall structure of a variable satellite connector shock absorption device according to the present invention. Figure 1 (a) is a schematic diagram of the device's appearance. Figure 1 (b) is a bottom view of the device. Figure 1 (c) is a cross-sectional view of the apparatus;

[0058] Figure 2 A schematic diagram of the specific structure of the fixed outer ring. Figure 2 (a) is a schematic diagram of the overall structure of the fixed outer ring. Figure 2 (b) is a fixed outer ring bottom view. Figure 2 (c) is a sectional view of the internal structure of the fixed outer ring;

[0059] Figure 3 This is a schematic diagram of the specific structure of the intermediate damping layer. Figure 3(a) is a schematic diagram of the overall structure of the intermediate damping layer. Figure 3 (b) is a cross-sectional view of the internal structure of the intermediate damping layer. Figure 3 (c) is a sectional view of the 120° through-hole on the inner end face of the intermediate damping layer. Figure 3 (d) is a sectional view of the 60° through hole at the end face of the intermediate damping layer;

[0060] Figure 4 This is a schematic diagram of the specific structure of the upper connecting frame. Figure 4 (a) is a schematic diagram of the three-dimensional structure of the upper connecting frame. Figure 4 (b) is a sectional view of the internal structure of the upper connecting frame. Figure 4 (c) is a planar sectional view of the surface-machined hole;

[0061] Figure 5 This is a schematic diagram of the specific structure of the lower connecting frame. Figure 5 (a) is a schematic diagram of the three-dimensional structure of the lower connecting frame. Figure 5 (b) is a sectional view of the lower connecting frame;

[0062] Figure 6 This is a schematic diagram of a variable support rod structure;

[0063] Figure 7 This is a schematic diagram of the bottom fixing washer structure. Figure 7 (a) is a schematic diagram of the end face of the bottom fixing washer. Figure 7 (b) is a schematic diagram of the locating pin;

[0064] Figure 8 This is a schematic diagram of a low-melting-point polymer scheme. Figure 8 (a) is a full sectional view of the device, and (b) is a schematic diagram of the variable support rod.

[0065] In the attached diagram:

[0066] 1. Fixed outer ring; 2. Middle damping layer; 3. Upper connecting frame; 4. Lower connecting frame; 5. Variable support rod; 6. Bottom fixing washer;

[0067] 101. Fix the left end of the outer ring; 102. Fix the right end of the outer ring; 103. Fix the holes at 120° intervals on the inner end face of the outer ring; 104. Fix the holes at 60° intervals on the end face of the outer ring; 105. Fix the holes at 60° intervals on the bottom surface of the outer ring; 106. Fix the layered inlay bosses on the outer ring;

[0068] 201. Left end of the intermediate damping layer; 202. Right end of the intermediate damping layer; 203. 120° through hole on the inner end face of the intermediate damping layer; 204. 60° through hole on the end face of the intermediate damping layer; 205. Layered inlaid bosses in the intermediate damping layer;

[0069] 301. Stepped cylindrical support; 302. Countersunk hole; 303. Stepped layered inlaid boss; 304. Machined holes on the surface of the cylindrical support;

[0070] 401. Layered inlaid boss of lower connecting frame; 402. Stepped cylindrical sleeve; 403. Lower surface; 404. Machined holes on the surface of cylindrical sleeve;

[0071] 501. Inner ring fixing surface; 502. Outer ring fixing surface; 503. Intermediate contact surface;

[0072] 601. Uniformly distributed 60° through holes; 602. Locating pins;

[0073] 8. Low melting point polymer components; 801. External circuitry; 802. Internal metal wires. Detailed Implementation

[0074] To make the technical solution, objectives and advantages of the present invention clearer, the implementation process of the present invention will be clearly and completely described below in conjunction with specific embodiments.

[0075] Example 1:

[0076] A variable satellite connector shock absorption device includes: a fixed outer ring 1, a middle shock absorption layer 2, an upper connector 3, a lower connector 4, a variable support rod 5, and a bottom fixed washer 6;

[0077] The fixed outer ring 1 is composed of a left end 101 and a right end 102 of the fixed outer ring;

[0078] The left end 101 and the right end 102 of the fixed outer ring are symmetrically distributed in the center. Five fixed outer ring layered inlay bosses 106 are axially and equally spaced on the inner ring cylindrical surface of the two, and the cross section is sawtooth-shaped.

[0079] The bottom of the inner cylindrical surface is evenly distributed with holes 104 at 60° intervals to fix the end face of the outer ring, with a total of 6 holes in one layer;

[0080] The inner cylindrical surface of the inner ring has two fixed outer ring layered inlay bosses 106, which are evenly distributed with holes 103 at 120° intervals on the inner end face of the outer ring, with three holes in each layer for a total of two layers.

[0081] The holes 104 at 60° intervals on the bottom surface of the fixed outer ring and the holes 103 at 120° intervals on the inner end face of the fixed outer ring are countersunk holes, and variable support rods 5 are fixedly connected inside them.

[0082] The intermediate damping layer 2 is composed of a symmetrical intermediate damping layer left end 201 and an intermediate damping layer right end 202;

[0083] The intermediate damping layer 2 has a columnar structure, with axially spaced, equally spaced intermediate damping layer inlaid protrusions 205 on its columnar surface, and the cross-section is sawtooth-shaped.

[0084] The sawtooth boss structure of the inner ring of the fixed outer ring 1 and the sawtooth boss structure of the outer ring of the intermediate damping layer 2 are connected to each other.

[0085] The bottom of the intermediate damping layer 2 is evenly distributed with 60° through holes 204 on the end face of the intermediate damping layer, with a total of 6 holes in one layer;

[0086] The intermediate damping layer 2 has three through holes 203 at 120° angle on the inner end face of the intermediate damping layer 2, with three holes per layer and two layers in total.

[0087] The top and bottom of the inner side of the intermediate shock-absorbing layer 2 are connected to the upper connecting frame 3 and the lower connecting frame 4, respectively.

[0088] The intermediate damping layer 2 is made of vulcanized silicone rubber RTV, fluorosilicone rubber or foamed silicone rubber, and has a sponge-like loose porous structure.

[0089] The variable support rod 5 passes through the 60° through hole 204 on the end face of the intermediate damping layer 2 and the 120° through hole 203 on the inner end face of the intermediate damping layer 2, and abuts against the outer wall of the upper connecting frame 3 and the lower connecting frame 4.

[0090] The variable support rod 5 can be heated to change from a rigid rod to a flexible rod.

[0091] The upper connecting frame 3 is composed of a stepped cylindrical frame 301, surface countersunk holes 302, stepped layered inlaid bosses 303, and surface machined holes 304 of the cylindrical frame.

[0092] The stepped cylindrical frame 301 is a multi-step cylindrical structure, and its upper bearing surface is provided with a surface countersunk hole 302, which can be connected to the satellite part.

[0093] The stepped cylindrical frame 301 has multiple stepped layered inlaid bosses 303 (serrated bosses) axially and evenly fixed in the middle, and two of the stepped layered inlaid bosses 303 are provided with circumferentially distributed cylindrical frame surface machining holes 304 (counter-holes) for connecting with the inner end of the variable support rod 5.

[0094] The lower connecting frame 4 is composed of a layered inlaid boss 401, a stepped cylindrical sleeve 402, a lower surface 403, and a machining hole 404 on the surface of the cylindrical sleeve.

[0095] The stepped cylindrical sleeve 402 is a multi-step cylindrical structure, and its radial dimension is larger than that of the stepped cylindrical frame 301.

[0096] The lower end of the stepped cylindrical sleeve 402 is provided with a lower surface 403 that connects to the satellite part, and a lower connecting frame layered inlay boss 401 is fixedly provided in the middle part;

[0097] The lower connecting frame has layered inlaid bosses 401 with countersunk cylindrical sleeve surface machining holes 404 evenly distributed on them.

[0098] The intermediate damping layer 2 has a gradually changing cavity and a layered inlay structure inside according to the contacting upper connecting frame 3 and lower connecting frame 4, forming a tight fit with the upper connecting frame 3 and lower connecting frame 4, and a solid layer in the middle separates the upper connecting frame 3 and lower connecting frame 4.

[0099] The solid layer inside the intermediate damping layer 2 is connected to the lower end of the upper connecting frame 3 and the upper end of the lower connecting frame 4 on the upper and lower sides, respectively. The contact surface is provided with a cavity to unload stress and to absorb part of the deformation when the intermediate damping layer is deformed significantly due to severe external load, thus preventing the device from being squeezed and damaged.

[0100] The fixed outer ring 1 has 6 holes 105 evenly distributed on its bottom circumference at 60° intervals. These holes cooperate with 6 evenly distributed 60° through holes 601 on the bottom fixed washer 6. The fixed outer ring 1 is positioned and fixed by a positioning pin 602.

[0101] The bottom fixing washer 6 is a thin circular ring structure with an axial dimension much smaller than its radial dimension. Its outer diameter is equal to the outer diameter of the fixing outer ring 1. The inner diameter of the ring is equal to the outer diameter of the position of the intermediate damping layer 2 where the intermediate damping layer is not installed, which can limit the bottom end of the intermediate damping layer 2.

[0102] The fixed outer ring 1 is columnar and is made of boron fiber reinforced aluminum matrix composite material Bf / Al, titanium alloy Ti-6Al-4V or copper-based alloy Cu-Al-Ni, which has high rigidity and high temperature resistance.

[0103] The variable support rod 5 comprises an inner ring fixing surface 501, an outer ring fixing surface 502, and a middle contact surface 503.

[0104] The inner ring fixing surface 501 contacts the countersunk hole on the outer ring of the upper connecting frame 3 and the lower connecting frame 4, the middle contact surface 503 cooperates with the through hole on the middle damping layer 2 (that is, the variable support rod 5 passes through the middle damping layer 2), and the outer ring fixing surface 502 is fixed with the countersunk hole on the inner ring of the fixing outer ring 1.

[0105] The variable support rod 5 is made of shape memory alloy or low melting point polymer; the shape memory alloy may be Ni-Ti-Hf high temperature nickel-titanium alloy, and the low melting point polymer may be polyamide hot melt adhesive or polyurethane hot melt adhesive.

[0106] This invention discloses an installation method for a variable satellite connector shock absorption device:

[0107] The main structure of this invention can be manufactured using 3D printing technology;

[0108] During installation, the variable support rod 5 is fixed to the inner end face of the fixed outer ring at a 120° interval hole 103 and the end face of the fixed outer ring at a 60° interval hole 104 on the left end 101 of the fixed outer ring.

[0109] The intermediate damping layer layer-shaped inlay protrusion 205 at the left end 201 of the intermediate damping layer is matched with the fixed outer ring layer-shaped inlay protrusion 106 of the fixed outer ring 1.

[0110] And it is fixed by connecting the intermediate contact surface 503 of the variable support rod 5 to the 120° through hole 203 on the inner end face of the intermediate damping layer and the 60° through hole 204 on the end face of the intermediate damping layer;

[0111] Then, the stepped cylindrical frame 301 of the upper connecting frame 3, the stepped layered inlay boss 303 and the lower connecting frame layered inlay boss 401 of the lower connecting frame 4 are respectively matched, and the lower connecting frame layered inlay boss 401 is connected to the internal cavity structure processed by the intermediate damping layer 2.

[0112] The inner ring fixing surface 501 of the variable support rod 5 is connected to the machined hole 304 on the cylindrical frame surface of the upper connecting frame 3 and the machined hole 404 on the cylindrical sleeve surface of the lower connecting frame 4 for fixation.

[0113] The right end 202 of the intermediate damping layer, the right end 102 of the fixed outer ring, and the remaining variable support rod 5 are connected in sequence, and the bottom fixing washer 6 is connected to the fixed outer ring 1 and the intermediate damping layer 2 respectively through the positioning pin 602 to realize the installation and fixation of the entire device.

[0114] The present invention discloses a method for using a variable satellite connector shock absorption device:

[0115] The device of this invention has two operating states: satellite launch and satellite in-orbit operation;

[0116] Based on the material selection of the variable support rod (5), the usage method is as follows:

[0117] a. The variable support rod 5 is made of shape memory alloy: Ni-Ti-Hf high-temperature nickel-titanium alloy;

[0118] Step a1: Satellite launch

[0119] During the satellite launch phase, the surface countersunk hole 302 of the upper connecting frame 3 is connected to the upper half of the satellite, and the lower surface 403 of the lower connecting frame 4 is connected to the lower half of the satellite.

[0120] At this time, the satellite connector is in a normal temperature environment. The shape memory alloy has good rigidity at normal temperature, and the variable support rod 5 remains rigid. It mainly serves to connect and fix the outer ring 1 with the internal working structure, so as to prevent the satellite connector from disintegrating during the violent shaking of the launch.

[0121] Step a2: The satellite is operating normally in orbit.

[0122] When the satellite is operating normally in orbit, it can be connected to the variable support rod 5 via the satellite's circuitry and heated. Due to the shape memory effect of the shape memory alloy, it can recover its soft state at high temperatures, causing the variable support rod 5 to soften and lose its fixing function to the device, and then attach to the intermediate damping layer 2. At this time, the entire device relies on the layered structure on the outer and inner sides of the intermediate damping layer for flexible connection. When subjected to the impact of the unstable environment of outer space, the intermediate damping layer 2 has a sponge-like structure filled with elastic material, which has excellent shock absorption and buffering effect when bearing large axial and radial loads, effectively preventing the satellite from being damaged by impact and extending its working life. At this time, the entire satellite connection frame device mainly plays a shock absorption role.

[0123] b. The variable support rod 5 is made of a low-melting-point polymer: polyamide hot melt adhesive or polyurethane hot melt adhesive;

[0124] At this time, the variable support rod 5 is provided with an internal metal wire 802 at its center. The internal metal wire 802 can be connected to the external circuit 801. The internal metal wire 802 is wrapped with a low melting point polymer material, which together constitutes the low melting point polymer component 8.

[0125] Step b1: Satellite launch

[0126] During the satellite launch phase, the surface countersunk hole 302 of the upper connecting frame 3 is connected to the upper half of the satellite, and the lower surface 403 of the lower connecting frame 4 is connected to the lower half of the satellite.

[0127] At this time, the satellite connector is in a normal temperature environment. The low-melting-point polymer has a certain rigidity at normal temperature. The low-melting-point polymer component 8 remains rigid and mainly serves to connect and fix the outer ring 1 with the internal working structure, so as to prevent the satellite connector from disintegrating during the violent shaking of the launch.

[0128] Step b2: The satellite is operating normally in orbit.

[0129] When the satellite is operating normally in orbit, it can connect to the external circuit 801 around the fixed outer ring 1 via the satellite's circuitry. The external circuit 801 is then connected to the internal metal wire 802 of the low-melting-point polymer component 8, which is then heated. Because the low-melting-point polymer has a low melting point, it can often completely melt when heated to 150°C, causing the low-melting-point polymer component 8 to soften and lose its fixing effect on the device. It then adheres to the intermediate damping layer 2. At this time, the entire device relies on the layered inlay structure on the outer and inner sides of the intermediate damping layer for flexible connection. When subjected to the impact of the unstable environment of outer space, the intermediate damping layer 2, which is filled with elastic material and has a sponge-like structure, has excellent shock absorption and buffering effect when subjected to large axial and radial loads. This can effectively prevent the satellite from being damaged by impact and extend its service life. At this time, the entire satellite connection frame device mainly plays a shock absorption role.

Claims

1. A variable satellite connector shock absorption device, characterized in that, include: Fixed outer ring (1), middle shock-absorbing layer (2), upper connecting frame (3), lower connecting frame (4), variable support rod (5), bottom fixed washer (6); The fixed outer ring (1) has a cylindrical structure and is composed of a symmetrical left end (101) and a right end (102) of the fixed outer ring; The inner cylindrical surface of the fixed outer ring (1) is axially and equally spacedly embedded with multiple fixed outer ring layered inlay bosses (106), the cross-section of which is sawtooth-shaped; Holes (104) are evenly distributed at 60° intervals on the bottom of the inner cylindrical surface to fix the outer end face. Holes (103) are evenly distributed on the fixed outer ring layered inlay boss (106) at the top of the inner ring cylindrical surface, with a spacing of 120° between them. The 60° interval holes (104) on the bottom surface of the fixed outer ring and the 120° interval holes (103) on the inner end face of the fixed outer ring are countersunk holes, and variable support rods (5) are fixedly connected inside them. The intermediate damping layer (2) is composed of a symmetrical left end (201) and a right end (202) of the intermediate damping layer; The intermediate damping layer (2) has a columnar structure, and its columnar surface is provided with axially spaced intermediate damping layer inlaid protrusions (205), and the cross section is sawtooth-shaped; The sawtooth boss structure of the inner ring of the fixed outer ring (1) and the sawtooth boss structure of the outer ring of the intermediate damping layer (2) are connected in a cooperative manner. The bottom of the intermediate damping layer (2) has 60° through holes (204) evenly distributed on the end face of the intermediate damping layer. The intermediate damping layer (2) has 120° through holes (203) evenly distributed in the groove between the intermediate damping layer layer-shaped inlaid protrusions (205) at the top. The top and bottom of the inner side of the intermediate damping layer (2) are connected to the upper connecting frame (3) and the lower connecting frame (4) respectively; The intermediate damping layer (2) adopts a sponge-like loose porous structure; The variable support rod (5) passes through the through hole (204) on the intermediate damping layer (2) and abuts against the outer walls of the upper connecting frame (3) and the lower connecting frame (4); The variable support rod (5) transforms from a rigid rod into a flexible rod after being heated.

2. The variable satellite connector shock absorption device according to claim 1, characterized in that: The upper connecting frame (3) is composed of a stepped cylindrical frame (301), surface countersunk holes (302), stepped layered inlaid bosses (303), and surface machined holes (304) of the cylindrical frame; The stepped cylindrical frame (301) is a multi-step cylindrical structure, and its upper bearing surface is provided with a surface countersunk hole (302) to connect with the satellite part; The stepped cylindrical frame (301) has multiple stepped layered inlaid bosses (303) axially and evenly fixed in the middle, and the cylindrical frame surface is provided with circumferentially distributed countersunk holes (304) for connecting with the inner end of the variable support rod (5).

3. The variable satellite connector shock absorption device according to claim 2, characterized in that: The lower connecting frame (4) consists of a layered inlaid boss (401), a stepped cylindrical sleeve (402), a lower surface (403), and machining holes (404) on the surface of the cylindrical sleeve; The stepped cylindrical sleeve (402) is a multi-step cylindrical structure. Its lower end is provided with a lower surface (403) that connects to the satellite part, and its middle part is fixed with a lower connecting frame layered inlay boss (401). The lower connecting frame layered inlay boss (401) is provided with countersunk cylindrical sleeve surface machining holes (404) evenly distributed.

4. The variable satellite connector shock absorption device according to claim 3, characterized in that: The intermediate damping layer (2) is connected to the upper connecting frame (3) and lower connecting frame (4) through a gradually changing cavity and a layered inlay structure. A solid layer is provided in the middle to separate the upper connecting frame (3) and lower connecting frame (4). The solid layer inside the intermediate shock-absorbing layer (2) is connected to the lower end of the upper connecting frame (3) and the upper end of the lower connecting frame (4) respectively. The contact surface is provided with a cavity to unload stress.

5. The variable satellite connector shock absorption device according to claim 4, characterized in that: The fixed outer ring (1) has holes (105) spaced 60° apart on its bottom circumference, which are arranged to cooperate with the evenly distributed 60° through holes (601) on the bottom fixed washer (6) and are positioned and fixed by positioning pins (602).

6. The variable satellite connector shock absorption device according to claim 5, characterized in that: The bottom fixing washer (6) is a thin circular ring structure, and its outer diameter is equal to the outer diameter of the fixing outer ring (1); the inner diameter of the ring limits the bottom end of the middle shock-absorbing layer (2).

7. A variable satellite connector shock absorption device according to claim 6, characterized in that: The fixed outer ring (1) is columnar and is made of boron fiber reinforced aluminum matrix composite material Bf / Al, titanium alloy Ti-6Al-4V or copper-based alloy Cu-Al-Ni. It has high rigidity and high temperature resistance.

8. A variable satellite connector shock absorption device according to claim 7, characterized in that: The variable support rod (5) consists of an inner ring fixing surface (501), an outer ring fixing surface (502), and a middle contact surface (503); The inner ring fixing surface (501) is in contact with the countersunk holes on the outer ring of the upper connecting frame (3) and the lower connecting frame (4), the middle contact surface (503) is in cooperation with the through hole on the middle damping layer (2), and the outer ring fixing surface (502) is fixed with the countersunk hole on the inner ring of the fixing outer ring (1). The variable support rod (5) is made of shape memory alloy or low melting point polymer.

9. A method of using a variable satellite connector shock absorption device, characterized in that: The specific method of using the variable satellite connector shock absorption device as described in claim 8 is as follows: The device of this invention has two operating states: satellite launch and satellite in-orbit operation; a. The variable support rod (5) is made of shape memory alloy: Ni-Ti-Hf high-temperature nickel-titanium alloy; Step a1: Satellite launch At room temperature, the variable support rod (5) is rigid and the entire device is fixed by connecting it with the fixed outer ring (1), the middle damping layer (2), the upper connecting frame (3), and the lower connecting frame (4); After the satellite is launched into space, the variable support rod (5) is heated to soften it and attaches to the intermediate damping layer (2), thus losing its fixing function. The entire device is connected by the intermediate damping layer (2), which plays a role in damping and buffering. b. The variable support rod (5) is made of a low-melting-point polymer: polyamide hot melt adhesive or polyurethane hot melt adhesive; The variable support rod (5) has an internal metal wire (802) at its center. The internal metal wire (802) can be connected to the external circuit (801). The internal metal wire (802) is wrapped with a low melting point polymer material to form a low melting point polymer component (8). Step b1: Satellite launch At room temperature, the low-melting-point polymer component (8) is rigid and the entire device is fixed by connecting it with the fixed outer ring (1), the middle damping layer (2), the upper connecting frame (3), and the lower connecting frame (4); Step b2: The satellite is operating normally in orbit. After the satellite is launched into space, the internal metal wires (802) of the low melting point polymer component (8) are heated by the external circuit (801) to soften them and attach to the intermediate damping layer (2), thus losing their fixing function. The entire device is connected by the intermediate damping layer (2), which also plays a role in damping and buffering.

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