A kind of nickel-titanium memory alloy wire shockproof support for space instrument

Abstract

The utility model relates to spaceflight shockproof support technical field, and disclose a kind of for spaceflight instrument's nickel-titanium memory alloy line shockproof support, including support plate, the one side of support plate is fixedly connected with two groups of support bolt, the surface of support bolt is rotatably connected with support sleeve, the inside fixedly connected with support assembly of support sleeve, the one side of support plate is fixedly installed with fixed base by bolt, the inside of fixed base is sleeved with buffer assembly;The support assembly includes the rubber seat fixedly connected in the inside of support sleeve, the one end of rubber seat is fixedly connected with nickel-titanium alloy spring;The buffer assembly includes the rubber buffer disc that is sleeved in the inside of fixed base, the center of rubber buffer disc is sleeved with positioning column.The nickel-titanium memory alloy line shockproof support for spaceflight instrument, by the setting of buffer assembly, reach the effect of effective absorption and buffer equipment microvibration, improve the shockproof characteristic of support and equipment service life.

Description

Technical Field

[0001] This utility model relates to the field of aerospace anti-vibration support technology, and in particular to a nickel-titanium shape memory alloy wire anti-vibration support for spacecraft. Background Technology

[0002] Nickel-titanium shape memory alloy (NTiM) wire shock-absorbing brackets used in spacecraft refer to the use of NTiM wire in the shock-absorbing brackets of spacecraft. Because NTiM possesses unique superelasticity and a shape memory effect, it can recover its original shape under stress changes. This is highly beneficial for the stability and durability of spacecraft. NTiM wire can be used as an elastic connector in the bracket; when the instrument is subjected to vibration, the NTiM wire can absorb and buffer the vibration energy through its superelastic properties. When the vibration disappears, the alloy wire will return to its original shape, thus effectively reducing the impact of vibration on the spacecraft.

[0003] Patent document CN207442740U discloses a vibration-damping solar cell module support, including a support, a scissor-type damping mechanism, a damping platform, a spring support, and an integral rotating bearing. The scissor-type damping mechanism buffers and reduces vibration at the support end, the damping platform provides multi-degree-of-freedom damping for the solar cells, and the spring support provides secondary damping for the solar cells. This invention uses the scissor-type damping mechanism to buffer and reduce the force acting on the support, preventing vibrations from the support end caused by external environmental factors from being directly transmitted to the solar cells. The damping platform provides direct buffering protection for the solar cells mounted on it. Because it provides multi-degree-of-freedom damping, it avoids damage to the cells caused by multi-directional impacts. The spring support provides secondary damping, gradually reducing vibration during transmission, thus increasing the device's vibration resistance.

[0004] However, existing nickel-titanium shape memory alloy wire anti-vibration brackets used in spacecraft are difficult to effectively absorb micro-vibrations of spacecraft equipment during use, and are not conducive to volume compression and on-orbit vibration dissipation during the launch phase, thus reducing their adaptability to extreme environments. Utility Model Content

[0005] (a) Technical problems to be solved

[0006] The purpose of this invention is to provide a nickel-titanium shape memory alloy wire anti-vibration bracket for spacecraft, which solves the problems mentioned in the background art, such as the difficulty in effectively absorbing micro-vibrations of spacecraft equipment during use, and the inconvenience of volume compression and on-orbit vibration dissipation during the launch phase, thus reducing the adaptability to extreme environments.

[0007] (II) Technical Solution

[0008] To achieve the above objectives, this utility model provides the following technical solution: a nickel-titanium shape memory alloy wire shockproof bracket for spacecraft, comprising a support plate, two sets of support bolts fixedly connected to one side of the support plate, a support sleeve rotatably connected to the surface of the support bolts, a support assembly fixedly connected inside the support sleeve, a fixing seat fixedly installed on one side of the support plate by bolts, and a buffer assembly sleeved inside the fixing seat; the support assembly includes a rubber seat fixedly connected inside the support sleeve, a nickel-titanium alloy spring fixedly connected to one end of the rubber seat; the buffer assembly includes a rubber buffer disc sleeved inside the fixing seat, a positioning post sleeved at the center of the rubber buffer disc, and a tower-type nickel-titanium spring fixedly connected to one side of the rubber buffer disc.

[0009] As a further embodiment of this utility model, the inner wall of the fixed base is fixedly connected with two sets of buffer side pads, and one end of the positioning column is slidably connected with a connecting plate. The connecting plate serves to connect the movable base.

[0010] As a further embodiment of this utility model, a movable seat is sleeved on the surface of the connecting plate. The movable seat is slidably connected to the inner side of the buffer side pad. The movable seat serves to guide and position the object.

[0011] As a further embodiment of this utility model, a flange is sleeved on one end of the movable seat, and a rubber pad is fixedly connected to one side of the movable seat. The rubber pad provides initial shock absorption.

[0012] As a further embodiment of this utility model, one end of the nickel-titanium alloy spring is fixedly connected to a support rod, one end of the support rod is rotatably connected to a rotating bolt, and the other end of the support rod is slidably connected to the inside of the support sleeve. The rotating bolt serves to push the support frame.

[0013] As a further embodiment of this utility model, a support frame is fixedly connected to the top of the rotating bolt, and one end of the support frame is rotatably connected to the top of the support plate. The support frame facilitates the installation of the solar cell fins.

[0014] As a further embodiment of this utility model, the surface of the support frame is provided with several sets of positioning and mounting holes, and a rotating rod is sleeved on one end of the support frame. The rotating rod facilitates the rotation of the support frame.

[0015] As a further embodiment of this utility model, the top of the support plate is provided with a groove that matches the support frame, and a weight-reducing groove is provided at the center of the support plate. The weight-reducing groove reduces the weight.

[0016] (III) Beneficial Effects

[0017] This utility model provides a nickel-titanium shape memory alloy wire shockproof bracket for spacecraft, which has the following beneficial effects:

[0018] 1. This nickel-titanium shape memory alloy wire anti-vibration bracket for spacecraft, through the setting of buffer components, allows micro-vibrations generated by equipment inside the spacecraft to be initially absorbed by the rubber pad during use. Then, some vibration is transmitted, causing the movable seat to slide at one end of the fixed seat. Subsequently, the connecting plate inside the movable seat slides on the positioning column, compressing the tower-type nickel-titanium spring. The tower-type nickel-titanium spring adopts a conical structure, with the spring coils contacting each other sequentially from large to small during loading. The stiffness gradually increases with the load, forming a gradually increasing characteristic line, which effectively avoids resonance, has a higher energy storage density, and stronger adaptability to extreme environments. Combined with the rubber buffer plate, it further disperses the remaining vibration, forming a secondary buffer at the mechanical level, thereby effectively absorbing and buffering micro-vibrations of the equipment, improving the anti-vibration characteristics of the bracket and the service life of the equipment.

[0019] 2. This nickel-titanium shape memory alloy wire shockproof bracket for spacecraft, through the setting of the support components, allows the solar panels of small satellites to be connected and installed via the support frame during use. During satellite launch, the support frame is in a folded state to reduce its volume. When the nickel-titanium alloy spring is heated, it restores its shape, causing the nickel-titanium alloy spring to push the support rod, which slides within the support sleeve. Then, through the rotating bolt at one end of the support rod, the solar panel is stably supported. At the same time, when the solar panel shakes, the support rod slides within the support sleeve, compressing the nickel-titanium alloy spring and rubber seat and causing deformation. The high elastic deformation absorbs vibration energy, and the deformation of the rubber seat further dissipates residual vibration, forming a composite damping system that further enhances the overall shockproof performance. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0021] Figure 2 This is a schematic diagram of the disassembled structure of this utility model;

[0022] Figure 3 This is a schematic diagram of the support component structure of this utility model;

[0023] Figure 4 This is a schematic diagram of the buffer component structure of this utility model.

[0024] In the diagram: 1. Support plate; 2. Support bolt; 3. Support sleeve; 4. Support assembly; 401. Rubber seat; 402. Nickel-titanium alloy spring; 5. Fixed seat; 6. Buffer assembly; 601. Rubber buffer disc; 602. Positioning post; 603. Tower-type nickel-titanium spring; 7. Buffer side pad; 8. Connecting disc; 9. Movable seat; 10. Flange; 11. Rubber pad; 12. Support rod; 13. Rotating bolt; 14. Support frame; 15. Rotating rod. Detailed Implementation

[0025] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the scope of protection of the present utility model.

[0026] Please see Figures 1 to 4 This utility model provides a technical solution: a nickel-titanium shape memory alloy wire shockproof bracket for spacecraft, including a support plate 1, two sets of support bolts 2 fixedly connected to one side of the support plate 1, a support sleeve 3 rotatably connected to the surface of the support bolts 2, and a support assembly 4 fixedly connected inside the support sleeve 3. Through the setting of the support assembly 4, its high elastic deformation absorbs vibration energy, and the deformation of the rubber seat 401 further dissipates residual vibration, forming a composite damping system, further enhancing the overall shockproof performance. A fixing seat 5 is fixedly installed on one side of the support plate 1 by bolts, and two sets of buffer side pads 7 are fixedly connected to the inner wall of the fixing seat 5. One end of the positioning column 602 slides... The moving connection includes a connecting plate 8, which serves to connect the movable seat 9. The fixed seat 5 has a buffer component 6 inside. The buffer component 6 effectively absorbs and buffers the micro-vibrations of the equipment, improving the shock absorption characteristics of the support and the service life of the equipment. The support component 4 includes a rubber seat 401 fixedly connected inside the support sleeve 3, and a nickel-titanium alloy spring 402 fixedly connected to one end of the rubber seat 401. The buffer component 6 includes a rubber buffer plate 601 sleeved inside the fixed seat 5, a positioning post 602 sleeved at the center of the rubber buffer plate 601, and a tower-type nickel-titanium spring 603 fixedly connected to one side of the rubber buffer plate 601.

[0027] Furthermore, a movable seat 9 is fitted onto the surface of the connecting plate 8. The movable seat 9 is slidably connected to the inner side of the buffer side pad 7, serving as a guide and positioning element. A flange 10 is fitted onto one end of the movable seat 9, and a rubber pad 11 is fixedly connected to one side of the movable seat 9, providing initial shock absorption. A support rod 12 is fixedly connected to one end of the nickel-titanium alloy spring 402, and a rotating bolt 13 is rotatably connected to one end of the support rod 12. The other end of the support rod 12 is slidably connected to the inside of the support sleeve 3, pushing the support frame 14. The top of the rotating bolt 13 is fixedly connected to the support frame 14, and one end of the support frame 14 is rotatably connected to the top of the support plate 1, facilitating the installation of the solar cell wings. Several sets of positioning and mounting holes are provided on the surface of the support frame 14, and a rotating rod 15 is fitted onto one end of the support frame 14, facilitating the rotation of the support frame 14. The top of the support plate 1 is provided with a groove that matches the support frame 14, and a weight reduction groove is provided at the center of the support plate 1. The weight reduction groove is designed to reduce the weight.

[0028] In this invention, the working steps of the device are as follows:

[0029] First step: During use, the micro-vibrations generated by the equipment inside the spacecraft are transmitted from the fuselage to the rubber pad 11 for initial vibration absorption, and then part of the vibration is transmitted, causing the movable seat 9 to slide at one end of the fixed seat 5. Then, the connecting plate 8 inside the movable seat 9 slides on the positioning column 602 and squeezes the tower-type nickel-titanium spring 603. The tower-type nickel-titanium spring 603 adopts a conical structure. When loaded, the spring coils contact from the large coil to the small coil in sequence. The stiffness gradually increases with the increase of the load, forming a gradually increasing characteristic line, which can effectively avoid resonance, and has a higher energy storage density and stronger adaptability to extreme environments. Together with the rubber buffer plate 601, it further disperses the remaining vibration, forming a secondary buffer at the mechanical level.

[0030] The second step: During use, the solar panel of the small satellite can be connected and installed through the support frame 14. During satellite launch, the support frame 14 is in a folded state to reduce its volume. When the nickel-titanium alloy spring 402 is heated, it restores its shape, causing the nickel-titanium alloy spring 402 to push the support rod 12, which slides inside the support sleeve 3. Then, through the rotating bolt 13 at one end of the support rod 12, the solar panel is stably supported. At the same time, when the solar panel shakes, the support rod 12 slides inside the support sleeve 3, compressing the nickel-titanium alloy spring 402 and the rubber seat 401 and causing deformation.

[0031] It should be noted that the device structure and accompanying drawings of this utility model mainly describe the principle of this utility model. In terms of the technical aspects of this design principle, the setting of the power mechanism, power supply system and control system of the device is not fully described. However, under the premise that those skilled in the art understand the principle of the above utility model, the specific details of its power mechanism, power supply system and control system can be clearly understood. The control method in the application document is automatic control through a controller. The control circuit of the controller can be implemented by those skilled in the art through simple programming.

[0032] All standard parts used can be purchased from the market, and can be customized according to the instructions and drawings. The specific connection methods of each part adopt conventional methods such as bolts, rivets, and welding that are mature in the existing technology. The machinery, parts and equipment adopt conventional models in the existing technology, and the structure and principle of the components known to those skilled in the art can be known by those skilled in the art through technical manuals or conventional experimental methods.

[0033] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A nickel-titanium shape memory alloy wire shockproof bracket for spacecraft, comprising a support plate (1), characterized in that: Two sets of support bolts (2) are fixedly connected to one side of the support plate (1). A support sleeve (3) is rotatably connected to the surface of the support bolt (2). A support assembly (4) is fixedly connected inside the support sleeve (3). A fixing seat (5) is fixedly installed on one side of the support plate (1) by bolts. A buffer assembly (6) is sleeved inside the fixing seat (5). The support assembly (4) includes a rubber seat (401) fixedly connected inside the support sleeve (3), and a nickel-titanium alloy spring (402) is fixedly connected to one end of the rubber seat (401). The buffer assembly (6) includes a rubber buffer disc (601) sleeved inside the fixed base (5), a positioning post (602) sleeved at the center of the rubber buffer disc (601), and a tower-type nickel-titanium spring (603) fixedly connected to one side of the rubber buffer disc (601).

2. The nickel-titanium shape memory alloy wire shockproof bracket for spacecraft according to claim 1, characterized in that: The inner wall of the fixed base (5) is fixedly connected with two sets of buffer side pads (7), and one end of the positioning column (602) is slidably connected with a connecting plate (8).

3. The nickel-titanium shape memory alloy wire shockproof bracket for spacecraft according to claim 2, characterized in that: The surface of the connecting plate (8) is fitted with a movable seat (9), which is slidably connected to the inside of the buffer side pad (7).

4. The nickel-titanium shape memory alloy wire shockproof bracket for spacecraft according to claim 3, characterized in that: A flange (10) is fitted onto one end of the movable seat (9), and a rubber pad (11) is fixedly connected to one side of the movable seat (9).

5. A nickel-titanium shape memory alloy wire shockproof bracket for spacecraft according to claim 1, characterized in that: One end of the nickel-titanium alloy spring (402) is fixedly connected to a support rod (12), one end of the support rod (12) is rotatably connected to a rotating bolt (13), and the other end of the support rod (12) is slidably connected to the inside of the support sleeve (3).

6. A nickel-titanium shape memory alloy wire shockproof bracket for spacecraft according to claim 5, characterized in that: The top of the rotating bolt (13) is fixedly connected to a support frame (14), and one end of the support frame (14) is rotatably connected to the top of the support plate (1).

7. A nickel-titanium shape memory alloy wire shockproof bracket for spacecraft according to claim 6, characterized in that: The surface of the support frame (14) is provided with several sets of positioning and mounting holes, and a rotating rod (15) is sleeved on one end of the support frame (14).

8. A nickel-titanium shape memory alloy wire shockproof bracket for spacecraft according to claim 1, characterized in that: The top of the support plate (1) is provided with a groove that matches the support frame (14), and the center of the support plate (1) is provided with a weight reduction groove.

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