Satellite flywheel micro-vibration frameless self-resetting vibration isolator

Abstract

The utility model belongs to satellite flywheel vibration isolation technical field, concretely relates to a satellite flywheel microvibration frameless self-resetting vibration isolator, including mounting bracket and flywheel, the top fixed mounting of mounting bracket has the frame, the inside of frame is provided with flywheel, through the deformation of spring one and spring two to absorb and buffer the microvibration of flywheel operation, reduce the transmission of vibration to satellite other components, thereby guarantee the normal work of satellite precision instrument equipment, improve the operation stability and mission reliability of satellite, can through the stiffness of spring two reset to quick adaptation, need not to replace the vibration isolator, enhance the mission adaptability of satellite, when vibration disappears, the elastic recovery force of spring element can make the vibration isolation mechanism automatically return to the initial position, realize self-resetting function, ensure that the vibration isolator still can keep good vibration isolation performance when the subsequent vibration occurs, need not manual intervention or additional reset device.

Description

Technical Field

[0001] This utility model belongs to the field of satellite flywheel vibration isolation technology, specifically relating to a frameless self-resetting vibration isolator for satellite flywheel micro-vibration. Background Technology

[0002] The frameless self-resetting vibration isolator for satellite flywheel micro-vibration is a device used to reduce the impact of satellite flywheel micro-vibration on satellite payload.

[0003] Chinese Patent Publication No. CN219101939U discloses a frameless self-resetting vibration isolator for satellite flywheel micro-vibration. Its features include four circumferentially distributed vibration isolation components; each component has an upper vibration isolation pad, a lower vibration isolation pad, and four elastic elements in the middle layer; each elastic element includes a shape memory alloy skeleton, a rubber ring, and a connector. The shape memory alloy skeleton is a multi-groove hollow cylinder, the rubber ring is disposed within the shape memory alloy grooves and distributed layer by layer with the shape memory alloy layer, and the connector is threaded to the holes of the vibration isolation pads. This device, with its multiple elastic elements in different spatial positions, can achieve multi-degree-of-freedom vibration isolation for the satellite flywheel. After micro-vibration of the flywheel, the deformed parts maintain minimal deformation and can self-reset after deformation, fully ensuring the accuracy of the satellite payload. It also saves overall satellite resources, features a lightweight design, and ensures stable satellite payload position even with large deformations, which is beneficial for achieving clear imaging of optical satellites.

[0004] Based on the above review of a frameless self-resetting vibration isolator for micro-vibration of a satellite flywheel, the following problems exist: If the spring stiffness is fixed and relatively soft, when the flywheel is under high speed and large vibration conditions, the spring will lose its stable vibration isolation capability due to excessive deformation, and may even cause damage to the vibration isolation mechanism structure, thus failing to effectively isolate vibration. Therefore, we propose a frameless self-resetting vibration isolator for micro-vibration of a satellite flywheel. Summary of the Invention

[0005] The purpose of this invention is to provide a frameless self-resetting vibration isolator for satellite flywheel micro-vibration, which can solve the problem in related technologies where, if the spring stiffness is fixed and too soft, the spring will lose its stable vibration isolation ability due to excessive deformation when the flywheel is under high speed and large vibration conditions, and may even cause damage to the vibration isolation mechanism structure, thus failing to effectively isolate vibration.

[0006] The specific technical solution adopted by this utility model is as follows: A frameless self-resetting vibration isolator for satellite flywheel micro-vibration includes a mounting bracket and a flywheel. A frame is fixedly mounted on the top of the mounting bracket, and the flywheel is disposed inside the frame. A connecting rod is fixedly mounted on the inner wall of the frame, and a vibration isolation mechanism is disposed inside the frame. The vibration isolation mechanism includes a fixing button, which is fixedly mounted on the inner wall of the flywheel. A knob is rotatably mounted on the inner wall of the fixing button. A hollow cylinder is fixedly mounted on the surface of the knob. A sliding plate is slidably mounted on the inner wall of the hollow cylinder. A rotating rod is fixedly mounted on one side of the sliding plate, and one side of the connecting bracket is rotatably mounted on the surface of the rotating rod.

[0007] The connecting rod has a connecting frame sleeved on its circumferential surface, and the connecting rod has a threaded groove on its circumferential surface. A spring is provided between the sliding plate and the hollow cylinder.

[0008] A second spring is provided at the bottom of the connecting frame, and a vibration damping pad is fixedly installed at the bottom of the second spring. The movement of the flywheel itself drives the fixed button to move, which in turn drives the rotary knob to move, which in turn drives the hollow cylinder to move, which in turn drives the rotating rod to move, which in turn drives the connecting frame to move, which in turn drives the second spring to move, which in turn drives the vibration damping pad to move, and the vibration damping pad will eventually come into contact with the adjustment knob.

[0009] The connecting rod is threaded with an adjustment knob. By rotating the adjustment knob, its position is brought closer to the vibration isolation pad. The number of the fixing knob, the rotating knob, the hollow cylinder, the slider, the rotating rod and the spring are set to three, and they are arranged in a circular array along the center of the flywheel.

[0010] An auxiliary mechanism is provided below the flywheel. The auxiliary mechanism includes a fixed frame, which is fixedly installed on the inner wall of the frame. A lower vibration isolation pad is fixedly installed on the top of the fixed frame, and an upper vibration isolation pad is fixedly installed on the bottom of the flywheel. A vibration isolation element is provided between the upper and lower vibration isolation pads.

[0011] The vibration isolation element is made of alternating layers of rubber and steel plates. The number of the fixed frame, lower vibration isolation pad, vibration isolation element and upper vibration isolation pad is set to four, and they are arranged in a circular array along the center of the flywheel. The movement of the flywheel drives the upper vibration isolator to move, which in turn drives the vibration isolation element to move. The four vibration isolators at the bottom of the flywheel are symmetrically distributed, which can isolate the micro-vibrations of the flywheel from multiple directions.

[0012] The technical effects achieved by this utility model are as follows: 1. This utility model, through the setting of a vibration isolation mechanism, absorbs and buffers the micro-vibrations generated during the operation of the flywheel by the deformation of spring one and spring two, reducing the transmission of vibration to other components of the satellite, thereby ensuring the normal operation of precision instruments and equipment on the satellite, improving the operational stability and mission reliability of the satellite. By rotating the adjustment knob to bring its position closer to the vibration isolation pad, the stiffness of the spring two's reset can be adjusted. The stiffness of the spring two's reset can be adjusted for quick adaptation without replacing the vibration isolator, enhancing the satellite's mission adaptability. When the vibration disappears, the elastic restoring force of the springs and other components can make the vibration isolation mechanism automatically return to its initial position, realizing the self-reset function, ensuring that the vibration isolator can still maintain good vibration isolation performance when subsequent vibrations occur, without manual intervention or additional reset devices.

[0013] 2. This utility model, through the setting of auxiliary mechanisms, enables the flywheel to move, thereby driving the upper vibration isolator to move, which in turn drives the vibration isolation element to move. With the four vibration isolators at the bottom of the flywheel symmetrically distributed, the micro-vibrations of the flywheel can be isolated from multiple directions, so that the vibration of the flywheel in space, including the horizontal and vertical directions, can be effectively buffered. Compared with a single or fewer vibration isolators, the stability is significantly improved, and the vibration can be more comprehensively prevented from being transmitted to other components of the satellite. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the entire utility model; Figure 2 This is a schematic diagram of the internal structure of the frame of this utility model; Figure 3 This is a schematic diagram of the structure at the location of the connecting frame and the adjusting knob of this utility model; Figure 4 This is a utility model Figure 3 Enlarged schematic diagram of section A of the structure; Figure 5 This is a schematic diagram of the structure at the location of the flywheel and vibration isolation element of this utility model.

[0015] The attached diagram lists the components represented by each number as follows: 1. Mounting bracket; 2. Frame; 3. Flywheel; 4. Connecting rod; 5. Vibration isolation mechanism; 50. Fixing button; 51. Knob; 52. Hollow cylinder; 53. Sliding plate; 54. Rotating rod; 55. Spring 1; 56. Connecting bracket; 57. Spring 2; 58. Vibration isolation pad; 59. Adjusting knob; 6. Auxiliary mechanism; 60. Fixing bracket; 61. Lower vibration isolation pad; 62. Vibration isolation element; 63. Upper vibration isolation pad. Detailed Implementation

[0016] To make the objectives and advantages of this utility model clearer, the following detailed description is provided in conjunction with embodiments. It should be understood that the following text is merely used to describe one or more specific embodiments of this utility model and does not strictly limit the scope of protection specifically claimed by this utility model.

[0017] like Figure 1-5 As shown, a frameless self-resetting vibration isolator for satellite flywheel micro-vibration includes a mounting frame 1 and a flywheel 3. A frame 2 is fixedly mounted on the top of the mounting frame 1. The flywheel 3 is disposed inside the frame 2. A connecting rod 4 is fixedly mounted on the inner wall of the frame 2. A vibration isolation mechanism 5 is disposed inside the frame 2. The vibration isolation mechanism 5 includes a fixing button 50, which is fixedly mounted on the inner wall of the flywheel 3. A knob 51 is rotatably mounted on the inner wall of the fixing button 50. A hollow cylinder 52 is fixedly mounted on the surface of the knob 51. A sliding plate 53 is slidably mounted on the inner wall of the hollow cylinder 52. A rotating rod 54 is fixedly mounted on one side of the sliding plate 53. A side of a connecting frame 56 is rotatably mounted on the surface of the rotating rod 54.

[0018] The other side of the connecting bracket 56 is sleeved on the circumferential surface of the connecting rod 4. The circumferential surface of the connecting rod 4 is provided with a threaded groove. A spring 55 is provided between the sliding plate 53 and the hollow cylinder 52.

[0019] A second spring 57 is installed at the bottom of the connecting frame 56. A vibration isolation pad 58 is fixedly installed at the bottom of the second spring 57. The deformation of the first spring 55 and the second spring 57 absorbs and buffers the micro-vibrations generated by the flywheel 3 during operation, reduces the transmission of vibration to other parts of the satellite, thereby ensuring the normal operation of precision instruments and equipment on the satellite and improving the operational stability and mission reliability of the satellite.

[0020] The connecting rod 4 is threaded with an adjustment knob 59, which can be quickly adapted by adjusting the stiffness of the spring 57 to reset, without the need to replace the vibration isolator, thus enhancing the satellite's mission adaptability. The number of the fixing knob 50, the rotating knob 51, the hollow cylinder 52, the slider 53, the rotating rod 54, and the spring 55 is set to three, and they are arranged in a circular array around the center of the flywheel 3.

[0021] An auxiliary mechanism 6 is provided below the flywheel 3. The auxiliary mechanism 6 includes a fixed frame 60, which is fixedly installed on the inner wall of the frame 2. A lower vibration isolation pad 61 is fixedly installed on the top of the fixed frame 60, and an upper vibration isolation pad 63 is fixedly installed on the bottom of the flywheel 3. A vibration isolation element 62 is provided between the upper vibration isolation pad 63 and the lower vibration isolation pad 61.

[0022] The vibration isolation element 62 is made of alternating layers of rubber and steel plates. The number of the fixed frame 60, lower vibration isolation pad 61, vibration isolation element 62 and upper vibration isolation pad 63 is set to four, and they are arranged in a circular array along the center of the flywheel 3. The four vibration isolators at the bottom of the flywheel 3 are symmetrically distributed, which can isolate the micro-vibration of the flywheel 3 from multiple directions, so that the vibration of the flywheel 3 in space, including the horizontal and vertical directions, can be effectively buffered. Compared with a single or fewer vibration isolators, the stability is significantly improved, and the vibration can be more comprehensively prevented from being transmitted to other components of the satellite. Working principle: The flywheel 3 moves, driving the fixed knob 50 to move. The movement of the fixed knob 50 drives the rotary knob 51 to move, which in turn drives the hollow cylinder 52 to move. The movement of the hollow cylinder 52 causes the rotary rod 54 to move, which in turn drives the connecting frame 56 to move. The movement of the connecting frame 56 drives the second spring 57 to move, which in turn drives the vibration damping pad 58 to move. The vibration damping pad 58 eventually contacts the adjusting knob 59. During this movement, the rotary rod 54 drives the slider 53 to move along the inner wall of the hollow cylinder 52. The movement of the slider 53 compresses the first spring 55. The deformation of the first spring 55 and the second spring 57 absorbs and buffers the flywheel. 3. The micro-vibrations generated during operation reduce the transmission of vibration to other components of the satellite, thereby ensuring the normal operation of precision instruments and equipment on the satellite, improving the operational stability and mission reliability of the satellite. By rotating the adjustment knob 59 to bring its position closer to the vibration isolation pad 58, the stiffness of the spring 57 reset can be adjusted. The stiffness of the spring 57 reset can be adjusted to quickly adapt without replacing the vibration isolator, enhancing the satellite's mission adaptability. When the vibration disappears, the elastic restoring force of the spring and other components can make the vibration isolation mechanism 5 automatically return to the initial position, realizing the self-reset function, ensuring that the vibration isolator can still maintain good vibration isolation performance when subsequent vibrations occur, without manual intervention or additional reset devices. The movement of flywheel 3 drives the upper vibration isolator 63 to move, which in turn drives the vibration isolation element 62 to move. The four vibration isolators at the bottom of flywheel 3 are symmetrically distributed, which can isolate the micro-vibrations of flywheel 3 from multiple directions. This effectively buffers the vibrations of flywheel 3 in space, including both horizontal and vertical directions. Compared with a single or fewer vibration isolators, the stability is significantly improved, and the vibration can be more comprehensively prevented from being transmitted to other components of the satellite.

[0023] The above description is merely a preferred embodiment of this utility model. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principle of this utility model, and these improvements and modifications should also be considered within the scope of protection of this utility model. Structures, devices, and operating methods not specifically described or explained in this utility model, unless otherwise specified or limited, shall be implemented using conventional methods in the field.

Claims

1. A frameless self-resetting vibration isolator for micro-vibration of satellite flywheels, characterized in that: The device includes a mounting frame (1) and a flywheel (3), characterized in that a frame (2) is fixedly installed on the top of the mounting frame (1), a flywheel (3) is provided inside the frame (2), a connecting rod (4) is fixedly installed on the inner wall of the frame (2), and a vibration isolation mechanism (5) is provided inside the frame (2). The vibration isolation mechanism (5) includes a fixed button (50), which is fixedly installed on the inner wall of the flywheel (3). A knob (51) is rotatably installed on the inner wall of the fixed button (50). A hollow cylinder (52) is fixedly installed on the surface of the knob (51). A sliding plate (53) is slidably installed on the inner wall of the hollow cylinder (52). A rotating rod (54) is fixedly installed on one side of the sliding plate (53). A connecting frame (56) is rotatably installed on one side of the rotating rod (54).

2. The frameless self-resetting vibration isolator for satellite flywheel micro-vibration according to claim 1, characterized in that: The connecting rod (4) has a connecting bracket (56) sleeved on its circumferential surface. The connecting rod (4) has a threaded groove on its circumferential surface. A spring (55) is provided between the sliding plate (53) and the hollow cylinder (52).

3. A frameless self-resetting vibration isolator for satellite flywheel micro-vibration according to claim 2, characterized in that: The bottom of the connecting frame (56) is provided with a second spring (57), and the bottom of the second spring (57) is fixedly installed with a vibration damping pad (58).

4. The frameless self-resetting vibration isolator for satellite flywheel micro-vibration according to claim 1, characterized in that: The connecting rod (4) is threaded with an adjusting knob (59). The number of the fixing knob (50), the rotating knob (51), the hollow cylinder (52), the sliding plate (53), the rotating rod (54), and the spring (55) are set to three and arranged in a circular array around the center of the flywheel (3).

5. A frameless self-resetting vibration isolator for satellite flywheel micro-vibration according to claim 1, characterized in that: An auxiliary mechanism (6) is provided below the flywheel (3). The auxiliary mechanism (6) includes a fixed frame (60). The fixed frame (60) is fixedly installed on the inner wall of the frame (2). A lower vibration isolation pad (61) is fixedly installed on the top of the fixed frame (60). An upper vibration isolation pad (63) is fixedly installed on the bottom of the flywheel (3). A vibration isolation element (62) is provided between the upper vibration isolation pad (63) and the lower vibration isolation pad (61).

6. A frameless self-resetting vibration isolator for satellite flywheel micro-vibration according to claim 5, characterized in that: The vibration isolation element (62) is made of alternating layers of rubber and steel plates. The number of the fixed frame (60), lower vibration isolation pad (61), vibration isolation element (62) and upper vibration isolation pad (63) is set to four, and they are arranged in a circular array along the center of the flywheel (3).

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