An adaptive stiffness and damping compound support device for a spaceborne camera
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- XIAN ZHONGKE XIGUANG AEROSPACE TECHNOLOGY GROUP CO LTD
- Filing Date
- 2025-09-03
- Publication Date
- 2026-08-07
AI Technical Summary
该方案的缺陷在于：a)锁紧释放机构增加了大量额外的质量和复杂度；b)火工品解锁过程会产生新的冲击，对相机造成二次风险；c)一旦解锁，无法再次锁紧，若卫星需要进行大机动变轨，相机将面临风险
[0015]与现有技术相比，本实用新型在箭体固定具有空腔的缸体，缸体内设置活塞，活塞与缸体的空腔内壁活动且密封连接，从而将缸体的空腔分隔为两个密闭的腔体，在两个腔体内均填充磁流变液，且在活塞设置电磁单元，电磁单元电连接至箭体的控制系统，活塞连接活塞杆，活塞杆的端部从缸体一端的开口伸出，将相机安装于活塞杆伸出缸体的端部，从而通过缸体、活塞、活塞杆、电磁单元以及缸体空腔内的磁流变液形成了一个磁流变缓冲的支撑装置。从而在发射或刚性锁定模式下，通过在发射前利用控制系统向电磁单元施加高强度直流电流，电磁单元产生强大磁场，使缸体内的磁流变液在毫秒级时间内由液体迅速转变为高强度的半固体状态，其剪切屈服强度剧增。此时，活塞相对于缸体的运动被极大地约束，整个装置表现为一根高刚度的刚性连杆，将相机牢牢固定在箭体、卫星平台等飞行器上，以抵抗发射时的剧烈振动和冲击。在轨或柔性隔振模式下，当箭体、卫星等飞行器进入预定轨道后，控制系统根据地面指令或自主程序，将施加于电磁单元的电流减小至零或一个极小的维持值。磁场消失，磁流变液恢复到低粘度的液体状态。此时，活塞可在缸体内自由运动，仅受液体自身粘滞阻力的影响，整个装置表现为一个低刚度、高阻尼的柔性隔振器，能够有效吸收和耗散来自箭体、卫星等飞行器的微振动，为相机提供一个平静的力学环境。本实用新型能够根据具体实际需求改变自身刚度和阻尼，从而适应发射和在轨工作的双重需求。
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Figure CN224606916U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of precision payload support technology for spacecraft, specifically to an adaptive stiffness and damping composite support device for spaceborne cameras. Background Technology
[0002] Optical payloads such as spaceborne cameras face drastically different mechanical environments throughout their lifecycle: During launch, the launch vehicle generates intense low-frequency, high-amplitude vibrations and significant overload shocks. At this stage, the support structure must possess extremely high stiffness and strength to securely "lock" the camera to the satellite platform, preventing structural damage or excessive displacement. In the on-orbit environment, while the orbital environment itself is quasi-static, moving components on the satellite platform, such as reaction wheels, control moment gyroscopes, and cryogenic pumps, generate continuous high-frequency, low-amplitude micro-vibrations. These micro-vibrations are a critical factor affecting the quality of ultra-high-resolution imaging, requiring the support structure to have extremely low stiffness (i.e., very "flexible") and appropriate damping to effectively isolate these micro-vibrations.
[0003] Existing technical solutions mainly include passive vibration isolation and locking-release solutions. Passive vibration isolation uses metal springs or rubber dampers. The stiffness and damping of this solution are fixed, requiring a compromise between launch load capacity and on-orbit vibration isolation performance, and cannot simultaneously meet both extreme requirements. The locking-release solution is currently the mainstream approach. It involves designing an independent, high-rigidity locking device for the camera during launch, and then unlocking it after orbit insertion using a one-time method such as pyrotechnic explosion or melting a metal wire, "releasing" the camera onto a flexible on-orbit isolator. The drawbacks of this solution are: a) the locking-release mechanism adds significant additional mass and complexity; b) the pyrotechnic unlocking process generates new impacts, posing a secondary risk to the camera; c) once unlocked, it cannot be locked again, posing a risk to the camera if the satellite needs to perform large maneuvers. Currently, there is no highly integrated support device capable of seamlessly and repeatedly switching between the two extreme modes of "rigid lock-on at launch" and "flexible isolation on-orbit." Summary of the Invention
[0004] To address the problems in the existing technology, this utility model provides an adaptive stiffness and damping composite support device for spaceborne cameras, which can change its stiffness and damping according to specific actual needs, thereby adapting to the dual requirements of launch and on-orbit operation.
[0005] To achieve the above objectives, the technical solution adopted by this utility model is as follows: It includes a cavity-shaped cylinder, which is fixed to the arrow body. The first end of the cylinder is open, and the second end is sealed. A piston is disposed within the cavity of the cylinder, and the piston is movably and sealingly connected to the inner wall of the cavity. The piston divides the cavity of the cylinder into a sealed first cavity and a second cavity. Both the first cavity and the second cavity are filled with magnetorheological fluid. The piston is equipped with an electromagnetic unit, which is electrically connected to the control system of the arrow body. The piston is connected to a piston rod, one end of which is connected to the piston, and the other end of which extends from the opening at the first end of the cylinder. The piston rod is movably and sealingly connected to the inner wall of the cavity. A camera is mounted on the end of the piston rod extending out of the cylinder.
[0006] Furthermore, the piston has a mounting groove, and the mounting groove is located near the second end of the cylinder body, and the electromagnetic unit is mounted in the mounting groove.
[0007] Furthermore, the electromagnetic unit includes an excitation coil, which is electrically connected to the control system of the rocket body, and the excitation coil is wound inside the mounting groove.
[0008] Furthermore, a gap is provided between the outer wall of the piston near the second end of the cylinder and the inner wall of the second cavity, forming a damping gap to facilitate the flow of magnetorheological fluid.
[0009] Furthermore, an elastic element is connected between the piston and the cylinder, and the elastic element is configured to give the piston a tendency to move toward a set position.
[0010] Furthermore, the elastic element includes a spring plate, which is sleeved on the first end of the piston near the cylinder body, and the spring plate is tightly connected to the inner wall of the cavity of the cylinder body.
[0011] Furthermore, the elastic element includes a compression spring, which is sleeved at the first end of the piston near the cylinder body. Both the first end of the piston near the cylinder body and the inner wall of the cylinder body are provided with retaining plates, and the two ends of the compression spring abut against the retaining plates respectively.
[0012] Furthermore, a compensation airbag is provided in the second cavity, and the compensation airbag is located near the second end of the cylinder.
[0013] Furthermore, the first end cover of the cylinder body is provided with a cylinder cover, the opening is provided on the cylinder cover, and a sealing element is provided at the opening and at the position of the piston near the first end of the cylinder body. The sealing element is sealed to the inner wall of the cavity of the cylinder body.
[0014] Furthermore, guides are provided at the opening and at the first end of the piston near the cylinder.
[0015] Compared with existing technologies, this invention features a cylinder with a cavity fixed to the rocket body. A piston is installed inside the cylinder, and the piston is movable and sealed to the inner wall of the cylinder cavity, thus dividing the cylinder cavity into two sealed chambers. Both chambers are filled with magnetorheological fluid. An electromagnetic unit is installed on the piston, which is electrically connected to the rocket's control system. The piston is connected to a piston rod, the end of which extends from an opening at one end of the cylinder. A camera is mounted on the end of the piston rod that extends out of the cylinder. Thus, the cylinder, piston, piston rod, electromagnetic unit, and magnetorheological fluid inside the cylinder cavity form a magnetorheological buffer support device. Therefore, in launch or rigid lock-up mode, by applying a high-intensity DC current to the electromagnetic unit using the control system before launch, the electromagnetic unit generates a strong magnetic field, causing the magnetorheological fluid inside the cylinder to rapidly transform from a liquid to a high-strength semi-solid state within milliseconds, resulting in a dramatic increase in its shear yield strength. At this point, the piston's movement relative to the cylinder is greatly constrained. The entire device functions as a high-rigidity rigid connecting rod, firmly fixing the camera to the rocket body, satellite platform, or other spacecraft to resist the severe vibrations and impacts during launch. In on-orbit or flexible vibration isolation mode, once the rocket body, satellite, or other spacecraft enters the predetermined orbit, the control system, according to ground commands or autonomous programs, reduces the current applied to the electromagnetic unit to zero or a very small sustaining value. The magnetic field disappears, and the magnetorheological fluid returns to a low-viscosity liquid state. At this time, the piston can move freely within the cylinder, only affected by the viscous resistance of the liquid itself. The entire device functions as a low-rigidity, high-damping flexible vibration isolator, effectively absorbing and dissipating micro-vibrations from the rocket body, satellite, or other spacecraft, providing a calm mechanical environment for the camera. This invention can adjust its stiffness and damping according to specific practical needs, thereby adapting to the dual requirements of launch and on-orbit operation. Attached Figure Description
[0016] Figure 1 This is a schematic diagram of the structure of this utility model;
[0017] Figure 2 This is a schematic diagram of the installation structure of this utility model;
[0018] Among them, 1 is the arrow body, 2 is the camera, 3 is the support device, 301 is the cylinder, 302 is the piston, 303 is the first cavity, 304 is the second cavity, 305 is the piston rod, 306 is the electromagnetic unit, 307 is the cylinder head, 308 is the guide, 309 is the elastic element, 310 is the sealing element, 311 is the mounting groove, 312 is the compensating airbag, and 313 is the damping clearance. Detailed Implementation
[0019] The present invention will be further explained and described below with reference to the accompanying drawings and specific embodiments. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0020] This invention provides an adaptive stiffness and damping composite support device for spaceborne cameras, relating to precision payload support devices for spacecraft such as rockets and satellites. It is suitable for supporting and installing precision instruments such as spaceborne optical cameras and telescopes. This intelligent support device can actively change the mechanical properties of rockets, satellites, and other spacecraft during the launch phase or the mission phase in orbit. It can achieve shock-free and repeatable switching between two extreme modes: rigid locking at launch and flexible isolation in orbit, and is highly integrated. See details. Figure 1 and Figure 2 The support device 3 includes a hollow cylinder 301, which is fixed to the arrow body 1. The first end of the cylinder 301 is open, and the second end of the cylinder 301 is sealed. A piston 302 is disposed inside the cavity of the cylinder 301. The piston 302 is movable and sealed to the inner wall of the cavity of the cylinder 301. The piston 302 divides the cavity of the cylinder 301 into a sealed first cavity 303 and a second cavity 304. Both the first cavity 303 and the second cavity 304 are filled with magnetorheological fluid. The piston 302 is provided with an electromagnetic unit 306, which is electrically connected to the control system of the arrow body 1. The piston 302 is connected to a piston rod 305. One end of the piston rod 305 is connected to the piston 302, and the other end of the piston rod 305 extends out from the opening at the first end of the cylinder 301. The piston rod 305 is movable and sealed to the inner wall of the cavity of the cylinder 301. A camera 2 is installed at the end of the piston rod 305 that extends out of the cylinder 301.
[0021] This invention features a cylinder 301 with a cavity fixed to the rocket body 1. A piston 302 is installed inside the cylinder 301. The piston 302 is movably and sealingly connected to the inner wall of the cavity of the cylinder 301, thereby dividing the cavity of the cylinder 301 into two sealed cavities. Both cavities are filled with magnetorheological fluid. An electromagnetic unit 306 is installed on the piston 302 and is electrically connected to the control system of the rocket body 1. The piston 302 is connected to a piston rod 305. The end of the piston rod 305 extends out from the opening at one end of the cylinder 301. A camera 2 is installed at the end of the piston rod 305 that extends out of the cylinder 301. Thus, a magnetorheological buffer support device 3 is formed by the cylinder 301, piston 302, piston rod 305, electromagnetic unit 306, and magnetorheological fluid in the cylinder cavity. Thus, in launch or rigid lock-up modes, by applying a high-intensity DC current to the electromagnetic unit 306 using the control system before launch, the electromagnetic unit 306 generates a strong magnetic field, causing the magnetorheological fluid in the cylinder 301 to rapidly transform from a liquid to a high-strength semi-solid state within milliseconds, resulting in a dramatic increase in its shear yield strength. At this time, the movement of the piston 302 relative to the cylinder 301 is greatly constrained, and the entire support device 3 acts as a high-rigidity rigid connecting rod, firmly fixing the camera 2 to the rocket body 1, satellite platform, and other spacecraft to resist the severe vibrations and impacts during launch. In on-orbit or flexible vibration isolation modes, after the rocket body 1, satellite, and other spacecraft enter the predetermined orbit, the control system, according to ground commands or autonomous programs, reduces the current applied to the electromagnetic unit 306 to zero or a very small maintenance value. The magnetic field disappears, and the magnetorheological fluid returns to a low-viscosity liquid state. At this time, piston 302 can move freely within cylinder 301, only affected by the viscous resistance of the liquid itself. The entire support device 3 acts as a low-stiffness, high-damping flexible vibration isolator, effectively absorbing and dissipating micro-vibrations from the rocket body 1, satellite, and other spacecraft, providing a calm mechanical environment for camera 2. This invention can change its stiffness and damping according to specific practical needs, thereby adapting to the dual requirements of launch and on-orbit operation.
[0022] Specifically, the piston 302 has a mounting groove 311, which is located near the second end of the cylinder 301. The electromagnetic unit 306 is mounted in the mounting groove 311. The electromagnetic unit 306 includes an excitation coil, which is electrically connected to the control system of the rocket body 1. The excitation coil is wound within the mounting groove 311. Utilizing the mounting groove 311 to house the wound excitation coil improves the efficiency of electromagnetic conversion, thereby increasing the rate of magnetorheological liquid phase change and enhancing the reliability of this invention. Furthermore, the mounting groove 311 provides a simple structure for housing the excitation coil, making the structure more compact and easier to install. In other embodiments, the excitation coil can also be wound outside or inside the cylinder 301, depending on the specific requirements. The electromagnetic unit 306 can also be any other electromagnetic conversion structure capable of achieving magnetorheological liquid phase change.
[0023] More specifically, a gap is provided between the outer wall of the piston 302 near the second end of the cylinder 301 and the inner wall of the second cavity 304, forming a damping gap 313 to facilitate the flow of magnetorheological fluid. Utilizing the damping gap 313 formed between the piston 302 and the inner wall of the second cavity 304, in on-orbit or flexible vibration isolation modes, the damping gap 313 serves as a channel for the flow of liquid magnetorheological fluid. The flow of the liquid magnetorheological fluid achieves flexible buffering, ensuring effective absorption and dissipation of micro-vibrations caused by the aircraft.
[0024] Specifically, an elastic element 309 is connected between the piston 302 and the cylinder 301. The elastic element 309 is configured to give the piston 302 a tendency to move towards a set position. In on-rail or flexible vibration isolation mode, the elastic element 309 is used to better buffer the movement of the piston 302, and after the micro-vibration is eliminated, the elastic element 309 helps to better maintain the reliable reset of the piston 302.
[0025] Preferably, the elastic element 309 includes a spring plate, which is sleeved on the first end of the piston 302 near the cylinder 301, and the spring plate is tightly connected to the inner wall of the cavity of the cylinder 301, that is, the spring plate is interference-fitted with the inner wall of the cavity of the cylinder 301, or a groove or other structure is provided on the inner wall of the cavity of the cylinder 301 to achieve the connection of the spring plate through the groove.
[0026] Of course, the elastic element 309 may also include a compression spring, which is sleeved at the first end of the piston 302 near the cylinder 301. Both the first end of the piston 302 near the cylinder 301 and the inner wall of the cylinder 301 are provided with retaining plates. The two ends of the compression spring abut against these retaining plates, thus securing the compression spring in place. The elastic element 309 may also include tension springs, torsion springs, and other elastic components, selected according to actual needs; no specific limitations are made here.
[0027] Preferably, a compensating airbag 312 is provided in the second cavity 304, and the compensating airbag 312 is located near the second end of the cylinder 301. In the on-rail or flexible vibration isolation mode, if the rocket body 1 suddenly experiences a large vibration, the piston 302 may experience a large displacement. At this time, the compensating airbag 312 provides a buffering effect to minimize the violent movement of the piston 302, prevent the piston 302 from touching the end of the cylinder 301, and avoid damage to the support device 3 or camera 2.
[0028] Specifically, the first end cap of the cylinder body 301 is provided with a cylinder cover 307, with an opening located in the cylinder cover 307. A sealing element 310 is provided at the opening and at the position of the piston 302 near the first end of the cylinder body 301. The sealing element 310 is sealed to the inner wall of the cavity of the cylinder body 301. By ensuring the sealing element 310, reliable sealing is achieved between the piston rod 305 and the opening of the cylinder cover 307, and between the first end of the piston 302 near the cylinder body 301 and the inner wall of the cavity of the cylinder body 301, preventing leakage of the magnetorheological fluid and improving the stability of the device. The sealing element 310 can be an oil seal or other sealing ring; however, considering the harsh operating conditions of spacecraft, aerospace-grade sealing elements are preferred to improve the reliability and stability of the device.
[0029] Specifically, guide members 308 are provided at the opening and at the first end of the piston 302 near the cylinder 301. These guide members provide reliable guidance between the piston rod 305 and the opening of the cylinder head 307, and between the first end of the piston 302 and the inner wall of the cavity of the cylinder 301. This ensures smooth and stable movement of the piston rod 305 and the piston 302, guaranteeing the buffering effect of the piston rod 305 and the piston 302 in on-rail or flexible vibration isolation modes.
[0030] This invention uses a cylinder 301 as the outer shell and main load-bearing structure of the support device 3, which is installed on the rocket body 1. A piston 302 is movable within the cylinder 301. One end of the piston rod 305 extends out of the cylinder 301 and connects to the interface of the camera 2, while the other end connects to the piston 302. Magnetorheological fluid is filled in the cavities of the cylinder 301 on both sides of the piston 302. An excitation coil is precisely wound around the piston 302 inside the cylinder, generating a magnetic field that passes through the intelligent fluid cavity. The excitation coil is electrically connected to a control system. The control system receives telemetry commands from the rocket body 1 or a spacecraft platform such as a satellite, and controls the current of the excitation coil according to specific operating conditions to adjust the magnetic field strength under different conditions. This allows for control of different viscosities of the magnetorheological fluid, adapting to the damping adjustment of the camera 2 under different vibration conditions. Multiple support devices 3 of this invention can be installed on the rocket body 1 or other spacecraft to meet the installation requirements of multiple cameras 2.
[0031] This utility model's support device 3 serves two purposes in one highly integrated unit, perfectly combining launch locking and on-orbit vibration isolation into a single device. It replaces the complex combination of locking mechanism and vibration isolator, greatly simplifying system design and reducing structural weight. It is impact-free and repeatedly switchable; stiffness and damping changes are controlled by electromagnetic fields, resulting in a smooth process without any mechanical impact, avoiding the risks associated with unlocking pyrotechnic devices. Furthermore, the process is completely reversible; the camera can be locked again at any time according to mission requirements (such as during high-speed maneuvers), and unlocked again after the mission is completed, providing extremely high mission flexibility. Its performance is adjustable and actively optimized. During on-orbit operation, the damping characteristics of the device can be actively changed by finely adjusting the coil current to suppress vibration sources of specific frequencies, achieving a vibration isolation effect superior to traditional passive vibration isolators. It is inherently safe; in the worst-case scenario, if the control system loses power, the device will automatically enter a magnetic field-free flexible vibration isolation mode. This ensures that even in the event of a failure, the device can maintain its core on-orbit function, safeguarding the main mission objectives.
[0032] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and not to limit it; although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this utility model.
Claims
1. An adaptive stiffness and damping composite support device for a spaceborne camera, characterized in that, The device includes a hollow cylinder (301) fixed to the arrow body (1). The first end of the cylinder (301) is open, and the second end is sealed. A piston (302) is disposed within the cavity of the cylinder (301). The piston (302) is movably and sealingly connected to the inner wall of the cavity of the cylinder (301). The piston (302) divides the cavity of the cylinder (301) into a sealed first cavity (303) and a second cavity (304). Both the first cavity (303) and the second cavity (304) are filled with magnetorheological agents. The piston (302) is equipped with an electromagnetic unit (306), which is electrically connected to the control system of the rocket body (1). The piston (302) is connected to a piston rod (305). One end of the piston rod (305) is connected to the piston (302), and the other end of the piston rod (305) extends out from the opening at the first end of the cylinder (301). The piston rod (305) is movably and sealingly connected to the inner wall of the cavity of the cylinder (301). A camera (2) is installed at the end of the piston rod (305) that extends out of the cylinder (301).
2. The adaptive stiffness and damping composite support device for a spaceborne camera according to claim 1, characterized in that, The piston (302) has a mounting groove (311), and the mounting groove (311) is located near the second end of the cylinder (301). The electromagnetic unit (306) is mounted in the mounting groove (311).
3. The adaptive stiffness and damping composite support device for a spaceborne camera according to claim 2, characterized in that, The electromagnetic unit (306) includes an excitation coil, which is electrically connected to the control system of the rocket body (1) and is wound in the mounting groove (311).
4. The adaptive stiffness and damping composite support device for a spaceborne camera according to claim 1, characterized in that, A gap is provided between the outer wall of the piston (302) near the second end of the cylinder (301) and the inner wall of the second cavity (304), and a damping gap (313) is formed between the outer wall of the piston (302) near the second end of the cylinder (301) and the inner wall of the second cavity (304) to facilitate the flow of magnetorheological fluid.
5. The adaptive stiffness and damping composite support device for a spaceborne camera according to claim 1, characterized in that, An elastic element (309) is connected between the piston (302) and the cylinder (301), and the elastic element (309) is configured to cause the piston (302) to have a tendency to move toward a set position.
6. The adaptive stiffness and damping composite support device for a spaceborne camera according to claim 5, characterized in that, The elastic element (309) includes a spring plate, which is sleeved on the piston (302) at the first end near the cylinder (301), and the spring plate is tightly connected to the inner wall of the cavity of the cylinder (301).
7. The adaptive stiffness and damping composite support device for a spaceborne camera according to claim 5, characterized in that, The elastic element (309) includes a compression spring, which is sleeved on the piston (302) at the first end near the cylinder (301). The piston (302) at the first end near the cylinder (301) and the inner wall of the cavity of the cylinder (301) are both provided with retaining plates, and the two ends of the compression spring abut against the retaining plates respectively.
8. The adaptive stiffness and damping composite support device for a spaceborne camera according to claim 1, characterized in that, The second cavity (304) is provided with a compensation airbag (312), and the compensation airbag (312) is located near the second end of the cylinder (301).
9. The adaptive stiffness and damping composite support device for a spaceborne camera according to claim 1, characterized in that, The first end of the cylinder body (301) is covered with a cylinder cover (307), the opening is provided on the cylinder cover (307), and a sealing element (310) is provided at the opening and at the position of the piston (302) near the first end of the cylinder body (301). The sealing element (310) is sealed to the inner wall of the cavity of the cylinder body (301).
10. The adaptive stiffness and damping composite support device for a spaceborne camera according to claim 9, characterized in that, Guide members (308) are provided at the opening and at the first end of the piston (302) near the cylinder (301).