Launch section vibration attenuation and orbital section vibration isolation integrated load supporting device

Abstract

The invention provides a launch section vibration attenuation and orbital section vibration isolation integrated load supporting device which can realize the variable stiffness requirements of high stiffness and high damping in a launch section and low stiffness and low damping in an orbit section, can realize launch section vibration attenuation and orbital section vibration isolation function integration and meanwhile has the very high reliability. The launch section vibration attenuation and orbital section vibration isolation integrated load supporting device comprises a load platform, a vibration isolation module and a connection support module. The upper and lower ends of the vibration isolation module are connected to the load platform and the connection support module, the vibration isolation module is of a closed parallel structure, and the requirements of the launch section for the large load and the high reliability of the mechanical environments can be realized. Meanwhile,symmetrical and inclined support design is adopted, the three-dimensional equal stiffness and equal fundamental frequency function in a space coordinate system is achieved, and the good stability is achieved. By bidirectionally adjusting the compression of a gel vibration isolation component, the variable stiffness design requirements are met, and the strong adaptability to the complex space mechanical environments is achieved. The supporting device is light in weight, small in size, simple in structure, low in manufacturing cost and broad in application prospect.

Description

technical field [0001] The invention relates to a load support device, in particular to a load support device used for the integration of anti-mechanical environment and on-orbit vibration isolation in a spacecraft, and belongs to the technical field of spacecraft vibration reduction and isolation. Background technique [0002] With the rapid development of spacecraft technology, the accuracy, sensitivity and complexity of spacecraft payloads continue to increase. On the one hand, during the launch phase, it is necessary to reduce the vibration level of the payload installation to prevent the vibration environment caused by the rocket from affecting the high Precision loads cause damage; on the other hand, during the on-orbit working phase, it is necessary to reduce the micro-vibration interference generated by moving parts on the star (such as control moment gyro, reaction wheel, solar wing drive mechanism, etc.) to ensure that the accuracy of the payload meets the requireme...

AI Technical Summary

Problems solved by technology

[0006] (1) Only increase the bearing capacity but cannot take into account the variable stiffness, and the applicable environment is limited

Although the traditional vibration isolator uses vibration isolation springs connected in parallel with rubber to increase its load-carrying capacity, it cannot achieve variable stiffness adjustment, which in turn leads to the inability to achieve natural frequency adjustment in complex mechanical environments, and the application environment is limited.

However, adding active control links to achieve variable stiffness and variable damping functions can effectively improve adaptability, but at the same time increases the complexity of the system, thereby reducing reliability.

[0007] (2) The low-order natural frequency distribution is scattered, and the effect of vibration reduction and isolation is not ideal

Due to the scattered natural frequency distribution of the existing vibration isolator, it is impossible to effectively avoid the above-mentioned interference frequency points, and it is easy to couple and resonate with the entire star structure and payload

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