Variable-rigidity large-bearing vibration isolator suitable for vibration isolation of satellite equipment

Abstract

The invention discloses a variable-rigidity large-bearing vibration isolator suitable for vibration isolation of satellite equipment. The vibration isolator is mainly composed of a vibration isolationmodule, a rope module and a connecting module. The vibration isolation module is located in the vibration isolator, and the rope module is connected with the connecting module to form a bearing pathconnected with the vibration isolation module in parallel. The lower end and the lower end of the connecting module are connected with satellite equipment and a satellite structure correspondingly. The rope module has the advantages of being large in bearing capacity and high in rigidity under large deformation and can well adapt to the large-load environment in the launching process. The vibration isolation module has the advantages of being high in damping and low in rigidity under micro-deformation, and can well meet the efficient vibration isolation requirement in the on-orbit stage. The vibration isolator is simple in structure, good in space environment adaptability, high in reliability, light in weight and wide in application prospect.

Description

technical field [0001] The invention discloses a variable stiffness vibration isolator used for satellite equipment vibration isolation, belonging to the technical field of spacecraft vibration reduction and isolation. Background technique [0002] With the rapid development of aerospace technology, the accuracy, sensitivity and complexity of satellite equipment are constantly increasing. On the one hand, in the strong vibration environment during the launch phase, the satellite equipment installation structure needs to have high rigidity and large load-bearing capacity to withstand load, and prevent the high-precision equipment from being damaged by the strong vibration load caused by the rocket; on the other hand, during the on-orbit working stage after the satellite is in Control the micro-vibration interference caused by the normal operation of the torque gyroscope, reaction wheel, solar wing drive mechanism, etc., to ensure the realization of high-precision indicators o...

AI Technical Summary

Problems solved by technology

The first method needs to reduce the vibration isolation performance requirements of the in-orbit segment, which is difficult to meet the current and future satellite performance requirements and equipment precision is getting higher and higher

For the second method, its system is complex, consumes a lot of power, and its life and reliability are usually low, and the cost of use is high, which greatly limits its engineering application

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