Multi-degree-of-freedom micro-gravity assembling and gravity unloading device for satellite large loads

Abstract

The invention discloses a multi-degree-of-freedom micro-gravity assembling and gravity unloading device for satellite large loads. The multi-degree-of-freedom micro-gravity assembling and gravity unloading device comprises a supporting frame, a counterweight support, a counterweight assembly, a hanging device, a steel wire rope and a sensor. The supporting frame is used for bearing the weight of the counterweight support, the counterweight assembly, the hanging device, the loads and the like. The counterweight support is used for supporting the counterweight assembly and changing the direction of the steel wire rope. The steel wire rope is used for connecting the counterweight assembly, the sensor and load hanging points and is used for transmitting the weight of the counterweight assembly. The sensor is used for measuring the load gravity borne by the load hanging points. The micro-gravity assembling and gravity unloading device achieves assembling of the loads under a micro-gravity environment, deformation of a satellite structure platform caused by large-scale load gravity is avoided, and the load assembling precision is improved. The multi-degree-of-freedom micro-gravity assembling and gravity unloading device has the multi-degree-of-freedom adjusting function, can achieve micro-gravity assembling of different satellites and different loads, and is simple in implementation process and high in working efficiency.

Description

technical field [0001] The invention relates to a gravity unloading device, in particular to a multi-degree-of-freedom satellite large-scale load microgravity assembly gravity unloading device. Background technique [0002] With the continuous maturity of satellite technology, the weight and quantity of payloads continue to increase. For example, a certain type of satellite is designed with two large payloads, both of which weigh about 300Kg. According to the simulation analysis results, the weight of the two loads will cause the deformation of the satellite structure platform, resulting in an error of more than 1′ between the installation accuracy and mutual pointing accuracy measured in the ground gravity environment and the installation accuracy and mutual pointing accuracy in the weightless environment. [0003] When installing a single payload satellite, the deformation of the satellite structure platform caused by the gravity of the payload is often ignored, and the in...

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Problems solved by technology

[0005] At present, there is no description or report of the similar technology of the present invention, and no similar data at home and abroad have been collected yet.

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