Unfolding device achieving high precision, miniaturization and high torque output

Abstract

The invention provides an unfolding device achieving high precision, miniaturization and high torque output. The unfolding device comprises a stepping motor, a planetary gear reducer, a harmonic reducer, a rotary transformer, an output shaft, a male hinge and a shell; the stepping motor is used for providing driving power, the planetary gear reducer and the stepping motor are of an integrated structure, and the planetary gear reducer is connected with the harmonic reducer; the output shaft and the harmonic reducer are of an integrated structure, the output shaft is connected with the male hinge, and the male hinge is used for being connected with a target load; a rotor of the rotary transformer is connected with the output shaft, a stator of the rotary transformer is connected with the shell, and the rotary transformer is used for achieving high-precision control over the output shaft. The unfolding device solves the problems that the requirement for the weight of a driving mechanism is high, the load is heavy, and adaptation to lunar surface high vacuum, large temperature difference and lunar dust environments can not be achieved, the problems cannot be solved in the prior art, and the unfolding device achieves the high precision and adaptation to lunar day working and lunar night existence.

Description

technical field [0001] The invention relates to a deploying and folding device for aerospace vehicles, in particular to a deploying device with high precision, miniaturization and large torque output. Background technique [0002] At present, the known devices for deploying satellite solar wings in place are good both in terms of the maturity of the design technology and the application of the product. However, the prior art is still not satisfied with the deployment device that is suitable for the environment of extreme high and low temperature, high vacuum and lunar dust on the lunar surface, and has high transmission precision and light mechanism weight. [0003] In addition, domestic spacecraft solar cell wing deployment adopts a one-time continuous deployment mechanism (commonly known as passive deployment mechanism), which cannot meet the load of large-area solar wings. [0004] Prior art, its weak point is as follows: [0005] 1. It cannot meet the requirements of ...

AI Technical Summary

Problems solved by technology

[0005]1. It cannot meet the requirements of high weight, large load and high precision of the driving mechanism, and cannot adapt to the environment of high vacuum, large temperature difference, and lunar dust on the lunar surface, as well as lunar and daytime work , the problem of survival on a moonlit night;

[0006]2. The carrying capacity of the deployment is small, which cannot meet the large torque requirements required for the deployment of large-area solar wings

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