A space station solar wing simulation load test system

Abstract

The invention discloses a space station solar wing simulated load test system. The space station solar wing simulated load test system comprises a driving locking module, a switching locking module and a display module, wherein an input end of the driving locking module is connected with a first output end of a driving controller; a first output end of the driving locking module is connected witha first input end of the driving controller; the driving locking module tests a driving locking control function and feeds back a result to the driving controller; an input end of the switching locking module is connected with a second output end of the driving controller; a first output end of the switching locking module is connected with a second input end of the driving controller; the switching locking module tests a switching locking control function and feeds back a result to the driving controller; and the display module is respectively connected with a second output end of the drivinglocking module and a second output end of the switching locking module, and monitors a first test result and a second test result. According to the space station solar wing simulated load test system, problems of difficulty and single-flow test of a space station solar wing simulated load test technology are solved, two flow tests of driving locking control and switching locking control are combined, the easy operation of the space station solar wing ground simulated load test is implemented, and test efficiency is improved.

Description

technical field [0001] The invention relates to the field of space station technology, in particular to a space station solar wing simulation load test system. Background technique [0002] The space station is a large-scale model project in the field of space science with completely independent intellectual property rights in my country. In the past, the solar wings of spacecraft or satellites were relatively small, and the rotation direction was only a single degree of freedom around the central axis of the solar wing. The control difficulty and complexity were relatively simple, and the control technology for small single-degree-of-freedom solar wings was relatively mature, and the ground verification was relatively simple. [0003] However, for the solar wing of the space station experiment module, it not only has the characteristics of large size, large inertia, and large flexibility, but also has a prominent feature that it can rotate around the central axis of the exp...

AI Technical Summary

Problems solved by technology

This system solves the technical difficulties of the ground simulation load test of the space station's solar wing and can only be tested in a single process. It combines the two major process tests of drive lock control and switching lock control to realize the simple operation of the ground simulation load test of the space station's solar wing and improve Test efficiency

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