Method and system for identifying displacement of satellite flexible attachment on orbit using gyroscope data

Abstract

The invention provides an in-orbit end position displacement method for distinguishing a satellite flexible appendage by gyroscope data. The method comprises the following steps that: attitude angularvelocity obtaining: obtaining attitude angular velocity measurement data [Omega]i(t) corresponding to the i shaft of an underdamping free vibration zone after a satellite is subjected to in-orbit airinjection closed-loop control; filtering: carrying out filtering on the [Omega]i(t) to obtain the filtered attitude angular velocity measurement data [Omega]'i(t) of the i shaft; time sequence calculation: according to the [Omega]'i(t), carrying out calculation to obtain the time sequence [Eta]i(t) of the time sequence of a modal variable; end position displacement calculation: according to the [Eta]i(t) and end position node formation data di, carrying out calculation to obtain the in-orbit vibration end position displacement mi(t) of the satellite flexible appendage. Correspondingly, the invention also provides an in-orbit position displacement system for distinguishing the satellite flexible appendage by the gyroscope data. By use of the method, other sensors do not need to be installed on the flexible appendage, and only the measurement data of the existing attitude sensor of a satellite platform is used for carrying out analytic processing.

Description

technical field [0001] The invention relates to the field of satellite monitoring, in particular to a method and a system for using gyroscope data to identify the displacement of the on-orbit vibration end of a satellite flexible attachment. In particular, it relates to an on-orbit identification method and system for vibration state information of a flexible satellite, in particular to an identification method and system for end displacement of a flexible satellite during on-orbit vibration. Background technique [0002] With the continuous development of aerospace technology, large-scale space structures have become an important development direction in the field of aerospace, and will also be the necessary infrastructure for space development [Research on Identification Technology of Dynamic Parameters of In-orbit Spacecraft—Yu Dengyun]. In order to obtain the dynamic characteristics of flexible satellite structures, finite element modeling, ground tests, and on-orbit ide...

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Problems solved by technology

[0004] The above identification methods of dynamic parameters of flexible satellites in orbit have two constraints in terms of engineering application: one is that it is difficult to apply known excitations required for dynamic parameter identification on orbiting spacecraft, and only the deployment and retraction of the space structure in orbit can be used. , The docking and separation of the structure, the ignition of the engine, etc. generate excitation sources for excitation, and the signals of these excitation sources are difficult to measure [Research on Identification Technology of Dynamic Parameters of On-orbit Spacecraft——Yu Dengyun]

Second, the number of vibration sensors installed on flexible accessories is limited by engineering implementation

Generally, flexible accessories need to be deployed on rails, and the installation and fixing of various speed, acceleration, and displacement sensors, as well as cable laying, will have adverse effects on the deployment mechanism, increasing the difficulty of design

In addition, for rotating flexible components such as solar arrays, it is necessary to increase the number of signal channels of the drive mechanism slip ring

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