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|1. (WO2018176877) ON-ORBIT FAULT COUNTERMEASURE METHOD USING OPTIMIZED CONTROL MODE FOR DYNAMICS OF SATELLITE WITH MULTIPLE FLEXIBLE APPENDAGES|
|Applicants:||CHINA ACADEMY OF SPACE TECHNOLOGY
|Title:||ON-ORBIT FAULT COUNTERMEASURE METHOD USING OPTIMIZED CONTROL MODE FOR DYNAMICS OF SATELLITE WITH MULTIPLE FLEXIBLE APPENDAGES|
Disclosed is an on-orbit fault countermeasure method using an optimized control mode for dynamics of a satellite with multiple flexible appendages. According to the method, a three-axis attitude controller of a satellite with multiple flexible appendages employs a long-life gyroscope in a normally open operating mode to provide the attitude controller with attitude angular speed information, thereby improving the ability of the three-axis attitude controller to cope with a decrease in a characteristic frequency of the satellite with multiple flexible appendages. The present invention can resolve a low-probability fault in which, in a launching environment, the rigidity of a coupling link of a large flexible appendage of a satellite decreases greatly. Said fault causes significant decreases in both a system frequency of the satellite in an on-orbit free state and a constraint frequency of the corresponding large flexible appendage, such that an original theoretical allowance range of a control system can be exceeded, and safe on-orbit operation of the satellite is put at risk. The present invention can rapidly determine whether a characteristic frequency of a flexible appendage has changed, determine whether the change is within an allowance range, and if the allowance range is exceeded, rapidly switch to an offset characteristic modal frequency control mode and realize system reconfiguration, thereby ensuring satellite safety and user requirements.