On-orbit fault countermeasure method based on multi-flexible appendage satellite dynamics optimization control mode

Abstract

The invention provides an on-orbit fault countermeasure method based on a multi-flexible appendage satellite dynamics optimization control mode. The on-orbit fault countermeasure method comprises the following steps that a three-axis attitude controller of a multi-flexible appendage satellite adopts a long-life gyroscope in a normal-on mode, attitude angular speed information is provided for the attitude controller, and the capacity of the three-axis attitude controller for coping with characteristic frequency lowering of the multi-flexible appendage satellite is improved. The on-orbit fault countermeasure method based on the multi-flexible appendage satellite dynamics optimization control mode solves the problems that in the launching environment, the small-probability fault of great reducing of stiffness of a satellite large flexible appendage connecting link occurs, the fault causes great lowering of the system frequency of a satellite under an on-orbit free state and the constraint frequency of a corresponding large flexible appendage, the original theoretical allowance range of a control system can be exceeded, and therefore satellite on-orbit safe operating is menaced. According to the on-orbit fault countermeasure method based on the multi-flexible appendage satellite dynamics optimization control mode, whether the flexible appendage characteristic frequency is changed or not can be found as soon as possible, whether the flexible appendage characteristic frequency is within the allowance range or not is determined, if the flexible appendage characteristic frequency exceeds the allowance, the flexible appendage characteristic frequency needs to shift into a control mode of the offset characteristic mode frequency in time to achieve system reconfiguration, and satellite safety and user requirements are ensured.

Description

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AI Technical Summary

Benefits of technology

This patented technology describes an aircraft navigation aid called flexibility attached devices (FUSE). These FUSE's have multiple sensors like accelerometers or magnetometer units embedded within them. When they detect any changes made by external factors such as gravity or magnetic field strength, their data will change accordingly. If these measurements indicate deviations beyond acceptable limits, indicating potential issues during flight, then certain commands may trigger a resetting process. To avoid this issue, there should always keep track of how well the device operates at all times based upon its own internal state variables.

Problems solved by technology

This patented technical problem addressed in this patents relates to improving the flight quality or mission lifetime of space vehicles equipped with flexure attachings attached thereto without compromising their ability to maintain proper orientation and behavior under extreme environmental stress such as high altitudes.

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