Time-varying rotational inertia considered adaptive fault tolerance control method of spacecraft attitude tracking

Abstract

The invention relates to a time-varying rotational inertia considered adaptive fault tolerance control method of spacecraft attitude. The method comprises that a dynamic spacecraft attitude tracking model which does not take faults of a performer into consideration but includes external disturbance and a time-varying rotational inertia is established, and a time-varying rotational inertia model isestablished; and on the basis of the dynamic spacecraft attitude tracking model, a nominal controller and corresponding adaptive laws are designed, and the system stability and tracking error convergence without faults are ensured; and the performance fault is added to the dynamic spacecraft attitude tracking model, an auxiliary controller is designed on the basis of the nominal controller, the problem that a fault occurs in the performer, the time-varying rotational inertia exists and the spacecraft is influenced by an external disturbance moment during on-orbit work of the spacecraft is solved, and the fault tolerant capability and robustness of the system are ensured.

Description

technical field [0001] The invention relates to the technical field of spacecraft control, in particular to a spacecraft attitude tracking adaptive fault-tolerant control method considering time-varying moments of inertia. Background technique [0002] The vigorous development of the aerospace industry has played an important role in the national economy and social development. In the first half of 2017, the "Tianzhou-1" cargo spacecraft was successfully launched and successfully completed the first in-orbit propellant replenishment with Tiangong-2. In the test, my country's first high-orbit high-throughput communication satellite "Shijian 13" was successfully launched. In the second half of 2017, it is expected to launch two sets of "Beidou-3" global networking satellites and plan to launch "Chang'e-5" lunar exploration instrument, and the multi-payload, high-precision seismic monitoring test satellite "Zhangheng-1". For the purpose of orbit maintenance and self-attitude adj...

AI Technical Summary

Problems solved by technology

[0004] Since the spacecraft attitude tracking process will be subject to the disturbance force of the space environment, the change of the moment of inertia caused by fuel consumption, and the problem that the actuator may fail, the purpose of the present invention is to overcome the deficiencies of the prior art and provide a The spacecraft attitude tracking adaptive fault-tolerant control method considering the time-varying moment of inertia is mainly used in the case of actuator failures when satellites are in orbit and are subject to external disturbance moments from space and time-varying moments of inertia due to fuel consumption. The attitude tracking control system solves the problem that the actuator fails when the spacecraft is in orbit and there is a time-varying moment of inertia and is affected by the external disturbance moment, ensuring the fault tolerance and robustness of the system

Images