Patent ID: 9694918
Date: 2017-07-04
CPC Classifications: B64G

Claim:
1. A method for disturbance compensation based on a sliding mode disturbance observer for a spacecraft with a large flexible appendage, comprising the following steps of: a) building a spacecraft attitude control system Σ b) constructing an external system Σ wherein, the external system Σ (1) incorporating an uncertain portion C in which, C (2) defining state variables w in which, I is a unit matrix, and a matrix G=(I−δJ (3) defining the following coefficient matrix: (4) the external system Σ in which, w=[w c) configuring a sliding mode disturbance observer for estimating the value of the sum of flexible vibration and environmental disturbance; d) compounding a nominal controller with the sliding mode disturbance observer in step c) to obtain a compound controller; the compound controller compensating for the sum of flexible vibration and environmental disturbance according to the estimated value of the sum of flexible vibration and environmental disturbance.