Three-axis L1 adaptive attitude control of spacecraft using solar radiation pressure

Abstract

Based on the [Formula: see text] adaptive control theory, a novel three-axis attitude control system for an axisymmetric spacecraft with uncertain dynamics moving in elliptic orbits, using solar radiation pressure, is derived. The nonaffine-in-control nonlinear spacecraft model includes the gravity gradient torque, the control torque produced by four solar flaps, and external time-varying disturbance moments. For the three-axis attitude control, an [Formula: see text] adaptive control system is designed, which includes a state predictor. A smooth projection algorithm is used to confine the estimated parameters within a desirable set. In the closed-loop system, the designed adaptive law accomplishes three-dimensional attitude control. A special feature of the attitude control system is that it is possible to select large adaptation gains for fast adaptation and to obtain quantifiable performance bounds. Simulation results show that in the closed-loop system, precise roll, yaw, and pitch angle control is accomplished, despite unmodeled nonlinearities, parameter uncertainty, and external disturbance inputs in the model.

Model Predictive Control-Based Attitude Control of Under-Actuated Spacecraft Using Solar Radiation Pressure

“…For high-orbiting spacecraft, the main environmental torque is the solar radiation pressure (SRP) which cannot be ignored. Lee studied the stable control of the pitch axis of the spacecraft by using only the solar pressure torque [25,26]. The Kepler telescope lost two out of its four RWs before its mission was completed, and the small thrusters and SRP torque were used to assist the attitude control [27].…”

Robust adaptive attitude manoeuvre control with finite-time convergence for a flexible spacecraft

“…In recent years, a great deal of attention has been paid to the robust attitude control of spacecraft and several nonlinear control methods have been proposed, such as adaptive control, sliding mode control and active disturbance rejection control (Chen and Huang, 2009, 2014; Hu et al, 2008; Lai et al, 2012; Lee and Singh, 2015; Li et al, 2014; Zhong et al, 2013). Although these nonlinear control laws have shown adequate effectiveness and robustness in spacecraft attitude control systems, they can only guarantee asymptotic convergence, i.e.…”