A Station-Keeping Control Strategy for a Symmetrical Spacecraft Utilizing Hybrid Low-Thrust Propulsion in the Heliocentric Displaced Orbit

• Published in: Symmetry (Basel) Vol. 15; no. 8; p. 1549
• Main Authors: Zhang, Tengfei, Mu, Rongjun, Zhou, Yilin, Liao, Zizheng, Zhang, Zhewei, Liao, Bo, Yao, Chuang
• Format: Journal Article
• Language: English
• Published: Basel MDPI AG 01.08.2023
• Subjects: Accuracy; Adaptive control; Analysis; Controllers; Cylindrical coordinates; Design; Disturbances; Energy consumption; improved integral sliding surface; multivariate super-twisting sliding mode approaching law; Neural networks; Orbital mechanics; Orbits; Propellant consumption; Radial basis function; radial basis function neural network; Radiation; Solar electric propulsion; solar sail spacecraft; Solar sails; Space ships; Space vehicles; Spacecraft; Spacecraft propulsion; Stability analysis; station-keeping; Stationkeeping; Sun; Thrust; Tracking errors; China
• ISSN: 2073-8994; 2073-8994
• DOI: 10.3390/sym15081549

The solar sail spacecraft utilizing a hybrid approach of solar sail and solar electric propulsion in the heliocentric displaced orbit is affected by external disturbances, internal unmodeled dynamics, initial injection errors, and input saturation. To solve the station-keeping control problem under such complex conditions, an adaptive control strategy is proposed. First, the dynamical equations of the spacecraft utilizing hybrid low-thrust propulsion in the cylindrical coordinate system are derived. Second, the combined disturbance acceleration introduced by external disturbances and internal unmodeled dynamics is constructed, and a radial basis function neural network estimator is designed to estimate it online in real time. Third, an adaptive high-performance station-keeping controller based on an improved integral sliding surface and multivariate super-twisting sliding mode approaching law is designed. Then, stability analysis is conducted using Lyapunov theory, adaptive laws are designed, and the introduced virtual control accelerations are converted into actual control variables. Finally, simulations are conducted under different simulation conditions based on the disturbance sources. The results show that although the use of hybrid low-thrust propulsion breaks the symmetry of the solar sail in configuration, the proposed control strategy can effectively achieve the station-keeping and disturbance estimation of the spacecraft with only a small amount of propellant consumed and position tracking errors up to decimeters.