Orbit-Attitude Coupled Tracking and Landing Control for an Asteroid

• Published in: IOP conference series. Materials Science and Engineering Vol. 685; no. 1; pp. 12003 - 12008
• Main Authors: Zhu, Lingchao, Wang, Shuquan
• Format: Journal Article
• Language: English
• Published: Bristol IOP Publishing 01.11.2019
• Subjects: Asteroid detection; Asteroid mining; Asteroid missions; Attitudes; Hovering; Inner solar system; Landing; Nonlinear control; Space exploration; Spacecraft; Spacecraft tracking; Thrust control; Thrusters; Tracking control
• ISSN: 1757-8981; 1757-899X
• DOI: 10.1088/1757-899X/685/1/012003

Recent research on asteroid exploration has shown tremendous potential to provide humankind detailed views of unexplored worlds in the inner solar system. A potential market of asteroid mining has aroused interest from commercial companies gradually. Asteroid exploration has the potential to offer the possibility to revolutionize the supply of many resources which are vital but exorbitant for human. A typical asteroid exploration mission is composed of remote asteroid detecting, approaching, hovering, landing and sampling, take-off and return, re-entry stage. Among these stages the tracking and landing control of the asteroid is crucial for the exploration. Rendezvous, approaching, fly-around and landing problem of an asteroid is investigated in this paper. The expected motion of the tracking spacecraft determined by the asteroid' orbital and attitude status is presented firstly. According to the design of the OSIRIS-REx project, several constant thrusters are used for spacecraft to track the asteroid. Different control strategies like pulse control, saturated nonlinear control, limit cycle control and PWM based low-thrust control are developed to fulfil the asteroid's tracking mission of different stages. Numerical simulations demonstrate the effectiveness of the tracking control.