期刊
IEEE TRANSACTIONS ON CONTROL SYSTEMS TECHNOLOGY
卷 23, 期 4, 页码 1638-1647出版社
IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC
DOI: 10.1109/TCST.2014.2379639
关键词
Constraints; model predictive control; obstacle avoidance; rendezvous and docking; spacecraft control
资金
- American Society for Engineering Education through the Air Force Summer Faculty Fellow Program
- National Science Foundation through the University of Michigan, Ann Arbor, MI, USA, [1130160]
- Div Of Civil, Mechanical, & Manufact Inn
- Directorate For Engineering [1130160] Funding Source: National Science Foundation
This paper presents a strategy and case studies of spacecraft relative motion guidance and control based on the application of linear quadratic model predictive control (MPC) with dynamically reconfigurable constraints. The controller is designed to transition between the MPC guidance during a spacecraft rendezvous phase and MPC guidance during a spacecraft docking phase, with each phase having distinct requirements, constraints, and sampling rates. Obstacle avoidance is considered in the rendezvous phase, while a line-of-sight cone constraint, bandwidth constraints on the spacecraft attitude control system, and exhaust plume direction constraints are addressed during the docking phase. The MPC controller is demonstrated in simulation studies using a nonlinear model of spacecraft orbital motion. The implementation uses estimates of spacecraft states derived from relative angle and range measurements, and is robust to estimator dynamics and measurement noise.
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