Abstract Current and future space observation missions need to perform many large-angle, multi-axis slew maneuvers between observations while keeping the scientific instrument’s attitude in a safe region. The state-of-practice typically divides each multi-axis maneuver into a series of single-axis sub-maneuvers, each of which is computed by restricting its guidance solution to the exact spacecraft momentum capacity. This ensures that the constraints are explicitly considered and results in a simple on-board implementation of the guidance algorithm, but is time-consuming and non-optimal for the whole multi-axis maneuver. Addressing this issue, this article presents a novel analytical guidance approach that relies on the convexity of the permissible attitude zone. The proposed guidance is time-optimal for a given spacecraft design and set of admissible observation targets. Both guidance approaches are compared using a multi-body/multi-actuator benchmark spacecraft, whose complex repointing phase requires an autonomous on-board guidance computation. It is shown that the proposed approach is systematic and that the reduction in maneuver time, compared to the state-of-practice approach, is considerable.
Highlights Observation spacecraft need to perform slew maneuvers under attitude constraints. Minimizing the time spent reorienting the spacecraft is a driver to save mission time. Spacecraft agility envelopes enable to consider actuator limitations in the guidance. The proposed approach is systematic, analytical, time-optimal, and can run on-board. The time saved reorienting a benchmark observation spacecraft is considerable.
Guidance for autonomous spacecraft repointing under attitude constraints and actuator limitations
Acta Astronautica ; 207 ; 340-352
2023-03-15
13 pages
Article (Journal)
Electronic Resource
English
Autonomous Spacecraft Attitude Constraints Avoidance
British Library Conference Proceedings | 2013
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