Multi-objective Optimization of Zero Propellant Spacecraft Attitude Maneuvers

The zero propellant maneuver (ZPM) is an advanced space station, large angle attitude maneuver technique, using only control momentum gyroscopes (CMGs). Path planning is the key to success, and this paper studies the associated multi-objective optimization problem. Three types of maneuver optimal control problem are formulated: (i) momentum-optimal, (ii) time-optimal, and (iii) energy-optimal. A sensitivity analysis approach is used to study the Pareto optimal front and allows the tradeoffs between the performance indices to be investigated. For example, it is proved that the minimum peak momentum decreases as the maneuver time increases, and the minimum maneuver energy decreases if a larger momentum is available from the CMGs. The analysis is verified and complemented by the numerical computations. Among the three types of ZPM paths, the momentum-optimal solution and the time-optimal solution generally possess the same structure, and they are singular. The energy-optimal solution saves significant energy, while generally maintaining a smooth control profile. Communicated by Mauro Pontani. S. Zhang · G. J. Tang (B) College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China e-mail: [email protected] S. Zhang e-mail: [email protected] M. I. Friswell College of Engineering, Swansea University, Singleton Park, Swansea SA2 8PP, UK D. J. Wagg Faculty of Engineering, University of Bristol, University Walk, Bristol BS8 1TR, UK