Affiliation:
1. Harbin Institute of Technology
Abstract
This paper studies the spacecraft attitude maneuver optimization problem. The maneuver aim is to avoid fuel cost by only using CMGs in the maneuver course. The nonlinear dynamic equations of the attitude system are established, the attitude maneuver optimization is depicted into a two point boundary value problem (TPBVP). The adjoint method is used to convert the TPBVP into the initial value problem. Numerical results indicate that the adjoint method is efficiently capable for attitude maneuver optimization.
Publisher
Trans Tech Publications, Ltd.
Reference12 articles.
1. N. Bedrossian, S. Bhatt, in: Space Station Zero-Propellant Maneuver Guidance Trajectories Compared to Eigenaxis, American Control Conference (2008).
2. N. Bedrossian, S. Bhatt, M. Lammers, L. Nguyen, Y. Zhang, in: First Ever Flight Demonstration of Zero Propellant Maneuver Attitude Control Concept, AIAA Guidance, Navigation and Control Conference and Exhibit (2007).
3. S. Bhatt, in: Optimal Reorientation of Spacecraft Using Only Control Momentum Gyroscopes, " Master Thesis, Rice University (2007).
4. J. Goss, K. Subbarao, in: Adjoint Methods for Inlet Shape Optimization, 38th Fluid Dynamics Conference and Exhibit, Seattle, (2008).
5. B. Tapley, W. Williamson, in: Comparison of Linear and Riccati Equations Used to Solve Optimal Control Problem, AIAA Journal, Vol. 10, No. 9, pp.1154-1159, (1972).