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The multi-impulse and multi-criteria optimal trajectories of the spacecraft transfer between orbits of various types are considered. A practical goal is the inspection or service of a number of space objects moving along these orbits at the initial data set. It is required to define a set of the admissible solutions taking into account priorities and possible restrictions on time or on expenses of...
The performance comparison is performed among Legendre (LPM), Gauss (GPM), and Radau (RPM) pseudospectral methods, which are utilized to optimize the low-thrust Earth-Mars rendezvous trajectories. In order to provide a fair comparison condition, a shape-based approach is implemented to provide equivalent initial guesses for all the next accurate optimization, and the SQP algorithm is used to solve...
In this paper, based on recently developed deterministic learning (DL) theory, we investigate the problem of stabilization for an underactuated rigid spacecraft with unknown system dynamics. Our objective is to learn the unknown underactuated system dynamics while tracking to a desired orbit and design the control law to achieve stabilization. Firstly, the system dynamic and kinematic equations are...
A new nonlinear optimal tracking control method is proposed and analyzed which stabilizes a class of unstable periodic orbits near collinear libration points. Since such libration point orbits are, in general, unstable, spacecraft moving on these orbits must use some form of trajectory control to remain close to their nominal paths. In this study, the control law based on optimal control theory gives...
This paper discusses the problem of optimal motion planning for a rigid underactuated spacecraft. Firstly, we derive the dynamic and kinematic equations of the spacecraft, and for given initial and terminal states, the performance index to be optimized is selected as minimizing the total fuel consumption. Moreover, the control input saturation restriction is transformed into an inequality constraint...
The initial sizing of the propulsion system takes an important role in the preliminary design stage for space missions. The aim of this paper is to present an initial sizing method to evaluate the amount of propellant required for the on-orbit servicing spacecraft that can upgrade on-orbit satellites. Specially, one servicing spacecraft (SSc) is considered to be initially in the same direction as...
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