Solution of a Problem of Spacecraft's Orbit Optimal Reorientation Using Quaternion Equations of Orbital System of Coordinates Orientation

The problem of optimal reorientation of the spacecraft's orbit is solved with the help of the Pontryagin maximum principle and quaternion equations. Control (thrust vector, orthogonal to the orbital plane) is limited in magnitude. Functional, which determines a quality of control process, is weighted sum of time and impulse (or square) of control. We have formulated a differential boundary problems of reorientation of spacecraft's orbit. Optimal control laws, transversality conditions, not containing Lagrange multipliers, examples of numerical solution of the problem are given.