Corresponding author: Pankratov Ilia A., Ph. D., Associate Professor, Researcher, Department of Mathematic and Computer Modeling, National Research Saratov State University, Saratov, 410012, Russian Federation, Laboratory of Mechanics, Navigation and Motion Control, Precision Mechanics and Control Problems Institute, RAS, Saratov, 410028, Russian Federation
e-mail: PankratovIA@info.sgu.ru

Accepted on August 17, 2017

The problem of optimal reorientation of spacecraft orbit is considered in quaternion formulation. Control (jet thrust vector orthogonal to the plane of the orbit) is limited in magnitude. It is necessary to minimize the costs of characteristic velocity for the process of reorientation of the spacecraft orbit. To describe the motion of the spacecraft center of mass quaternion differential equation of the orientation of the orbital coordinate system was used. The actual special case of the problem, when the spacecraft's orbit is circular and control equals to its maximum (in modulus) value on adjacent parts of active spacecraft motion (there are also parts of passive motion of the spacecraft), was considered. Various iterative methods (Newton's method, gradient descent method, etc.) are often used to solve boundary value problems obtained as a result of the maximum principle. There are no formulas for finding unknown initial values of conjugate variables. Original evolutionary algorithm for finding the trajectories of spacecraft fastest flights is built. In this case the lengths of the sections of the spacecraft motion are unknown. This method does not require any information about the unknown initial values of conjugate variables. The high speed of operation of the proposed evolutionary algorithm is achieved through the use of existing in this case, a known analytical solution of equations of the problem. Examples of numerical solution of the problem for the case when the difference between the initial and final orientations of the spacecraft's orbit equals to a few (or tens of) degrees in angular measure, are given. Also the case was considered when the final orientation of the spacecraft's orbit corresponds to one of the satellites of Russian GLONASS orbital grouping. The graphs of components of the quaternion of orientation of the orbital coordinate system, the deviation of the current position of the spacecraft's orbit to the required and optimal control are drawn. Specific features and regularities of the process of optimum reorientation of the spacecraft's orbit are given.
Keywords: spacecraft, orbit, optimization, quaternion, gene