The problem of optimal control of the orientation of an orbit of a spacecraft as a deformable figure

被引：4

作者：

Afanas'eva, Yu. V. ^{[1
]}

Chelnokov, Yu. N. ^{[1
]}

机构：

[1] Russian Acad Sci, Precis Mech & Control Problems Inst, Saratov 410028, Russia

来源：

JOURNAL OF COMPUTER AND SYSTEMS SCIENCES INTERNATIONAL | 2008年 / 47卷 / 04期

关键词：

System Science International; Adjoint Variable; True Anomaly; Spacecraft Motion; Spacecraft Orbit;

D O I：

10.1134/S106423070804014X

中图分类号：

TP18 [人工智能理论];

学科分类号：

081104 ; 0812 ; 0835 ; 1405 ;

摘要：

The problem of optimal control of the orbit orientation of a spacecraft regarded as a deformable figure is studied. The problem of optimal re-orientation of an orbit is formulated as a problem of optimal control of the motion of the center of mass of a spacecraft with a movable right end of the trajectory and is solved based on the Pontryagin maximum principle. To describe the orientation of an instantaneous orbit, a new quaternion osculating element that replaces three classical angular elements of the orbit is applied. Necessary optimality conditions are obtained; several first integrals of the system of equations of the boundary-value problem of the maximum principle are found; transformations that reduce the dimension of the system of differential equations of the boundary-value problem (without their complication) are proposed; the proposed approach is analyzed, and an example of numerical solution of the problem is presented.

引用

页码：621 / 634

页数：14