Some issues of time-optimal control over a spacecraft programmed turn |
| |
Authors: | M V Levskii |
| |
Institution: | 1.Maximov Research Institute of Space Systems,Khrunichev State Center for Space Science and Engineering,Yubileiny, Moscow oblast,Russia |
| |
Abstract: | The problem of optimal turn of a spacecraft from an arbitrary initial position to a final specified angular position in a
minimum time is considered and solved. A case is investigated, when the constraint on spacecraft’s angular momentum during
the turn is essential. Based on the quaternion method a solution to the posed problem has been found, and an optimal control
program is constructed taking the constraints on controlling moment into account. The optimal control is found in the class
of regular motions. A condition (calculation expression) is presented for determining the moment to begin braking with the
use of measurements of current motion parameters, which considerably improves the accuracy of putting the spacecraft into
a preset position. For a dynamically symmetrical spacecraft the solution to the problem of optimal control by the spacecraft
spatial turn is presented in analytical form (expressions in elementary functions). An example of mathematical modeling of
the spacecraft motion dynamics under optimal control over reorientation is given. |
| |
Keywords: | |
本文献已被 SpringerLink 等数据库收录! |
|