On Improving the Maneuverability of a Space Vehicle Managed by Inertial Executive Bodies
- PDF / 808,055 Bytes
- 20 Pages / 612 x 792 pts (letter) Page_size
- 51 Downloads / 133 Views
ROL SYSTEMS OF MOVING OBJECTS
On Improving the Maneuverability of a Space Vehicle Managed by Inertial Executive Bodies M. V. Levskii Maksimov Research Institute of Space Systems, Branch of Khrunichev State Space Research and Production Center, Korolev, Russia e-mail: [email protected] Received April 18, 2019; revised November 20, 2019; accepted November 25, 2019
Abstract—The problem of increasing the maneuverability of a spacecraft (SC) by minimizing the duration of rotations around the center of mass is solved. The case is studied when the orientation is controlled using inertial actuators (power gyroscopes, gyrodynamics). The problem of the fastest possible turn of an SC using gyrodynes from an arbitrary initial angular position to the desired final angular position is considered in detail. Using the maximum principle of L.S. Pontryagin, as well as quaternion models and methods for solving the problems of controlling the motion of an SC, a solution to the problem is obtained. The conditions of the optimality of the reorientation mode without unloading the gyrosystem are written in an analytical form and the properties of the optimal motion are studied. Formalized equations and calculation expressions are presented for constructing an optimal control program taking into account the possible perturbations. The key relationships that determine the optimal values of the parameters of the rotation control law are given. The results of mathematical modeling of the motion of an SC with the optimal control are presented, demonstrating the practical feasibility of the developed algorithm for controlling the spatial orientation of an SC. A condition is formulated for determining the moment of the start of braking from measurements of the current motion parameters, which significantly increases the accuracy of bringing an SC into a predetermined resting position in the presence of restrictions on the control moment. DOI: 10.1134/S1064230720020094
INTRODUCTION The effectiveness of the means and methods of controlling the motion of a spacecraft (SC) directly affects the efficiency of the implementation of target programs: the number of tasks to be performed, observations, and experiments; the accuracy of the results; the time spent in orbit and the targeted use of an SC, etc. The problem of controlled rotations of a rigid body around the center of mass has been repeatedly addressed by many researchers [1–19]. In this paper, we solve the problem of bringing an SC into the position of the given orientation in the optimal way. Most of the existing solutions to the spatial rotation problem correspond to rotation around a fixed axis [1–4]. Although the principles of optimization and control algorithms are different (based on fuzzy logic [1], inverse problems of dynamics [2], etc.), the resulting control leads to a turn around an axis that is stationary relative to the connected coordinate system. At the same time, the pivot in the plane of the smallest pivot angle in many practical cases is not optimal, regardless of how accura
Data Loading...
