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Aerospace Instrument-Making

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OPTIMAL CONTROL OF ANGULAR MOMENTUM OF A SPACECRAFT DURING SPATIAL TURN
M.V. Levskii

The method of optimal controlling the angular momentum of a spacecraft controlled by system of gyrodynes for a turn in minimum time without “unloading” the gyro-system is offered. The conditions of optimality were written in an analytical form using the quaternion models. Key relations and equations for constructing the optimal control program for spacecraft turn taking into account the possible disturbances are presented. The properties of optimal motion are investigated. Numerical solution of the formulated problem of optimal control is presented. Also, the illustration of dynamics of spacecraft motion during a turn according to the designed control method is given.
Keywords: optimal control, quaternions, attitude, maximum principle.


DOI: 10.25791/aviakosmos.02.2020.1143

Pp. 34-47.

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