Arbitrary fuel-optimal attitude maneuvering of a non-symmetric space vehicle in a vehicle-fixed coordinate frame (Q1868067)

The space vehicle is modeled by a rigid body rotating about its centre of mass under the action of control torques. The control system consists of three pairs of reactive jets, which produce three limited control torques directed along the vehical principal axes of inertia. The initial and final angular velocity vectors are fixed, and the process time is unlimited. In the paper, the problem of fuel-optimal synthesis for attitude maneuver of this vehicle is solved analytically. This solution is obtained with the use of the Krotov-Bellman function, the cyclic sliding modes and the author's passive integral method.