Aerospace Instrument-Making Annotation << Back To a question of the unification of solution of the optimal control problems of spacecraft attitude М.V. Levskii The general approaches to the solution of the optimal control problems of spacecraft at-titude based on Pontryagin’s maximum principle are formulated. It is shown, that in cases when the criterion of an optimality (minimised functional) does not explicitly contain position coordinates, the resulting solution (including the calculated dependences of the optimal controlling functions from phase coordinates) and optimal motion of the spacecraft not depend from the form of kinematic equations and from type of the param-eters describing spacecraft's angular position. The conjugate system of the equations corresponding to kinematics of spacecraft rotation is reduced and presented in the ca-nonical form. Such unified characteristics (as analogues of the conjugate variables) which allow us to write down necessary conditions of an optimality independently from the way of description of kinematics of spacecraft rotation are defined. Comparative example of construction of optimal control for different variants of a choice of the kinematic parameters system (the directing cosines, the quaternions and so forth) is given. Key words: optimal control, maximum principle, spacecraft, attitude, kinematic parameters, optimality criterion, the controlling function. Contacts: E-mail: niiks@khrunichev.com Pp. 18-26.