The programme of three-channel control of suborbital motion trajectory of orbit plane

Suborbital motion trajectories of an orbit plane when the second stage of a multipurpose air-and-space system is stopped from being placed into orbit are discussed, based on the successive linearization method. The algorithm, forming nominal control, is developed, allowing to calculate controlling functions of the attack angle, the velocity angle of rolling and the thrust which optimize the given criteria, taking into account constraints on control, phase coordinates and motion modes. The character of controlling functions providing maximum lateral range is defined.