Terminal control of aerospace system subhypersonic first stage

Abstract

The problem of forming command control of the subhypersonic first stage of an aerospace system in climb is considered. Passive motion of spacecraft in conditions of maximum atmospheric density disturbance is analyzed. Achieving the prescribed value of the angle of climb is the terminal motion condition. Terminal height is a controlled value. An algorithm of terminal control for the formation of command value of aerodynamic lift coefficient is proposed. The Newton method with one or more iterations at the correction step is used in determining command control. The serviceability and efficiency of the algorithm compensating the influence of variations of atmospheric density on the preset terminal altitude condition of spacecraft motion are analyzed. The results of simulating spacecraft motion with terminal control for maximally rarefied and maximally dense atmosphere are discussed. Possible improvement of the terminal control algorithm is suggested.

Keywords

• аэрокосмическая система
• субгиперзвуковая первая ступень
• летательный аппарат
• терминальное управление
• алгоритм
• коэффициент подъёмной силы
• угол атаки
• возмущения плотности атмосферы