| 摘要 |
PURPOSE: To realize the safe flight by switching a control system even at the time of the fault of a missile. CONSTITUTION: A deviation signal of a pitch/yaw airframe acceleration signal nz (ny) from a pitch/yaw acceleration command signal ncz (ncy) and a pitch/yaw airframe angular velocity signal q(r) are supplied to control changeover switches 11, 13, and a rolling airframe attitude angle signalϕand a rolling attitude angle command signalϕcs deviation signal and rolling airframe angular velocity signal (p) are supplied to control changeover switches 12, 14. Control systems 15, 16 in which rear wing steering is mainly conducted are connected to the switches 11, 12, and control systems 17, 19 in which front wing steering is conducted are connected to the switches 13, 14. The switches 11 to 14 are immediately switched to the front wing (rear wing) steering when the fault of the rear wing (front wing) is detected, and the control system is reconstructed to execute the safe flight control.
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