FLIGHT CONTROL DEVICE FOR A GUIDED MISSILE AND METHOD FOR STEERING A GUIDED MISSILE

摘要

A flight control device (18) for a guided by a rolling, pitching and yawing (20, 22, 24) guided missile (2) with at least two, at least partially pivotable wing assemblies (12) comprising a control and navigation device (30) and a Control electronics (32) for the actuators (14) of the wing arrangements (12), wherein the control and navigation device (30) generates roll, pitch and yaw commands (R, N, G) and the control electronics (32) control signals (A1, A2, A3, A4) for the actuators (14), contains a signal-processing electronic circuit (34, 40, 44) which acts on the actuators (14) optionally with complete control signals (A1, A2, A3, A4) or with modified Actuator signals (A1 ', A2', A3 ', A4') applied, wherein at least one of the roll, pitch and yaw commands (R, N, G) is zeroed.;In a method for steering a guided missile (2) which can be decoupled from a carrier platform with a flight control device (18) according to the invention, the missile (2) is decoupled from the carrier platform, a timer (36, 42, 46) is activated and at least one of the controllers is activated the layers of roll attitude and / or pitch attitude and / or yaw attitude of the guided missile (2) in a first flight phase subsequent to the decoupling during a period of time by means of modified activation signals (A1 ', A2', A3 ', A4') for the actuators (14) omitted, the corresponding at least one rolling and / or yawing and / or pitching moment, which is dispensed on the missile (2) does not cause, and the roll, pitch and yaw position of the missile (2) after the expiry of Period of time in a second phase of flight, regulated by means of unmodified complete control signals (A1, A2, A3, A4).