Automatic control for missile - has loop with dual subtractors, gain stage and integrator fed from angle and inertia devices

摘要

For at least one of the two channels for height or side control, the determining device (2) for the angle value is so mounted on the aircraft (1) that the motion of its sight line (21) relative to the aircraft is zero on average. The controller has a first subtractor coupled to the angle determining device and the output of an integrator (7). It has an amplifier (4) at the subtractor (3) output, and a second subtractor (6) coupled to the amplifier and an inertia central unit (5), the integrator (7) being coupled to the output of the second subtractor. The output (GS) of the amplifier (4) controls the directing device.