Verfahren und Vorrichtung zur Steuerung und Stabilisierung von Flugkoerpern

摘要

904,496. Automatic steering control systems. BOLKOW, L. Jan. 12, 1959 [Jan. 15, 1958], No. 1042/59. Class 38 (4). [Also in Group XXI] In a system for steering a missile and stabilizing it about a longitudinal axis, intersecting fins are provided with control elements each movable in opposite senses under the control of a switch for periods which are arranged to differ for steering purposes, and a gyroscope prevents operation of control elements in such sense as to correct roll automatically. Fig. 5 is a rear view of a missile having fins 41, 42, 43, 44. Spoiler plates 32, 33, 36, 37, at right angles to the fins, which project to an equal extent on either side of the fins in their normal position, may be continuously oscillated to project further on each side of the fins alternately. By making the period for which spoilers 32, 33 are moved in one direction longer than the period for which they are moved in the other direction, the missile may be steered about axis CC. Similarly by moving spoilers 36, 37 for unequal periods in each direction, the missile may be steered about axis C1C1. By combining these two effects, the missile may be steered about an intermediate axis determined by the relative phasing of the two movements. In Fig. 1, continuous each-way operation of a relay 5 energizes solenoid 11 or 12 to move spoiler 32 in one direction or the other as well as a solenoid 13 or 14 to move spoiler 33 in one direction or the other. Continuous each-way operation of a relay 6 similarly controls solenoids 15-18 operating spoilers 36, 37. The periods of operation in each sense and the relative phasing of relays 5 and 6 is determined by pulses transmitted over lines from a remote controller 2. On rotation of the missile in one sense or the other from a normal position about its longitudinal axis, a gyro (not shown) operates a twoway switch 25 to prevent movement of the spoilers in one sense so that in addition to any steering torque, a torque is developed to reverse the direction of rotation of the missile. The missile thus executes small amplitude oscillations about its longitudinal axis. Control of torpedoes and steering by pivoted control surfaces is referred to.