MISSILE ROLL STABILIZATION BY A FLICKER-TYPE CONTROL SYSTEM
Abstract
An investigation was made of (1) the roll-motion frequency response of a missile equipped with the system and (2) the system components and subcomponents. The system is one in which the servo response is not dependent upon the magnitude of the command signal but is programmed according to the sign of the signal. The roll angular velocity of the missile is sensed by a gyroscope, and the rate output signal of the gyroscope is integrated to yield the missile angular displacement. The system was considered particularly adaptable to pilotless flight vehicles. It maintained well controlled oscillations with components upon which it placed liberal requirements. Complete simulation of the system for 1 axis was performed on a single REAC unit with a small amount of supporting equipment. The method of returning the control surface to a neutral position by means of air-stream forces resulted in higher system frequencies and smaller amplitudes than are possible with a symmetrical system having equal velocities for outbound and inbound travel of the surface. An effective means of controlling the system frequency within its limits of operation is provided by regulating the ratio of position signal gain to angular velocity signal gain. The steady-state operation of a flicker-type system may be approximated by simple graphic methods which permit the introduction of many of the practically difficult component characteristics.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1953
- Accession Number
- AD0020340
Entities
People
- Charles J. Zoet
- Martin W. Ruhnke