Accession Number : AD0822574

Title :   SUPERSONIC STABILITY AND CONTROL CHARACTERISTICS OF LOW-ASPECT-RATIO PLANAR CONFIGURATIONS DESIGNED FOR LARGE MANEUVERS.

Descriptive Note : Technical memo.,

Corporate Author : JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB

Personal Author(s) : Hart, Humes H.

Report Date : AUG 1967

Pagination or Media Count : 152

Abstract : A study was made of the possibility of attaining good high-altitude maneuverability in a supersonic volume-limited missile. The approach was to design a planar configuration with minimum angle-of-attack restrictions imposed by pitch-roll-yaw coupling. A 'twist and steer' type of control was assumed. In the Mach number range 2.5 to 3.5, three types of planar configurations were studied, characterized by their lifting surfaces as being dorsal-finned configurations, delta-winged configurations, and dart-winged configurations. The dart-winged configuration was designed as an optimum solution to the problem within the flight regime hypothesized and does give good stability and control characteristics within this regime. (Author)

Descriptors :   *FLIGHT CONTROL SYSTEMS), (*SURFACE TO AIR MISSILES, SUPERSONIC CHARACTERISTICS, STABILIZATION SYSTEMS, ROLL, YAW, PITCH(MOTION), WIND TUNNEL MODELS, MODEL TESTS, ANGLE OF ATTACK, DELTA WINGS, AERODYNAMIC CONTROL SURFACES, LIFT, MANEUVERABILITY, FINS, STABILITY, HIGH ALTITUDE.

Subject Categories : Guided Missile Dynam, Config & Cntrl Surfaces
      Surface-launched Guided Missiles

Distribution Statement : APPROVED FOR PUBLIC RELEASE