Accession Number : AD0834022

Title :   INVESTIGATION OF X-11 NOSE CONE ATTITUDE CONTROL SYSTEM IN PITCH,

Corporate Author : GENERAL DYNAMICS SAN DIEGO CA CONVAIR DIV

Personal Author(s) : Wexler, H. T. ; Beharrell, J.

Report Date : 30 MAY 1954

Pagination or Media Count : 13

Abstract : A preliminary investigation, in pitch alone, was made to determine approximate values of the system parameters. In this memorandum, the pitch equations, corresponding analog computer circuits and the results of the investigation are presented. From these results, estimates of the design parameters for the Model X-11 nose cone attitude control system are determined. (Author)

Descriptors :   *ATTITUDE CONTROL SYSTEMS), (*GUIDED MISSILES, NOSE CONES, FLIGHT CONTROL SYSTEMS, EQUATIONS OF MOTION, ANALOG COMPUTERS, PITCH(MOTION), GYRO STABILIZERS, APPROXIMATION(MATHEMATICS), COMPUTER PROGRAMMING, STAGING, DAMPING, TORQUE.

Subject Categories : Surface-launched Guided Missiles

Distribution Statement : APPROVED FOR PUBLIC RELEASE