Accession Number : AD0843350
Title : Pitch Maneuver Test, and Single Plane Limit Cycle Tests of the Centaur Attitude Control System,
Corporate Author : GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
Personal Author(s) : House, P. A.
Report Date : 20 JUL 1961
Pagination or Media Count : 27
Abstract : The primary objectives in the pitch plane orientation and recovery maneuver tests were to evaluate the angular accelerations produced by the attitude control engines, measure engine decay impulses, and establish the position of the autopilot switching lines on a plot of vehicle angular velocity versus angular position. The objective of the single plane limit cycle tests was to determine the stable limit cycle characteristics in each of the planes of rotation (pitch, yaw, and roll). The characteristics of primary interest were the vehicle angular position and velocities at the engine 'on command', the engine 'off command', and at the conclusion of the engine decay impulse. (Author)
Descriptors : (*LAUNCH VEHICLES, ATTITUDE CONTROL SYSTEMS), (*VERNIER ROCKET ENGINES, FLIGHT TESTING), AUTOMATIC PILOTS, PITCH(MOTION), GYRO STABILIZERS, ACCELERATION, SWITCHING CIRCUITS, YAW, ROLL, CAPTIVE TESTS.
Subject Categories : Liquid Rocket Propellants
Ground Support Sys & Facil For Space Vehicles
Distribution Statement : APPROVED FOR PUBLIC RELEASE