Accession Number:

AD0843350

Title:

Pitch Maneuver Test, and Single Plane Limit Cycle Tests of the Centaur Attitude Control System,

Descriptive Note:

Corporate Author:

GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

Personal Author(s):

• House, P. A.

Report Date:

1961-07-20

Pagination or Media Count:

27.0

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 Systems and Facilities for Space Vehicles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE