Pitch Maneuver Test, and Single Plane Limit Cycle Tests of the Centaur Attitude Control System,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 20, 1961
- Accession Number
- AD0843350
Entities
People
- P. A. House
Organizations
- General Dynamics