Accession Number:

ADA058475

Title:

Control Aspects of Highly Constrained Guidance Techniques

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

Personal Author(s):

Report Date:

1978-02-01

Pagination or Media Count:

202.0

Abstract:

This thesis examines the design of the guidance, steering, control, and attitude measurement systems for the third stage of a space vehicle in exoatmospheric powered flight. The guidance methods used in this study include position offset guidance and energy management fuel depletion guidance. A generalized flight control system design method is developed which allows the autopilot filter gains and coefficients to be readily determined for any desired crossover frequency. Several steering modes for velocity-to-be-gained and fuel depletion guidance are then discussed. The effect of terminal steering on the end-of-burn stability and velocity-to-be gained residuals is discussed for abrupt thrust termination and thrust tailoff conditions. An empirical approach to the determination of sensitivities to thrust direction errors for fuel depletion and simultaneous control of reentry angle and time-on-target guidance is discussed and compared to analytical predictions. Finally, an attitude measurement study is presented which compares several methods of processing the IMU attitude measurements with regard to reducing computational requirements and minimizing worst-case error.

Subject Categories:

  • Ground Support Systems and Facilities for Space Vehicles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE