Accession Number : ADA329008
Title : Tightly Coupled GPS-Gyro Integration for Spacecraft Attitude Determination.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH
Personal Author(s) : Puri, Varun
PDF Url : ADA329008
Report Date : SEP 1997
Pagination or Media Count : 201
Abstract : A Global Positioning System (GPS) based attitude determination system has never been used as the primary source of attitude information for a spacecraft application. The fundamental reason for this is that a spacecraft attitude determination system must achieve fast attitude acquisition and near perfect solution reliability. Existing GPS based attitude systems cannot meet these requirements, so GPS has only been used as a secondary sensor for spacecraft missions. In this thesis, an attitude determination system is developed which meets spacecraft performance requirements using GPS as the primary source of attitude information. System hardware includes a multiple antenna GPS receiver and a low cost three axis gyro assembly. The attitude determination software consists of an integer ambiguity solution algorithm, an Extended Kalman Filter and an integrity monitoring architecture to improve robustness of the design. The integer solution algorithm resolves GPS integer ambiguity with no a priori attitude knowledge or external aiding. Processing is streamlined by solving the two-dimensional yaw and pitch problem and the one-dimensional roll problem independently.
Descriptors : *ATTITUDE CONTROL SYSTEMS, *GLOBAL POSITIONING SYSTEM, *SATELLITE ATTITUDE, COMPUTER PROGRAMS, ALGORITHMS, REQUIREMENTS, YAW, DETECTORS, ACQUISITION, MONITORING, PERFORMANCE(ENGINEERING), TWO DIMENSIONAL, KALMAN FILTERING, THESES, RELIABILITY, RADIO RECEIVERS, ANTENNAS, DETERMINATION, SPACE MISSIONS.
Subject Categories : Space Navigation and Guidance
Spacecraft Trajectories and Reentry
Distribution Statement : APPROVED FOR PUBLIC RELEASE