The impact of GPS velocity based flight control on flight instrumentation architecture
Name
43596050-MIT.pdf
Description
Full printable version
Size
16.65 MB
Format
Adobe PDF
Checksum (MD5)
510dccea0b079e2a46aa572094bee836
Author(s)
Kornfeld, Richard P
Advisor(s)
R. John Hansman.
Alternative Title
Impact of Global Positioning System velocity based flight control on flight instrumentation architecture
Date Issued
1999
Publisher
Massachusetts Institute of Technology
Abstract
This thesis explores the use of velocity information obtained by a Global Positioning System (GPS) receiver to close the aircraft's flight control loop. A novel framework to synthesize attitude information from GPS velocity vector measurements is discussed. The framework combines the benefits of high-quality GPS velocity measurements with a novel velocity vector based flight control paradigm to provide a means for the human operator or autopilot to close the aircraft flight control loop. Issues arising from limitations in GPS as well as the presence of a human in the aircraft control loop are addressed. Results from several flight tests demonstrate the viability of this novel concept and show that GPS velocity based attitude allows for equivalent aircraft control as traditional attitude. Two possible applications of GPS velocity based attitude, an autopilot and a tunnel-in- the-sky trajectory guidance system, are demonstrated in flight. Unlike traditional autopilot and trajectory guidance systems, these applications rely solely on the information obtained from a single-antenna GPS receiver which makes them affordable to the larger General Aviation aircraft community. Finally, the impact of GPS velocity based flight control on the instrumentation architecture of flight vehicles is investigated.
Description
Thesis (Ph.D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.
Includes bibliographical references (p. 191-195).
Subjects
Aeronautics and Astronautics.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.
Persistent DSpace Link
