Accession Number : AD0779724

Title :   Kalman Filter Design for an Inertial Navigation System Aided by Non-Synchronous Navigation Satellite Constellations.

Descriptive Note : Master's thesis,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING

Personal Author(s) : Butler,Ronald Ray ; Rhue,George Truitt

Report Date : MAR 1974

Pagination or Media Count : 174

Abstract : The report is a Kalman filter design study for the proposed Integrated Navigation Satellite/Inertial System (INI). Primary emphasis is placed upon determination of the 'best' filter state variable vector and investigation of various measurement rates using external range measurements from a set of 27 non-synchronous satellites. The INI system errors are assumed to be represented by a 44 state linear system model, and the filter operates without benefit of an altimeter. A one-hour INI flight at constant speed and altitude over a great circle path is simulated on the digital computer and filter designs are compared by plotting the system position, velocity, and attitude error covariances versus time. A 15 state filter with weak coupling terms removed is determined to provide the best tradeoff between accuracy and computational burden. Filter performance is compared at 5, 15, 30, 60 and 90 second measurement update rates. Additionally, 'optimal' sequencing of satellite observables is shown to provide improved performance. (Author)

Descriptors :   *Inertial navigation, *Kalman filtering, Navigation satellites, Control theory, Optimization, Integrated systems, Navigation, Theses

Subject Categories : Numerical Mathematics

Distribution Statement : APPROVED FOR PUBLIC RELEASE