A Comparative Analysis of Kalman Filters Using a Hypervelocity Missile Simulation.
Abstract
A systematic procedure is used to design Kalman Filters for a hypervelocity missile system. The procedure includes truth model development, state space model formulation, filter tuning and Monte Carlo analysis. The study is based upon a planar engagement of highly dynamic missile, a constant-velocity aircraft, and a stationary target. Two line-of-sight filters are developed using the rotating aircraft-to-target line-of-sight frame as a reference and two inertial filters are developed using an inertial frame reference. The angle between the aircraft-to-target line-of-sight and the aircraft-to-missile line-of-sight is the only physical measurement processed by the filters. Due to observability considerations, the inertial filters also process additional pseudo-measurements of range. The filters are compared by calculation of miss distance statistics, probability of kill, and computational loading. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1981
- Accession Number
- ADA115545
Entities
People
- Donald Chris Nelson
- Donald W. Capps
Organizations
- Air Force Institute of Technology