Accession Number : ADA115545


Title :   A Comparative Analysis of Kalman Filters Using a Hypervelocity Missile Simulation.


Descriptive Note : Master's thesis,


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


Personal Author(s) : Capps,Donald W ; Nelson,Donald Chris


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a115545.pdf


Report Date : Dec 1981


Pagination or Media Count : 220


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)


Descriptors :   *Kalman filtering , *Mathematical models , *Air to surface missiles , *Targeting , *Guidance , Line of sight , Angle of attack , Linear systems , Control theory , Stochastic processes , Monte Carlo method , Computer applications , Trade off analysis , Hypersonic velocity , Antiarmor ammunition , Theses


Subject Categories : Statistics and Probability
      Air- and Space-launched Guided Missiles


Distribution Statement : APPROVED FOR PUBLIC RELEASE