A Practical Three Dimensional , 11 State Extended Kalman Filter for Use in a Fire Control System against Non-Thrusting Missiles. Volume I.
Abstract
A previously designed extended Kalman filter, based upon the proportional guidance law, aerodynamic drag equation, and a first order lag model of the missile time response; is modified for three dimensional use. Its purpose is to estimate various states of an offensive missile by processing the line of sight measurements made by the target aircraft. A six-degree-of-freedom, stochastic missile model is developed and presented in Fortran code. Monte Carlo analyses of the filter's performance are generated for four different trajectories. These trajectories test for different orientations of the line of sight, different acceleration profiles of the missile, and different amount of roll induced upon the missile by a three dimensional, conic turn. The extended Kalman filter is designed in the line of sight frame and is composed of eleven states. They are: two line of sight orientation angles, two inertial angular velocites of the line of sight, range, closing velocity, two lateral accelerations of the missile, and three constant parameters. The constant parameters are the proportional navigation constant (which exploits an assumed missile guidance scheme), a time constant (for the first order lag model of missile time response), and the missile's mass over surface ratio (for computing aerodynamic drag of the missile). The filter assumes that the missile is non-rolling with respect to the line of sight frame, and that the line of sight frame is non-rolling with respect to the inertial frame. It also assumes that the missile is non-thrusting.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1978
- Accession Number
- ADA064759
Entities
People
- Charles W. Hlavaty
Organizations
- Air Force Institute of Technology