Estimation of Launch Vehicle Performance Parameters from Two Orbiting Sensors.

摘要

A technique was developed for estimation of launch vehicle performance parameters. This technique used an inverse covariance or Bayes filter. Both a seven state and an eight state dynamics model were implemented and their performance investigated. Observations consisted of angular, infrared measurements from two orbital sensors. The seven state filter had 3 position, 3 velocity and an acceleration component for its state vector. The acceleration state was modelled as constant between measurement updates. After the addition of a fading memory, the seven state filter showed good performance in estimating a variable acceleration profile. The eight state filter had 3 states each for position and velocity, and seventh and eighth states involving engine exit velocity and propellant mass flow rate. Although the eight state filter had a better model for the acceleration, the filter proved to be unsuccessful in its estimation attempts. (Author)