Optimal mid-course guidance of variable flow ducted rocket missiles

Abstract

A numerical research has been done on the optimal mid-course guidance of variable flow ducted rocket missiles. The objective of this study is to learn the dominant parameters in the variable flow ducted rocket when used in the mid-course of airto-air missiles. The parameter results are then fedback to the variable flow ducted rocket designs in order to take maximum advantage of their potential in the guidance and control of air-to-air missiles. In this study, the minimum time problem to a specified point as well as the down range maximization problem in a variable flow ducted rocket air-to-air missile are solved as typical scenarios, which are based on a variable flow ducted rocket. The suggestive trajectories and time histories of states and control inputs, which depend on specific impulse characteristic curves and constraints (e.g., air-to-fuel ratio and fuel flow mass rate limitations), have been obtained by numerical simulations. The trajectories and time histories are considered to contribute to extracting the maximum performance of variable flow ducted rockets as propulsion system for air-to-air missiles.