Ascent Trajectory Optimization And Simulation Of A Flight Demonstration

A flight demonstrator subject to various constraints limit, making it difficult for normaltrajectory design to meet requirements, required the use of trajectory optimization designmethod, to meet a variety of processes and terminal constraints.This thesis in a flight demonstrator for the study of the conception, increased researchand simulation of trajectory optimization design method, main content are as follows:Analysis the flight trajectory of typical foreign flight vehicle, summed up the ascenttrajectory characteristics of the aircraft, analysis of a flight demonstrator Flight facedvarious constraints;The research summarized the optimal control theory and its application in the field ofvehicle trajectory optimization;Establish the conception of a mathematical model of the flight demonstrator, mainlyincluding: Hypersonic vehicle longitudinal of particle, and non-linear programming modelof optimal control model. And nonlinear programming method based on sequentialquadratic programming algorithm design of the flight demonstrator rise of flight trajectory;Simulation validated trajectory design and trajectory design and traditional methodswere compared. By contrast, come to optimization design method for adaptability to variousconstraints are good, and the design method for Hypersonic can expand to a kind ofatmosphere.