Trajectory Optimization Of Hypersonic Cruise Vehicle

At present, hypersonic technology has become an important technology which is researched by Great Powers of military affairs of the world, and the correlative researches of hypersonic weapons have been considered to important instruments to the Great Powers of military affairs which want to consolidate or exalt the status in the world. optimization simulation research is an essential research of the correlative researches of hypersonic weapons which is based on the initial trajectory designing. with one or more than one object requests to recomputed a optimization satisfying some restricts. Optimization is not only good at saving cost but also be supervising a certain capability to higher target on the same cost.So many countries put their eyes on the Hypersonic Cruiser Vehicle which can fill current capability shortfalls in exiting weapons. In particular, the high speed vehicles have high strategic value but are historically difficult to neutralize due to their short dwell times. Owing to the time flight short, high speed and far striking distance, so it is necessary to do some researches in the optimization of the range.Studies of hypersonic cruise trajectory are conducted in this paper. The main points are:1) Mathematical models of hypersonic cruise vehicle are established including following factors: Basic Algorithm Library,Environment Model Library, Force and Moment Model,Motion Model,Climb,Cruise and Attack Models.2)The main point is introducing the numerical arithmetic of trajectory optimization, basing on the identity of the object which involved in the text, select several classical optimal arithmetic and scheme out a method of hybrid genetic algorithm to figure out the problems of trajectory optimization.3)With the elements of the mathematic model, the problems of vehicle with minimum-fuel climbing and the maximum range within climb and cruise segments is investigated by using c\c++ to simulate in the VC flat form.4) Finally the optimal control and the optimal trajectory corresponding to this control at three dimensional entry of hypersonic vehicle are determined related with maximum terminal velocity. The optimal solution was obtained by means of optimization guiding law, with the constraint of given angle .