Research On Modeling Design And Optimization Method Of Takeoff Mass Of Tactical Missile

The modeling design and optimization methods of takeoff mass of tactical missiles were studied in this thesis. First of all, study on the existing takeoff mass design methods. According to the initial conditions and the type and quantity of the available data, the existing takeoff mass design methods can be divided into two categories. The first category is getting takeoff mass directly by empirical formula and statistical data; The second category is getting take-off mass by empirical formula, statistical data and motion equations of missiles. The second category can be further classified as numerical integration method and analytical method. Typical models of all kinds of takeoff mass design categories have been introduced in the thesis.Secondly, a takeoff mass design model has been built with the application of analytical methods.The takeoff mass of design model was calculated.The particle trajectory simulation was Completed.The thesis analysed the pros and cons of the model, according to the simulation results. The design model was then improved based on the error sources of the model, using a method of combining analytic method with numerical integral method. The takeoff mass of improved model was then calculated.The particle trajectory simulation was completed.Comparing the results of the two models,the thesis analysed the pros and cons of the improved model.A model to optimize takeoff mass was established.Speed program and thrust requirements were set as the main constraints, the minimum takeoff mass was set as the optimization objective. Pattern search method, sequential quadratic programming method and genetic algorithms have been applied respectively to optimize takeoff mass. Compareing the optimization results and efficiency, the most suitable optimization method to this model-sequential quadratic programming was selected.The optimization of takeoff mass was completed.Comparing the results,the thesis analysed the pros and cons of the optimization model.With the characteristics of low fuel consumption and high specific impulse, turbojet engines are widely used in long-range missiles.About 10% of more than 300 kinds of missiles which are currently on duty or in the research adopt turbojet engine, most of which are subsonic remote cruise missiles. While the takeoff mass design model for missiles with solid rocket engines can not be used to the missiles with turbojet engines.Therefore, the thesis specifically studied on the takeoff mass design methods for the cruise missiles with turbojet engine. A parameters estimation method of turbojet engine has been designed, considering turbojet engine characteristics.A method to calculate and optimize take-off mass has been designed, considering the flight mission profiles of the cruise missiles.The calculation and optimization of the takeoff mass have been completed.Based on the results of calculation and optimization of the takeoff mass,the thesis analysed the pros and cons of the models.