Optimization Design Of Waverider-Hypersonic Cruise Vehicle

Hypersonic technique is an important technique to study Hypersonic Cruise Vehicle (HCV)with air-breathing engine. It stands for the abilities of exploring and utilizing space of a country,and it is an important symbol of measuring battle and survival effectiveness of military.Hypersonic technique has an important military value and a wide applied prospect, and it is also anew technical field focused on the advantages of aeronautics and astronautics fields, which canaccelerate greatly the development of material, propulsion, aerodynamics, control and electronicssubjects so that it will become the strategetic high land of aeronautics and astronautics fields in21 th century.The aerodynamic configuration and integral optimization design is a key technique of HCV.Because HCV has some characteristics such as great flight height and high velocity, complexflight environment and different mission aim, the optimization design is more difficult. Thetraditional design method is not easy to reach the design goal. Through the optimization work, weexpect to summarize and develop an integral optimization design theory and method ofaerodynamic configuration of HCV.Based on the air-breathing hypersonic cruise vehicle, and by means of building parametricmodeling of HCV, this dissertation develops a widely complete research on aerodynamic partsoptimization design, integral optimization design and airframe/scramjet integration of HCV withMulti-Objective Genetic Algorithms (MGA) and Hybrid Multi-Objective Genetic Algorithms(HMGA) introduced. In the optimization design, many performances are considered as objectivessuch as aerodynamics, aeroheating, radar cross section (RCS), volume of airframe andairframe/scramjet integration and so on, a series of innovative advantages are got. Theseadvantages attained are as follows.1) The theoretical frame of integral optimization design of aerodynamic configuration andperformance for HCV is constructed. In virtue of theoretical analysis, engineering computation,optimization design, configuration comparison, numerical and experimental validation, and basedon geometrical modeling, performance modeling and optimal method modeling, this dissertationconstructs the theoretical frame of optimization design of aerodynamic configuration for HCV.2) Through the optimization work, the theory and method of optimization design for HCVis developed, which puts forward that optimization should be done from a global and systemichighness of integral performance. The integral performance should include aerodynamics,aeroheating, RCS, maneuverability and stability, volume of body and airframe/scramjetintegration. In addition, according to the mission aim and flight environment, other performancescan also be introduced. This optimization method deepens traditional design idea, and will be anew method in aircraft design field.3) A complete parametric modeling of HCV is built. With the modeling, we can describeall of quasi-waverider configurations. And this idea of parametric modeling can also be used intoother HCV, which provides a foundation of numerical optimization to aircraft with a complicatedshape.4) The engineering methods of performances are improved from optimization design pointof view. In the computations of aerodynamics, aeroheating and RCS, the better generalcomputation models are built. Especially in RCS, the surface shadowing and multi-reflection areconsidered, and aimed at the characteristics of wing-body joint such as trapeziform face and body shadowing, the concept of equivalent illumination area (EIA) are presented, which enlarges theapplied range of classical formula from ideal dihedral corner reflector to a normal one.5) On the base of performance analysis of scramjet, the integrated design ofairframe/scramjet is performed with one-dimensional flow model applied, which overcomes theshortage of forebody/inlet integration and aftbody/nozzle integration.6) Aimed at the integral optimization design of aerodynamic configuration, themodification to Genetic Algorithms(GA) is performed; MGA and HMGA with restrictions andthe concept of Pareto class in global and local search are built. As an attempt, HMGA is appliedinto a complicated multi-objective optimization problem with a big scale, for an example, ourintegral optimization design to HCV. From the optimization work, some optimal results such asthe optimal configuration D, E, F, G and H are recommended from different performances anddifferent points of view. These optimal configurations have better performances than basic shape,which proves the optimization work is successful and the design aim and optimization effect havebeen achieved.In this dissertation, we firstly introduce the method of multi-objective optimization designfrom normal aircraft into HCV, and then put forward the optimization design to aerodynamicconfiguration of HCV aimed at its integral performance. These optimization work and methodsimprove the design level of aircraft and overcome some shortcomings of traditional designmethods such as paying only attention to local perfermance and insufficient care to integralperformances of aircraft. At the same time, through the computation, analysis and wind tunnel testvalidation of optimized configurations, a suit of optimization design theory and method of HCV issummarized, which has a great innovative meaning and engineering applied value.