CAJ | 학술논문

针对一种两级运载器、滑翔级翼身组合体外形的导弹片案,采用多学科没计优化方法研究了包括两级发动机装药量、上作时问、滑翔级翼而形状和助推一滑翔弹道在内的优化设计问题.将系统分为总体、气动、发动机、弹道四个学科.采用增强协同优化方法进行分解协调优化.目标函数为最大射程和最小总加热量的加权和,约束条件为驻点热流、导弹质量、滑翔段终点速度、高度等.采用试验没计方法进行不同外形的气动力计算,并构造响应曲面.结果表明该MD0方法可适用于助推-滑翔导弹的概念研究.
침대일충량급운재기、활상급익신조합체외형적도탄편안,채용다학과몰계우화방법연구료포괄량급발동궤장약량、상작시문、활상급익이형상화조추일활상탄도재내적우화설계문제.장계통분위총체、기동、발동궤、탄도사개학과.채용증강협동우화방법진행분해협조우화.목표함수위최대사정화최소총가열량적가권화,약속조건위주점열류、도탄질량、활상단종점속도、고도등.채용시험몰계방법진행불동외형적기동력계산,병구조향응곡면.결과표명해MD0방법가괄용우조추-활상도탄적개념연구.
A missile scheme has been studied that has two stage launcher and wing-body configuration glider. The optimum design problem of sohd rockct fuel mass and working time, wing shape of glider and boost- glide trajectory is solved by means of mulfidisciphnary design optimization technique. The system has been decomposed into disciplinary subsystems describing system coordation, aerodynamics, engine and trajectory analyses. The enhanced collaborative optimization methodology has been used to decompose, coordinate and optimization. The weighted sum of maximum range and minimum total heat load is considered as the objective. Constraints are imposed on the stagnation heating rate, weight of the missile, gliding terminal velocity and altitude, etc.Design of experiment method is used to calculate aerodynamic characteristic of different shape and build response surface. The re-sults show this MDO methodology can be used in the conceptual study of boost-glide missile.