飞行器固体火箭助推器设计优化方法比较

综合考虑飞行器总体设计约束、轨道设计、气动特性与固体火箭助推器设计间相互影响的情况下,建立了飞行器固体火箭助推器总体/气动/轨道/动力多学科的系统分析模型和设计优化模型。采用传统设计优化方法和多学科设计优化(MDO)方法进行了固体火箭助推器设计优化。结果表明,固体推进单学科的最优设计不等价于飞行器总体多学科的最优设计;与传统设计优化方法相比,MDO方法一次设计优化就可得到满足飞行器总体设计指标的最优设计,得到内外弹道相匹配的助推器最优推力-时间曲线。传统设计优化方法需要飞行器总体和固体推进学科两个设计优化过程不断迭代协调,容易漏掉满足飞行器总体设计指标的最优设计。采用MDO方法,可提高固体火箭助推器的设计质量,大大减少设计迭代次数,从而缩短设计周期。

Comparison of design optimization methods for flight vehicle solid rocket booster

In comprehensive consideration of flight vehicle system constraints,trajectory design,aerodynamic characteristics and solid rocket booster design,a series of system/aerodynamics/trajectory/solid propellant integration design analysis and optimization models for solid rocket booster of flight vehicle were derived.Design optimization of solid rocket booster was carried out by using traditional and multi-disciplinary design optimization(MDO)method.The results show that optimum design of solid propulsion in single discipline doesn't stand for multi-disciplinary optimum design for flight vehicle system.Compared with traditional design optimization method,MDO method can gain the optimum design for flight vehicle as well as the optimum thrust-time curves of booster.Traditional design optimization method needs multiple iteration of two design optimization processes for flight vehicle and solid propulsion system,which may miss the optimum design for flight vehicle system.MDO method can improve design quality for solid rocket booster,and greatly reduce iterative times and shorten design period.