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. 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(SRB)设计间相互影响的情况下,建立了飞行器固体火箭助推器(SRB)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。
MDO method can improve design quality for solid rocket booster, and greatly reduce iterative times and shorten design period. 采用MDO方法,可提高固体火箭助推器(SRB)的设计质量,大大减少设计迭代次数,从而缩短设计周期。
The tentative design of constant altitude flight solid rocket composed of the sustainer, the booster and its simple control method is presented. 介绍了主发动机加助推器和简易控制方法实现固体火箭等高飞行的设计方案。
The paper presents a CAD system developed for solid propellant ramjet rocket motor design. It includes gas generator design, booster chamber design, air inlet design, performance evaluation of a ramjet rocket motor and missile trajectory demonstration. 针对固体火箭冲压发动机的特点,研制了固体火箭冲压发动机CAD软件,该软件系统包括了燃气发生器设计、助推补燃室设计、进气道设计、发动机性能计算和飞行弹道的计算。