基于整体级概念的多级固体运载火箭设计与优化

Design and optimization of multi-stage solid launch rocket based on integrated stage concept

针对多级固体运栽火箭小型化需求，采用整体级概念（ISC）进行总体方案改造和优化设计。描述了2种ISC概念的特点，以某三级常规方案固体运载火箭为基准，通过利用级间的剩余空间，完成ISC方案改造。建立了运载火箭的整体级发动机动力计算模型、气动计算模型和弹道计算模型，并结合任务指标要求，提出了运载火箭的总体参数优化模型。在相同的任务条件下，完成了常规方案和2种ISC方案的优化。结果表明，引入ISC概念可将运载火箭体积缩小15％～20％，起飞总重缩小1％-1．5％，满足了总体指标要求，达到了运载火箭小型化设计目的。

For the purpose of decreasing the volume of multi-stage solid launch vehicle, Integrated Stage Concept （ISC） was introduced to improve performance of the launch vehicle. Two kinds of ISC scheme characteristics were described. Taking a traditional three-stage solid launch rocket as example, ISC scheme was used for inter-stage residual space modification of the rocket. The dynamic calculation model, aerodynamic calculation model and ballistic calculation model for integrate stage launch rocket motor were derived respectively. In combination of design index requirements, system parameter optimization model was put forward. Under the given task conditions ,the traditional scheme and two kinds of the ISC scheme were optimized respectively. The results show that the volume of multi-stage solid launch vehicle can be decreased by 15 % -20% by using ISC concept, and the takeoff mass can be decreased by 1% - 1.5% ,which can meet system index demands and miniaturized requirements.