临近空间直接入轨运载火箭级间比/弹道一体化优化设计

Integrated optimization design for mass distribution / trajectory of near space directly injecting carrier rocket

研究了适用于直接入轨的多级固体运载火箭级间比/弹道一体化优化设计问题。建立了飞行器质量模型、动力学模型、控制模型和优化模型,运用遗传算法实现了运载器级间比/弹道一体化设计。仿真结果表明,与仅优化飞行程序参数相比,级间比/弹道一体化优化一定程度提高了运载火箭整体设计性能,在相同条件下关机点速度提高了5.2%,说明优化后的级间比更能满足直接入轨运载模式的需要。

Integrated optimization design for mass distribution/trajectory of near space directly injectingmulti-stage solid rocket was studied in this paper. The mass model, dynamical model, control model andoptimization model of the vehicle were established and the genetic algorithm was applied to realize inte-grated optimization design for mass distribution/trajectory. Simulation results show that, compared withonly flight process parameters, the integrated optimization design for mass distribution/trajectory improvesthe overall design performance of carrier rocket. The velocity of burnout point is increased by 5.2% , in-dicating that the optimized mass distribution is better for directly injecting mode.