多级固体运载火箭总体/弹道/轨道一体化设计与优化

Orbit,Trajectory and System Integration Design and Optimization of Multi-Stage Solid Rocket

针对小型多级固体运载火箭,设计了合理的飞行轨迹,并综合分析弹道设计、轨道设计和总体特性相互作用,建立了总体/弹道/轨道一体化优化设计数学模型。应用自适应模拟退火法、虎克直接搜索法、多岛遗传算法、逐次近似法和有向启发式搜索法,针对300 km LEO轨道进行了多级固体运载火箭总体/弹道/轨道一体化优化,并比较了5种算法优化结果。计算表明:所建立的一体化优化设计模型是合理的;总体参数优化结合轨迹优化最大程度地挖掘了运载火箭整体设计性能,并且优化设计效果明显,优化所得变轨消耗推进剂质量比原方案减轻了12%。该模型和软件也可推广应用到其它固体火箭的方案论证和初步设计过程中。

Considering the mutually interacting phenomenon of such aspects as trajectory, orbit and system, this paper designs a suitable trajectory and presents a mathematical model of system/trajectory/orbit integration design and optimization for the small - sized multi - stage solid rocket. By adopting Adaptive Simulated Annealing, Hooke - Jeeves direct searching method, Multi -Island Genetic Algorithm, Successive Approximation method and Directed Heuristic searching method, a major/trajectory/orbit integration optimization for a multi -stage solid rocket is performed aimed at 300 km LEO, and then the optimization results of the five methods are compared with each other. According to the results, here comes to a conclusion that： the model of integration optimization is reasonable; parameter optimization of major design integrated with trajectory optimization digs out the vehicle＇s merit to a great extent ; what＇s more, the optimization has great effect on vehicle design, and the liquid fuel consumed in orbit - transfer is decreases by 12%. The models and the software can be generalized to the scheme demonstration and conceptual design of other solid rockets.