火箭弹概念设计的多学科优化设计方法

为了在火箭弹概念设计阶段就可综合考虑质量、气动、动力及弹道等诸多学科的影响和耦合作用,引入了多学科优化设计方法。对该方法应用中的问题定义、基本流程、总体方案作了详细说明,对涉及的一些难点和关键点进行了分析,并给出了可行的解决方案。通过算例验证了该方法的可行性和有效性,与原型弹相比,单级推力方案的有效载荷比更高、最大马赫数更小、发动机工作时间更短;在射程基本不变的情况下,双级推力方案比单级推力方案的最大马赫数更小、火箭弹总的飞行时间更短,有效载荷比大幅降低。最后,讨论了包括密集度问题在内的进一步研究方向。

Multi-disciplinary design optimization on conceptual design of rockets

In order to comprehensively considering influence and coupling effect of multi-disciplines,i.e.mass,aerodynamics,kinetics,trajectory,a kind of multidisciplinary design optimization(MDO) method was introduced.Some problems,definition,general flowchart and overall scheme of the method were discussed in details,and difficult and critical problems were analyzed,then a kind of solving scheme was proposed.The scheme was verified to be feasible and effective by the example.Compared with prototype rocket,payload ratio of the rocket with single-stage thrust is larger,the maximum Mach number is smaller,and the working time is shorter;under the same range,the maximum Mach number of the rocket with double-stage thrust is smaller than that with single-stage thrust,the total flight time is shorter,and payload ratio greatly decreases.Finally further investigation on the scheme containing concentration problem was discussed.