火箭弹概念设计的多学科优化设计方法  

Multi-disciplinary design optimization on conceptual design of rockets

作　　者：赵良玉[1] 杨树兴[1] 

机构地区：[1]北京理工大学宇航科学技术学院,北京100081

出　　处：《固体火箭技术》2008年第2期103-106,共4页Journal of Solid Rocket Technology

基　　金：国防基础科研项目基金(K1305060614)

摘　　要：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。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 singlestage thrust, the total flight time is shorter, and payload ratio greatly decreases. Finally further investigation on the scheme containing concentration problem was discussed.

关 键 词：火箭弹 概念设计 多学科优化 

分 类 号：TJ415[兵器科学与技术—火炮、自动武器与弹药工程]