液体推进剂发动机试验多工况流量控制方法  

Multiple-working-conditions flowrate control for liquid engine test

作　　者：姬俊锋[1] 吴光中[1] 马利亚[1] 李久龙[1] 林萌[1] 游良平[1] 

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《火箭推进》2011年第2期71-75,共5页Journal of Rocket Propulsion

基　　金：国家航天技术支撑项目

摘　　要：分析了液体发动机试验多工况流量控制的难点及单个汽蚀管在流量控制中的缺点,提出了一种汽蚀管组合方法来实现发动机试验多工况流量控制。利用汽蚀管的汽蚀裕度的特点,指出了单个汽蚀管可以覆盖的工况范围。首先计算得到未确定汽蚀管工况中满足要求的具有最小喉部直径汽蚀管,然后计算该汽蚀管可以覆盖的工况,最后计算该汽蚀管与已得到的汽蚀管的组合所能覆盖的工况,直到所有工况均已得到对应的汽蚀管或汽蚀管组。计算实例表明,可以用较少的汽蚀管通过不同的组合方式来实现多工况流量控制。通过发动机试验证明,本方法可以经济。After analyzing the difficulty of the multiple-working-condition flowrate control during the liquid engine test and the shortcoming of the single cavitation venturi for the flowrate control, a cavitation venturi combination method is proposed. The characteristic of the cavitation margin of the venturi is considered in the method. The range of the working-conditions covered by the single venturi is pointed out in this paper. Firstly, the minimum throat diameter satisfying the demand of the working-conditions is obtained by computation, and then the working-conditions covered by this venturi are computed. Finally, the working-conditions covered by the combination of the venturi and the previously-obtained venturis are eliminated until no working-condition remains. The instance shows that less venturis can realize the flowrate control of the multiple-working-condition engine test and the cavitation margin affects the result. Test proves that the proposed method can solve the problem of the multiple-working-condition flowrate control effectively and economically.

关 键 词：液体火箭发动机 发动机试验 流量控制 汽蚀管 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]