脉冲发动机中金属膜片式隔舱动态破坏过程研究  

Research on the process of dynamic failure of metal diaphragm pulse separation device in pulse motor

作　　者：王春光[1] 任全彬[1] 田维平[2] 刘洪超[1] 杨德敏[1] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025 [2]中国航天科技集团公司四院,西安710025

出　　处：《固体火箭技术》2013年第1期22-26,共5页Journal of Solid Rocket Technology

摘　　要：为了实现固体火箭发动机的多脉冲启动功能,设计了一种金属膜片式隔舱(PSD)结构,利用断裂力学理论和圆板大挠度理论建立了金属膜片的设计公式,根据燃烧室的使用要求确定了打开压强为2.2 MPa的金属膜片尺寸,利用脆性断裂模型模拟了膜片的破坏过程,得到其打开压强为2.15 MPa,有限元数值计算结果与公式计算结果符合较好。设计了金属膜片打开破坏的单项试验,5次试验平均打开压强为2.10 MPa,数值模拟的破坏形式与试验结果一致。通过区间估计,计算了膜片真实平均打开压强置信度为90%的置信区间为[1.90 MPa,2.30 MPa],该范围可以较好满足脉冲发动机的使用要求。In order to achieve the pulse start of solid rocket motor, one metal diaphragm pulse separation device （PSD） was de- signed. Fracture mechanics theory and circular plates with large deflection theory were used to establish metal diaphragm designing formula. The sizes of metal diaphragm with 2.2 MPa opening pressure were determined. Brittle cracking model was used to simulate the process of dynamic failure of the diaphragm, and the numerical opening pressure was 2.15 MPa. The designing formula results a- gree with the computational results very well. The verification monomial test was designed to verify the accuracy of designing formula and simulation. The average opening pressure of five tests was 2.10 MPa. The simulation failure mode agreed with the test results. The probability of true average opening pressure between 1.90 MPa and 2.30 MPa is 90%, which can satisfy with the design re- quirements.

关 键 词：脉冲发动机 金属膜片式隔舱 设计公式 脆性断裂模型 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]