固体发动机低温点火适应性模拟试验技术  

Simulation experiment technology for low temperature ignition adaptability of solid rocket motor

作　　者：刘中兵[1] 张兵[2] 周艳青[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》2015年第2期203-207,213,共6页Journal of Solid Rocket Technology

摘　　要：考虑影响固体发动机低温点火适应性的推进剂低温力学性能、药柱固化降温应变以及药柱在发动机点火升压条件下应变等3个关键因素,设计了可用于全尺寸发动机低温点火适应性研究的ф202 mm模拟试验发动机。通过选取合适的药柱设计参数和发动机初始压强,可对全尺寸发动机在低温点火下药柱应变状态进行模拟。模拟发动机已成功应用于A、B和C等全尺寸发动机低温-40℃或-50℃点火适应性研究中,获得了各发动机低温点火试车时的结构安全余量,可在类似发动机低温点火适应性研究中推广应用。Considering three key factors influencing solid rocket motor low temperature ignition adaptability,including low tem-perature mechanical property of solid propellant,grain strain induced by curing cooling down process,grain strain induced by ignition pressurization,the φ202 mm simulation solid motors were devised to investigate low temperature ignition adaptability of full-scale solid rocket motor.By choosing appropriate designing parameters of grain and initial operation pressure of simulation motors,the grain strain situation of full-scale solid rocket motors at low temperature ignition was simulated.The simulation motors were used to investi-gate low temperature ignition adaptability for A,B and C full-scale solid rocket motors at -40 ℃ or -50 ℃.The structure safety margin of each full-scale solid motor at low temperature ignition was gotten.The results can be widely used to investigate low temper-ature ignition adaptability for more solid motors.

关 键 词：固体火箭发动机 推进剂药柱 低温点火 结构完整性 粘弹性 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]