基于旋转阀的固体推进剂压强耦合响应测试方法

Experimental Method for Pressure-coupled Response of Solid Propellants Based on Rotary Valve

针对固体发动机燃烧不稳定问题,提出一种基于旋转阀的固体推进剂压强耦合响应测试方法,并对应设计了一套可开展冷气和推进剂点火实验的旋转阀实验系统。通过23 Hz、46 Hz、69 Hz 3种不同振荡频率的冷气实验及理论计算,发现两种结果对比误差最大值为4.35%,验证了圆光栅定位组件测试旋转阀次级排气通道面积和压强延迟时间的有效性。进行23 Hz、46 Hz、69 Hz、115 Hz、138 Hz 5种振荡频率的固体推进剂点火实验,结果表明:燃烧室平均压强受振荡频率的影响,由23 Hz的2.88 MPa减小至138 Hz的2.523 MPa;被测推进剂的压强耦合响应函数受振荡频率影响较小,维持在0.80±0.13;该旋转阀方案可行和可靠。

For the combustion instability of solid motors,an experimental method of pressure-coupled response of solid propellant based on rotary valve is proposed,and a rotary valve experimental system for cold gas and solid propellant ignition experiments is designed.In the cold gas experiments and theoretical calculations of 23 Hz,46 Hz and 69 Hz oscillation frequencies,the maximum error of the two methods is 4.35%,which verifies the effectiveness of the circular grating positioning assembly to obtain the secondary exhaust passage area and pressure delay time of the rotary valve.Five ignition experiments of solid propellant at 23 Hz,46 Hz,69 Hz,115 Hz and 138 Hz oscillation frequencies were carried out.The results show that the mean pressure of the combustion chamber is affected by the oscillation frequency,which is reduced from 2.88 MPa at 23 Hz to 2.523 MPa at 138 Hz.The pressure-coupled response function of the measured solid propellant is less affected by the oscillation frequency,which is maintained at 0.80±0.13.The rotary valve scheme is feasible and reliable.