Study on the Low Aluminum NEPE Propellant with Low Burning Rate
- 摘要
|
- 图/表
|
- 访问统计
|
- 参考文献
|
- 相似文献
|
- 引证文献
|
- 资源附件
|
- 文章评论
摘要:为了降低少铝NEPE推进剂的燃速，分别研究了AP粒度和含量、Al粉粒度、(NG/BTTN)/PET比例、催化剂及降速剂对推进剂燃烧性能的影响，计算了不同配方推进剂的标准理论比冲，并采用Φ165标准发动机对降燃速的推进剂内弹道性能进行验证。结果表明：增大AP和Al粉粒度，降低AP和催化剂含量、(NG/BTTN)/PET比例，以及添加降速剂均可降低推进剂燃速；添加降速剂T8的降速效果较好，推进剂标准理论比冲为2 503.08 Ns·kg-1，2 MPa下燃速降至3.54 mm·s-1，2～8 MPa下的压强指数为0.48；采用降燃速的推进剂制备的Φ165标准发动机装药工作正常、性能曲线平稳，2.78 MPa下的实测比冲为219.25 s，燃速为4.57 mm·s-1。
Abstract:In order to reduce the burning rate of low aluminum NEPE propellant, the effects of AP particle size and content, Al powder particle size, (NG/BTTN)/PET proportion, combustion catalysts and burning rate inhibitors on the combustion performances of propellant were studied. The standard theoretical specific impulses of different formulations of propellant were calculated, and the interior ballistic properties of the propellant with reduced burning rate were validated through Φ165 standard motor. The results show that the burning rate of propellant can be reduced through increasing the particle sizes of AP and Al, reducing the contents of AP and catalysts, the proportion of NG/BTTN and PET, and adding burning rate inhibitors; The addition of burning rate inhibitor T8 has a better deceleration effect, with a standard theoretical specific impulse of 2 503.08 Ns·kg-1 for the propellant, a burning rate of 3.54 mm·s-1 at 2 MPa, and a pressure exponent of 0.48 at 2～8 MPa; The Φ165 standard motor charge prepared using the reduced burning rate propellant works normally and has a stable performance curve. The measured specific impulse at 2.78 MPa is 219.25 s, and the burning rate is 4.57 mm·s-1.
var swiper = new Swiper('.swiper_xq', {
navigation: {
nextEl: '.swiper-button-next',
prevEl: '.swiper-button-prev',
},
});
$(function(){
$('img').bigic();
});
jQuery(".slideTxtBox").slide({ trigger: "click" });
