基于含硼推进剂的微推进器燃烧特性及推进性能  

Combustion characteristics and propulsion performance of microthruster with boron-based propellants

作　　者：李和平[1,2] 席剑飞[3] 罗淋旺 赵文敬 梁导伦 刘建忠[1] 

机构地区：[1]浙江大学能源清洁利用国家重点实验室,杭州310027 [2]杭州电子科技大学能源研究所,杭州310018 [3]南京师范大学能源与机械工程学院,南京210042

出　　处：《固体火箭技术》2017年第6期671-677,共7页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(51106135)

摘　　要：为研究使用含硼推进剂的微推进器点火燃烧特性及推进性能,搭建了激光点火测试实验台,配制了B/AP、B/KNO_3及B/AP/HTPB三种含硼推进剂配方,分别在2~6 mm不同内径微燃烧室中进行了燃烧测试实验。实验结果表明,配方B/KNO_3的燃速快,推力大,在内径为2.76 mm燃烧室中的平均推力达到0.028 56 N;配方B/AP的推力作用时间长,冲量大,在内径为4.92 mm燃烧室中的最大冲量为0.042 28 N·s;配方B/AP/HTPB燃烧较稳定,粘合剂的添加可改善燃烧特性,但会降低推进性能,且推力、比推力、冲量、比冲量等推进性能均随燃烧室内径的增大呈先增大、后减小的趋势。In order to study the ignition and combustion characteristics, and propulsion properties of microthrusters using boron- based propellants,the laser ignition test bench was set up.Three different boron-containing propellants （the formulation B/AP, the formula B/KNO3 and the formulation B/AP/HTPB） were modulated, and they were carried on combustion tests in different internal micro-combustion chambers （2- 6 mm）.The experimental results show that with quick burning rate and large thrust, the B/KNO3 has the average thrust of 28.56 mN in the combustion chamber with 2.76 mm inner diameter;with long effect time and large im- pulse,the formulation B/AP has the maximum impulse of 0.042 28 N s in the combustion chamber with 4.92 mm inner diameter. The combustion of formulation B/AP/HTPB is more stable, and the addition of adhesive can improve combustion performance, but also reduce the thrust performance. And thrust, specific thrust, impulse, specific impulse and other propulsion performances increase first and then decrease with the increase diameter of combustion chamber.

关 键 词：微推进器 含硼推进剂 燃烧特性 推进性能 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]