Preliminary experimental study on solid-fuel rocket scramjet combustor
Preliminary experimental study on solid-fuel rocket scramjet combustor
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DOI：
10.1631/jzus.a1600489
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发表时间：
2017-02
影响因子：
3.2
通讯作者：
Zhong Lv;Zhiming Xia;Bing Liu;Liya Huang
中科院分区：
文献类型：
--
作者：
Zhong Lv;Zhiming Xia;Bing Liu;Liya Huang
液体或气体燃料超燃冲压发动机技术已经取得了很大的进展，固体燃料超燃冲压发动机也得到了一定的研究关注。对一种以固体燃料为推进剂的新型超燃冲压发动机构型--固体燃料火箭超燃冲压发动机进行了实验研究。它由两个燃烧室组成。一种是用作燃气发生器的火箭燃烧室，另一种是用于二次燃烧的超声速燃烧室。实验模拟高空飞行马赫数为4（驻点温度和压力分别为1170 K和1.16 MPa），推进剂采用金属化固体燃料。结果表明，从燃气发生器出来的富燃气可以在超声速燃烧室中与空气混合燃烧。初步评价结果表明，该推进剂的燃烧效率约为90%，超声速燃烧室内总压恢复系数约为0.6。这些结果表明，固体燃料火箭超燃冲压发动机的布局是可行的。
Liquid or gaseous fuel scramjet technology has made great progress, and there has been some research attention to solid-fuel scramjet. A new scramjet configuration using solid fuel as propellant, namely solid-fuel rocket scramjet, is tested experimentally. It consists of two combustors. One is a rocket combustor used as gas generator, and the other is a supersonic combustor used for secondary combustion. The experiment simulates a flight Mach number of 4 at high altitude (stagnation temperature and pressure are 1170 K and 1.16 MPa, respectively), and metalized solid fuel is used as propellant. The results reveal that fuel-rich gas from the gas generator can burn with air in the supersonic combustor. Preliminary evaluation results show that the combustion efficiency of the propellant is about 90%, and the total pressure recovery coefficient in the supersonic combustor is about 0.6. These results indicate that the configuration of solid-fuel rocket scramjet is feasible.