航空学报 > 2022, Vol. 43 Issue (12): 126075-126075   doi: 10.7527/S1000-6893.2021.26075

固体火箭超燃冲压发动机性能试验

李潮隆, 夏智勋, 马立坤, 赵翔, 罗振兵, 段一凡   

  1. 国防科技大学 空天科学学院, 长沙 410073
  • 收稿日期:2021-07-07 修回日期:2021-07-28 发布日期:2021-08-25
  • 通讯作者: 夏智勋,E-mail:zxxia@nudt.edu.cn E-mail:zxxia@nudt.edu.cn
  • 基金资助:
    国家自然科学基金(51706241,52006240)

Experiment on performance of solid rocket scramjet

LI Chaolong, XIA Zhixun, MA Likun, ZHAO Xiang, LUO Zhenbing, DUAN Yifan   

  1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
  • Received:2021-07-07 Revised:2021-07-28 Published:2021-08-25
  • Supported by:
    National Natural Science Foundation of China (51706241, 52006240)

摘要: 为了研究发动机构型、推进剂类型和当量比对固体火箭超燃冲压发动机的性能影响,选取了3种固体火箭超燃冲压发动机燃烧室构型,分别使用碳氢推进剂和含硼质量分数35%推进剂共计开展了8次地面直连试验。试验模拟了23 km、马赫数5.5的飞行工况,通过测量推力、流量和压力等参数,得出了超声速燃烧室和发动机的整体性能参数,进而研究了发动机构型、推进剂类型以及当量比3个关键因素对固体火箭超燃冲压发动机的性能影响。结果表明:带有凹腔-支板组合装置的燃烧室构型虽然冷流内阻最大,但试验燃烧效率和比冲性能最优。针对带有凹腔-支板组合装置的燃烧室构型,使用碳氢推进剂的发动机性能整体优于使用含硼质量分数35%推进剂对应的性能参数;使用碳氢推进剂的极限掺混当量比大于0.7,而使用含硼质量分数35%推进剂的极限掺混当量比在0.65附近。这是由于相对碳颗粒,硼颗粒在超声速气流中燃烧组织更为困难导致的。相对于使用碳氢推进剂,使用含硼质量分数35%推进剂的一次燃烧产物更容易在喉部沉积,其燃气发生器压力曲线也存在更多峰值振荡的现象。在所研究的试验当量比范围内,使用碳氢推进剂的燃烧效率峰值约0.82,此时对应内推力比冲峰值约687 s;而使用含硼质量分数35%推进剂的燃烧效率峰值约0.69,此时对应内推力比冲峰值约592 s。

关键词: 固体火箭超燃冲压发动机, 凹腔-支板组合装置, 燃烧性能, 当量比, 地面试验

Abstract: To obtain the influence of combustor configurations, propellant types, and equivalence ratio on the performance of solid rocket scramjet, a total of eight ground direct-connected tests were carried out with three solid rocket scramjet combustors using hydrocarbon propellant and 35% (by weight) boron propellant, respectively. The experiments simulated a flight Mach number 5.5 at 23 km. By measuring the three parameters of thrust, mass flow rate, and pressure, the overall performance parameters of supersonic combustor and scramjet can be obtained. Then, the effects of combustor configurations, propellant types, and equivalence ratio on the performance of solid rocket scramjet were analyzed. The results show that although the internal resistance of that configuration is the largest, the combustion efficiency and specific impulse are the best in the combustor configuration with combined cavity and strut device. For the combustor configuration with combined cavity and strut device, the performance of the scramjet using hydrocarbon propellant is better than that using 35% (by weight) boron propellant. The limit mixing equivalence ratio of hydrocarbon propellant is greater than 0.7, while the limit mixing equivalence ratio of 35% (by weight) boron propellant is about 0.65 due to the reason that it is more difficult for boron particles to achieve high combustion efficiency in supersonic flow than the carbon particles. Compared with the tests using hydrocarbon propellant, the primary combustion products in these tests using 35% (by weight) boron propellant are more likely to deposit in the surface of throat, and there are more peak oscillations in the pressure curve measured in the gas generator. Within the range of experimental equivalence ratio, the peak value of combustion efficiency using hydrocarbon propellant is about 0.82, and the corresponding peak value of specific impulse for internal thrust is about 687 s. The peak combustion efficiency using 35% (by weight) boron propellant is about 0.69, corresponding to the peak value of specific impulse for internal thrust is about 592 s.

Key words: solid rocket scramjet, combined cavity and strut device, combustion performance, equivalence ratio, ground test

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