固体火箭超燃冲压发动机性能试验

doi:10.7527/S1000-6893.2021.26075

Abstract

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

CLC Number:

V435

LI Chaolong, XIA Zhixun, MA Likun, ZHAO Xiang, LUO Zhenbing, DUAN Yifan. Experiment on performance of solid rocket scramjet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(12): 126075-126075.

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Experiment on performance of solid rocket scramjet

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