Direct-Connect Test of Solid Scramjet with Symmetrical Structure

Pengnian Yang, Zhixun Xia, Likun Ma, Binbin Chen, Yunchao Feng, Chaolong Li and Libei Zhao
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Pengnian Yang: Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China
Zhixun Xia: Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China
Likun Ma: Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China
Binbin Chen: Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China
Yunchao Feng: Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China
Chaolong Li: Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China
Libei Zhao: Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China

Energies, 2021, vol. 14, issue 17, 1-16

Abstract: The solid scramjet has become one of the most promising engine types. In this paper, we report the first direct-connect test of a solid scramjet with symmetrical structure, carried out using boron-based fuel-rich solid propellant as fuel. During the test, which simulated a flight environment at Mach 5.6 and 25 km, the performance of the solid scramjet was obtained by measuring the pressure, thrust, and mass flow. The results show that, due to the change in the combustion area of the propellant and the deposition of the throat in the gas generator during the test, the equivalence ratio gradually increased from 0.54 to 0.63. In a solid scramjet, it is possible to obtain a symmetrical distribution of the flow field within the combustor. Moreover, in a multi-cavity combustor, the combustion state expands from the cavity to the center of the flow channel. The performance of the solid scramjet increased during the test, reaching a combustion efficiency of about 42%, a total pressure recovery coefficient of 0.35, and a thrust gain specific impulse of about 418 s. The solid scramjet with symmetrical structure is feasible. The cavity configuration adopted in this paper can reduce the ignition delay time of fuel-rich gas and improve the combustion efficiency of gas-phase combustible components. The shock trains in the isolator are conducive to the recovery of the total pressure. The performance of the solid scramjet is limited by the low combustion efficiency of the particles.

Keywords: direct-connect test; solid scramjet; symmetrical structure; multi-cavity; boron-based propellant (search for similar items in EconPapers)
JEL-codes: Q Q0 Q4 Q40 Q41 Q42 Q43 Q47 Q48 Q49 (search for similar items in EconPapers)
Date: 2021
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