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Direct-Connect Test of Solid Scramjet with Symmetrical Structure

Author

Listed:
  • 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)

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.

Suggested Citation

  • Pengnian Yang & Zhixun Xia & Likun Ma & Binbin Chen & Yunchao Feng & Chaolong Li & Libei Zhao, 2021. "Direct-Connect Test of Solid Scramjet with Symmetrical Structure," Energies, MDPI, vol. 14(17), pages 1-16, September.
    • Handle: RePEc:gam:jeners:v:14:y:2021:i:17:p:5589-:d:630267
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    References listed on IDEAS

    as
    1. Chaolong Li & Zhixun Xia & Likun Ma & Xiang Zhao & Binbin Chen, 2019. "Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity," Energies, MDPI, vol. 12(7), pages 1-17, March.
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