Journal of Applied Science and Engineering

Published by Tamkang University Press


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Chang-Fei Zhuo This email address is being protected from spambots. You need JavaScript enabled to view it.1, Yu-Jiao Cai2, Yan-Yan Ma2, Gang Chai2 and Xiao-Ming Wang1

1School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing 210094, P.R. China
2Institute of Precision Equipment, Chongqing Changan Industries Group Co., Ltd, Chongqing 401120, P.R. China


Received: April 9, 2018
Accepted: December 7, 2018
Publication Date: June 1, 2019

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The high-speed ramjet kinetic energy projectile uses the solid fuel ramjet as its power plant to increase end velocity and its strike force. The solid fuel ramjet relies on self-ignition to start work. This study adopts polyethylene as a solid fuel of solid fuel ramjet, and uses an air heater in the ground laboratory to generate the inflow air with high enthalpy for the propose of simulating high Mach number flight condition. The experiment of solid fuel ramjet under the inflow air with high enthalpy is carried out. It discusses the effect law of nozzle throat diameter and air mass flow rate on the self-ignition characteristics and the burning rate of solid fuel. The experimental results show that:With the increase of nozzle throat diameter, the pressure in the entire flow channel gradually decrease, the operation state of the solid fuel ramjet gradually changes from stable operation, unstable operation, and no self-ignition. The pressure in the combustion chamber has almost no influence on average burning rate of solid fuel. With the increase of air mass flow rate, the pressure in entire flow channel increases and the burning rate of solid fuel also increases.

Keywords: Kinetic Energy Projectile, Solid Fuel Ramjet, Self-ignition Characteristics, Burning Rate Characteristics


  1. [1] Zhang, W., H. Zhu, and D. Y. Fang (1998) Development of ramjet and ducted rocket engines, Journal of Solid Rocket Technology 21(5), 2430.
  2. [2] Liu, X. Z. (1992) Aerodynamic Missile Power Plant, Beijing: Aerospace Press.
  3. [3] Tan, F. G. (1997) Solid fuel ramjet projectiles-the conceptual structure, progress to date and development prediction, Journal of Projectile and Rockets Technology 2, 16.
  4. [4] Chen, J., F. Y. Zhu, and C. S. Zhou (1999) SFRJ used on minor-diameter ammunition, Journal of Ballistics 11(2), 8588.
  5. [5] Peter, W., and N. Yngve (1993) Initial study of a 40 mmSFRJ projectile, 14th International Symposium on Ballistics, Quebec, Canada.
  6. [6] Buisson, J. J., D. C. Redelinghuys, and G. F. Botha (1996) Solid fuel ramjet (SFRJ) propulsion for kinetic energy penetrator applications-progress to date, 16th International Symposium on Ballistics, San Francisco, U.S.A.
  7. [7] Ronald, G. V. (1995) A computer program for flight performance prediction of solid fuel ramjet propelled projectiles, 15th International Symposium on Ballistics, Jerusalem, Israel.
  8. [8] Krishnan, S., and P. George (1998) Solid fuel ramjet combustor design, Progress in Aerospace Sciences 34(3), 219-256. doi: 10.1016/S0376-0421(98)00005-0
  9. [9] Veraar, R. G., K. Andersson, and Y. Nillsson (2001) Flight test results of the Swedish-dutch solid fuel ramjet propelled projectile, 19th International Symposium on Ballistics, Interlaken, Switzerland.
  10. [10] Veraar, R. G., and A. E. H. J. Mayer (2005) The role of the TNO free jet test facility in solid fuel ramjet projectile development,41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Tucson, Arizona, U.S.A. doi: 10.2514/6.2005-3828