THRUST PREDICTION USING A 1-D MODELLING OF THE RAM ACCELERATOR IN THE SUB-DETONATIVE PROPULSION MODE
The ram accelerator is a ramjet-in-tube hypervelocity launcher concept that uses chemical energy to propel a projectile up to very high speed. Of three identified propulsion modes by experiments, the thermally-choked propulsion mode of the ram accelerator operates at a typical in-tube Mach number ranging from 2.5 to S and the projectile velocity is just below the Chapman-Jouguet detonation speed. To predict the thrust of the projectile, one-dimensional quasi-steady computer code (TARAM) has been developed to evaluate and assess the ram accelerator performance. This code considers compressible flow governing equations and also incorporates various equations of state of ideal gas, Boltzmann, PercusYevick, and Becker-Kistiakowsky-Wilson to include the real gas corrections. The computational results have shown good agreements with experimental data over a wide range of fill pressures from 0.61 MPa to 20 MPa, demonstrating the validity of the code.
Tarek Bengherbia YAO Yu-feng Pascal Bauer Carl Knowlen
Kingston University, Faculty of Engineering, London, SW15 3DW, UK Laboratoire de Combustion et de De Kingston University, Faculty of Engineering, London, SW15 3DW, UK Laboratoire de Combustion et de Detonique(LCD), UPR9028CNRS, ENSMA - Poitiers 86961, FRANCE University of Washington, AERP Box 352250, Seattle, WA 98195-2250, USA
国际会议
25th International Symposium on Ballistics(第25届国际弹道会议)
北京
英文
239-245
2010-05-17（万方平台首次上网日期，不代表论文的发表时间）