Combustion and performance evaluation of Paraffin/GOX for hybrid rocket motors
(0) In propulsion system, to ensure a suitable thrust, so to obtain a better engine performance, the selection of pair of the fuel/oxidizer is of utmost importance.Thus, the combination of propellant influences the characteristics of the chemical reaction process, the facility and the fuel vaporization speed, the ignition temperature, the volatility of hot gases, among others.Once, determined the propellant, as important is a suitable injector design, which will allow better use of the propellant mixture, and thus achieve better engine performance, less instability of combustion and pollutants emissions.This study evaluated the radial injector data, compared with those for other types of injectors, orifice-plate and swirl.Combustion behavior was also analyzed by reactive molecular dynamics simulations.It was analyzed how each contributes to the engines performance, by using solid fuel-based paraffin and oxygen gas as an oxidizer in the gas phase (GOX), constituting a hybrid propellant.For orifice plate and swirl injectors, the specific impulse values were higher at higher test pressures.However, for the radial injector, the Isp was increased to the test pressure up to 25 bar.All injectors yielded good operation and met the goal of injecting oxidizer flow efficiently.The RMD simulation was able to show the behavior of paraffin during decomposition and combustion, as well as explain the pressure effects on the system by the gaseous molecules generation.
Combustion Hybrid rocket motor Paraffin Specific Impulse Reactive Molecular Dynamics
Rene E B.Gon(c)alves Shirley M.Pedreira Marcela G.Domingues Koshunlha José A.E Rocco
Departamento de Química, Instituto Tecnológico de Aeronáutica, S(a)o José dos Campos/SP, Brasil Leopoldo Rocco Jr Flowtest Engenharia e Pesquisa Ltda., Caieiras/SP, Brasil
国际会议
2018 International Conference on Defence Technology (2018国际防务技术会议)
北京
英文
301-306
2018-10-21（万方平台首次上网日期，不代表论文的发表时间）