Multiphysics Simulation of a Novel Concept of MEMS-based Solid Propellant Thruster for Space Propulsion

作     者：José A.Moríigo José Hermida-Quesada 

作者机构：Dept.of Space ProgrammesNational Institute for Aerospace Technology Ctra.Ajalvir km.4Torrejón de Ardoz 28850 MadridSpain Propulsion EngineerPh.D. Dept.of Aerodynamics and PropulsionNational Institute for Aerospace Technology Ctra.Ajalvir km.4Torrejón de Ardoz 28850 MadridSpain 

出 版 物：《Journal of Thermal Science》 (热科学学报（英文版）)

年 卷 期：2011年第20卷第6期

页      面：527-533页

核心收录：

学科分类：080703[工学-动力机械及工程] 08[工学] 082502[工学-航空宇航推进理论与工程] 0807[工学-动力工程及工程热物理] 0805[工学-材料科学与工程（可授工学、理学学位）] 0825[工学-航空宇航科学与技术] 0702[理学-物理学] 

基　　金：funded by the Spanish Ministry of Defence as part of the micropropulsion activities in the Small Satellites Programme 

主　　题：micronozzles spacecraft micropropulsion solid propellant thrusters 

摘      要：This work analyzes a novel MEMS-based architecture of submillimeter size thruster for the propulsion of small spacecrafts,addressing its preliminary characterization of *** architecture of microthruster comprises a setup of miniaturized channels surrounding the solid-propellant reservoir filled up with a high-energetic *** channels guide the hot gases from the combustion region towards the nozzle entrance located at the opposite side of the *** simulations of the transient response of the combustion gases and wafer heating in thruster firings have been conducted with FLUENT under a multiphysics modelling that fully couples the gas and solid parts *** approach includes the gas-wafer and gas-polymer thermal exchange,burnback of the polymer with a simplified non-reacting gas pyrolysis model at its front,and a slip-model inside the nozzle portion to incorporate the effect of gas-surface and rarefaction onto the gas ***,accurate characterization of thruster operation requires the inclusion of the receding front of the polymer and heat transfer in the moving gas-solid *** study stresses the improvement attained in thermal management by the inclusion of lateral micro-channels in the *** particular,the temperature maps reveal the significant dependence of the thermal loss on the instantaneous surface of the reservoir wall exposed to the heat flux of hot ***,the simulations stress the benefit of implementing such a pattern of micro-channels connecting the exit of the combustion reservoir with the *** results prove that hot gases flowing along the micro-channels exert a sealing action upon the heat flux at the reservoir wall and partly mitigate the overall thermal loss at the inner-wall vicinity during the *** analysis shows that propellant decomposition rate is accelerated due to surface preheating and it suggests that a delay of the flame extinction into the reservoir