Numerical simulation of hydrogen arcjet thruster with coupled sheath model  

作　　者：Deepak AKHARE Hari Prasad NANDYALA Jayachandran THANKAPPAN Amit KUMAR 

机构地区：[1]Department of Aerospace Engg,Indian Institute of Technology Madras,Chennai 600036,India

出　　处：《Plasma Science and Technology》2022年第2期145-161,共17页等离子体科学和技术（英文版）

基　　金：supported by the Indian Space Research Organization(VSSC under grants ASE1415160ISROAMIK and ASE1718174ISROAMIK)。

摘　　要：In the present work,a complete 2D chemical and thermal non-equilibrium numerical model coupled with a relatively simple sheath model is developed for hydrogen arcjet thruster.Conduction heat transfer in the anode wall is also included in the model.The operating voltages predicted by the model are compared with those in the literature and are found to be in close agreement.Power distributions for the various operating conditions are obtained,anode radiation loss primarily determines the thruster efficiency.Higher thruster efficiency was found to be associated with longer arc length.At cathode ion diffusion contribution dominates except at low input current where thermo-field electron current is dominant.

关 键 词：ARCJET HYDROGEN numerical modeling plasma sheath space electric propulsion 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]