Simulation Research On Catalytic Decomposition And Combustion Characteristics Of ADN-based Monopropellant Thruster

The thrust system is an important part of the satellite,determining the positioning of satellite,attitude control precision and the life of service.With the development of space technology,micro thrusters are widely used in spacecraft.Micro thruster can realize accurate impulse control and precisely control spacecraft attitude with characters of small volume,fast response,high reliability and etc.Micro thruster can have a variety of working medium.Due to the toxicity of based-hydrazine propellant,recently,ADN monopropellant thruster using green and high-energy ADN propellant becomes a hot research.ADN thruster contain complex physical and chemical processes,including propellant jet spray,evaporation,catalytic decomposition and combustion reaction,and many other complex process,and have a strong coupling relationship between them.For the further study of ADN thruster in the working process,this article adopts the method of simulation to explore the internal working process.In this paper,based on the research of the complex working process in ADN thruster,the spray model multicomponent evaporation model and porous media model are established,to study the catalytic decomposition and combustion characteristics of ADN-based monopropellant thruster.Adopt the method of experiment for researching the characteristics of flow resistance in porous media of ADN thruster to get the flow resistance characteristics curve.In determining the boundary conditions of heat radiation,the calculation process of thruster.Compare the simulation results and experimental results of the temperature and pressure peak value of combustion chamber to verify the accuracy of the simulation model.Finally,carry on the deep analysis the thruster starting up process,steady working state and the shutdown process.In this paper,study the ADN thruster working process under different initial conditions including different propellant mass flow rate,catalytic bed porosity and nozzle divergence angle.Research the influence of propellant mass flow rate,porosity and catalytic bed expansion nozzle angle to the AND working performance.