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Numerical investigation of an aerospace thruster with ADN-based liquid propellant |
| JING Liyue1, HUO Jialong1, YAO Zhaopu2, YOU Xiaoqing1, ZHU Min1 |
1. Department of Thermal Engineering, Tsinghua University, Beijing 100084, China;
2. Beijing Institute of Control Engineering, Beijing 100190, China |
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Abstract The ammonium dinitramide (ADN) based liquid propellant is an environmentally friendly propellant that can be used in small rockets. Combustion of an ADN-based liquid propellant in an aerospace thruster is investigated numerically with the droplets described by the Euler-Lagrange approach and with the heat transfer in the porous media using the non-equilibrium model. The interactions among the gas, liquid droplets and porous media are all included. An 18 species and 40 reactions reduced chemical mechanism is used to model the reactions between ADN and CH3OH in the gaseous phase to estimate the thruster performance. The results show that the heat release from the combustion is transferred upstream to enhance the evaporation of the liquid propellant by the porous media. In the thruster, the ADN decomposition and the CH3OH oxidization do not happen at the same time. The ADN decomposition occurs near the inlet while the CH3OH is oxidized downstream of the porous media and in the combustor.
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| Keywords
ammonium dinitramide (ADN)-based liquid propellant
aerospace thruster
numerical simulation
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Issue Date: 15 October 2016
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2016,
Vol. 56
