Effects of Different Initial Conditions on Combustion Process of Ammonium Dinitramide-Based Energetic Propellant in Straight Nozzle
Luyun Jiang,
Chentao Mao,
Jianhui Han,
Haichao Cui,
Baosheng Du,
Yongzan Zheng,
Jifei Ye,
Yanji Hong
Affiliations
Luyun Jiang
State Key Laboratory of Laser Propulsion & Application, Department of Aerospace Science and Technology, Space Engineering University, Beijing 101416, China
Chentao Mao
State Key Laboratory of Laser Propulsion & Application, Department of Aerospace Science and Technology, Space Engineering University, Beijing 101416, China
Jianhui Han
State Key Laboratory of Laser Propulsion & Application, Department of Aerospace Science and Technology, Space Engineering University, Beijing 101416, China
Haichao Cui
State Key Laboratory of Laser Propulsion & Application, Department of Aerospace Science and Technology, Space Engineering University, Beijing 101416, China
Baosheng Du
State Key Laboratory of Laser Propulsion & Application, Department of Aerospace Science and Technology, Space Engineering University, Beijing 101416, China
Yongzan Zheng
State Key Laboratory of Laser Propulsion & Application, Department of Aerospace Science and Technology, Space Engineering University, Beijing 101416, China
Jifei Ye
State Key Laboratory of Laser Propulsion & Application, Department of Aerospace Science and Technology, Space Engineering University, Beijing 101416, China
Yanji Hong
State Key Laboratory of Laser Propulsion & Application, Department of Aerospace Science and Technology, Space Engineering University, Beijing 101416, China
As a new type of green propellant, ammonium dinitramide (ADN)-based energetic propellants have wide application value and development potential in the field of space propulsion. This paper delves into the intricate impact of varying initial temperatures, pressures, and propellant component ratios on critical parameters, including temperature, combustion rate, and heat release, in the straight nozzle of an ADN-based propellant. The findings indicate that an elevation in both initial temperature and ADN ratio expedites the thermal decomposition rate of ADN, thereby elevating the average temperature in the nozzle. However, the elevation in initial temperature has a negative effect on the overall rise amplitude of average temperature. Furthermore, the initial pressure setting is crucial in determining whether the oxidation reaction of the fuel CH3OH occurs in ADN propellants. When the initial pressure is greater than 10 atm, CH3OH is completely consumed, and the final average temperature is about 2650 K, which increases by 558.89% compared with that at 1 atm. Our work aims to provide theoretical guidance and practical optimization strategies for enhancing propellant performance and optimizing thruster structure design.
