Theoretical Research on the Combustion Characteristics of Ammonium Dinitramide-Based Non-Toxic Aerospace Propellant
Abstract
:1. Introduction
2. Theoretical Methods
3. Results and Discussion
3.1. Time-Evolution Temperature and Pressure Analysis of ADN-Based Propellant
3.2. Combustion Products Analysis of ADN-Based Propellant
3.3. Equilibrium Pressure and Adiabatic Temperature Analysis of ADN-Based Propellant
3.4. Ignition Delay Time Analysis of ADN-Based Propellant
4. Conclusions
- ADN-based propellants exhibit distinct two-stage combustion characteristics under low-temperature and low-pressure conditions. However, under high-temperature and high-pressure conditions, these two combustion stages occur concurrently and cannot be clearly distinguished.
- An increase in temperature effectively shortened the ignition delay time and accelerated the combustion reactions. When the initial temperature rises from 400 K to 2800 K, the ignition delay time decreases from 3.5 ms to 0.6 μs at a pressure of P0 = 10 atm.
- Compared to changes in initial temperature, an increase in initial pressure has a relatively minor effect on the ignition delay time. These results indicate that temperature has a more significant impact on the combustion characteristics of ADN-based propellants than pressure.
Supplementary Materials
Author Contributions
Funding
Data Availability Statement
Conflicts of Interest
References
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Conditions | Pressure (atm) | Temperature (K) | Conditions | Pressure (atm) | Temperature (K) |
---|---|---|---|---|---|
1 | 1 | 400 | 13 | 7 | 2000 |
2 | 1 | 1200 | 14 | 7 | 2800 |
3 | 1 | 2000 | 15 | 10 | 400 |
4 | 1 | 2800 | 16 | 10 | 1200 |
5 | 4 | 400 | 17 | 10 | 2000 |
6 | 4 | 1200 | 18 | 10 | 2800 |
7 | 4 | 2000 | 17 | 15 | 400 |
8 | 4 | 2800 | 18 | 15 | 1200 |
9 | 7 | 400 | 19 | 15 | 2000 |
10 | 7 | 1200 | 20 | 15 | 2800 |
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Han, J.; Wen, M.; Hong, Y.; Du, B.; Jiang, L.; Cui, H.; Feng, G.; Song, J. Theoretical Research on the Combustion Characteristics of Ammonium Dinitramide-Based Non-Toxic Aerospace Propellant. Aerospace 2025, 12, 295. https://doi.org/10.3390/aerospace12040295
Han J, Wen M, Hong Y, Du B, Jiang L, Cui H, Feng G, Song J. Theoretical Research on the Combustion Characteristics of Ammonium Dinitramide-Based Non-Toxic Aerospace Propellant. Aerospace. 2025; 12(4):295. https://doi.org/10.3390/aerospace12040295
Chicago/Turabian StyleHan, Jianhui, Ming Wen, Yanji Hong, Baosheng Du, Luyun Jiang, Haichao Cui, Gaoping Feng, and Junling Song. 2025. "Theoretical Research on the Combustion Characteristics of Ammonium Dinitramide-Based Non-Toxic Aerospace Propellant" Aerospace 12, no. 4: 295. https://doi.org/10.3390/aerospace12040295
APA StyleHan, J., Wen, M., Hong, Y., Du, B., Jiang, L., Cui, H., Feng, G., & Song, J. (2025). Theoretical Research on the Combustion Characteristics of Ammonium Dinitramide-Based Non-Toxic Aerospace Propellant. Aerospace, 12(4), 295. https://doi.org/10.3390/aerospace12040295