Influence of Thermal Decomposition of Ammonia Propellant in Solar Thermal Propulsion

Abstract:

Solar thermal propulsion is a kind of space propulsion technology with great potential applications. Due to the difficulty of hydrogen storage in orbit, ammonia becomes an ideal candidate propellant as its stability and easier storage. In solar thermal propulsion system, the working temperature is usually above 2300K, and in this condition the dissociation of ammonia will occur. Thus, using ammonia as a single component propellant to compute and analysis the performance of thruster is not precise, and the mixture components produced from ammonia dissociation must be taken into account. In this paper a novel heat exchanger configuration with platelet technology is designed, and based on finite-rate chemical reaction method and computational fluid dynamics, the dissociation process of ammonia in the heat exchanger and nozzle is simulated. Then the influence to the specific impulse of the solar thermal propulsion system is comparatively analyzed. The simulation result indicates that the main productions of the dissociation are N₂ and H₂, and the mole fraction of other components is small value that can be neglected. The specific impulse considering dissociation reaction is higher than not considering, so that this research can estimate the performance of solar thermal propulsion with ammonia propellant more precisely.

• Periodical: Applied Mechanics and Materials (Volume 598)
• Pages: 257-264
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.598.257
• Online since: July 2014
• Authors: Bao Yu Xing, Min Chao Huang, Mou Sen Cheng, Kun Liu
• Keywords: Ammonia Dissociation, Finite-Rate Chemical Reaction, Fluid-Solid Coupled, Platelet, Solar Thermal Propulsion

References

[1] Scharfe D B, Ketsdever A D. A Review of High Thrust, High Delta-V Options for Microsatellite Missions. AIAA Paper, 2009, AIAA-2009-4824.

DOI: 10.2514/6.2009-4824

[2] Henshall P, Palmer P. Solar Thermal Propulsion Augmented with Fiber Optics: Technology Development. AIAA Paper, 2006, AIAA-2006-4874.

DOI: 10.2514/6.2006-4874

[3] Kennedy F G, Palmer P, Paul M. Results of a microscale solar thermal engine ground test campaign at the Surrey Space Centre. AIAA Paper, 2004, AIAA-2004-4137.

DOI: 10.2514/6.2004-4137

[4] Nakamura T, Sullivan D, McClanahan J A, et al. Solar Thermal Propulsion for Small Spacecraft. AIAA Paper, 2004, AIAA-2004-4138.

DOI: 10.2514/6.2004-4138

[5] Nakamura T, Krech R H, McClanahan J A, et al. Solar Thermal Propulsion for Small Spacecraft -Engineering System Development and Evaluation. AIAA Paper, 2005, AIAA-2005-3923.

DOI: 10.2514/6.2005-3923

[6] Gilpin M R, Scharfe D B, Young M P, et al. Molten boron phase-change thermal energy storage: containment and applicability to microsatellites. AIAA Paper, 2001, AIAA-2011-3637.

DOI: 10.2514/6.2011-3637

[7] Gilpin M R, Scharfe D B, Young M P, et al. Phase-change thermal energy storage and conversion: development and analysis for solar thermal propulsion. AIAA Paper, 2012, AIAA-2012-3715.

DOI: 10.2514/6.2012-3715

[8] Davidson D F, Kohse-Hoingaus K, Chang Y, et al. A pyrolysis mechanism for ammonia. Int. J. Chem. Kinet, 1990, 22: 513-535.

DOI: 10.1002/kin.550220508

[9] Konnov A A, De Ruyck J. Kinetic modeling of the thermal dissociation of ammonia combust. Sci. and Tech, 2000, 152: 23-37.

[10] Gianpiero C, Giulia C, Mario C, et al. Model for ammonia solar thermal thruster. Journal of Thermophysics and Heat Transfer, 2006, 20(4): 772-779.

[11] Xing B Y, Cheng M S, Huang M C, Liu K. Fluid-solid coupled heat transfer and flow simulation of platelet heat exchanger in thermal thruster. Journal of National Univercity of Defense Technology, 2013, 35(4) : 20-25.

DOI: 10.4028/www.scientific.net/amm.598.281