Browse > Article
http://dx.doi.org/10.5139/JKSAS.2013.41.4.299

Performance Evaluation of 1 N Class HAN/Methanol Propellant Thruster  

Lee, Jeongsub (Korea Advanced Institute of Science and Technology, Division of Aerospace Engineering)
Huh, Jeongmoo (Korea Advanced Institute of Science and Technology, Division of Aerospace Engineering)
Cho, Sungjune (Chonnam National University, Department of Advanced Chemicals & Engineering)
Kim, Suhyun (Chonnam National University, Department of Advanced Chemicals & Engineering)
Park, Sungjun (Chonnam National University, Department of Advanced Chemicals & Engineering)
Kim, Sukyum (Korea Aerospace Research Institute)
Kwon, Sejin (Korea Advanced Institute of Science and Technology, Division of Aerospace Engineering)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.41, no.4, 2013 , pp. 299-304 More about this Journal
Abstract
The HAN which is an ionic liquid is a non-toxic monopropellant with high storability, and its specific impulse can be increased by blending methanol, thereby it can substitute the hydrazine. The HAN was synthesized by acid-base reaction of hydroxylamine and nitric acid, and the blending ratio of HAN and methanol is 8.2:1. The iridium catalyst was used to decompose the HAN, and 1 N class thruster with shower head type injector having one orifice was used to evaluate the HAN/Methanol propellant. The thermal stability of distributor was increased by using ceramic material to endure the high temperature of product gas. The preheating temperature of catalyst should be $400^{\circ}C$ at least for the complete decomposition. The feeding pressure should be increased to increase the $C^*$ efficiency, thereby the decomposition performance was decreased upstream catalyst, and the performance of thruster was decreased. The fine metal mesh was inserted after the injector to improve the atomization of propellant, thereby it can settle the performance decrease problem. The phenomenon of performance decrease was remarkably improved owing to the insertion of fine metal mesh.
Keywords
Ionic Liquid; Hydroxylammonium Nitrate; Blending Method; Ceramic Distributor;
Citations & Related Records
연도 인용수 순위
  • Reference
1 Ventura, M. and Mullens, P., "The Use of Hydrogen Peroxide for Propulsion and Power," 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA-99-2880, Los Angeles, CA, 1999.
2 An, S., Jin, J., Lee, J., Jo, S., Park, D., and Kwon, S., "Chugging Instability of $H_2O_2$ Monopropellant Thrusters with Reactor Aspect Ratio and Pressures," Journal of Propulsion and Power, Vol. 27, No. 2, 2011, pp.422-427.   DOI   ScienceOn
3 Pasini, A., Torre, L., Romeo, L., Cervone, A., and d'Agostino, L., "Performance Characterization of Pellet Catalytic Beds for Hydrogen Peroxide Monopropellant Rockets," Journal of Propulsion and Power, Vol. 27, No. 2, 2011, pp.428-436.   DOI   ScienceOn
4 Wernimont, J. E., "System Trade Parameter Comparison of Monopropellants: Hydrogen Peroxide vs Hydrazine and Others," 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, AIAA-2006-5235, Sacramento, CA, 2006.
5 Masse, K. R., Overly, A, J., Allen, Y, M., and Spores, A. R., "A New State-of The-Art in AF-M315E Thruster Technologies," 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, AIAA-2012-4335, Atlanta, GE, 2012.
6 Anflo, K., Persson, S., Thormählen, P., Bergman, G., Hasanof, T., "Flight Demonstration of an ADN-Based Propulsion System on the PRISMA Satellite," 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, AIAA-2006-5212, Sacramento, CA, 2006.
7 Lee, J., An, S., Kim, M., Moon, K., Song, S., Choi, W., Park, S., Kwon, S., "Design and Performance Evaluation of the 10 N Level Monopropellant Thruster", Proceeding of the 2007 KSAS Fall Conference, pp.1349-1352.
8 Harlow, D. G., Felt, R. E., Agnew, S., Barney S., McKibben, J. M., Garber, R., and Lewis, M., Technical Report on Hydroxylamine Nitrate, DOE/EH-0555, U. S. Department of Energy, 1998, pp.2-7.