Investigation on Performance Characteristics of Hydrazine Monopropellant Thruster according to Reaction Chamber Adiabatic Temperature

Rouholamini, Seyyed Rashad; Amirifar, Mohammad Ali; Rajabi, Alireza; Ghadiri Massoom, Nooredin

doi:10.30699/jsst.2022.1362

Document Type : Research Paper

Authors

¹ M.Sc., Space Transportation Research Institute, Iranian Space Research Center, Tehran, Iran

² M.Sc., Space Transportation Research Institute, Iranian Space Research Center, Tehran. Iran

³ Ph.D., Space Transportation Research Institute, Iranian Space Research Center Tehran. Iran

⁴ Assistant Professor‎, Space Transportation Research Institute, Iranian Space Research Center Tehran. Iran

https://doi.org/10.30699/jsst.2022.1362

Abstract

In this paper, by creating and developing a code based on thermodynamics and gas dynamics equations, the performance characteristics of a 1N hydrazine monopropellant thruster such as thrust force, specific impulse, characteristic exhaust velocity, and propellant mass flow rate have been studied theoretically in terms of reaction chamber temperature. In this regard, by taking into account the adiabatic assumption, the reaction chamber temperature of monopropellant thruster has been analyzed zero-dimensionally using the ammonia dissociation rate as an independent variable under equilibrium and non-equilibrium conditions and it has been analyzed one-dimensionally using the hydrazine and ammonia homogeneous and heterogeneous reaction rate constants. Also, the effect of nozzle throat thermal expansion on reaction chamber pressure, thrust force, and propellant mass flow rate and the effect of reaction chamber pressure on ammonia dissociation rate and consequently on reaction chamber adiabatic temperature under thermodynamic equilibrium conditions have been studied.

Keywords

Main Subjects

Space subsystems design: (navigation, control, structure and…)

References

[1] A.R. Rezaieha, Design and Manufacturing a Laboratory Example of Pulsed Plasma Thruster, [M.Sc. Thesisi], Aerospace Engineering, Sharif University of Technology, 2015 (in persian).

[2] M. Martinez-Sanchez, and P. Lozano. "16.522 Space Propulsion," Massachusetts Institute of Technology: MIT Open Course Ware, https://ocw.mit.edu. Spring, 2015.

[3] E. W. Schmidt, Hydrazine and Its Derivatives: Preparation, Properties, Applications. J. Wiley, 1984.

[4] W. Ley, K. Wittmann, and W. Hallmann. Handbook of Space Technology, Wiley, 2009.

[5] V. Shankar, K. Anantha Ram, and K. A. Bhaskaran. "Prediction of the concentration of hydrazine decomposition products along a granular catalytic bed," Acta astronautica 11, no. 6, pp. 287-299, 1984.

[6] J. Parker, D. Thunnissen, J. Blandino, and G. Ganapathi. "The preliminary design and status of a hydrazine millinewton thruster development," In 35th Joint Propulsion Conference and Exhibit, p. 2596, 1999.

[7] A. Oren, and C. Gutfinger. "Performance evaluation of an augmented hydrazine thruster," In 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, p. 3761, 2000.

[8] D. I. Han, C. Y. Han, and H. D. Shin. "Empirical and Computational Performance Prediction for Monopropellant Hydrazine Thruster Employed for Satellite," Journal of Spacecraft and Rockets 46, no. 6, pp. 1186-1195, 2009.

[9] A. E. Makled, and H. Belal. "Modeling of hydrazine decomposition for monopropellant thrusters," In 13th International Conference on Aerospace Sciences & Aviation Technology, p. 22, 2009.

[10] C. H. Hwang, S. N. Lee, S. W. Baek, C. Y. Han, S. K. Kim, and M. J. Yu. "Effects of catalyst bed failure on thermochemical phenomena for a hydrazine monopropellant thruster using Ir/Al2O3 catalysts," Industrial & Engineering Chemistry Research 51, no. 15, pp. 5382-5393, 2012.

[11] B. Hou, X. Wang, T. Li, and T. Zhang. "Steady-state behavior of liquid fuel hydrazine decomposition in packed bed," AIChE Journal, vol. 61, no. 3, pp. 1064-1080, 2015.

[12] J. S. Kim, H. Jung, S. H. Bae, D. S. Bae, and J. H. Kim. "Performance Evaluation of a 70 N Hydrazine Thruster According to the Variation of Characteristic Length," In 51st AIAA/SAE/ASEE Joint Propulsion Conference, p. 4162, 2015.

[13] S. Krishnamachary, S. Krishna Mohan, S. G. Kulkarni, D. Jayaraman, M. Raghavendra Rao, L. Dev Singh, and Sai Krishna Prasad. "Propellant Grade Hydrazine in Mono/Bi-propellant Thrusters: Preparation and Performance Evaluation," Defence Science Journal, vol. 65, no. 1, pp. 31-38, 2015.

[14] W. J. Larson, G. N. Henry, and R. W. Humble, eds. Space propulsion analysis and design, McGraw-Hill, 1995.

[15] R. E. Sonntag, C. Borgnakke, G. J. Van Wylen. & G. J. Van Wylen., Fundamentals of thermodynamics., New York: Wiley., 1668.

[16] B. J. McBride, M. J. Zehe, and S. Gordon. "NASA Glenn coefficients for calculating thermodynamic properties of individual species," Technical Publication (TP), 2002.

[17] A. S. Kesten,. "Analytical Study of catalytic reactors for hydrazine decomposition," Quarterly Progress Report, UARL 1966.

[18] S. Gordon and B. J. McBride, "Computer program for calculation of complex chemical equilibrium compositions and applications," I. Analysis, NASA, RP-1311, 1994.

Space Science and Technology

Investigation on Performance Characteristics of Hydrazine Monopropellant Thruster according to Reaction Chamber Adiabatic Temperature

References

References

Volume 15, Issue 3 - Serial Number 53
September 2022
Pages 33-47

Investigation on Performance Characteristics of Hydrazine Monopropellant Thruster according to Reaction Chamber Adiabatic Temperature

References

References

Volume 15, Issue 3 - Serial Number 53September 2022Pages 33-47

Volume 15, Issue 3 - Serial Number 53
September 2022
Pages 33-47