### Experimental Investigations of Mass Flow Rate on Regression Rate of Hybrid Rocket

#### Abstract

A number of practical hybrid propulsion systems developed for booster and upper stage application,

at different Centers across the globe. The regression rate of hybrid fuel plays an important role on

development of viable hybrid propulsion system. In the present investigation an effort has been made

to study the regression rate behavior of PVC-DBP((C 2 H 3 Cl) n )-DBP(C 16 H 22 O 4 ) hybrid fuel burning in

the stream of gaseous oxygen using two different Swirl Injectors and a conventional Shower Head

Injector. In all the cases, the oxygen injection has been varied from 20bar (290 psi) and 40.68 bar

(590 psi). The local regression rate has been determined all along the grain length, measuring the

remaining web at each locations of the grain and assuming a uniform fuel consumption rate in small

interval of burning time of ten seconds or less. The local regression rate has been found to increase

with injection pressure at each location of grain for all the cases. The average regression rate of

PVC-DBP-DBP hybrid fuel has been found to increase with injection pressure, however this value is

highest for Swirl Injector, SWA and lowest for Shower Head Injector, while Swirl Injector SWB

resulted in values in between. The dependence of average regression rate on the injection pressure

has been found to follow a power law relationship. The fuel mass consumption rate has also been

found to increase with injection pressure and to follow a power law variation with injection pressure.

However, mass consumption rate is more pronounced in case of Swirl Injectors, and the pressure

exponent for Swirl Injectors have been found to be more than twice than that of Shower Head

Injector, similar to the case of average regression rate. The data have been analyzed in the light of

available combustion models and have been matched with experimental results. The Swirl Injectors

have been found to enhance the fuel regression, and, for the same oxidizer mass flow rate, it is

expected to result in higher thrust levels. The visual recordings indicate lower combustion efficiency

and movement towards fuel rich exhaust with condensed smoke; however, with the increase in

injection and combustion chamber pressure, higher combustion efficiency has been obtained with

higher regression rate as presented in Figure and table.

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Barato, F., Bellomo, N., Faenza, M. and Lazzarin, M., Bettella, A., Pavarin, D., “Numerical

Model to Analyze Transient Behavior and Instabilities on Hybrid Rocket Motors”, Jr. of

Propulsion and Power, March–April 2015, Vol. 31, No. 2, pp. 643–653.

Bianchi, D., Betti, B., Nasuti, F. and Carmicino, C., “Simulation of Gaseous

Oxygen/Hydroxyl–Terminated Polybutadiene Hybrid Rocket Flow fields and Comparison with

Experiments”, Jr. of Propulsion and Power, May–June 2015,Vol. 31, No. 3, pp. 919–929.

Carmicino, C. and Sorge, A. R., “Influence of a Conical Axial Injector on Hybrid Rocket

Performance”, Jr. of Propulsion and Power, Sept.–Oct. 2006, Vol. 22, No. 5, pp. 984–995.

Carmicino, C. and Sorge, A. R., “Role of Injection in Hybrid Rockets Regression Rate Behavior”,

Jr. of Propulsion and Power, Jul–Aug 2005, Vol. 21, No. 4, pp. 606–612.

Casalino, L. and Pastrone, D., “Optimization of Hybrid Sounding Rockets for Hypersonic

Testing”, Jr. of Propulsion and Power, Mar.–Apr 2012, Vol. 28, No. 2, pp. 405–411.

Coronetti, A. and Sirignano, W. A., “Numerical Analysis of Hybrid Rocket Combustion”, Jr. of

Propulsion and Power, Mar–Aprl 2013, Vol. 29, No. 2, pp. 371–384.

Chiaverini, M. J., Kuo, K. K., Peretz, A. and Harting, G. C., “Regression-Rate and Heat-Transfer

Correlations for Hybrid Rocket Combustion”, Jr. of Propulsion and Power, Jan–Feb 2001,Vol. 17,

No. 1, pp. 99–110.

Chiaverini, M. J., Serin, N., Johnson, D. K., Lu, Y. C., Kuo, K. K. and Risha, G. A., “Regression

Rate Behavior of Hybrid Rocket Solid Fuels”, Jr. of Propulsion and Power, Jan–Feb 2000, Vol.

, No. 1, pp. 125–132.

Chiaverini, M., “Review of Solid-Fuel Regression Rate Behavior in Classical and Nonclassical

Hybrid Rocket Motors,” Fundamentals of Hybrid Rocket Combustion and Propulsion, edited by

Chiaverini, M. J. and Kuo, K. K., Progress in Astronautics and Aeronautics, AIAA, Reston, VA,

, Vol. 218, pp. 83, 114–116.

Cherng, D. L. and Tao, C. C., “Analysis of hybrid rocket combustion”, Acta Astronautica

Pergamon Press Ltd., Great Britain, 1980,Vol. 7, pp. 619—631.

Chelaru, T. V. and Mingireanu, F., “Hybrid rocket engine, theoretical model and experiment”,

Acta Astronautica, 2011,Vol. 68, pp. 1891–1902.

Carmicino, C., Orlandi, O., Russo Sorge, A., Dauch, F., De Amicis, R., and De Rosa, M., “Basic

Aspects of the Hybrid Engine Operation,” 45 th AIAA/ASME/SAE/ASEE Joint Propulsion

Conference and Exhibit, AIAA Paper 2009, Aug. 2009.

Carmicino, C., and Russo Sorge, A., “Influence of a Conical Axial Injector on Hybrid Rocket

Performance,” Jr. of Propulsion and Power, 2006,Vol. 22, No. 5, pp. 984–995.

Carmicino, C., “Acoustics, Vortex Shedding, and Low-Frequency Dynamics Interaction in an

Unstable Hybrid Rocket,” Jr. of Propulsion and Power, 2009,Vol. 25, No. 6, pp. 1322–1335.

Carmicino, C., and Russo Sorge, A., “Performance Comparison Between Two Different Injector

Configurations in a Hybrid Rocket,” Aerospace Science and Technology, 2007,Vol. 11, No. 1, pp.

–67.

Carmicino, C., and Russo Sorge, A., “Role of Injection in Hybrid Rockets Regression Rate

Behavior,” Jr. of Propulsion and Power, 2005,Vol. 21, No. 4, pp. 606–612.

Cauty, F., Carmicino, C., and Russo Sorge, A., “The Pressure Sensitivity of the Ultrasonic Waves

Velocity: A Contribution to a Better Determination of the Energetic Material Regression Rate,”

Advancements in Energetic Materials and Chemical Propulsion, edited by Kuo, K., and de Dios

Rivera, J., Begell House, Redding, CT, Jan. 2007, pp. 749–774.

Daniele Bianchi, D. and Nasuti, F., “Numerical Analysis of Nozzle Material Thermochemical

Erosion in Hybrid Rocket Engines”, Jr. of Propulsion and Power, May–June 2013,Vol. 29, No. 3,

pp. 547-558.

Favaró, F. M. and Sirignano, W. A., Manzoni, M. and DeLuca, L. T., “Solid-Fuel Regression

Rate Modeling for Hybrid Rockets”, Jr. of Propulsion and Power, Jan–Feb 2013, Vol. 29, No. 1,

pp. 205–215.

Journal of Experimental & Applied Mechanics

Volume 12, Issue 2

ISSN: 2230-9845 (Online), ISSN: 2321-516X (Print)

© STM Journals 2021. All Rights Reserved

Farbar, E., Louwers, J., and Kaya, T., “Investigation of Metallized and Nonmetallized Hydroxyl

Terminated Polybutadiene/Hydrogen Peroxide Hybrid Rockets,” Jr. of Propulsion and Power,

,Vol. 23, No. 2, pp. 476–486.

Karabeyoglu, M. A., Zilwa, S. D., Cantwell, B. and Zilliac, G., “Modeling of Hybrid Rocket Low

Frequency Instabilities”, Jr. of Propulsion and Power, Nov.–Dec. 2005,Vol. 21, No. 6, pp.

–1116.

Kim, B., Na, Y., Shin, K. H. and Lee, C., “Nonlinear Combustion and Fluid Mechanics in a

Hybrid Rocket”, Jr. of Propulsion and Power, Nov – Dec 2012,Vol. 28, No. 6, pp. 1351–1358.

Knuth, W. H., Chiaverini, M. J., Sauer, J. A. and Gramer, D. J., “Solid-Fuel Regression Rate

Behavior of Vortex Hybrid Rocket Engines”, Jr. of Propulsion and Power, May–Jun 2002, Vol.

, No. 3, pp. 600–609.

Kobald, M., Schmierer, C., Ciezki, H. K. and Schlechtriem, S., “Viscosity and Regression Rate of

Liquefying Hybrid Rocket Fuels”, Jr. of Propulsion and Power, March 2017 (Online)

Lee, C., Na, Y., Lee, J. W. and Byun, Y. H., “Effect of induced swirl flow on regression rate of

hybrid rocket fuel by helical grain configuration”, Aerospace Science and Technology, 2007, Vol.

, pp. 68–76.

Lestrade, J. Y., Anthoine, J., Verberne, O., Boiron, A. J., Khimeche, G. and Figus, C.,

“Experimental Demonstration of the Vacuum Specific Impulse of a Hybrid Rocket Engine”, 50th

AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Cleveland, OH, 28–30 July 2014.

Lia, C., Caia, G. and Tiana, H., “Numerical analysis of combustion characteristics of hybrid

rocket motor with multi-section swirl Injection”, Acta Astronautica, Feb. 2016 (On line)

Lee, J., Kim, S., Kim, J. and Moon, H., “Mass Transfer Number Sensitivity on the Fuel Burning

Rate in Hybrid Rockets”, Jr. of Propulsion and Power, Jul–Aug 2015, Vol. 31, No. 4, pp.

–1050.

Lee, C., Lee, J. W. and Byun, D. Y., “Transient Analysis of Hybrid Rocket Combustion by the

Zeldovich-Novozhilov Method”, KSME Int. Jr., 2003, Vol. 17, No. 10, pp. 1572 –1582.

Lin, J. L., “Two-phase flow effect on hybrid rocket combustion”, Acta Astronautica, 2009, Vol.

, pp. 1042–1057.

Li, X., Tian, H., Yu, N. and Cai, G., “Experimental Investigation of Combustion in Axial-

Injection End-Burning Hybrid Rocket Motor”, Jr. of Propulsion and Power, May–Jun 2015, Vol.

, No. 3, pp. 930–936.

Lips, H. R., “Experimental Investigation on Hybrid Rocket Engines Using Highly Aluminized

Fuels,” Journal of Spacecraft and Rockets, Sept. 1977, Vol. 14, No. 9, pp. 539–545.

Lazzarin, M., Barato, F., Bettella, A., and Pavarin, D., “Computational Fluid Dynamics

Simulation of Regression Rate in Hybrid Rockets,” Jr. of Propulsion and Power, 2013, Vol. 29,

No. 6, pp. 1445–1452.

Frederick Jr., R. A., Whitehead, J. J, Knox, L. R. and Moser, M D., “Regression Rates Study of

Mixed Hybrid Propellants”, Jr. of Propulsion and Power, January–February 2007,Vol. 23, No. 1,

pp. 175–180.

Greatrix, D. R., “Regression rate estimation for standard-flow hybrid rocket engines”, Aerospace

Science and Technology, 2009,Vol. 13, pp. 358–363.

Gordon, S., and McBride, B. J., “Computer Program of Complex Chemical Equilibrium

Compositions and Applications,” NASA Reference Publ. 1311, 1994

George, P., Krishnan, S., Varkey, P. M., Ravindran, M., and Ramachandran, L., “Fuel Regression

Rate in Hydroxyl-Terminated-Polybutadiene/Gaseous-Oxygen Hybrid Rocket Motors,” Jr. of

Propulsion and Power, 2001,Vol. 17, No. 1, pp. 35–42.

Gany, A., “Similarity and Scaling Effects in Hybrid Rocket Motors,” Fundamentals of Hybrid

Rocket Combustion and Propulsion, ed. by Chiaverini, M. J., and Kuo, K. K., Progress in

Astronautics and Aeronautics, AIAA, Reston VA, 2007, Vol. 218, pp. 489–520.

Hitt, M. A. and Frederick, R. A., “Experimental Evaluation of a Nitrous-Oxide Axial-Injection,

End-Burning Hybrid Rocket”, Jr. of Propulsion and Power, May 2017 (Online)

Experimental Investigations of Mass Flow Rate on Regression Rate of Hybrid Rocket *1Mr. Dash

et al.

© STM Journals 2021. All Rights Reserved

Jung, E. S. and Kwon, S., “Autoignitable and Restartable Hybrid Rockets Using Catalytic

Decomposition of an Oxidizer”, Jr. of Propulsion and Power, March-April 2014, Vol. 30, No. 2,

pp.514-518.

Kumar, R. and Ramakrishna, P.A., “Measurement of regression rate in hybrid rocket using

combustion chamber pressure”, Acta Astronautica, 2014,Vol.103, pp. 226–234.

Karabeyoglu, M. A., Cantwell, B. J., and Zilliac, G., “Development of Scalable Space–Time

Averaged Regression Rate Expressions for Hybrid Rockets”, Jr. of Propulsion and Power,

Jul–Aug 2007, Vol. 23, No. 4, pp. 737–747.

Kang, S. and Kwon, S., “Difficulties of Catalytic Reactor for Hydroxyl-ammonium Nitrate

Hybrid Rocket”, Jr. of Spacecraft and Rockets, Sept.–Oct. 2015, Vol. 52, No. 5, pp. 1508–1510.

Kang, S. and Kwon, S., “Difficulties of Catalytic Reactor for Hydroxyl-ammonium Nitrate

Hybrid Rocket”, Jr. of Spacecraft and Rockets, Sept–Oct 2015, Vol. 52, No. 5, pp. 1508–1510.

Karabeyoglu, M. A., Cantwell, B. J., and Zilliac, G., “Development of Scalable Space–Time

Averaged Regression Rate Expressions for Hybrid Rockets,” Jr. of Propulsion and Power, 2007,

Vol. 23, No. 4, pp. 737–747.

Kanazaki, M., Ariyairt A., Chiba, K., Kitagawa, K., and Shimada, T., “Conceptual Design of

Single-stage Rocket Using Hybrid Rocket by Means of Genetic Algorithm, “APISAT2014”, 2014

Asia-Pacific International Symposium on Aerospace Technology, 2014.

Martino, G. D. D., Carmicino, C. and Savino, R., “Transient Computational Thermofluid -

Dynamic Simulation of Hybrid Rocket Internal Ballistics”, Jr. of Propulsion and Power, 2017

(Online)

Marxman, G. A., Wooldridge, C. E., and Muzzy, R. J., “Fundamentals of Hybrid Boundary Layer

Combustion,” AIAA Progress in Astronautics and Aeronautics: Heterogeneous Combustion,

edited by Wolfhard, H. G., Glassman, I., and Green, L., Jr., 1963, Vol. 15, pp. 485–522.

Mukunda, H. S., Jain, V. K. and Paul, P. J., “A review of hybrid rockets: present status and future

potential”, Proe. Indian Acad. Sci., May 1979, Vol. C 2, part 1, pp. 215–242.

Martin, F., Chapelle, A., Orlandi, O., and Yvart, P., “Hybrid Propulsion Systems for Future Space

Applications,” 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA

Paper 2010–6633, July 2010.

Netzer, D.W., “Hybrid Rocket Internal Ballistics,” Chemical Propulsion Information Agency

Publ. No. 222, Naval Postgraduate School, Monterey, CA, Jan. 1972.

Peretz, A., Einav, O., Hashmonay, B. A., Birnholz, A. and Sobe, Z., “Development of a

Laboratory-Scale System for Hybrid Rocket Motor Testing”, Jr. of Propulsion and Power,

Jan–Feb 2011, Vol. 27, No. 1, pp. 190 – 196.

Pastrone, D., Casalino, L. and Carmicino, C., “Analysis of Acoustics and Vortex Shedding

Interactions in Hybrid Rocket Motors”, AIAA Early Edition Jr. of Propulsion and Power, 2006,

pp. 1–7.

Quigley, N. and Lyne, J. E., “Development of a Three-Dimensional Printed, Liquid-Cooled

Nozzle for a Hybrid Rocket Motor”, Jr. of Propulsion and Power, November–December 2014,

Vol. 30, No. 6, pp. 1726–1727.

Gomes, S. R., Rocco, L., and Rocco, J. A. F. F., “Swirl Injection Effects on Hybrid Rocket

Motors”, J. Aerosp. Technol. Manag., São José dos Campos, Oct.-Dec., 2015, Vol.7, No 4, pp.

–424. (doi: 10.5028/jatm.v7i4.368)

Sutton, G. P., and Biblarz, O., “Hybrid Propellant Rockets,” Rocket Propulsion Elements, 7th ed.,

Wiley, New York, 2001, pp. 585–593.

Whitmore, S. A., Peterson, Z. W. and Eilers, S. D., “Closed-Loop Precision Throttling of a

Hybrid Rocket Motor”, Jr. of Propulsion and Power, Mar–Apr 2014, Vol. 30, No. 2, pp. 325–336.

Zilwa, S. D., Zilliac, G. and Reinath, M., “Time-Resolved Fuel-Grain Port Diameter

Measurement in Hybrid Rockets”, Jr. of Propulsion and Power, Jul.–Aug. 2004, Vol. 20, No. 4,

pp. 684–689.

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