Title: Combustion of advanced non-toxic hybrid propellants

Authors: Jeremy H. Corpening, R.K. Palmer, Stephen D. Heister, John J. Rusek

Addresses: School of Aeronautics and Astronautics, Purdue University, 315 North Grant St., West Lafayette, IN 47907, USA. ' School of Aeronautics and Astronautics, Purdue University, 315 North Grant St., West Lafayette, IN 47907, USA. ' School of Aeronautics and Astronautics, Purdue University, 315 North Grant St., West Lafayette, IN 47907, USA. ' Swift Enterprises Ltd., Suite B102, 1291 Cumberland Ave., West Lafayette, IN 47906, USA

Abstract: Combustion characteristics and fuel regression behaviour have been studied for two fuels utilising 98% rocket-grade hydrogen peroxide (RGHP) as oxidiser. Two test series (A and C) involved a total of 13 firings of dicyclopentadiene (DCPD) fuel grains and series B involved nine firings of DCPD grains loaded with various amounts of lithium aluminium hydride, LiAlH4 (LAH). A laboratory-scale combustion chamber with a 4.09 cm diameter was used in all firings. Regression rate data have shown a substantial increase as compared to RGHP/low-density polyethylene oxidiser/fuel combination. Results with the LAH-loaded grains showed comparable regression rates, but disappointing levels of combustion efficiency.

Keywords: dicyclopentadiene; DCPD; hybrid rocket; rocket-grade hydrogen peroxide; RGHP; regression rate; lithium aluminium hydride; LAH; combustion efficiency; advanced hybrid propellants; non-toxic hybrid propellants; oxidisers.

DOI: 10.1504/IJAP.2007.013018

International Journal of Alternative Propulsion, 2007 Vol.1 No.2/3, pp.154 - 173

Available online: 03 Apr 2007 *

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