Accession Number : ADA470435


Title :   Investigation of Non-Conventional Bio-Derived Fuels for Hybrid Rocket Motors


Descriptive Note : Doctoral thesis


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT


Personal Author(s) : Putnam, Scott G


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a470435.pdf


Report Date : Aug 2007


Pagination or Media Count : 144


Abstract : Non-conventional bio-derived fuels have been evaluated for use in hybrid rocket motors. Tests were conducted at combustion pressures in the range of 100 - 220 psig and thrust levels of 40 - 170 newtons. Beeswax was tested with oxygen as the oxidizer and showed a regression rate at least three times as high as traditional hybrid propellant combinations such as hydroxyl-terminated polybutadiene (HTPB) and liquid oxygen (LOX). This provides the promise of a high thrust hybrid rocket motor using a simple, single port geometry and overcomes the main weakness of traditional hybrid rocket motor propellants, which are low regression rates. Beeswax was also tested with nitrous oxide as an oxidizer, but further testing is needed to attain high enough combustion chamber pressures to achieve stable combustion. Experimental evaluation of the specific impulse for beeswax and oxygen was moderately successful for lab scale testing, but needs further refinement. Analytical studies were performed to evaluate the theoretical performance of non-conventional hybrid rocket motors This analysis indicates beeswax, lard, a mixture of paraffin and lard, and combinations of beeswax and aluminum should all perform better than traditional hybrid rocket propellants considered when burned with oxygen.


Descriptors :   *FUELS , *HYBRID ROCKET ENGINES , TEST AND EVALUATION , LABORATORY TESTS , THESES , SCALE , COMBUSTION CHAMBERS , ROCKET ENGINES , ROCKETS , NITROUS OXIDE , HYBRID ROCKET PROPELLANTS , HYBRID PROPELLANTS , HYDROXY TERMINATED POLYBUTADIENE , BEESWAX , SUBORBITAL TRAJECTORIES , LIQUID OXYGEN , SPECIFIC IMPULSE , LAUNCH VEHICLES , OXIDIZERS , PRESSURE , REGRESSION ANALYSIS , OXYGEN , COMBUSTION


Subject Categories : Fuels
      Rocket Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE