This article describes an experimental investigation into the heat fluxes generated by combustion of AP/HTPB solid propellant samples inside 1?MPa pressurized chambers. Fluxmeters developed at ONERA and recently improved were used to measure local flux densities. Two kind fluxmeters used: total for which convective radiative components are measured component is suppressed use a sapphire window ...

Enhancement of Volumetric Specific Impulse in HTPB/Ammonium Nitrate Mixed Hybrid Rocket Systems by Jacob W. Forsyth, Master of Science Utah State University, 2016 Major Professor: Dr. Stephen A. Whitmore Department: Mechanical and Aerospace Engineering Hybrid rocket systems are safer and have higher specific impulse than solid rockets. However, due to large oxidizer tanks and low regression rat...

The paper presents a useful engineering model for the design of preliminary hybrid rocket engines. This involves experimentally obtained equation regarding speed burning interface between solid fuel and gaseous phase, called regression rate. rate characterizes mass additionally oxidizer through imposed ratio these rates during combustion. is applied to combustion using pure HTPB oxygen was deve...

The feasibility of 3D-printed molds for complex solid fuel block geometries hybrid rocket engines is investigated. Additively produced offer more degrees freedom in designing an optimized but easy to manufacture mold. used this demonstration was hydroxyl-terminated polybutadiene (HTPB). Polyvinyl alcohol (PVA) chosen as the mold material due its good dissolving characteristics. It shown that co...