Large-Scale CAMUI Type Hybrid Rocket Motor Scaling, Modeling, and Test Results

Large Class 1.3 Rocket Motor Detonation Character

Large explosive class 1.3 solid .propellant rocket motors utilizing polybutadiene binder, aluminum fuel, and ammonium perchlorate oxidizer are typically considered explosively vlsafell. That is, the required stimulus is so large that motor detonation is extremely unlikely, even when donored by a sizeable high explosive charge. Two large ground cratering events have occurred during recent years ...

Design and Test of a Lab-scale N2o/htpb Hybrid Rocket

The MaCH-SR1 project involved the design of a 1000lb thrust hybrid rocket with the effort being undertaken during two semesters by 8 senior aerospace engineering students at the University of Colorado at Boulder. The 2002-2003 team was the second year for the project, as the previous team built two static engines and performed test burns on both. The hybrid implemented a liquid O2/HTPB oxidizer...

Modeling and Simulation of Large-scale Hybrid Systems

Visualization of Combustion Within a Hybrid Rocket Motor

A visualization facility has been developed at Stanford University in order to study flow in a turbulent combustion boundary layer. The motivation for the facility arises from recent studies of fast burning fuels for hybrid rocket propulsion where droplet lift-off from the melting fuel surface is the dominant mass transfer mechanism. The facility, shown in Figure 1, has been used to image the c...

A Labscale Hybrid Rocket Motor for Instrumentation Studies

An interest in plume spectroscopy led to the development of a labscale Hybrid Rocket Facility at the University of Arkansas at Little Rock (UALR). The goal of this project was to develop a reliable, consistent rocket motor testbed for the development of plume spectroscopy instrumentation. Hybrid motor technology was selected because it has proven to be safe and inexpensive to operate. The proje...