| Summary: | The paper is part of the research aimed at determining if the vortex flow pancake (VFP) hybrid rocket engine is feasible as green in-space chemical propulsion. The objective of this study is to test an N<sub>2</sub>O/HDPE VFP hybrid ignited with N<sub>2</sub>O/C<sub>3</sub>H<sub>8</sub> torch igniter. The N<sub>2</sub>O is used in self-pressurizing mode, which results in two-phase flow and varying inlet conditions, thus better simulating real in-space behavior. The study begins with characterizing the torch igniter, followed by hot-fire ignition tests of the VFP. The results allow for the improved design of the torch igniter and VFP hybrid. The axial regression rate ballistic coefficients are reported for the N<sub>2</sub>O/HDPE propellants in the VFP configuration.
|
|---|