Nitrous oxide/propane rocket test results

Smith, Norman F.; Moser, Marlow D.; Kopicz, Charles; Herdy, Roger

doi:10.2514/6.2000-3222

Cited by 3 publications

(1 citation statement)

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“…Hydrocarbons have been used to decrease the required temperature for the catalytic decomposition of N 2 O [42]. Although most developed bipropellants using N 2 O/C 3 H 8 have utilized catalyst beds [43,44], direct arc ignition of the N 2 O-hydrocarbon has been applied commercially in chemical thrusters with growing space heritage [32]. Among the considered storable hydrocarbons, C 3 H 8 offers low pressure, which will not result in a meaningful mass penalty, while still being high enough to allow for self-pressurizing.…”

Section: Propellants Selection and Study Objectivesmentioning

confidence: 99%

Testing of the N2O/HDPE Vortex Flow Pancake Hybrid Rocket Engine with Augmented Spark Igniter

Palacz,

Cieślik

2023

Aerospace

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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 N2O/HDPE VFP hybrid ignited with N2O/C3H8 torch igniter. The N2O 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 N2O/HDPE propellants in the VFP configuration.

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Section: Propellants Selection and Study Objectivesmentioning

confidence: 99%