Advances in Hypergolic Propellants: Ignition, Hydrazine, and Hydrogen Peroxide Research

Stephen M Davis,Nadir Yilmaz

doi:10.1155/2014/729313

Stephen M Davis, Nadir Yilmaz

Open Access

https://doi.org/10.1155/2014/729313

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Abstract

A review of the literature pertaining to hypergolic fuel systems, particularly using hydrazine or its derivatives and hydrogen peroxide, has been conducted. It has been shown that a large effort has been made towards minimizing the risks involved with the use of a toxic propellant such as the hydrazine. Substitution of hydrazines for nontoxic propellant formulations such as the use of high purity hydrogen peroxide with various types of fuels is one of the major areas of study for future hypergolic propellants. A series of criteria for future hypergolic propellants has been recommended, including low toxicity, wide temperature range applicability, short ignition delay, high specific impulse or density specific impulse, and storability at room temperature.

Highlights

In typical combustion systems an ignition source such as a spark is needed to begin the combustion reaction [1]
By observing the ignition of high test peroxide (HTP) with Block 0 it was determined that the pressure dependence on ignition delay for liquid hypergols is inversely proportional to the log of the pressure [8]
Specific impulses approximately 10% greater than monomethyl hydrazine (MMH)/nitrogen tetroxide (NTO) at 3371 N∗s/kg and 3161 N∗s/kg were reported for SiH4-98% HTP and Si5H14-98% HTP, respectively

Summary

Introduction

In typical combustion systems an ignition source such as a spark is needed to begin the combustion reaction [1]. A combination of two materials which self-ignites at room temperature is called hypergolic Because they do not require external ignition forces (compression, spark, heating, catalytic decomposition, etc.), hypergolic mixtures need only a valve to mix the fluids and initiate combustion. This simple mechanism for controlling combustion reduces the number of components in the ignition system which reduces the statistical chances for failure as well as the payload of the system relative to nonhypergolic systems. Such a system with few mechanical parts and low weight is favorable to extraterrestrial craft. Regardless of definition the time to ignition is important to the performance of a rocket propellant where a long delay leads to combustion outside of the combustion chamber or causes hard-starts, whereas a very short delay risks damaging the injection nozzle [7]

Ignition Measurements

Hydrazine-Based Hypergolics

Hydrogen Peroxide-Based Hypergolics

Other Propellant Formulations

Findings

Conclusions