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Hot Firing Tests of a Novel Green Hypergolic Propellant in a Thruster

Negri, Michele and Lauck, Felix (2022) Hot Firing Tests of a Novel Green Hypergolic Propellant in a Thruster. Journal of Propulsion and Power. American Institute of Aeronautics and Astronautics (AIAA). doi: 10.2514/1.B38413. ISSN 0748-4658.

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Official URL: https://arc.aiaa.org/doi/10.2514/1.B38413


This study investigates the ignition and combustion behavior of the recently developed green hypergolic combination named HIP_11 in a small thruster. The combination HIP_11 consists of highly concentrated hydrogen peroxide as oxidizer and a fuel based on the ionic liquid 1-ethyl-3-methylimidazolium thiocyanate (EMIM SCN) with addition of copper thiocyanate (Cu SCN) to facilitate the hypergolic ignition. A dedicated thruster, featuring a 2-on-1 unlike impinging jet injector, was designed and manufactured. The initial tests were conducted with the injector only, without the combustion chamber mounted. These tests were conducted with two different amounts of catalyst: 1% and 5% Cu SCN. Subsequently, three hot firing series (around 35 tests) were conducted with the complete thruster, using the propellant combination 97% high-test peroxide and EMIM SCN+5% Cu SCN. The propellant mass flow rates were varied between 7 and 13  g/s and the oxidizer-to-fuel ratio from 3 to 7.

Item URL in elib:https://elib.dlr.de/148609/
Document Type:Article
Title:Hot Firing Tests of a Novel Green Hypergolic Propellant in a Thruster
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Negri, MicheleUNSPECIFIEDhttps://orcid.org/0000-0003-2204-9916UNSPECIFIED
Lauck, FelixUNSPECIFIEDhttps://orcid.org/0000-0002-6599-0805UNSPECIFIED
Date:18 January 2022
Journal or Publication Title:Journal of Propulsion and Power
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:Yes
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
Keywords:Bipropellant Thruster, Hypergolic Propellant, Green Propellant, Chamber Pressure, Total Mass Flow Rate, High Test Peroxide, Catalysts, Steady State Combustion, Characteristic Velocity, Combustors
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transportation
DLR - Research area:Raumfahrt
DLR - Program:R RP - Space Transportation
DLR - Research theme (Project):R - Agile development of advanced rocket propulsion systems
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Spacecraft and Orbital Propulsion
Deposited By: Lauck, Felix
Deposited On:06 Apr 2022 08:23
Last Modified:06 Apr 2022 08:23

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