Ammonium dinitramide (ADN, NH4+ N(NO2)2−) based monopropellants are extremely promising as hydrazine replacement. Thermal igniters are attractive for ADN thrusters as they allow a more prompt ignition and may be better suited for larger engines (100‐500 N) compared to the currently used preheated catalysts. The results of an experimental campaign conducted on the ignition of two ADN‐based monopropellants (LMP‐103S and FLP‐106) with a torch igniter are presented. Several combustion chamber configurations have been tested to facilitate the ignition. Through the use of porous inlays in the chamber, ignition of both propellants was achieved. It was not possible, however, to achieve sustained combustion under the chosen test conditions.
In 2014 DLR started research activities focused on premixed monopropellants consisting of nitrous oxide and hydrocarbons. Those propellants offer promising characteristics as they are non-toxic, deliver a high I sp consist of components with low cost and could simplify a propulsion system due to self-pressurized operation. Initially DLR chose a mixture of nitrous oxide (N 2 O) and ethene (C 2 H 4 ). In the course of the project, a mixture of nitrous oxide and ethane (C 2 H 6 ) was included to the research activities. The activities are part of DLR's Future Fuels project and divided into five main parts: 1) investigations of the combustion behavior of the propellant in a rocket combustor, 2) testing and developing of flame arresters, 3) development and reduction of reaction mechanisms, 4) numerical simulations of the combustion process and 5) basic miscibility investigations. The emphasis within the project is on the first three tasks, while the last two tasks are used to widen the knowledge about the Head Facilities Group, Propellants Department, AIAA Member.
In the European project Rheform research activities aimed at improving ADN-based propulsion systems have been conducted. ADN-based propellants are extremely promising as hydrazine replacement. They have a lower overall life cycle cost due to simplified handling, higher specific impulse and higher density compared to hydrazine. In the paper an overview of the main results achieved during the project will be given.
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