Abstract
AbstractAmmonium 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.
Highlights
Hydrazine and its derivatives have been the standard propellants for spacecraft propulsion system since the 1960s, but they are highly toxic and carcinogenic
Ammonium dinitramide (ADN, NH4+ N(NO2)2-) based monopropellants are extremely promising as hydrazine replacement
This is a limitation of ADN thrusters compared to hydrazine ones: the catalysts currently used for hydrazine (S405 or similar) are cold start capable, even if preheating is often used to increase the lifetime of the catalyst
Summary
Hydrazine and its derivatives have been the standard propellants for spacecraft propulsion system since the 1960s, but they are highly toxic and carcinogenic. Ammonium dinitramide (ADN, NH4+ N(NO2)2-) based monopropellants are extremely promising as hydrazine replacement. In the case of the PRISMA thruster the maximum load during preheating was 9.25W and 8.3W during firing [2] Cold start is not possible: the decomposition starts only if the catalyst has reached its operational temperature of 350 °C. This is a limitation of ADN thrusters compared to hydrazine ones: the catalysts currently used for hydrazine (S405 or similar) are cold start capable, even if preheating is often used to increase the lifetime of the catalyst. A reduction in preheat power would be a benefit for small satellites, where the available power is limited [2]
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