The RHEFORM Project - Developments for ADN-Based Liquid Monopropellant Thrusters

Wilhelm, Marius; Negri, Michele; Hendrich, Christian; Wingborg, Niklas; Gediminas, Linus; Adelö, Leif; Maleix, Corentin; Chabernaud, Pierre; Brahmi, Rachid; Beauchet, Romain; Batonneau, Yann; Kappenstein, Charles; Koopmans, Robert-Jan; Schuh, Sebastian; Bartok, Tobias; Scharlemann, Carsten; Anflo, Kjell; Persson, Mats; Dingertz, Wilhelm; Gotzig, Ulrich; Schwentenwein, Martin

doi:10.2514/6.2017-4672

Cited by 4 publications

(1 citation statement)

References 4 publications

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“…The only "green" satellite propulsion technology that has to date gained actual space heritage as monopropellant replacement is the ADN-based monopropellant by ECAPS that made its debut in 2010 aboard the Swedish Prisma satellite and was recently launched aboard the American SkySat constellation [7][8][9][10][11][12][13][14][15][16][17][18]. While the ADN-based monopropellant technology has thus gained the highest technological readiness level (TRL) among the emerging "green" monopropellants, it is still being evaluated in R&D programs, such as the European Horizon 2020 [19][20][21][22][23], US "green" propulsion evaluation programs [15], and before that the European FP7 Green Advanced Space Propulsion (GRASP) program in which the corresponding author too had actively contributed to the information generated by the program [18].…”

Section: Introductionmentioning

confidence: 99%

Green Comparable Alternatives of Hydrazines-Based Monopropellant and Bipropellant Rocket Systems

Hasan¹,

Grinstein²,

Kuznetsov³

et al. 2019

Aerospace Engineering

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Concepts are presented for "green" (with reduced hazards) replacements for monopropellant hydrazine propulsion systems and for hypergolic bipropellant systems while maintaining similar performance. At the onset of the "green propulsion" age, "green" alternatives to hydrazine propulsion have been emerging. The introduction rate of these into space systems is very slow due to the conservatism of the space propulsion industry. The concept presented here for monopropellant hydrazine systems offers gradual conversion to "green propellants" by dual capability of conventional hydrazine systems and ammonium dinitramide (ADN)-based systems. An initial risk reduction program has been carried out for materializing the concept. It includes proof of concept of dual use of all propulsion system parts. Materials compatibility and actual operation have been demonstrated. For bipropellants, we present the emerging "green" hypergolic system based on kerosene and peroxide, similar in performance to MMH/N 2 O 4 . Results of the proof-of-concept and development model systems are presented. The experimental results of various engine types demonstrate the capability to operate in both pulse and steady-state modes and the ability to produce different thrust levels. The fuel and oxidizer show very robust hypergolicity and short ignition delay times, as well as characteristic velocity efficiency exceeding 98%.

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Section: Introductionmentioning

confidence: 99%

Green Comparable Alternatives of Hydrazines-Based Monopropellant and Bipropellant Rocket Systems

Hasan¹,

Grinstein²,

Kuznetsov³

et al. 2019

Aerospace Engineering

View full text Add to dashboard Cite

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Continuous‐Wave Laser Ignition of Non‐Solvent Ionic Liquids Based on High Energetic Salts with Carbon Additives

Itouyama

Habu

2019

Propellants Explo Pyrotec

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The ignition system for ammonium dinitramide‐based non‐solvent ionic liquids (ADN‐EILPs) with a continuous‐wave (CW) laser was investigated. The efficiency of conversion from CW laser power to ignition energy for ADN‐EILPs is important, and carbon additives are expected to enhance the efficiency of conversion. The impact of additive shapes on ADN‐EILP ignition by CW lasers is discussed herein by comparing the results of the ignition behavior observation using a high‐speed infrared camera. The shapes of the carbon additives are of two different types: fine fiber mass, called carbon wool, and powder of graphite. The ignition delay of carbon wool mixed ADN‐EILPs is shorter than that of the sample with graphite powder. The difference in these results might depend on the low dispersibility in ADN‐EILPs of carbon wools and the presence of local heat spots owing to the CW laser. The addition of carbon wools in ADN‐EILPs is expected to facilitate their ignition by CW laser heating.

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Thermal Ignition of ADN‐Based Propellants

Negri

Wilhelm

Ciezki

2019

Propellants Explo Pyrotec

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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.

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The RHEFORM Project - Developments for ADN-Based Liquid Monopropellant Thrusters

Cited by 4 publications

References 4 publications

Green Comparable Alternatives of Hydrazines-Based Monopropellant and Bipropellant Rocket Systems

Green Comparable Alternatives of Hydrazines-Based Monopropellant and Bipropellant Rocket Systems

Continuous‐Wave Laser Ignition of Non‐Solvent Ionic Liquids Based on High Energetic Salts with Carbon Additives

Thermal Ignition of ADN‐Based Propellants

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