New technologies for ammonium dinitramide based monopropellant thrusters – The project RHEFORM

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

doi:10.1016/j.actaastro.2017.11.016

Cited by 64 publications

(33 citation statements)

References 7 publications

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“…The decrease in I sp and density compared to FLP-106 shall lead to a larger propellant volume, which is a critical resource for a CubeSat. Although LMP-103S has been flight demonstrated, FLP-106 is preferred due ot its better performance and its presumed maturation within 2024 [28], at which the MARIO mission is envisaged to be launched.…”

Section: A System Types and Trade-offmentioning

confidence: 99%

Combined Chemical–Electric Propulsion for a Stand-Alone Mars CubeSat

Mani

Cervone

Topputo

2019

Journal of Spacecraft and Rockets

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Stand-alone interplanetary CubeSats require primary propulsion systems for orbit maneuvering and precise trajectory control. The current work focuses on the design and performance characterization of the combined chemical-electric propulsion systems that shall enable a stand-alone 16U CubeSat mission on a hybrid high-thrust-low-thrust trajectory from a Supersynchronous Geostationary Transfer Orbit to a circular orbit about Mars. The high-thrust chemical propulsion is used to escape Earth and to initiate stabilization at Mars. The low-thrust electric propulsion is used in heliocentric transfer, ballistic capture, and circularization. For chemical propulsion, design and performance characteristics of a monopropellant thruster and feed system utilizing ADN-based FLP-106 propellant are presented. For electric propulsion, a performance model of an Iodine-propelled inductively coupled miniature radiofrequency ion thruster is implemented to calculate the variation of thrust, specific impulse and efficiency with input power. A power constrained low-thrust trajectory optimization utilizing the thruster performance model is pursued to calculate the transfer time, ∆V and the required propellant mass for fuel-optimal and time-optimal transfers. Overall, the combined chemical-electric systems yield a feasible propulsion solution for stand-alone CubeSat missions to Mars that balances propellant mass and transfer time.

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Section: A System Types and Trade-offmentioning

confidence: 99%

Combined Chemical–Electric Propulsion for a Stand-Alone Mars CubeSat

Mani

Cervone

Topputo

2019

Journal of Spacecraft and Rockets

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“…A secondary satellite using ADN-based monopropellant will be better ac-cepted as rideshare compared to a satellite using hydrazine, due to the safer propellant. The present work has been conducted in the framework of the Rheform project [6], [7]. Rheform was a project funded from the European's Union Horizon 2020 programme.…”

Section: Introductionmentioning

confidence: 99%

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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“…For example, SHP163 [2][3][4] and AFÀ M315E [5][6][7] have been investigated as aqueous GmPs with hydroxylammonium nitrate (HAN). FLP-106 [8][9][10] and LMP-103 S [11][12][13] are known as aqueous GmPs with ammonium dinitramide (ADN). Meanwhile, the utilization of HEMs is expected to increase the energy density of GmPs and water; alcohol, as a solvent, is expected to decrease the combustion temperature of HEMs.…”

Section: Introductionmentioning

confidence: 99%

“…For example, laser ignition has been applied to internal combustion engines [29][30][31]. In the field of space propulsion, laser ignition has been actively investigated in recent years [8,32].…”

Section: Introductionmentioning

confidence: 99%

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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New technologies for ammonium dinitramide based monopropellant thrusters – The project RHEFORM

Cited by 64 publications

References 7 publications

Combined Chemical–Electric Propulsion for a Stand-Alone Mars CubeSat

Combined Chemical–Electric Propulsion for a Stand-Alone Mars CubeSat

Thermal Ignition of ADN‐Based Propellants

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

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