Assessment of high performance HAN-monopropellants

Wucherer, E.; Christofferson, Stacy; Reed, Brian D.

doi:10.2514/6.2000-3872

Cited by 44 publications

(20 citation statements)

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“…HAN-based aqueous blends have been investigated mainly by US (Meinhardt et al, 1999;Wucherer et al, 2000), French (Courthéoux et al, 2002) and Japanese groups (Katsumi et al, 2010 (Klingenberg et al, 1997;Hisatsune et al, 2004 (Schmidt & Gavin, 1996): unsupported platinum group metals (wire mesh and sponge) and supported catalysts (32 % Ir, 10 % Pt, 12 % Rh) were proposed to start ignition between 80 and 120 °C. Decomposition of HAN-glycine-water mixtures on Shell 405 (Ir/Al 2 O 3 catalyst developed for the decomposition of hydrazine) and other home made catalysts was studied for application in small thrusters (Meinhardt et al, 1999).…”

Section: Results On Han-based Propellantsmentioning

confidence: 99%

Application of Ionic Liquids to Space Propulsion

Kamal¹,

Yann²,

Brahmi³

et al. 2011

Applications of Ionic Liquids in Science and Technology

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Section: Results On Han-based Propellantsmentioning

confidence: 99%

Application of Ionic Liquids to Space Propulsion

Kamal¹,

Yann²,

Brahmi³

et al. 2011

Applications of Ionic Liquids in Science and Technology

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“…Initial experience was gained with HAN/glycine and HAN/methanol formulations 6 . Shifting focus to AFRL-developed AF-M315E ionic liquid advanced monopropellant in 2001, AR's green thruster technologies had matured to TRL5 by 2011, meeting the IHPRPT Phase II objective of 50% increased density-Isp over conventional hydrazine equivalents.…”

Section: Introductionmentioning

confidence: 99%

GPIM Propulsion System Development Status

Spores¹

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The NASA Space Technology Mission Directorate's (STMD) Green Propellant Infusion Mission (GPIM) Technology Demonstration Mission (TDM) will demonstrate an operational AF-M315E green propellant propulsion system. Aerojet-Rocketdyne is responsible for the development of the propulsion system payload. This paper statuses the propulsion system module development, including thruster design and system design; Initial test results for the 1N engineering model thruster are presented.The culmination of this program will be high-performance, green AF-M315E propulsion system technology at TRL 7+, with components demonstrated to TRL 9, ready for direct infusion to a wide range of applications for the space user community. NomenclatureEM = Engineering model ESPA = EELV secondary payload adapter GPIM = Green Propellant Infusion Mission HAN = Hydroxyl ammonium nitrate I sp = Specific Impulse IHPRPT = Integrated High Payoff Rocket Propulsion Technology SCAPE = Self-Contained Atmospheric Protection Ensemble TRL = Technology Readiness Level

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“…An iridium based solid catalyst is widely used as the ignition system in RCS thrusters, and a majority of them is S405 from Aerojet Rocketdyne in the United States. However, S405 reportedly has been tested to the recent green monopropellant, especially HAN-based, and S405 could not deliver sufficient performance and acceptable lifetime to RCS thrusters [10][11] . In order to employing the recent green monopropellants, either of two technical challenges in the field of ignition system, listed as follows, needs to be solved.…”

Section: Introductionmentioning

confidence: 99%

Basic Characteristics of Discharge Plasma Ignition System for 1N-class RCS Thruster with Green Monopropellant

Iizuka¹,

Shindo²,

Wada³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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A new ignition system utilizing discharge plasma for reaction control system (RCS) thrusters with green monopropellant is designed and evaluated experimentally in this study. The discharge plasma ignition system laboratory model (DPI-LM) is designed for one of hydroxyl ammonium nitrate (HAN) based monopropellant, SHP163; moreover, the DPI-LM is in substitution for conventional solid catalyst. Objectives of this study are (1) to design and build of DPI-LM and (2) evaluate basic propellant ignition characteristics in terms of successful and stable propellant ignition conditions, power consumption, and fundamental lifetime estimation. In addition, in order to generate discharge plasma prior to propellant ignition, a noble gas is used. Effect of noble gas type, argon and helium, on propellant ignition characteristics are also evaluated. Argon gas shows better propellant ignition with wide ranges of argon and SHP163 mass flow rates. It is considered that the propellant ignition strongly connects to discharge plasma diffusion condition prior to ignition. The power consumption at an argon mass flow rate of 0.075 g/s and a SHP163 mass flow rate of 0.3 g/s is approximately 270 W. The electrode degradation as a function of accumulated experiment time is evaluated as simplified lifetime estimation. The results of the degradation is only 0.1 % in electrode mass at 2000s , and the stable propellant ignition keeps at an accumulated time of 2000 s. Nomenclature I (t) = instantenous discharge current PW = power consumption t p,i = beginning time of the phase t p,f = end time of the phase V (t) = instantenous discharge voltage Δt p = duration of the phase 1 Graduate Student, Department of Aerospace Engineering, tiizuka@astak3.sd.tmu.ac.jp, Student Member.

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Assessment of high performance HAN-monopropellants

Cited by 44 publications

References 0 publications

Application of Ionic Liquids to Space Propulsion

Application of Ionic Liquids to Space Propulsion

GPIM Propulsion System Development Status

Basic Characteristics of Discharge Plasma Ignition System for 1N-class RCS Thruster with Green Monopropellant

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