Thermal Ignition of ADN‐Based Propellants

Negri, Michele; Wilhelm, Marius; Ciezki, Helmut

doi:10.1002/prep.201900154

Cited by 22 publications

(8 citation statements)

References 8 publications

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“…The most known ADN-based propellants are LMP 103S, invented by the Swedish company ECAPS and FLP-106, developed by FOI (Swedish Defense Research Agency). LMP-103S offers a 6%-8% higher specific impulse (253 s) than hydrazine and a 24% higher density while being less toxic and not carcinogenic [4,7,8]. The storability of LMP-103S was already tested for more than 7 years and the propellant can be ignited by using a preheated catalyst (approx.…”

Section: A Green Propellants Overviewmentioning

confidence: 99%

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Parameters Influencing the Characteristic Exhaust Velocity of a Nitrous Oxide/Ethene Green Propellant

Werling

Bätz

2022

Journal of Propulsion and Power

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Currently several green propellants are under investigation to replace the toxic and carcinogenic monopropellant hydrazine (N 2 H 4 ). Beside alternatives as Ammonium dinitramide (ADN)-based propellants, Hydroxylammonium nitrate (HAN)-based mixtures or high concentrated hydrogen peroxide (H 2 O 2 ), mixtures of fuels with nitrous oxide -called HyNOx or NOFBX represent promising green propellants. Compared to classical hydrazine, N 2 O/fuel mixtures offer a higher performance ( , * ), no or low toxicity and low propellant costs. To investigate the handling and performance of a propellant mixture consisting of nitrous oxide (N 2 O) and ethene (C 2 H 4 ), hot gas combustion tests with an experimental combustor were conducted. This paper summarizes the results of 134 combustion tests conducted with the premixed propellant injected in gaseous state. Calculated and measured performance ( * and * ) depending on mixture ratio, characteristic combustion chamber length ( * ) and chamber pres-* ℎ

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Section: A Green Propellants Overviewmentioning

confidence: 99%

“…The main difference of FLP-106 in comparison to LMP-103S is the usage of a less volatile fuel. Detailed information about ADN-based monopropellants can be found in references [4,[7][8][9].…”

Section: A Green Propellants Overviewmentioning

confidence: 99%

Parameters Influencing the Characteristic Exhaust Velocity of a Nitrous Oxide/Ethene Green Propellant

Werling

Bätz

2022

Journal of Propulsion and Power

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“…The ECAPS 1N thrusters, specifically developed for ADN-based monopropellant, use a 10 W heater. The preheating time is 1800 s. In the case of the Prisma thruster, the maximum load during preheating was 9.25 and 8.3 W during firing [46].…”

Section: Preheating Temperature Capabilitymentioning

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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“…Three different designs were so built and tested, called respectively Porous-A, Porous-B, and Porous-C. More than 200 hot fire tests were conducted. The results of this test campaign are described in details in [6], here only a summary of the main results is give. The idea behind the three designs (Porous A, B and C) was to use a disc of porous material inside a copper inlay.…”

Section: Fig 4 Schematic Drawing Of the Torch Igniter Experimental Smentioning

confidence: 99%

Development of ADN-based Thruster Technologies – An overview of the European Project Rheform

Negri

Wilhelm

Hendrich

et al. 2018

2018 Joint Propulsion Conference

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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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Thermal Ignition of ADN‐Based Propellants

Cited by 22 publications

References 8 publications

Parameters Influencing the Characteristic Exhaust Velocity of a Nitrous Oxide/Ethene Green Propellant

Parameters Influencing the Characteristic Exhaust Velocity of a Nitrous Oxide/Ethene Green Propellant

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

Development of ADN-based Thruster Technologies – An overview of the European Project Rheform

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