Economic Benefits of the Use of Non-Toxic Mono-Propellants for Spacecraft Applications

Bombelli, V.; Simon, Daniel; Marée, T.; Moerel, J.L.P.A.

doi:10.2514/6.2003-4783

Cited by 51 publications

(33 citation statements)

References 2 publications

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“…A RECENT study by the European Space Agency's (ESA's) European Space Research and Technology Center (ESTEC) has identified two essential design elements to achieving low-cost commercial space access and operations: 1) reduced production, operational, and transport costs due to lower propellant toxicity and explosion hazards, and 2) reduced costs due to an overall reduction in subsystems complexity and overall systems interface complexity [1,2]. The ESA/ESTEC study showed the potential for considerable operational cost savings by simplifying propellant shipping, storage, and ground-handling procedures.…”

Section: Introductionmentioning

confidence: 99%

Three-Dimensional Printing of “Green” Fuels for Low-Cost Small Spacecraft Propulsion Systems

Whitmore

2018

Journal of Spacecraft and Rockets

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This paper details the advantages of employing modern additive manufacturing methods to fabricate hybrid rocket fuels for intrinsically safe and green small spacecraft propulsion systems. Using additive manufacturing overcomes multiple issues frequently associated with hybrid propulsion, including poor volumetric efficiency, system ignitability, and low fuel regression rates. When certain three-dimensionally printed thermoplastics are subjected to a high-voltage low-wattage charge, electrostatic arcing along the surface pyrolizes a small amount of material that, with the introduction of an oxidizer, "seeds" combustion and produces immediate and reliable ignition. Thermoplastic fuel grains can be printed with port shapes that enhance burn properties and increase volumetric efficiencies. Embedded helical fuel ports significantly increase regression rates. The presented test results from several prototype systems using gaseous oxygen and printed acrylonitrile butadiene styrene demonstrate the various advantages of additive manufacturing, including low-power ignition, regression rate enhancement, and system scalability. The test results from both ambient and vacuum tests of a 25 N flight-weight small spacecraft thruster are presented. Multiple burn tests allowed statistical characterization of ignition timing and burn-to-burn thrust, as well as total impulse consistency. The test results demonstrating specific impulse values exceeding 295 s are presented. When fully developed, this propulsion technology has the potential for "drop-in" replacement of many hydrazine-based propulsion applications. = propellant mass flow rate, kg∕s N = number of fuel grain helical loops n = fuel regression rate fit exponential factor O∕F = oxidizer-to-fuel ratio P = helical pitch distance, cm P R = helical pitch ratio P 0 = combustion chamber pressure, kPa p exit = nozzle exit pressure, kPa R g = gas constant for combustion products, J∕kg ⋅ K r = instantaneous longitudinal mean of the fuel port radius, cm r 0 = initial fuel port radius, cm _ r = instantaneous longitudinal mean of the fuel port regression rate, cm S = internal fuel port run length, cm T 0 = combustor flame temperature, K t = time, s γ = ratio of specific heats ΔM fuel = consumed fuel mass, g η = combustion efficiency μ = sample mean ρ fuel = fuel material density, g∕cm 3 σ = sample standard deviation τ rise = motor ignition time, ms

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Section: Introductionmentioning

confidence: 99%

Three-Dimensional Printing of “Green” Fuels for Low-Cost Small Spacecraft Propulsion Systems

Whitmore

2018

Journal of Spacecraft and Rockets

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“…In several publications and studies performed by the space propulsion industry and the European Space Agency, it was outlined that the handling and manipulation of toxic propellants on ground (e. g., on test benches and spacecraft prelaunch preparation facilities) are an increasing cost and time factor which has to be accounted for during the planning of satellite projects. It is a common opinion that the transition to green propellants would bring a high economic bene¦t for the space industry for the near future ¡ despite the fact that a new technology has to be introduced and quali¦ed (see [2] for additional information).…”

Section: Introductionmentioning

confidence: 99%

Development of a green bipropellant hydrogen peroxide thruster for attitude control on satellites

Woschnak

Krejci

Schiebl

et al. 2013

Progress in Propulsion Physics

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This document describes the selection assessment of propellants for a 1-newton green bipropellant thruster for attitude control on satellites. The development of this thruster was conducted as a part of the project GRASP (Green Advanced Space Propellants) within the European FP7 research program. The green propellant combinations hydrogen peroxide (highly concentrated with 87.5 %(wt.)) with kerosene or hydrogen peroxide (87.5 %(wt.)) with ethanol were identi¦ed as interesting candidates and were investigated in detail with the help of an experimental combustion chamber in the chemical propulsion laboratory at the Forschungsund Technologietransfer GmbH ¡ Fotec. Based on the test results, a ¦nal selection of propellants was performed.

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“…Because of hydrazine's toxicity, it is expensive to manufacture and operate spacecraft in terms of their propulsion systems. 1) In order to improve this problem, hydroxylammonium-nitrate-based (HAN-based) solutions and ammonium-dinitramide-based (ADN-based) solutions have been studied as prospective candidates. 2,3) JAXA and Carlit Holdings Co., Ltd. have developed an ADN-based ionic liquid propellant (ADN-based ILP) as one of the prospective candidates.…”

Section: Introductionmentioning

confidence: 99%

Combustion Characteristics of an Ammonium-Dinitramide-Based Ionic Liquid Propellant

Ide

Takahashi

Iwai

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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As a replacement for hydrazine, ammonium-dinitramide-based ionic liquid propellant (ADN-based ILP) has been developed by JAXA and Carlit Holdings Co., Ltd. This propellant is made by mixing three solid powers: ADN, monomethylamine nitrate, and urea. The propellant's theoretical specific impulse is 1.2 times higher than that of hydrazine, and its density is 1.5 times higher at a certain composition. Although ionic liquids were believed to be non-flammable for a long time owing to their low-volatility, recently combustible ILs have been reported. The combustion mechanism of ILs is not yet understood. The objective of this paper is to understand the combustion wave structure of ADN-based ILP. The temperature distribution of the combustion wave in a strand burner test shows a region of constant temperature. This region would indicate boiling in a gas-liquid phase. Thus, the combustion wave structure consists of liquid, gas-liquid, and gas phases. The dependence of boiling point on pressure would identify chemical substances in the gas-liquid phase. The dependence of combustion and ignition characteristics on ADN content is also discussed.

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Economic Benefits of the Use of Non-Toxic Mono-Propellants for Spacecraft Applications

Cited by 51 publications

References 2 publications

Three-Dimensional Printing of “Green” Fuels for Low-Cost Small Spacecraft Propulsion Systems

Three-Dimensional Printing of “Green” Fuels for Low-Cost Small Spacecraft Propulsion Systems

Development of a green bipropellant hydrogen peroxide thruster for attitude control on satellites

Combustion Characteristics of an Ammonium-Dinitramide-Based Ionic Liquid Propellant

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