Investigations of the 1 kW Class Arcjet ARTUR-2 with Helium as Propellant

Rybakov, Andriy; Heiermann, Joerg; Auweter‐Kurtz, Monika; Kurtz, H.; Riehle, Martin

doi:10.2514/6.2002-3659

Cited by 3 publications

(5 citation statements)

References 2 publications

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“…14, which assumes constant tangential thrust, the approximations in Eqs. (18) and (19) can also be shown to be valid for the case where the nominal thruster performs a two-impulse Hohmann transfer maneuver. From the rocket equation,…”

Section: B Preliminary Cost/benefit Analysis For Incorporating the Hmentioning

confidence: 87%

“…(20), and last performing a Taylor series for m HIT in terms of small , the simplified result is identical to that in Eq. (18). Therefore, the break-even mass approximation in Eq.…”

Section: B Preliminary Cost/benefit Analysis For Incorporating the Hmentioning

confidence: 95%

“…Although helium is a heavier atom than hydrogen, it is monatomic, and thus it is less prone to frozen flow losses [17]. The helium arcjet design has achieved a maximum specific impulse I SP of 760 s and thrust of 112 mN at a thrust efficiency of 50.2% [18].…”

Section: Previous Workmentioning

confidence: 99%

“…In all cases, the zeroth-order term in the Taylor series dominates, and the dependency on m 0 , is therefore removed, leaving a very simple approximation for the break-even mass: m HIT m P (19) Despite the fact that Eqs. (18) and (19) were derived using the burnout radius, Eq. 14, which assumes constant tangential thrust, the approximations in Eqs.…”

Section: B Preliminary Cost/benefit Analysis For Incorporating the Hmentioning

confidence: 99%

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Utilization of Residual Helium to Extend Satellite Lifetimes and Mitigate Space Debris

Walker

Russell

Singh

2012

Journal of Propulsion and Power

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A new electric propulsion device concept takes advantage of residual helium gas that is trapped in the chemical propellant feed system and currently unused at end of life. The helium ion thruster provides additional propellant resources to extend satellite lifetimes and transfer geostationary orbit space assets to ultrasafe disposal orbits. The predicted capability, if fully allotted to the disposal, allows for perigee heights above the geostationary altitude that are one order of magnitude greater than existing international guidelines of 250 km. Furthermore, the proposed helium ion thruster concept makes the classic propellant gauge uncertainty problem moot, as satellite operators could use all of their conventional propellant for nominal station-keeping operations. The helium ion thruster concept therefore mitigates future space debris arising from depleted assets in the geostationary orbit belt through both aggressive orbit raising and depressurization of satellites at end of life. An analysis of the helium ion thruster theoretical performance shows that the device could raise the altitude of an end-of-life 2500 kg, 5 kW spacecraft by 2200 km in two months using 2 kg of residual helium.

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Section: B Preliminary Cost/benefit Analysis For Incorporating the Hmentioning

confidence: 87%

“…(20), and last performing a Taylor series for m HIT in terms of small , the simplified result is identical to that in Eq. (18). Therefore, the break-even mass approximation in Eq.…”

Section: B Preliminary Cost/benefit Analysis For Incorporating the Hmentioning

confidence: 95%

Section: Previous Workmentioning

confidence: 99%

Section: B Preliminary Cost/benefit Analysis For Incorporating the Hmentioning

confidence: 99%

See 2 more Smart Citations

Utilization of Residual Helium to Extend Satellite Lifetimes and Mitigate Space Debris

Walker

Russell

Singh

2012

Journal of Propulsion and Power

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“…An investigation using helium as propellant was conducted at IRS (Rybakov et al , 2002) showing high thrust efficiency gains above 50-70 per cent due to high ionization energy threshold and absent dissociation but suffering operation stability problems. Similar performance has been proven by Aerospace Corp (Welle, 1997) realizing that an increased electrode gap and increased mass flow dramatically improves arc stability and thrust efficiency.…”

Section: Overview Of Arcjet Power Classesmentioning

confidence: 99%

Overview of thermal arcjet thruster development

Wollenhaupt¹,

Le²,

Herdrich³

2018

AEAT

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Purpose This paper aims to provide an overview of current and historical arcjet development. The reviewed arcjets are considered with respect to both design and thruster relevant parameters. Correspondingly, the paper enables the identification of adequate design criteria and of the probable thruster parameters. Design/methodology/approach The approach consists of a database for thruster relevant parameters in conjunction with relevant operational requirements (such as type of propellant) and specific design criteria (such as e.g. propellant injection systems). Findings The synopsis of both operational parameter and respectively assigned design allows for the derivation of development approaches for arcjets under given high level requirements such as power regime. Research limitations/implications The paper is a general review. However, its strength is in the synthesis of the arcjet classification, the functional evidence of design criteria and the application scenario. Practical implications Not only basic but also specific design criteria are analyzed and evaluated leading to a recommendation feature of the paper with respect to the overall design of adequate arcjets. Social implications Within the scope of the Clean Space initiative, new applications and scenarios from the operation of arcjets arise enabling EOL phases of spacecraft that fulfill respective levels of debris mitigation and, in addition, the requirements concerning the adequately adapted re-entry of spacecrafts that are at end of life. Originality/value The paper is a general review. However, its strength is in the synthesis of the arcjet classification, the functional evidence of design criteria and the application scenario.

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High-Power and High-Thrust-Density Electric Propulsion for In-Space Transportation

Auweter‐Kurtz¹,

Kurtz²

2008

Nuclear Space Power and Propulsion Systems

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Investigations of the 1 kW Class Arcjet ARTUR-2 with Helium as Propellant

Cited by 3 publications

References 2 publications

Utilization of Residual Helium to Extend Satellite Lifetimes and Mitigate Space Debris

Utilization of Residual Helium to Extend Satellite Lifetimes and Mitigate Space Debris

Overview of thermal arcjet thruster development

High-Power and High-Thrust-Density Electric Propulsion for In-Space Transportation

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