ARTEMIS orbit raising inflight experience with ion propulsion

Killinger, Rainer; Kukies, Ralf; Surauer, M.; Tomasetto, Angeo; Holtz, L. van

doi:10.1016/s0094-5765(03)80022-x

Cited by 43 publications

(18 citation statements)

References 3 publications

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“…(a) and (b), respectively. The field plots correspond to a coil current of Ĩ c = I c =5.28 A; i.e., a purely sinusoidal current with no starting phase, a volumetric xenon flow rate of V̇ = 0.15 sccm, and 116 3 Cartesian mesh nodes within the simulation domain. The coil current chosen corresponds to an extracted current of I b = 5 mA.…”

Section: Simulation Results and Verificationmentioning

confidence: 99%

Self-Consistent Numerical 0D/3D Hybrid Modeling of Radio-Frequency Ion Thrusters

Volkmar¹,

Ricklefs²,

Klar

2016

AEROSPACE TECHNOLOGY JAPAN

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In this paper, we show a numerical model of gridded radio-frequency (RF) ion thrusters. The model consists of a set of self-consistently coupled equations based on conservation of charge, energy, and mass inside the system. Those 0D models are again coupled to a 3D quasi-stationary electromagnetic field solver which offers the opportunity of evaluating arbitrary induction coil and discharge chamber geometries in fairly reasonable simulation time. Several input parameter sets can be computed in parallel due to multi-core implementation. Therefore, the model presented can be regarded as a toolbox for ion thruster engineering purposes and rapid virtual prototyping. The model predicts electrical parameters such as thruster and plasma impedance as well as propulsive performance data. It is thus possible to use it for finding optimized coil and chamber geometries together with optimized input parameters (coil current, volumetric propellant flow rate, and extraction grid voltages) in order to obtain improved mass and electrical efficiency. To prove the validity of the model, performance mappings experimentally performed on a RIM-4 RF ion thruster assembled at the University of Giessen are used to verify the computed data.

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Section: Simulation Results and Verificationmentioning

confidence: 99%

Self-Consistent Numerical 0D/3D Hybrid Modeling of Radio-Frequency Ion Thrusters

Volkmar¹,

Ricklefs²,

Klar

2016

AEROSPACE TECHNOLOGY JAPAN

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“…The masses of the components of the IPS were deduced largely from the Artemis programme [3], taking into account expected advances in electronics and propellant feed technologies [9]. The latter assumed the use of MEMS components for certain functions, such as temperature and pressure sensors.…”

Section: Spacecraft Designmentioning

confidence: 99%

“…This very large gain can be further enhanced by utilising an even less costly launch vehicle to deploy the spacecraft initially into a low Earth orbit (LEO) or to geostationary transfer orbit (GTO). Earth escape can then be achieved via a spiral orbit-raising manoeuvre, as recently undertaken by the Artemis communications satellite [3]. A similar transfer from GTO will soon be demonstrated during the SMART-1 [4] lunar mission.…”

Section: Introductionmentioning

confidence: 99%

The impact of advanced platform and ion propulsion technologies on small, low-cost interplanetary spacecraft

Clark

Fearn

2006

Acta Astronautica

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“…The Japanese ETS-VIII uses ion thrusters for north-south station keeping. ESA's GOCE mission, launched in March 2009, employs ion propulsion for precision orbital control in low Earth orbit [5], and ESA's Artemis mission used the RIT-10 ion propulsion system for transfer to a geostationary orbit [6]. Approximately 72 ion thrusters (13-cm-dia and 25-cm-dia) are aboard 32 communication satellites for orbit-raising and station-keeping functions, accumulating ~450,000 operating hours in flight [7].…”

Section: Introductionmentioning

confidence: 99%

In-Flight Operation of the Dawn Ion Propulsion System Through Year One of Cruise to Ceres

Garner

Rayman

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The Dawn mission, part of NASA's Discovery Program, has as its goal the scientific exploration of the two most massive main-belt asteroids, 4 Vesta, and the dwarf planet 1 Ceres. The Dawn spacecraft was launched from the Cape Canaveral Air Force Station on September 27, 2007 on a Delta-II 7925H-9.5 rocket that placed the 1218-kg spacecraft into an Earth-escape trajectory. On-board the spacecraft is an ion propulsion system (IPS) developed at the Jet Propulsion Laboratory which will provide an additional delta-V of approximately 11 km/s for the heliocentric transfers to each body and for all orbit transfers including orbit capture/escape and transition to the various science orbits. Deterministic thrusting to Vesta began in December 2007 and concluded with orbit capture at Vesta in July 2011. The transfer to Vesta included a Mars gravity assist flyby in February 2009 that provided an additional delta-V of 2.6 km/s and was the only postlaunch mission delta-V not provided by IPS. During the mission at Vesta the IPS was used for all orbit transfers which included six different near-polar science mapping orbits. Thrusting for departure from Vesta and the start of cruise to Ceres began on July 25, 2012 with escape from Vesta occurring on September 5, 2012. To date the IPS has been operated for approximately 31,000 hours, consumed approximately 300 kg of xenon, and provided a delta-V of approximately 8.3 km/s. IPS performance characteristics are very close to the expected performance based on analysis and testing performed prelaunch. Thrusting for cruise to Ceres will continue until the spring of 2015, with a planned arrival date at Ceres in April 2015. This paper provides an overview of Dawn's mission objectives and the results of Dawn IPS mission operations from Vesta departure through the first year of cruise to Ceres.

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ARTEMIS orbit raising inflight experience with ion propulsion

Cited by 43 publications

References 3 publications

Self-Consistent Numerical 0D/3D Hybrid Modeling of Radio-Frequency Ion Thrusters

Self-Consistent Numerical 0D/3D Hybrid Modeling of Radio-Frequency Ion Thrusters

The impact of advanced platform and ion propulsion technologies on small, low-cost interplanetary spacecraft

In-Flight Operation of the Dawn Ion Propulsion System Through Year One of Cruise to Ceres

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