Powered Flight of Electron Cyclotron Resonance Ion Engines on Hayabusa Explorer

Kuninaka, Hitoshi; Nishiyama, Kazutaka; Funaki, Ikko; Yamada, Tetsuya; Shimizu, Yukio; Kawaguchi, J.

doi:10.2514/1.25434

Cited by 119 publications

(59 citation statements)

References 12 publications

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“…2 shows that, for example, for a 35 km displaced geostationary orbit, a currently feasible specific impulse of 3200 s (e.g. as flown on the Hayabusa spacecraft [27]) and a mass fraction of 0.5, a lifetime of 3.7 years can be achieved. However, this lifetime degrades to 1.7 and 0.9 years when considering the larger displacements of 75 and 150 km, respectively.…”

Section: Displaced Geostationary Orbitsmentioning

confidence: 99%

Displaced geostationary orbits using hybrid low-thrust propulsion

et al. 2012

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In this paper, displaced geostationary orbits using hybrid low-thrust propulsion, a complementary combination of Solar Electric Propulsion (SEP) and solar sailing, are investigated to increase the capacity of the geostationary ring that is starting to become congested. The SEP propellant consumption is minimized in order to maximize the mission lifetime by deriving semi-analytical formulae for the optimal steering laws for the SEP and solar sail accelerations. By considering the spacecraft mass budget, the performance is also expressed in terms of payload mass capacity. The analyses are performed both for the use of pure SEP and hybrid low-thrust propulsion to allow for a comparison. It is found that hybrid lowthrust control outperforms the pure SEP case both in terms of payload mass capacity and mission lifetime for all displacements considered. Hybrid low-thrust propulsion enables payloads of 255 to 487 kg to be maintained in a 35 km displaced orbit for 10 to 15 years. Adding the influence of the 2 J and 2,2 J terms of the Earth"s gravity field has a small effect on this lifetime, which becomes almost negligible for small values of the sail lightness number. Finally, two SEP transfers that allow for an improvement in the performance of hybrid low-thrust control are optimized for the propellant consumption by solving the accompanying optimal control problem using a direct pseudospectral method. The first type of transfer enables a transit between orbits displaced above and below the equatorial plane, while the second type of transfer enables customized service for which a spacecraft is transferred to a Keplerian parking orbit when geostationary coverage is not needed. While the latter requires a modest propellant budget, the first type of transfer comes at the cost of an almost negligible SEP propellant consumption.

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Section: Displaced Geostationary Orbitsmentioning

confidence: 99%

Displaced geostationary orbits using hybrid low-thrust propulsion

et al. 2012

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“…It is the smallest ion thruster in the "μ" series of ion thrusters developed in ISAS of JAXA. [19][20][21] The μ1 has the 250 W/A ion production cost and 37% mass utilization efficiency for 1.0 W microwave input power and 0.15 sccm xenon mass flow.…”

Section: Introductionmentioning

confidence: 99%

Switching Operation of Ion Beam Extraction and Electron Emission Using the Miniature Ion Thruster μ1

Koizumi

Kuninaka

2010

AEROSPACE TECHNOLOGY JAPAN

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Ion thrusters are promising propulsion devices not only for standard-sized spacecraft but also for small spacecraft. However, difficulty of the development of a miniature neutralizer has been a critical problem for miniature ion thrusters. We have proposed a novel ion thruster system to solve this problem. That is a switching operation, where a plasma source can select ion beam extraction or electron emission by electrical switching. The major challenge of this study is to find the method to effectively performs both functions from one plasma source. To match the system to small spacecraft, the both modes must be conducted using low microwave power and low mass flow as low as 1.0 W and 0.15 sccm. Firstly, fundamental characteristics of electron emission were investigated using an orifice plate. Based on this result, secondly, a special grid system for the switching operation was designed and examined. This grid system has two-different-size apertures for ions and electrons respectively. This grid showed high ion beam extraction performance, that is, 4.1 mA ion beam current at 1.0 W microwave power input. It also showed much higher electron current than the old grid system, although the electron current of 1.0 mA has not reached the targeted current yet. As a result, the experiment showed that the special grid system proposed here is an effective method to realize the switching operation.

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“…Again, considering a mass fraction of 0.5 and assuming a currently feasible SEP specific impulse of 3200 s (e.g. as flown on the Hayabusa spacecraft [30]), the lifetime is increased from 4.3, 2.0 and 1.0 months for impulsive control to 3.7, 1.7 and 0.9 years for 35, 75 and 150 km displaced orbits, respectively. However, lifetimes of 10 -15 years as …”

Section: Sep Controlmentioning

confidence: 99%

Displaced Geostationary Orbit Design Using Hybrid Sail Propulsion

Heiligers

Ceriotti

McInnes

et al. 2011

Journal of Guidance, Control, and Dynamics

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Due to an increase in number of geostationary spacecraft and limits imposed by east-west spacing requirements, the geostationary orbit is becoming congested. To increase its capacity, this paper proposes to create new geostationary slots by displacing the geostationary orbit either out of or in the equatorial plane by means of hybrid solar sail and solar electric propulsion. To minimize propellant consumption, optimal steering laws for the solar sail and solar electric propulsion thrust vectors are derived and the performance in terms of mission lifetime is assessed. For comparison, similar analyses are performed for conventional propulsion, including impulsive and pure solar electric propulsion. It is shown that hybrid sails outperform these propulsion techniques and that out-of-plane displacements outperform in-plane displacements. The out-of-plane case is therefore further investigated in a spacecraft mass budget to determine the payload mass capacity. Finally, two transfers that enable a further improvement of the performance of hybrid sails for the out-ofplane case are optimized using a direct pseudo-spectral method: a seasonally transit between orbits displaced above and below the equatorial plane and a transit to a parking orbit when geostationary coverage is not needed. Both transfers are shown to require only a modest propellant budget, outweighing the improvements they can establish.

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Powered Flight of Electron Cyclotron Resonance Ion Engines on Hayabusa Explorer

Cited by 119 publications

References 12 publications

Displaced geostationary orbits using hybrid low-thrust propulsion

Displaced geostationary orbits using hybrid low-thrust propulsion

Switching Operation of Ion Beam Extraction and Electron Emission Using the Miniature Ion Thruster μ1

Displaced Geostationary Orbit Design Using Hybrid Sail Propulsion

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