Advanced propulsion for geostationary orbit insertion and north-south station keeping

Oleson, Steven R.; Myers, Roger; Kluever, Craig A.; Riehl, John P.; Curran, Francis M.

doi:10.2514/6.1995-2513

Cited by 21 publications

(9 citation statements)

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“…These components have been developed for commercial space missions including orbit-raising and station-keeping of geostationary communications satellites. Oleson et al [18] provide a concise summary of the state-of-the-art in their study on orbit-raising of geostationary satellites using SEP. They assume an ion engine specific mass of roughly 6 kg/kW, including support structure, gimbals and control unit.…”

Section: Nep System Massmentioning

confidence: 98%

“…They assume an ion engine specific mass of roughly 6 kg/kW, including support structure, gimbals and control unit. The specific mass of a complete PPU system, including thermal control and cabling, as well as the ion engine propellant feed system is typically as low as 9 kg/kW according to Oleson et al [18]. Commercial communications satellites typically operate with about 15 kW of electrical power and individual ion engines can operate at power levels in excess of 4 kW; these mass estimates are based on these power levels.…”

Section: Nep System Massmentioning

confidence: 99%

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Nuclear electric ion propulsion for three deep space missions

Chiravalle

2008

Acta Astronautica

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Section: Nep System Massmentioning

confidence: 98%

Section: Nep System Massmentioning

confidence: 99%

Nuclear electric ion propulsion for three deep space missions

Chiravalle

2008

Acta Astronautica

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“…Regarding station-keeping maneuvers that is more related to the topic of the present research, the literature also has several publications, like [49][50][51][52][53][54][55][56][57][58].…”

Section: Mathematical Problems In Engineeringmentioning

confidence: 99%

Searching for Orbits with Minimum Fuel Consumption for Station-Keeping Maneuvers: An Application to Lunisolar Perturbations

Prado

2013

Mathematical Problems in Engineering

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The present paper has the goal of developing a new criterion to search for orbits that minimize the fuel consumption for station-keeping maneuvers. This approach is based on the integral over the time of the perturbing forces. This integral measures the total variation of velocity caused by the perturbations in the spacecraft, which corresponds to the equivalent variation of velocity that an engine should deliver to the spacecraft to compensate the perturbations and to keep its orbit Keplerian all the time. This integral is a characteristic of the orbit and the set of perturbations considered and does not depend on the type of engine used. In this sense, this integral can be seen as a criterion to select the orbit of the spacecraft. When this value becomes larger, more consumption of fuel is required for the station keeping, and, in this sense, less interesting is the orbit. This concept can be applied to any perturbation. In the present research, as an example, the perturbation caused by a third body is considered. Then, numerical simulations considering the effects of the Sun and the Moon in a satellite around the Earth are shown to exemplify the method.

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“…In addition to Earth -Moon transfers, there have also been studies of combined propulsion systems for orbit transfers within the Earth's sphere of influence; most notably, transfers to GEO. This research has considered the use of a chemical system on-board the satellite in conjunction with an EP system, also on-board the satellite but for the main use of station keeping maneuvers, to perform part of the orbit raise maneuver [25][26][27]. In addition, work has considered the effect of the launch vehicle on the transfer [28].…”

Section: Introductionmentioning

confidence: 99%

Combined high and low-thrust geostationary orbit insertion with radiation constraint

Macdonald

Owens

2018

Acta Astronautica

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The sequential use of an electric propulsion system is considered in combination with a high-thrust propulsion system for application to the propellant-optimal Geostationary Orbit insertion problem, whilst considering both temporal and radiation flux constraints. Such usage is found to offer a combined propellant mass saving when compared with an equivalent high-thrust only transfer. This propellant mass saving is seen to increase as the allowable transfer duration is increased, and as the thrust from the low-thrust system is increased, assuming constant specific impulse. It was found that the required plane change maneuver is most propellant-efficiently performed by the high-thrust system. The propellant optimal trajectory incurs a significantly increased electron flux when compared to an equivalent high-thrust only transfer. However, the electron flux can be reduced to a similar order of magnitude by increasing the high-thrust propellant consumption, whilst still delivering an improved mass fraction

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Advanced propulsion for geostationary orbit insertion and north-south station keeping

Cited by 21 publications

References 1 publication

Nuclear electric ion propulsion for three deep space missions

Nuclear electric ion propulsion for three deep space missions

Searching for Orbits with Minimum Fuel Consumption for Station-Keeping Maneuvers: An Application to Lunisolar Perturbations

Combined high and low-thrust geostationary orbit insertion with radiation constraint

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