SPT sizing for integrated propulsion systems

Valentian, Dominique; Koppel, Christophe

doi:10.2514/6.1996-2722

Cited by 2 publications

(2 citation statements)

References 1 publication

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“…Because the duration of orbit raising corresponds to a delay in the generation of revenue, solutions resulting in transfer durations above 120 days were rejected, and values between 60 days and 90 days were preferably targeted as in similar past studies. 9,10,[16][17][18][19][20][21][22][23][24] Other initial orbit options, however, appear capable of leveraging significant benefits. The 6,000-km circular MEO orbits first, and the sub-GTO and GTO orbits then, are two groups of options generating mass capability increases by more than 60%, except for the GTO option (near 50%).…”

Section: J Summary Of Geo Insertion Optionsmentioning

confidence: 99%

Ariane 5-ME and Electric Propulsion: GEO Insertion Options

Duchemin¹,

Caratge²,

Cornu³

et al. 2011

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Electric propulsion is now widely used on commercial satellites, and the prospects of allelectric satellites may be considered for future comsats where all propulsive duties are fulfilled by the electric propulsion subsystem, including orbit raising. In such a configuration, the full benefits of using higher specific impulse devices for the satellite onboard propulsion would be realized. These benefits may be expressed in terms of increased payload capability in geostationary orbit, but also in terms of increased satellite operational life or decreased launch costs, depending on market demands. This study examines the best match options between electric propulsion and a launch vehicle with frozen specification, with Ariane 5-ME taken as a reference example. Departure orbit options before the electric orbit raising to GEO are traded in order to realize the full potential of both the launch vehicle performance and electric propulsion. The selection of the best options is discussed, depending on the priority given to fast electric orbit raising and low radiation fluence versus improved dry mass capability to geostationary orbit. Nomenclaturea = semi-major axis length, m g 0 = standard free fall, 9.81 m.s -2 i = orbit inclination, deg. Isp = specific impulse, s V a = apogee velocity, m/s Z a , Z p = apogee (respectively perigee) altitude, m ∆V = velocity increment, m/s α = ratio of satellite solar array power (Beginning of Life) to launch mass, W/kg β = power-specific thrust, N/W η = thrust efficiency µ = standard gravitational parameter for Earth, 3.99×10 14 m 3 /s 2

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Section: J Summary Of Geo Insertion Optionsmentioning

confidence: 99%

Ariane 5-ME and Electric Propulsion: GEO Insertion Options

Duchemin¹,

Caratge²,

Cornu³

et al. 2011

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…There have been efforts to reduce the plume divergence in Hall thrusters by optimizing the shape of the magnetic field in the thruster channel [3][4][5][6][7], adding ring-shaped electrodes to the channel walls [2,5], and optimizing the operation of the thruster cathode [8]. However, because the ionization of the gas flow, the acceleration of the ions and the transport of electrons to the anode are all self-organized by the plasma within the channel, it is difficult to optimize ion acceleration without affecting the other processes.…”

Section: Introductionmentioning

confidence: 99%

Cross-field plasma lens for focusing of the Hall thruster plume

Griswold

Raitses

Fisch³

2014

Plasma Sources Sci. Technol.

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Hall thrusters produce neutralized ion beams with high current density because the acceleration takes place in quasi-neutral plasma and is not subject to space charge limitation. We tested an external plasma lens (PL) in front of the thruster as a means to focus the thruster plume. In the PL, the plasma is nearly collisionless, with non-magnetized flowing ions and magnetized electrons. Surprisingly, we observed anomalous electron cross-field transport, leading to large currents to the PL electrode and enhanced power loss.

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SPT sizing for integrated propulsion systems

Cited by 2 publications

References 1 publication

Ariane 5-ME and Electric Propulsion: GEO Insertion Options

Ariane 5-ME and Electric Propulsion: GEO Insertion Options

Cross-field plasma lens for focusing of the Hall thruster plume

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