Development of an ion thruster and power processor for New Millennium's Deep Space 1 Mission

Sovey, James S.; Hamley, John A.; Haag, Thomas; Patterson, Michael J.; Pencil, Eric; Peterson, Todd; Pinero, Luis R.; Power, J. L.; Rawlin, Vincent K.; Sarmiento, Charles J.; Anderson, John R.; Bond, Thomas A.; Cardwell, G. I.; Christensen, J.A.

doi:10.2514/6.1997-2778

Cited by 32 publications

(10 citation statements)

References 3 publications

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“…The numerical values listed in Table 1 are not to be taken as recommended design values, but only as indicative of a range; for more detailed information, the reader is referred to the quoted literature. [2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20] …”

Section: Electric Thrustersmentioning

confidence: 99%

Spacecraft Electric Propulsion-An Overview

Martı́nez-Sánchez

Pollard

1998

Journal of Propulsion and Power

398

208

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A short review of the status of electric propulsion (EP) is presented to serve as an introduction to the more specialized technical papers also appearing in this Special Issue (Journal of Propulsion and Power, Vol. 14, No. 5, Sept. -Oct. 1998 ). The principles of operation and the several types of thrusters that are either operational or in advanced development are discussed rst, followed by some considerations on the necessary power sources. A few prototypical missions are then described to highlight the operational peculiarities of EP, including spacecraft interactions. We conclude with a historical summary of the accumulated ight experience using this technology.

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Section: Electric Thrustersmentioning

confidence: 99%

Spacecraft Electric Propulsion-An Overview

Martı́nez-Sánchez

Pollard

1998

Journal of Propulsion and Power

398

208

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“…The lifetime values so obtained can be compared to those required by previous missions where GIEs were employed and to those required by the HiPER missions. In particular, the lifetime obtained for the TypGIE is sufficient to achieve the requirements of the Deep Space 1 and GOCE mission (about 20 000 h [12], [40]) and of the Bepi Colombo mission (about 17 000 h [13]) but not enough if compared to the requirements specified in Table II. On the contrary, the DS3G shows lifetime in excess of those required by past missions and of those required by the HiPER project ( 28 000 h for the EML1 infrastructure and 45-48 000 h for Mars Infrastructure and NEP mission to Saturn).…”

Section: B Lifetime Predictionmentioning

confidence: 99%

The Applicability of Dual Stage Ion Optics to Ion Engines for High Power Missions

Coletti

Gabriel

2012

IEEE Trans. Plasma Sci.

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In this paper, the applicability of dual stage ion optics and in particular of the so-called dual stage ion engine to high power, high specific impulse missions will be evaluated. First, the performance limits of conventional two gridded ion engines (GIE) will be discussed and the advantages provided by dual stage ion engines reported. The limits of applicability of a dual stage ion engine will be analyzed analytically and the results confirmed numerically. The lifetime and performance of a three gridded dual stage ion engine (DS3G) will be numerically investigated and compared to those of a conventional GIE assessing for the first time in the open literature under what condition dual stage ion optics provide performance improvements over conventional GIEs and what is its impact on the thruster lifetime. Dual stage ion engines have been found to be capable of providing higher thrust density and longer lifetime with respect to conventional gridded ion engines.

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“…Table 1 illustrates these challenges by comparing the technology needs for JIMO with current SOA ion thruster technology as represented by the NASA Solar Electric Power Technology Application Readiness (NSTAR) thruster recently flown on NASA Deep-Space 1 spacecraft. 4 Figure 5 shows these challenges with respect to each electric propulsion subsystem. This comparison highlights technology areas requiring improvement for JIMO applications.…”

Section: Jimo Technology Challenges For Ion Propulsionmentioning

confidence: 99%

“…This approach has been successfully used in both the NSTAR and NASA's Evolutionary Xenon Thruster (NEXT) programs. 4,5 However, enlargement of the thruster is not enough to handle the fuel throughput requirement of JIMO type applications. The grid materials need to be more resistant to erosion than the molybdenum materials used in the NSTAR program.…”

Section: Jimo Technology Challenges For Ion Propulsionmentioning

confidence: 99%

Electric Propulsion Technology Development for the Jupiter Icy Moon Orbiter Project

Oleson

2004

40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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During 2004, the Jupiter Icy Moons Orbiter project, a part of NASA's Project Prometheus, continued efforts to develop electric propulsion technologies. These technologies addressed the challenges of propelling a spacecraft to several moons of Jupiter. Specific challenges include high power, high specific impulse, long lived ion thrusters, high power/high voltage power processors, accurate feed systems, and large propellant storage systems. Critical component work included high voltage insulators and isolators as well as ensuring that the thruster materials and components could operate in the substantial Jupiter radiation environment. A review of these developments along with future plans is discussed.

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Development of an ion thruster and power processor for New Millennium's Deep Space 1 Mission

Cited by 32 publications

References 3 publications

Spacecraft Electric Propulsion-An Overview

Spacecraft Electric Propulsion-An Overview

The Applicability of Dual Stage Ion Optics to Ion Engines for High Power Missions

Electric Propulsion Technology Development for the Jupiter Icy Moon Orbiter Project

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