Performance characteristics of 15-cm carbon-carbon composite grids

Garner, Charles E.; Mueller, Juergen; Brophy, John R.

doi:10.2514/6.1994-3118

Cited by 7 publications

(1 citation statement)

References 3 publications

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“…Output from the Stirling engine is fed to a DC/DC converter where the voltage and current are conditioned to provide the right operating parameters from the ion engine (from 100 V to 1000 V). The ion engine is a 15-cm diameter ion engine developed at JPL that incorporates several advanced ion engine technologies such as carbon-carbon ion optics (Brophy, 1993 andMueller, 1994). For the SAFE 30 tests, the Stirling engine output is fed to the grid, while discharge and neutralizer cathode will be run with laboratory power supplies.…”

Section: End-to-end System Concept Demonstrationmentioning

confidence: 99%

Phase 1 space fission propulsion system testing and development progress

Dyke¹

2001

AIP Conference Proceedings

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Abstract. Successful development of space fission systems requires an extensive program of affordable and realistic testing. In addition to tests related to design/development of the fission system, realistic testing of the actual flight unit must also be performed. If the system is designed to operate within established radiation damage and fuel bum up limits while simultaneously being designed to allow close simulation of heat from fission using resistance heaters, high confidence in fission system performance and lifetime can be attained through a series of non-nuclear tests. The Safe Affordable Fission Engine (SAFE) test series, whose ultimate goal is the demonstration of a 300 kW flight configuration system, has demonstrated that realistic testing can be performed using non-nuclear methods. This test series, carried out in collaboration with other NASA centers, other government agencies, industry, and universities, successfully completed a testing program with a 30 kWt core, Stirling engine, and ion engine configuration. Additionally, a 100 kWt core is in fabrication and appropriate test facilities are being reconfigured. This paper describes the current SAFE non-nuclear tests, which includes test article descriptions, test results and conclusions, and future test plans.

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Section: End-to-end System Concept Demonstrationmentioning

confidence: 99%

Phase 1 space fission propulsion system testing and development progress

Dyke¹

2001

AIP Conference Proceedings

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Segmented ion engine operation and performance

Brophy

Mueller

Pless

et al. 1994

30th Joint Propulsion Conference and Exhibit

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The continuing trend toward smaller and smaller planetary spacecraft to enable the use of smaller, less expensive launch vehicles has nmtivated an examination of new approaches to reduce the sire. and mass of xenon ion propulsion systems for these new spacecraft. A system is proposed which is based on the use of a single 4x15-cm segnxmted ion thruster operated horn a single internally redundant power processing unit. An engine input power throttling range of 380 to 4640 W is projected. The design and operation over a power range of 600 to 2400 W of a laboratory nwdel segrmmted ion engine equipped with carbon-carbon grids is presented. There appear to be no problems a..sociated with interactions with multiple ion sources operating fkom a single set of high voltage power supplies, neutralization of multiple ion sources tkom a single centratly-located neutralizer, or operation of flat, thin carbon-carbon grids.

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Fabrication and testing of 15-cm carbon-carbon grids with slit apertures

Meserole¹,

Rorabaugh²

1995

31st Joint Propulsion Conference and Exhibit

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Performance characteristics of 15-cm carbon-carbon composite grids

Cited by 7 publications

References 3 publications

Phase 1 space fission propulsion system testing and development progress

Phase 1 space fission propulsion system testing and development progress

Segmented ion engine operation and performance

Fabrication and testing of 15-cm carbon-carbon grids with slit apertures

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