Global ETD Search
Search theses and dissertations gathered from participating repositories worldwide. Every result links back to the library that holds it. No account is needed.
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Showing 1 to 12 of 12 for “"Arcjet"”.
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Multifluid nonequilibrium simulation of arcjet thrusters
Thesis (Sc. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1994.
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Spectroscopic analysis of a magnetoplasma dynamic arcjet
Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1988.
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Simplified modeling and analysis of arcjet thrusters
Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1993.
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A Low Power Pulsed Arcjet Thruster for Spacecraft Propulsion
A pulse-forming electrical circuit is developed to reduce energy losses in the storage capacitor, and greater than 85% of the initial stored energy is transferred to the arc in a unipolar pulse. A high current diode installed across the capacitor terminals is used to eliminate voltage reversals in …
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A theoretical study on alkali seeding of arcjet thrusters
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1998.
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Exit plane plasma measurements of a low-power hydrazine arcjet
Made available in DSpace on 2011-05-07T14:24:50Z (GMT). No. of bitstreams: 2 license.txt: 4922 bytes, checksum: 910b249b4beec47e7ab768910c8f966f (MD5) 9625115.pdf: 7628850 bytes, checksum: eca10f4d93ed536c344189cbf8e7be5a (MD5) Previous issue date: 1996
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Simulation and design of a hydrogen arcjet thruster seeded with cesium
In conventional arcjets the largest loss in efficiency is the energy required to ionize the propellant. Adding a small amount of a readily ionizable material should provide adequate electrical conductivity, without the main propellant being ionized, thereby reducing this frozen loss. To study the …
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An improved numerical model for flow computations of electrothermal arcjet thrusters
Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1996.
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A two-dimensional, non-equilibrium numerical model of an alkali seeded hydrogen arcjet thruster
Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1998.
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Plasma Properties and Heating at the Anode of a 1 kW Arcjet Using Electrostatic Probes
A 1 kW hydrazine arcjet thruster has been modified for internal probing of the near-anode boundary layer with an array of fourteen electrostatic micro-probes. The main objectives of this experimental investigation were to: (1) obtain axial and azimuthal distributions of floating potential …
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An actively cooled floating element skin friction balance for direct measurement in high enthalpy supersonic flows
… Laboratory (GASL) and in the Direct Connect Arcjet Facility (DCAF) supersonic combustor at the NASA AMES Research Center. Flow conditions in the high enthalpy combustor models ranged from total pressures of 275-800 psia (1900-5550 kPa) and total temperatures from 5800-8400 R (3222-4667 K). …
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Construction of predictive uncertainty quantification framework to the extension of TPS plasma wind tunnel experiment data to flight conditions
Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2022-11-15 without embargo terms