A hybridized discontinuous Galerkin formulation for modeling electrohydrodynamic thrusters
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015.
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| Format: | Thesis |
| Language: | eng |
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Massachusetts Institute of Technology
2015
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| Online Access: | http://hdl.handle.net/1721.1/98807 |
| _version_ | 1811069107491045376 |
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| author | Dexter, Andrew (Andrew Joseph) |
| author2 | Steven R. H. Barrett. |
| author_facet | Steven R. H. Barrett. Dexter, Andrew (Andrew Joseph) |
| author_sort | Dexter, Andrew (Andrew Joseph) |
| collection | MIT |
| description | Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015. |
| first_indexed | 2024-09-23T08:05:50Z |
| format | Thesis |
| id | mit-1721.1/98807 |
| institution | Massachusetts Institute of Technology |
| language | eng |
| last_indexed | 2024-09-23T08:05:50Z |
| publishDate | 2015 |
| publisher | Massachusetts Institute of Technology |
| record_format | dspace |
| spelling | mit-1721.1/988072019-04-09T16:36:55Z A hybridized discontinuous Galerkin formulation for modeling electrohydrodynamic thrusters Dexter, Andrew (Andrew Joseph) Steven R. H. Barrett. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics. Aeronautics and Astronautics. Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015. Cataloged from PDF version of thesis. Includes bibliographical references (pages 93-97). Electrohydrodynamic (EHD) thrusters utilize ion neutral collisions in air to produce a propulsive force. The ions are generated at an emitting electrode in an asymmetric capacitor by a corona discharge. This thesis presents a Hybridized Discontinuous Galerkin (HDG) formulation for solving the EHD thruster governing equations with the exception of fluid flow equations. The problem is two-way coupled and non-linear. A smoothed charge injection model from the literature for the corona discharge is included in the HDG scheme. The formulation is validated against a model problem which has an analytical solution and parallel wire single stage and dual stage thruster performance data from the literature. The model problem consists of concentric cylinders with charge density and potential specified on the inner and outer cylinders. The inner cylinder is offset to test the charge injection boundary condition in an asymmetric solution. The single stage thruster consists of two parallel wires of different diameters separated by a 1 cm gap. The dual stage thruster consists of three inline parallel wires of different diameters separated by 1 cm and 3 cm. The HDG solution for the model problem is found to produce normalized errors on the order of 10-3 for the potential and charge density solutions. The charge density applied to the inner emitter electrode is increased over several solution iterations to resolve high charge density gradients. The charge density boundary condition applied to the offset case represented the expected qualities of a corona discharge. The smoothed boundary condition is shown to be tunable to allow for a trade-off between accuracy and numerical stability. The single stage thruster model replicated experimental thrust results within 14% error using homogeneous charge injection and the smoothed charge injection model requires a less stable setting to achieve similar accuracy. The dual stage model shows the necessity of a mixed outflow boundary condition to avoid non-unique solutions. by Andrew Dexter. S.M. 2015-09-17T19:13:31Z 2015-09-17T19:13:31Z 2015 2015 Thesis http://hdl.handle.net/1721.1/98807 921147034 eng M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission. http://dspace.mit.edu/handle/1721.1/7582 97 pages application/pdf Massachusetts Institute of Technology |
| spellingShingle | Aeronautics and Astronautics. Dexter, Andrew (Andrew Joseph) A hybridized discontinuous Galerkin formulation for modeling electrohydrodynamic thrusters |
| title | A hybridized discontinuous Galerkin formulation for modeling electrohydrodynamic thrusters |
| title_full | A hybridized discontinuous Galerkin formulation for modeling electrohydrodynamic thrusters |
| title_fullStr | A hybridized discontinuous Galerkin formulation for modeling electrohydrodynamic thrusters |
| title_full_unstemmed | A hybridized discontinuous Galerkin formulation for modeling electrohydrodynamic thrusters |
| title_short | A hybridized discontinuous Galerkin formulation for modeling electrohydrodynamic thrusters |
| title_sort | hybridized discontinuous galerkin formulation for modeling electrohydrodynamic thrusters |
| topic | Aeronautics and Astronautics. |
| url | http://hdl.handle.net/1721.1/98807 |
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