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A feasibility study on using inkjet technology, micropumps, and MEMs as fuel injectors for bipropellant rocket engines

Glynne-Jones, Peter, Coletti, M., White, N.M., Gabriel, S.B. and Bramanti, C. (2010) A feasibility study on using inkjet technology, micropumps, and MEMs as fuel injectors for bipropellant rocket engines Acta Astronautica, 67, (1-2), pp. 194-203. (doi:10.1016/j.actaastro.2010.01.027).

Record type: Article


Control over drop size distributions, injection rates, and geometrical distribution of fuel and oxidizer sprays in bi-propellant rocket engines has the potential to produce more efficient, more stable, less polluting rocket engines. This control also offers the potential of an engine that can be throttled, working efficiently over a wide range of output thrusts. Inkjet printing technologies, MEMS fuel atomizers, and piezoelectric injectors similar in concept to those used in diesel engines are considered for their potential to yield a new, more active injection scheme for a rocket engine. Inkjets are found to be unable to pump at sufficient pressures, and have possibly dangerous failure modes. Active injection is found to be feasible if high pressure drop along the injector plate is used. A conceptual design is presented and its basic behavior assessed.

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Published date: July 2010
Keywords: inkjet technology, micropumps, mems, fuel injectors, bipropellant rocket engines
Organisations: Astronautics Group


Local EPrints ID: 156371
ISSN: 0094-5765
PURE UUID: 208dfd2b-f87b-46ac-b531-591d11eee9a7
ORCID for Peter Glynne-Jones: ORCID iD
ORCID for N.M. White: ORCID iD

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Date deposited: 02 Jun 2010 10:21
Last modified: 18 Jul 2017 12:43

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Author: M. Coletti
Author: N.M. White ORCID iD
Author: S.B. Gabriel
Author: C. Bramanti

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