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


Glynne-Jones, Peter, Coletti, Michele, White, Neil M., Gabriel, Stephen and Bramanti, Cristina (2008) A feasibility study on using inkjet technology, micropumps, and MEMs as fuel injectors for bipropellant rocket engines At 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, United States. 21 - 23 Jul 2008.

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Description/Abstract

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 are used. A conceptual design is presented and its basic behavior assessed.

Item Type: Conference or Workshop Item (Paper)
Venue - Dates: 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, United States, 2008-07-21 - 2008-07-23
Related URLs:
Keywords: inkjet, injector, liquid, rocket, motor, droplet size, diesel
Subjects:
Organisations: Astronautics Group
ePrint ID: 64436
Date :
Date Event
21 July 2008Published
Date Deposited: 07 Jan 2009
Last Modified: 16 Apr 2017 17:20
Further Information:Google Scholar
URI: http://eprints.soton.ac.uk/id/eprint/64436

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