Microfabrication of a high pressure bipropellant rocket engine
Microfabrication of a high pressure bipropellant rocket engine
A high pressure bipropellant rocket engine has been successfully micromanufactured by fusion bonding a stack of six individually etched single crystal silicon wafers. In order to test the device, an innovative packaging technique was developed to deliver liquid coolant and gaseous propellants to the rocket chip at pressures in excess of 200 atm at temperatures above 300°C. Testing continues on the 1.2 g devices, which have been run to date at a chamber pressure of 12 atm, generating 1 N of thrust, and delivering a thrust power of 750 W.
rocket, deep reactive ion etching, MEMS, combustion, high pressure fluid packaging
351-357
London, A.P.
31a4d48e-7725-42e5-acb6-0de00c0ed626
Ayón, A.A.
5af60c6b-b908-435b-9e9c-cabf8d51e480
Epstein, A.H.
e201ab04-6502-4e3a-9a28-e6f5cdd7f565
Spearing, S.M.
9e56a7b3-e0e8-47b1-a6b4-db676ed3c17a
Harrison, T
c7eb760c-5bbf-4bd5-ab9b-881c08d80e22
Peles, Y.
cc12a2e4-ff26-44a2-94f3-f9955bcc3a7e
Kerrebrock, J.L.
b49ea8a2-9522-4a66-8625-40ab612ccb3d
2001
London, A.P.
31a4d48e-7725-42e5-acb6-0de00c0ed626
Ayón, A.A.
5af60c6b-b908-435b-9e9c-cabf8d51e480
Epstein, A.H.
e201ab04-6502-4e3a-9a28-e6f5cdd7f565
Spearing, S.M.
9e56a7b3-e0e8-47b1-a6b4-db676ed3c17a
Harrison, T
c7eb760c-5bbf-4bd5-ab9b-881c08d80e22
Peles, Y.
cc12a2e4-ff26-44a2-94f3-f9955bcc3a7e
Kerrebrock, J.L.
b49ea8a2-9522-4a66-8625-40ab612ccb3d
London, A.P., Ayón, A.A., Epstein, A.H., Spearing, S.M., Harrison, T, Peles, Y. and Kerrebrock, J.L.
(2001)
Microfabrication of a high pressure bipropellant rocket engine.
Sensors and Actuators A: Physical, 92 (1-3), .
(doi:10.1016/S0924-4247(01)00571-4).
Abstract
A high pressure bipropellant rocket engine has been successfully micromanufactured by fusion bonding a stack of six individually etched single crystal silicon wafers. In order to test the device, an innovative packaging technique was developed to deliver liquid coolant and gaseous propellants to the rocket chip at pressures in excess of 200 atm at temperatures above 300°C. Testing continues on the 1.2 g devices, which have been run to date at a chamber pressure of 12 atm, generating 1 N of thrust, and delivering a thrust power of 750 W.
This record has no associated files available for download.
More information
Published date: 2001
Keywords:
rocket, deep reactive ion etching, MEMS, combustion, high pressure fluid packaging
Identifiers
Local EPrints ID: 23079
URI: http://eprints.soton.ac.uk/id/eprint/23079
ISSN: 0924-4247
PURE UUID: d4a219ed-152b-44fe-bbad-064f7fcf719d
Catalogue record
Date deposited: 10 Mar 2006
Last modified: 16 Mar 2024 03:37
Export record
Altmetrics
Contributors
Author:
A.P. London
Author:
A.A. Ayón
Author:
A.H. Epstein
Author:
T Harrison
Author:
Y. Peles
Author:
J.L. Kerrebrock
Download statistics
Downloads from ePrints over the past year. Other digital versions may also be available to download e.g. from the publisher's website.
View more statistics
