Please use this identifier to cite or link to this item:
|Title:||Low temperature co-fired ceramic vaporizing liquid microthruster for microspacecraft applications|
|Keywords:||Internal embedded resistor|
|Citation:||Karthikeyan, K., Chou, S.K., Khoong, L.E., Tan, Y.M., Lu, C.W., Yang, W.M. (2012-09). Low temperature co-fired ceramic vaporizing liquid microthruster for microspacecraft applications. Applied Energy 97 : 577-583. ScholarBank@NUS Repository. https://doi.org/10.1016/j.apenergy.2011.11.078|
|Abstract:||Low temperature co-fired ceramic (LTCC) technology is successfully employed for the first time to develop a vaporizing liquid propellant microthruster (VLM). The VLM has potential applications as micropropulsion system for attitude control of microsatellites. The design, fabrication and testing of the LTCC based VLM are presented. Preliminary testing is done by using water as liquid propellant. The VLM of nozzle throat size 220μm×200μm produces an average thrust in the range of 34-68μN for a flow rate of 1mgs-1 with an input heater power varying from 7.1-9.2W. An average specific impulse of 3.4-6.9s is measured. An average impulse bit of 0.67-1.4mNs, 3.40-6.70mNs is measured for thruster firing time of 20s and 100s during VLM stable mode operation at sea level conditions. © 2011 Elsevier Ltd.|
|Source Title:||Applied Energy|
|Appears in Collections:||Staff Publications|
Show full item record
Files in This Item:
There are no files associated with this item.
checked on Jul 14, 2018
WEB OF SCIENCETM
checked on Jun 19, 2018
checked on Apr 20, 2018
Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.