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.
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