Development of a low-temperature co-fired ceramic solid propellant microthruster

Abstract

Low-temperature co-fired ceramic (LTCC) technology has been first successfully employed for the realization of a solid propellant microthruster. The microthruster has potential applications in microspacecraft as an excellent micropropulsion system for high-accuracy station keeping, attitude control, drag compensation and orbit adjust. The design, fabrication and experimental investigation of LTCC microthrusters are reported. Results from experiments on microcombustion, and thrust and impulse measurements both at sea level and in vacuum are presented. Initial tests employing gunpowder-based solid propellant have produced 3.81 × 10−5–1.27 × 10−4 N s of total impulse and 5.55–14.41 s of specific impulse at sea level, and 1.31 × 10−4–2.79 × 10−4 N s of total impulse and 19.05–31.55 s of specific impulse in vacuum. The performance of the LTCC solid propellant microthruster is also compared with that of a silicon-based solid propellant microthruster.