This paper describes a micro solid propellant thruster array with improved ignition and thrust repeatability. The repeatability, low performance variation of each thruster unit with high ignition success rate is essential in micro solid propellant thruster array. To date, the study on the improvement of the repeatability has not yet been reported. As the first step for this study, we propose the new concept of the micro igniter called as the heater-contact micro igniter using a glass substrate. The prototype of the igniter array is designed and fabricated to establish its fabrication process and to verify the proposed ignite concept. Through the firing test of the prototype igniter, the concept of the heater-contact micro igniter is verified. The 5 × 5 sized micro solid propellant thruster array is designed and fabricated applying the developed heater-contact igniter. The measured average ignition delay and ignition energy are 12.35 ms and 22.92 mJ, respectively. Also calculated standard deviations of the ignition delay and ignition energy are 0.737 ms and 1.66 mJ, respectively. The measured average thrust of each thruster unit is 2.542 N, and calculated standard deviation is 0.369 N. The calculated average total impulse and its standard deviation are 0.182 mNs and 0.04 mNs, respectively. Based on these results the improvement of repeatability is verified.
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