MEMS-based solid propellant micro-rocket with micro-igniter on thin membrane for next generation of low-cost small space and aeronautic engines

摘要

A new planar structure of solid propellant micro-rocket for micro-spacecraft and Micro-Air-Vehicle applications is reported in this paper. We have successfully fabricated an array of micro-rockets using MEMS technology. For a low-power consumption, the micro-igniter used here is a resistor deposited on a low tensile stress thin membrane to ensure a good heat transfer to the propellant. Experimental tests of ignition and microcombustion employing Double-Base (DB) solid propellant mixed with Black-Powder (BP) are reported and discussed. Tests have showed successful and continuum combustion of about 1.3 mm diameter during few 100ms from BP ratio in the mixture (x) of 10%. Thrust force delivered by considered structure dimensions, is ranging from 0.1 mN to 1mN for x=10%, 20% and 30%. We expect that this planar structure will deliver a suitable thrust force of few 10mN when reducing micro-nozzle throat dimensions.