A description of a microthruster operating on the single-component propellant-hydrazine with the Shell-405 catalyst is presented. The hydrazine decomposition reaction at the specified parameters occurs on the surface. The gas temperature entering the nozzle actually depends on the catalyst temperature. It is established that if the temperature of hydrazine decomposition products at the catalyst outlet is lower than 400 K, ammonia condensation takes place in the supersonic nozzle part. The temperature distribution in the working chamber microchannel is calculated, the microthruster thrust and specific impulse are evaluated on the basis of a physico-mathematical model. A fundamental possibility of obtaining 10~(-3)-10~(-2) N level thrust is shown.
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