Document Type : Scientific extension


1 M.Sc., Materials and Energy Research Institutent, Iranian Space Research Center، Isfahan، Iran

2 M.Sc., Materials and Energy Research Institutent, Iranian Space Research Center, Isfahan, Iran

3 , M.Sc., Materials and Energy Research Institutent, Iranian Space Research Center, Isfahan, Iran

4 , M.Sc., Materials and Energy Research Institutent, Iranian Space Research Center Isfahan, Iran


 In this paper, MEMS-based micro-propulsions designed for small satellites are investigated and compared. Micro-propulsions based on this technology have many advantages over conventional systems, including small size, high integration, mass production, low power consumption and minimum cost. In addition, MEMS thrusters can produce very accurate, small, and repeatable thrusts required for controlling micro/nano satellites. These systems include cold gas, liquid propellant, digital solid propellant, resistojet, and electrospray micro thrusters. Solid and liquid propellant systems have the highest thrust among others. At the same time, electrospray microthrusters have the highest specific impulse, while cold gas and resistojet systems have the least. Finally, the technology readiness levels are different in these systems and there are some design challenges in using MEMS technology that still require further research.


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