Description – Recently, there has been a keen interest in researching and developing air-breathing plasma thrusters (ABPTs) for very low earth orbit applications, typically in the range 80–260km. ABPT uses an incoming air propellant that is ionized and then consequently accelerated to produce thrust. Typically, thrust level (90mN–90 N) is required to cancel drag that is (60mN–60 N) substantial at low altitudes. With an ABPT at a low altitude, there are many advantages such as increased satellite resolution, weight reduction, and low launch cost. Additionally, with an increased number of spacecrafts in high orbits, ABPT could be advantageous by effectively utilizing space resources and burning upon re-entry to prevent the formation of space debris. ABPT allows the elimination of propellant storage tanks and, therefore, the extension of the service lifetime of a satellite. However, many physical and operational challenges need to be addressed when dealing with these thrusters. The major challenge is developing an optimum approach to efficiently ionize air in a rarefied environment within an altitude range of 80–260 km. Due to the low density of gas at these altitudes, collimator designs are often used, introducing additional drag. We are proposing a collimator free design that would potentially operate in lower than 200 Km altitudes. Typically, plasma thrusters use neutralizers to neutralize the ion beam at the exit. They require complicated designs, gas tank and adds to the weight for the thruster. To solve that, our proposed design achieves self-neutralization without the use of external neutralizer as described in references below.