The figure above shows the applicability of the ABIE to space missions through a comparison of thrust output against altitude.  The figure shows the theoretical performance of the ABIE at different altitudes in Earth and Mars atmospheres and highlights the actual performance of the Mk 1 ABIE achieved in proof-of-concept testing.

The data is comprised of six separate data sets which have been compiled into a single graph to allow for easy comparison with each other.  The first three data sets show altitude vs air pressure for Earth and Mars. These lines show the areas of operation for the Mk 1 engine. 

The first data set (green dashed line) for Earth is shows the performance of the engine operating between sea-level and an altitude of 20km, the approximate operational altitude of commercial aircraft. 

The second data set (red dashed line) is again for Earth operation and shows the engine performance at an altitude of between 100km and 1000km.  This data set increases the attitude from the Karman line, the boundary between Earth’s atmosphere and space, to 1000km, Low Earth Orbit (LEO). 

The 1000km altitude does not represent the limit of the operating altitude for the ABIE, this altitude was set as a pragmatic limit for calculations.

The engine is operational within the zones shown by both the green and red dashed lines however, to bridge the gap between these zones, the electronics will require modification and upgrading to operate in the zone between 20km and 100km.

The third data set (blue dashed line) is for Mars operations is shows the performance of the engine between altitudes of 0km and 100km above the Martian surface.

The fourth data set (solid green line) is a computer-generated simulation of the thrust produced at different altitudes on Earth between sea-level and 1000km with the engine operating in neutral air. In this mode, the engine requires an ioniser to ionise the gas flowing through the engine.

The fifth data set (solid blue line) is a computer-generated simulation of the thrust produced at different altitudes on Earth between 100km and 1000km with the engine operating in the ionosphere. In this mode, the engine can utilise ions within the atmosphere flowing through the engine and does not require an ioniser. 

The sixth data set (yellow cross) is the performance of the Mk 1 ABIE during proof-of-concept testing at a simulated altitude of 100km on Earth.