Combined with a certain ultralight electric aircraft's design parameters

the layout of aircraft electric propulsion system

the principles and steps of the parameter matching of electric propulsion system were presented. The methods of parameter matching and performance verification of electric propulsion system were put forward. The feasibility of the system was verified from the mass of propulsion system

dynamics and economics. The maximum level flight speed of the reference aircraft is 175.5km/h

greater than the maximum level flight speed of 170km/h

which is design requirement

in compliance with the requirement of dynamic performance. The operation cost of electric propulsion system is RMB 6.8 yuan/h that is close to the 1/8 of the operation cost of piston engine with similar power. Compared with three electric aircrafts

the reference aircraft's power to mass ratio is still high up to 0.0842kW/kg

which is acceptable.