Lithium-Air Powered E-190 type aircraft By Michael Vegh 1

The Problem 2 Designs and optimizes the wing parameters, electric propulsion system, as well as the mission flight profile of a E-190 type aircraft, replacing the jet A and turbofan with lithium- air batteries (Esp=2000 W-h/kg, Psp=.64 kW/kg, est timeframe), ducted fans, and electric motors. The aircraft carry the same number of passengers a specified distance, and uses the same tail as the E-190

Design Variables 5 climb segments with target altitudes as well as climb velocities (vertical climb rate was maintained as equal to the given E-190 values) Cruise velocity Wing sweep, twist at the root and tip, as well as reference area Li-Air battery energy Li-S battery energy and power 3

Constraints 4

Sample Results (3800 km range) 5

Sample Design Results 6

Sample Design Variables (3800 km) 7 ElectricE-190 Climb Alt1(km) Climb Alt 2 (km) Climb Alt 3 (km) Climb Alt 4 (km) Climb Alt 5 (km) Vclimb1(m/s) Vclimb2(m/s) Vclimb3(m/s) Vclimb4(m/s) Vclimb5(m/s) Vcruise(m/s)230 alpha_rc (degrees) alpha_tc (degrees) wing sweep (degrees)8.79E-0522 Sref (m^2) cruise range