#MAE3402 Aircraft Specifications
Semester 2, 2016
Aircraft performance of a twin engine electric aircraft
This code is used to assess the specifications of final designs for the proposal outlined in the MAE3402 Request For Proposal (RFL) document.
Carry out preliminary design of a battery-powered 6-seat unpressurised commuter aircraft capable of 1000 km range.
The requirements below must be satisfied at maximum aircraft weight unless otherwise stated.
- Payload and crew Maximum payload for 1000 km range is one aircrew and five passengers each with standard size cabin baggage, 120 kg total mass per person. Ferry range payload: pilot and baggage, total 120 kg.
- Design mission 1000 km range, cruising at 10 000 ft altitude, M = 0.25 airspeed. Range includes take-off and landing segments, no loiter allowance.
- Power Two electric motors of equal size, energised by advanced-chemistry rechargeable Li-ion batteries with anticipated specific energy 1 MJ/kg. Batteries must be removeable for recycling and replacement.
- Service ceiling 12 000 ft with minimum rate of climb 100 ft/min at this altitude.
- Climb Minimum 2nd-segment climb gradient 1.5% with one engine inoperative. Minimum rate of climb at cruise altitude: 300 ft/min.
- Takeoff and landing 1 km maximum of paved runway. Additional minimum ground distance allowed to 35 ft screen height: 200m. Maximum landing approach speed: 100 kt.
- Load factors −1.5 ≤ n ≤ 3.5.
- General certification basis CASR Part 23