Auburn University LPC-02 DUeVTOL (concept design)

(Image credit: Vehicle Systems, Dynamics and Design Laboratory, Auburn University)

LPC-02 DUeVTOL (concept design)
Vehicle Systems, Dynamics and Design Laboratory
Aerospace Engineering
Auburn University
Auburn, Alabama, USA
www.vsddl.com

Founded in August 2018 by Dr. Imon Chakraborty, the Vehicle Systems, Dynamics and Design Laboratory is a research lab that focuses on aircraft systems, dynamics, control, flight simulation and incorporating these aspects into aircraft sizing and design. A flight vehicle, whether novel or conventional, is a central theme of the lab. The research team, consisting of Dr. Chakraborty, PhD seeking graduate students as well as undergraduate researchers, has designed multiple electric vertical takeoff and landing (eVTOL) and hybrid-electric VTOL concept designs for advanced air mobility (AAM).

Since the lab was founded, the research facility has received more than $1.7 million (USD) in externally funded research, including funding from Federal Aviation Administration (FAA), NASA and the United States Air Force (USAF) and is also collaborating with multiple industry partners.

LPC-02 DUeVTOL modular passenger and air cargo eVTOL concept design aircraft
The LPC-02 DUeVTOL is a modular passenger and air cargo eVTOL concept design aircraft that can be outfitted with multiple power sources. For passenger service, the aircraft is fitted with a passenger pod and holds one pilot, four passengers and their luggage. For air cargo service, the aircraft is flown by one pilot and is fitted with an air cargo pod.

The estimated cruise speed of the aircraft is 230 knots/ 230 mph/ 370 km/h at a nominal cruise altitude of 3,000 ft (914.4 m). The range of the aircraft using an all-battery power source is anticipated to be two back-to-back 63 mile (101 kilometer) trips. The range of the aircraft using a hybrid-electric power source is projected to be 149 miles (240 kilometers). The empty weight of the aircraft is approximately 3,128 lb (1,419 kg) for the all-electric variant and 3,673 lb (1,666 kg) for the hybrid-electric variant. The expected maximum takeoff weight is 5,525 lb (2,506 kg). The fuselage material has not been specified by the inventors.

The aircraft is a "three-surface" design, with a forward canard, a main wing, and an aft horizontal stabilizer. There are two vertical stabilizers mounted at the tips of the horizontal stabilizer. There are a total of eight propulsors, each comprising a propeller driven by an electric motor. The aircraft can be powered by all batteries or by all batteries (all-electric variant) or by a combination of turbine and battery power (hybrid-electric variant). For VTOL flight, there are six ducted fans in the fuselage, three in front of the main wing and three aft of it. When in forward flight, louvers close over the ducted fans for better aerodynamics. There are two tractor propellers located on the main wing for forward flight. The aircraft has fixed quadricycle wheeled landing gear.

Safety features include distributed electric propulsion (DEP) featuring multiple propulsors (propellers + drive motors) so that if one or more propulsors fail, the other working propulsors can safely land the aircraft. DEP provides safety through redundancy for passengers or cargo. There are also redundancies of critical components in the sub-systems of the aircraft providing safety through redundancy. Having multiple redundant systems on any aircraft decreases having any single point of failure. The lift-plus-cruise aircraft has no tilting components when transitioning between vertical and forward flight which increases safety by reducing complexity. The tricycle gear also allow the aircraft to land conventionally on a runway or road in emergencies.

Specifications:

• Aircraft type: Modular passenger and air cargo eVTOL and hybrid-electric VTOL concept design aircraft
• Piloting: 1 pilot
• Capacity: 4 passengers or air cargo pod
• Cruise speed: 230 mph (370 km/h)
• Cruise altitude: 3,000 ft (914.4 m)
• Range (batteries only): 63 m (101 km)
• Range (hybrid-electric): 149 m (240 km)
• Empty weight: 3,128 lb (1,419 kg) for the all-electric variant and 3,673 lb (1,666 kg) for the hybrid-electric variant
• Maximum payload weight: 882 lb (400 kg)
• Maximum takeoff weight: 5,525 lb (2,506 kg)
• Propellers: 8 propellers. 6 VTOL-only propellers and 2 tractor propellers for forward flight.
• Electric motors: 8 electric motors
• Power source: The aircraft can be powered by batteries alone or it can be outfitted with a hybrid-electric system using a turbine engine. There are 5 battery packs in both designs. The batteries are sized for a minimum 20% power reserve at the end of the design mission.
• Fuselage: Material unknown
• Wing: 1 canard, 1 high main wing, 33.23 ft (10.13 m) in span
• Tail: 1 canard (fore), 1 horizontal stabilizer (aft), two vertical stabilizers
• Windows: Larger windows than a general aviation airplane
• Landing gear: Fixed quadricycle wheeled landing gear
• Safety features: Distributed electric propulsion (DEP) means having multiple propulsors (propellers + drive motors) so that if one or more propulsors fail, the other working propulsors can safely land the aircraft. DEP provides safety through redundancy for passengers or cargo. There are also redundancies of critical components in the sub-systems of the aircraft providing safety through redundancy. Having multiple redundant systems on any aircraft decreases having any single point of failure. The lift-plus-cruise aircraft has no tilting components when transitioning between vertical and forward flight which increases safety by reducing complexity. The tricycle gear also allow the aircraft to land conventionally on a runway or road in emergencies.

Related Aircraft:

• Auburn University Hexa-Chakra Personal Air Vehicle (concept design)
• Auburn University LPC-01 Pushpak (concept design)
• Auburn University LPC-03 Phoenix (concept design)
• Auburn University TW-01 Minokawa (concept design)
• Auburn University TW-02 Pangolin (concept design)
• Auburn University VT-02 Sevak (concept design)

Company Insights:

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Resources:

• Chakraborty, I., Mishra, A.A., van Dommelen, D., and Anemaat, W.A.J., “Design and Sizing of an Electrified Lift-Plus-Cruise Ducted Fan Aircraft,” AIAA Journal of Aircraft, Vol. 60, No. 3, pp. 817-834, May 2023 (Article in Advance, Nov 30, 2022), DOI: 10.2514/1.C036811
• Vehicle Systems, Dynamics and Design Laboratory, Auburn University website
• Vehicle Systems, Dynamics and Design Laboratory (eVTOL aircraft list), Auburn University website
• Vehicle Systems, Dynamics and Design Laboratory, Auburn University Facebook
• Vehicle Systems, Dynamics and Design Laboratory, Auburn University Twitter
• Vehicle Systems, Dynamics and Design Laboratory, Auburn University YouTube Channel
• Imon Chakraborty LinkedIn
• Auburn University website
• Video: VSDDL - Meet the Crew (Dec 2020), Vehicle Systems, Dynamics, and Design Laboratory, Dec. 14, 2020
• Article: Aerospace faculty member part of six Air Force Agility Prime awards, Auburn University, Apr. 30, 2021
• Video: LPC-02 DUeVTOL (DARcorporation + VSDDL) Cockpit Flight Simulation, Vehicle Systems, Dynamics, and Design Laboratory, Jan. 15, 2022
• Video: LPC-02 DUeVTOL (DARcorporation + VSDDL) Flight Simulation, Vehicle Systems, Dynamics, and Design Laboratory, Jan. 15, 2022