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Auburn University TW-02 Pangolin (concept design)

TW-02 Pangolin passenger hybrid-electric VTOL concept design aircraft

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

TW-02 Pangolin (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 then 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 PhD seeking graduate students as well as undergraduate researchers, has designed multiple passenger and air cargo electric vertical takeoff and landing (eVTOL) and hybrid-electric VTOL concept design aircraft for advanced air mobility (AAM).

Since the lab was founded, the research facility has received more than $1.5 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.

TW-02 Pangolin passenger battery, hybrid-electric or turbine-electric VTOL concept design aircraft
The TW-02 Pangolin has been designed to accept multiple power sources and is a passenger VTOL tiltwing concept design aircraft. The aircraft is expected to be flown by one pilot and holds three to four passengers and their luggage. The aircraft can take off and land vertically or conventionally. The aircraft is very modern looking and due to the wing configuration, the aircraft can be used for either short or long range travel for advanced air mobility (AAM).

For the aircraft's power source, the aircraft can be powered by batteries alone, use turbine engines to create the electricity and uses batteries, or the aircraft power can be from turbine engines alone without the use of any batteries. The hybrid-electric power source is noted as H.E. The turbine electric power source (without the use of batteries) is noted as T.E.

The estimated cruise speed is 207 mph (333 km/h). The aircraft using a power source of batteries only,  the range of the aircraft is forecasted to be 44 miles (71 km). The aircraft using a power source of turbine engines and batteries, the range of the aircraft is intended to be 135 miles (217 km). The maximum payload weight is anticipated to be 1,100 lb (500 kg) and the maximum takeoff weight is calculated to be 8,818 lb (4,000 kg) for all power sources.

The aircraft is expected to have general aviation sized windows. The aircraft has a total of eight variable-pitch propellers and eight electric motors. Six propellers are located on the tiltwing, one VTOL variable-pitch propeller is in the nose section of the aircraft and one VTOL variable-pitch propeller is located in the tail section of the aircraft. The aircraft has a front canard wing and one H-tail. The aircraft has retractable tricycle wheeled landing gear. The fuselage is made from carbon fiber composite for a high strength to low weight ratio.

Some of the safety features include distributed electric propulsion (DEP) which means that is one or two of the propellers stop working, the other propellers can land the aircraft to safety. In case of an emergency where none of the VTOL propellers are working, the aircraft can land conventionally on a runway or road. DEP provides safety through redundancy for passengers or cargo. There are also redundancies of critical components in the sub-systems of the aircraft providing increased safety and reliability through redundancy. Having multiple redundant systems on any aircraft decreases having any single point of failure.

Specifications:

  • Aircraft type: Passenger battery, hybrid-electric and turbine-electric VTOL concept design aircraft
  • Piloting: 1 pilot
  • Capacity: 3-4 passengers and their luggage
  • Cruise speed: 207 mph (333 km/h)
  • Range (batteries only): 44 miles (71 km)
  • Range (hybrid-electric, turbine engines and batteries): 135 miles (217 km)
  • Range (turbo-electric, turbine engine and no batteries): 185 miles (298 km)
  • Empty weight, all-electric and without battery weight: 5,787 lb (2,625 kg),
  • Empty weight, hybrid-electric, without battery weight: 6,364 lb (2,887 kg)
  • Empty weight, turbo-electric: 7,118 lb (3,229 kg)
  • Maximum payload weight: 1,100 lb (500 kg)
  • Maximum takeoff weight: 8,818 lb (4,000 kg)
  • Propellers: 8 propellers (6 variable-pitch propellers on the tiltwing and 1 variable-pitch VTOL trim fan in the nose section and 1 variable-pitch VTOL trim fan in the tail section)
  • Electric motors: 8 electric motors
  • Power source: The aircraft has been designed to use multiple power sources. The aircraft can be powered by batteries only. The aircraft can be powered using a hybrid-electric using turbine engines  and batteries. The aircraft can be powered by turbine engines without using any batteries.
  • Fuselage: Carbon fiber composite
  • Window: General aviation sized windows
  • Wings: 1 main high tiltwing
  • Wingspan: 40.91 ft (12.47 m)
  • Tail: 1 H-tail
  • Landing gear: Retractable tricycle wheeled landing gear
  • Safety features: Distributed electric propulsion (DEP) means having multiple propellers (or electric ducted fans) and multiple electric motors on an aircraft so if one or more propellers (or electric ducted fans) or some electric motors fail, the other working propellers (or electric ducted fans) and electric motors 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.

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