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Auburn University VT-02 Sevak (concept design)

VT-02 Sevak hybrid-electric VTOL concept design aircraft

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

VT-02 Sevak (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.

VT-02 Sevak subscale hybrid-electric VTOL concept design aircraft
The VT-02 Sevak is subscale hybrid-electric VTOL scalable concept design aircraft. If the aircraft was ever built, it would be remote controlled and would be a technology demonstrator that carries no pilot or passengers. After the aircraft was proven to be aerodynamically sound, technology demonstrator would be scalable and could be made for air taxi or air cargo service for advanced air mobility (AAM). The VT-02 Sevak was developed in response to the Vertical Flight Society's (VFS) 2024 Design Competition Request for Proposal titled “Multi-Mission Modular UAV for Disaster Relief”.

While very few specifications were estimated for the subscale concept design aircraft, the maximum takeoff weight has been calculated at 353 lb (160 kg). The aircraft has been designed to have 10 propellers, 10 electric motors, one turbine powered engine and has battery packs. There is a front canard wing and one rear high main wing for lift. Between the canard wing and main wing, you will notice there is a thin spar with six propellers attached, used for VTOL and forward flight. This middle spar tilts as necessary for all modes of flight. The canard wing span is 11.87 feet (3.62 meters) and the high main wing has a wing span of 18.57 feet (5.66 meters). The aircraft has one rear vertical stabilizer.

In the nose of the aircraft are two propellers. In the tail of the aircraft, there are also two propellers. If you notice on the drawing above, you'll see there are side vents for the nose and tail propellers for air intake and exhaust. The fuselage is made from carbon fiber composite for a high strength to low weight ratio. The aircraft has retractable tricycle wheeled landing gear.

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.

VT-02 Sevak schematic

VT-02 Sevak schematic

Specifications:

  • Aircraft type: Passenger hybrid-electric VTOL scalable concept design aircraft
  • Piloting: Remote controlled
  • Capacity: No passengers but the aircraft can be scaled for air taxi and air cargo service
  • Cruise speed: Unknown
  • Maximum takeoff weight: 353 lb (160 kg)
  • Propellers: 10 propellers (6 propellers on a tilting spar, 2 VTOL propellers in the nose of the aircraft and 2 VTOL propeller in the tail of the aircraft)
  • Electric motors: 10 electric motors
  • Power source: Hybrid-electric power source with one turbine engine and batteries
  • Fuselage: Carbon fiber composite
  • Wings: 1 canard and 1 high main wing
  • High main wing, wingspan: 18.57 ft (5.66 m)
  • Canard wing span: 11.87 ft (3.62 m)
  • Tail: 1 vertical stabilizer
  • 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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