Glassock, Richard and Galea, Michael and Williams, Warren and Glesk, Tibor (2017) Hybrid electric propulsion systems for skydiving aircraft. In: MEA 2017 More Electric Aircraft, 1-2 February 2017, Bordeaux, France. (Unpublished) Access from the University of Nottingham repository: http://eprints.nottingham.ac.uk/50636/1/Posterv1.4.pdf Copyright and reuse: The Nottingham ePrints service makes this work by researchers of the University of Nottingham available open access under the following conditions. This article is made available under the University of Nottingham End User licence and may be reused according to the conditions of the licence. For more details see: http://eprints.nottingham.ac.uk/end_user_agreement.pdf A note on versions: The version presented here may differ from the published version or from the version of record. If you wish to cite this item you are advised to consult the publisher’s version. Please see the repository url above for details on accessing the published version and note that access may require a subscription. For more information, please contact [email protected]
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Glassock, Richard and Galea, Michael and Williams, Warren and Glesk, Tibor (2017) Hybrid electric propulsion systems for skydiving aircraft. In: MEA 2017 More Electric Aircraft, 1-2 February 2017, Bordeaux, France. (Unpublished)
Access from the University of Nottingham repository: http://eprints.nottingham.ac.uk/50636/1/Posterv1.4.pdf
Copyright and reuse:
The Nottingham ePrints service makes this work by researchers of the University of Nottingham available open access under the following conditions.
This article is made available under the University of Nottingham End User licence and may be reused according to the conditions of the licence. For more details see: http://eprints.nottingham.ac.uk/end_user_agreement.pdf
A note on versions:
The version presented here may differ from the published version or from the version of record. If you wish to cite this item you are advised to consult the publisher’s version. Please see the repository url above for details on accessing the published version and note that access may require a subscription.
For more information, please contact [email protected]
Richard Glassock- [email protected]
Michael Galea – [email protected]
Warren Williams – [email protected]
Tibor Glesk - [email protected]
Hybrid Electric Propulsion Systems for Skydiving Aircraft
Institute for Aerospace Technology, University Of Nottingham
Web: http://www.nottingham.ac.uk/aerospace/
Objectives• Show viability of novel hybrid electric and all-electric aircraft concept for skydiving missions.• Push forward investment in new electrical propulsion technology equipped light commuter category aircraft.
Missiona. Carriage of minimum eight parachutists (loads), to a height of
4000m with a duty cycle of 3 to 4 loads per hour.
b. Configurable for freight transport role.
IntroductionSkydiving is a popular aviation sport throughout the world.Hundreds of thousands of people are active in approximately 1000centres worldwide [1]. The United States Parachute Associationalone recorded 36,770 members at the end of 2014 [2].Continuing airworthiness of ageing legacy aircraft is a maintenancesafety challenge. Legacy aircraft also possess unsatisfactoryemissions qualities. Great opportunities exist for new paradigmaircraft type.Case study uses novel ‘Air Ute Pty Ltd’ [3] conceptual design forinvestigation of an alternative aircraft type for this application,including trade-off studies with a new analytical model.
Conclusions Summary• A Hybrid Electric skydiving lift aircraft has been found to be
viable using current state of the art Electrical Propulsion Systemtechnology from an aerodynamic standpoint.
• An All-Electric propulsion system is feasible given the conditionthat the battery is replaced or recharged for each mission.
• The time to climb for a fully electric example is acceptable andthe improvement over a non Flat Rated powerplant operatingto the prescribed altitude is very significant.
• Engine emissions can be reduced or eliminated for this aircraftmission without hindering performance or economic utility.
Hybrid Electric system weight and performance comparison analysis
FIG. 1 – Legacy Type FIG. 2 – New paradigm Hybrid
Hybrid Propulsion System
[1] Dropzone inc. "Where to dropzone". Available: http://www.dropzone.com/dropzone[2] The USA Parachute Association. "Who Skydives?". Available: http://www.uspa.org/facts-faqs/demographics[3] Air Ute Pty Ltd, Australia. Contact: Tibor Glesk
Conventional Propulsion System
• 800kW single turboprop• Large (LD3) cargo loading capacity
• 800kW installed power• Increased disc area• Higher propulsive efficiency at
lower airspeed• Increased climb angle• Lower drag
• Trade cargo capacity for modular Battery
• Rapid battery exchange via ultra-large cargo door or external “cargo pod” concept
Institute for Aerospace Technology, University Of Nottingham
Web: http://www.nottingham.ac.uk/aerospace/
FIG. 3 – Mission Profile FIG. 4 – Descent
FIG. 5 – Take-off Weight FIG. 6 – Time to Climb
FIG. 7 – Conventional Layout ‘Air Ute’ with LD3
FIG. 8 – New paradigm Hybrid
FIG. 9 – Hybrid Propulsion layout
FIG. 10 – New paradigm Hybrid
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