A Prospective: The Importance of Propulsion Technology to the Development of Helicopter Systems with a Vision for the Future The 27th Alexander A. Nikolsky Lecture

Rosen, Kenneth M.

doi:10.4050/jahs.53.307

Cited by 15 publications

(9 citation statements)

References 10 publications

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“…The state of the art data is taken from Ref. 23 but modified into a form suitable for such a comparison. Normally, the brake specific fuel consumption (BSFC) and specific power (SP) form suitable measures for comparing engines.…”

Section: Technology Status and Future Requirementsmentioning

confidence: 99%

Requirements for a Hydrogen Powered All-Electric Manned Helicopter

Datta¹

2012

12th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference and 14th AIAA/ISSMO Multidisciplinary Analysis And

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The objective of this paper is to set propulsion system targets for an all-electric manned helicopter of ultra-light utility class to achieve performance comparable to combustion engines. The approach is to begin with a current two-seat helicopter (Robinson R 22 Beta II-like), design an all-electric power plant as replacement for its existing piston engine, and study performance of the new all-electric aircraft. The new power plant consists of highpressure Proton Exchange Membrane fuel cells, hydrogen stored in 700 bar type-4 tanks, lithium-ion batteries, and an AC synchronous permanent magnet motor. The aircraft and the transmission are assumed to remain the same. The paper surveys the state of the art in each of these areas, synthesizes a power plant using best available technologies in each, examines the performance achievable by such a power plant, identifies key barriers, and sets future technology targets to achieve performance at par with current internal combustion engines. Nomenclature

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Section: Technology Status and Future Requirementsmentioning

confidence: 99%

Requirements for a Hydrogen Powered All-Electric Manned Helicopter

Datta¹

2012

12th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference and 14th AIAA/ISSMO Multidisciplinary Analysis And

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“…In the 1930s, engines were refined by the booming aircraft industry. They were delivering unprecedented power-to-weight ratios [47], enabling helicopters to sustain more efficiently hovering flights. The counter-torque effect was tackled in many ingenious ways.…”

Section: Introductionmentioning

confidence: 99%

“…This success was soon matched by other helicopter pioneers. Henrich Focke at the Focke Wulf Company and Juan de la Cierva within the Weir company demonstrated the hovering capabilities of a side by side rotor configuration in 1936 and 1938 respectivelly [3,22,47]. In 1940 Sikorsky flew a single rotor helicopter configuration with three auxiliary tail rotors to negate the counter-torque effect [22,51] as shown in Figure 2.…”

Section: Introductionmentioning

confidence: 99%

Smart Actuation for Helicopter Rotorblades

Paternoster¹,

Loendersloot²,

Boer³

et al. 2012

Smart Actuation and Sensing Systems - Recent Advances and Future Challenges

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“…This success was soon matched by other helicopter pioneers. Henrich Focke at the Focke Wulf Company and Juan de la Cierva at the Weir company demonstrated the hovering capabilities of a side-byside rotor configuration in 1936 and 1938 respectively [1,3,4]. In 1940 Sikorsky flew a single rotor helicopter configuration with three auxiliary tail rotors to negate the counter-torque effect [1,5] as shown in Figure 1.2.…”

Section: Introduction 11 Early Helicoptersmentioning

confidence: 99%

“…In the 1930s, engines were refined by the booming aircraft industry. They were delivering unprecedented power-to-weight ratios [3], enabling helicopters to sustain hovering flights more efficiently. Besides the Breguet design, other inventors used two and even quad-rotor configurations 1 to tackle the counter-torque effect [1,4,6].…”

Section: Introduction 11 Early Helicoptersmentioning

confidence: 99%

Smart actuation mechanisms for helicopter blades : design case for a Mach-scaled model blade

Paternoster¹

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Today's helicopters are the result of collaborative work in mechanical engineering and aeronautics. The European project "Clean Sky" aims at improving the efficiency and the global transport quality of aircraft. In the field of rotorcraft, the research in this project is currently focussing on active blade systems to adapt the aerodynamic properties of the blade to the local aerodynamic conditions. Fuel-efficiency, reduction of vibration and noise and increase of the helicopter maximum speed are the benefits expected from these new technologies. To envision the implementation of these innovative blade concepts, this thesis investigates the selection process for actuators, the methods to design and optimise actuation systems and the procedures to validate them through simulations and testing.Integrating an actuation system in helicopters is especially difficult because of a combination of challenges. To begin with, these include the tremendous loads due to the rotation of the blade, the limited space available, and constraints regarding durability. Secondly, the impact that the actuation system will have on the rotor blade behaviour has to be taken into account. And lastly, integrating the component inside the actual structure of a rotor blade should be feasible. A system based on piezoelectric actuators provides a potential solution to meet these challenges. A selection process has been established in Chapter 2 to match an actuation technology to application requirements. Among many of the smart blade concepts under development, the active Gurney flap is considered in the framework of the Clean Sky Innovative Technology Development project "Green Rotor Craft", for its potential impact on the blade performance and technology readiness. Actively deploying the Gurney flap on the retreating side of the helicopter increases the lift of the rotorcraft and its overall performances. To validate this technology, numerical studies and wind-tunnel testing on reduced-scale rotor blades are necessary. The procedures detailed in this work are applied to the design of an actuation system to fold and deploy a Gurney flap for a Mach-scaled rotor blade. Additional challenges arose due to the reduction in size: the centrifugal acceleration is increased and the space available inside the blade is drastically reduced.Computational Fluid Dynamic simulations are performed in the first step of the design procedure to obtain the aerodynamic loads on the Gurney flap for various realistic combinations of deployment levels, orientations of the blade in the flow and airspeeds (Chapter 4). Secondly, the design of the actuation mechanism is performed using a two-step approach: (1) computer generated topologies are analysed to find a suitable initial geometry; (2) an optimisation is carried out to maximise the displacement and force of the structure integrating a piezoelectric patch actuator. The resulting structure presents the characteristic shape of a "Z" (Chapter 5). It converts the strains generated by the piezoelectric actuator into rela...

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A Prospective: The Importance of Propulsion Technology to the Development of Helicopter Systems with a Vision for the Future The 27th Alexander A. Nikolsky Lecture

Cited by 15 publications

References 10 publications

Requirements for a Hydrogen Powered All-Electric Manned Helicopter

Requirements for a Hydrogen Powered All-Electric Manned Helicopter

Smart Actuation for Helicopter Rotorblades

Smart actuation mechanisms for helicopter blades : design case for a Mach-scaled model blade

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