PT656

GURNEY FLAP ACTUATOR AND MECHANISM FOR A FULL SCALE HELICOPTER ROTOR BLADE

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 Obiettivo del progetto (Objective)

'Microtecnica SrL (MT) have brought together industry leading expertise to support the design and development of a full scale Active Gurney Flap (AGF) system. The team have a combination of relevant experience in blade actuation across a range of technologies together with significant capabilities in fundamental engineering analysis to support a comprehensive review of potential solutions. The proposal reflects the joint desire of offering a risk managed baseline approach as well as ensuring all potential candidate solutions are assessed as part of the initial development task. The consortium is lead by MT who provide the technical and programme management and the detail design and manufacture of the wind tunnel and whirl test hardware. MT will be supported by Microtecnica Actuation Technologies (MAT), University of Bristol and the “Politecnico di Torino” based in Turin. The team ensures a balance of technical depth together with a commitment and capability to exploit technology for commercial gain.'

Introduzione (Teaser)

Little tabs off the trailing edge of helicopter rotor blades promise better lift and lower fuel consumption. Scientists are developing a demonstrator of the most promising structural and control technology to take eco-consciousness to new heights.

Descrizione progetto (Article)

Gurney flaps have been implemented on a variety of aerofoils from aeroplane wings to helicopter rotor blades to air turbines and race cars. Active gurney flaps (AGFs) are a key objective of the EU's Clean Sky aerospace research programme. Adding an active component provides the ability to adapt to changing conditions and a system that significantly outperforms its passive analogue. It could provide important vibration damping at less weight than current solutions as a system that addresses vibration at its source, the blades.

The EU is funding the project 'Gurney flap actuator and mechanism for a full scale helicopter rotor blade' (PT656) to evaluate the capabilities of a helicopter main rotor blade incorporating an AGF. The consortium has extensive experience in both blade actuation technologies and fundamental engineering analysis. The expertise puts the team in the best possible position to evaluate all potential candidate solutions as part of the preliminary development task.

Electromechanical actuation was chosen for its reliability, high power density, high bandwidth capability, and robustness to extreme conditions of temperature, vibration and acceleration. The AGF structural components and actuation system were embedded in a section of the helicopter main rotor blade and successfully evaluated in wind tunnel tests. The test campaign studied performance of the blade held in a fixed position. Stress analyses evaluated performance under various operational loads, whereas thermal analyses investigated heat transfer from the motor and moving parts of the actuator to the blade.

During the final months, the AGF system will be evaluated on a ground-based whirl tower subjected to realistic conditions for a flying helicopter's main rotor blade. In preparation, the actuation system will first be tested in a dedicated spin test rig to ensure safety and minimise risk.

By project-end, PT656 expects to have demonstrated both the technological feasibility and the performance capabilities of a helicopter main rotor blade incorporating an AGF. Benefits include greater lift, lower fuel consumption and fewer emissions. Implementation into rotorcraft will make a major contribution to the EU's Clean Sky programme to reduce the environmental impact of air travel.