Abstract
Within the scope of the SARISTU project (smart intelligent aircraft structures), a wingtip active trailing edge (WATE) is developed. Winglets are intended to improve the aircraft’s efficiency aerodynamically, but simultaneously they introduce important loads into the main wing structure. These additional loads lead to heavier wing structure and can thus diminish the initial benefit. Preliminary investigations have shown that a wingtip active trailing edge can significantly reduce these loads at critical flight points (active load alleviation). Additionally, it can provide adapted winglet geometry in off-design flight conditions to further improve aerodynamic efficiency. The idea of the active winglet has been successfully treated in several theoretical studies and small-scale experiments. However, there is a big step towards bringing this concept to a real flight application. In this project, a full-scale outer wing and winglet are currently being manufactured and will be tested, both structurally and at low speed in a wind tunnel. The scope for eventual EASA CS25 certification of a civil transport aircraft with such a winglet control device will then be assessed. In particular, a load alleviation system requires a minimum operational reliability to take effect on the applicable flight load envelope for structural design. Therefore, the potential failure modes are assessed, and a fault tree analysis is performed to draw key requirements for the system architecture design. In order to assess the overall system benefit, manufacturing, operation, and maintenance requirements are taken into account. The confined space inside the winglet loft-line presents a significant challenge for integration of an active control system. It is shown how small changes to the aerodynamic surface have both reduced the aerodynamic hinge moments (leading to lighter actuators) and created additional internal space for systems, whilst maintaining an equivalent overall drag level. The potential for reducing wing and winglet loads with a winglet control device is assessed. The kinematic design challenge of delivering the necessary power in a confined space is described. Actuation is accomplished by a single electromechanical actuator which is housed inside the CFRP winglet.
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Abbreviations
- ACE:
-
Actuator control electronics
- AS:
-
Assumption
- CAD:
-
Computer-aided design
- CFRP:
-
Carbon fibre reinforced polymer
- CG:
-
Centre of gravity
- CMM:
-
Coordinate measurement machine
- CNC:
-
Computerized numerical control
- DAL:
-
Development assurance level
- DAQ:
-
Data acquisition
- EMA:
-
Electromechanical actuator
- FC:
-
Failure condition
- FEA:
-
Finite element analysis
- FEM:
-
Finite element model
- FHA:
-
Failure hazard assessment
- FTA:
-
Fault tree analysis
- GLAS:
-
Gust load alleviation system
- GST:
-
Ground static testing
- GVT:
-
Ground vibration testing
- IS:
-
Integration scenario
- LCM:
-
Liquid composite moulding
- L/D:
-
Lift to drag (ratio)
- MARI:
-
Membrane-assisted resin infusion
- MCU:
-
Motor control unit
- MIF:
-
Multivariate mode indicator
- NDI:
-
Non-destructive inspection
- OOA:
-
Out of autoclave
- P :
-
Probability of occurrence of failure
- PSSA:
-
Preliminary system safety analysis
- Q :
-
Probability of being in failure state
- RQ:
-
Requirement
- RSDP:
-
Reference structure design principle
- RTM:
-
Resin transfer moulding
- WATE:
-
Wingtip active trailing edge
- WT:
-
Wind tunnel
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Acknowledgments
The research leading to these results has gratefully received funding from the European Union Seventh Framework Programme (FP7/2007–2013) under Grant Agreement no 284562. Many thanks also go to all SARISTU partners for their invaluable contributions.
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Wildschek, A., Storm, S., Herring, M., Drezga, D., Korian, V., Roock, O. (2016). Design, Optimization, Testing, Verification, and Validation of the Wingtip Active Trailing Edge. In: Wölcken, P., Papadopoulos, M. (eds) Smart Intelligent Aircraft Structures (SARISTU). Springer, Cham. https://doi.org/10.1007/978-3-319-22413-8_12
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DOI: https://doi.org/10.1007/978-3-319-22413-8_12
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