Aircraft Wing Movable Appendages for Downwash Interference
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current convertiplane and gyrodyne wing designs face challenges in optimizing aerodynamic efficiency, particularly at the interface between the wing box and movable appendages, which leads to increased resistance and interference with rotor downwash, limiting maneuverability and payload capacity.
Innovation Solution
The design incorporates movable appendages that are hinged to the wing box and arranged to minimize airflow interruption in the 'aeroplane' configuration, while in the 'helicopter' configuration, they are positioned to allow the downwash to flow through, reducing interference and enabling efficient operation without additional sealing elements, thus optimizing both aerodynamic performance and internal space for fuel and structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If movable appendages are positioned close to the wing box in aeroplane configuration, then aerodynamic efficiency is improved, but interference with rotor downwash increases in helicopter configuration
Solution Approach 1:
The movable appendages are designed to change position dynamically between aeroplane and helicopter configurations. In aeroplane mode, they are positioned close to the wing box to minimize wake turbulence and improve aerodynamic efficiency. In helicopter mode, they are repositioned to allow rotor downwash to pass through, reducing interference. This dynamic reconfiguration resolves the contradiction by adapting the appendage position to the operational mode.
Solution Approach 2:
The wing structure is segmented into the wing box and movable appendages that can be independently positioned. This segmentation allows the appendages to be moved to different locations relative to the wing box depending on the operational configuration, enabling optimization for both aeroplane and helicopter modes without compromising either performance.
2Loss of energy
If additional sealing elements are added to reduce airflow interruption, then aerodynamic efficiency is improved, but device complexity increases
Solution Approach 1:
The invention removes the need for additional sealing elements by utilizing the natural aerodynamic flow through the movable appendages in helicopter configuration. Instead of adding sealing components to prevent airflow interruption, the design allows the downwash to pass through the appendages, eliminating the harmful effect without requiring any sealing mechanism. This extraction of the sealing requirement simplifies the device while maintaining aerodynamic efficiency.
3Reliability
If rotor size is increased to overcome downwash interference, then helicopter performance is improved, but device complexity and bulk increase
Solution Approach 1:
Instead of increasing rotor size to overcome downwash interference, the invention dynamically repositions the movable appendages in helicopter configuration to allow the existing rotor's downwash to pass through effectively. This dynamic positioning maintains helicopter performance with the original rotor size, avoiding the need for larger, more complex rotor systems while achieving the same performance improvement.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This design enhances aerodynamic efficiency, reduces the need for larger rotors, increases payload capacity, and simplifies manufacturing by minimizing bulk and interference with rotor downwash, while also protecting critical components like the interconnection shaft.
Implementation Method 1
in the 'helicopter' configuration, they are positioned to allow the downwash to flow through, reducing interference
Implementation Method 2
aeroplanes use fixed wings to generate the lift necessary for sustaining the aeroplane in the air
Data Source
AI summary
A wing having a wing box (20) defining a first wing profile with a first leading edge, a first trailing edge, a first top surface and a first bottom surface; a first appendage hinged on the wing box and defining a second wing profile, in turn comprising an end wall and a second trailing edge, a second top surface and a second bottom surface; the first appendage is movable between: a first position, in which the first and the second wing profiles are contiguous with each other and a second position, in which the second bottom surface and second top surface are respectively separated from the first bottom surface and first top surface; the wing box comprises a first spar having a curved section in a plane orthogonal to the associated first axis; the end wall is curved and arranged abutting against the first spar at least along the second top surface and the second bottom surface when the first movable appendage is in the first position.