Convertible Wing Assembly for Pitch Control in VTOL Aircraft
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Solution Overview
Problem
Aircraft transitioning between vertical and horizontal flight modes face challenges in pitch control and stability due to difficulties in regulating pitch trim and pitch stability, making it difficult for pilots to operate efficiently.
Innovation Solution
A wing assembly comprising a rotatable wing spar with a first and second wing element, where the second wing element is pivotably connected to the first and can nest over it, allowing for varying overlap and effective wing area adjustment, enabling smooth transition between flight modes without imparting pitching moments to the airframe.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a conventional airfoil is used for vertical takeoff and landing, then the aircraft can achieve VTOL capability, but the pitch control and pitch stability become difficult to regulate during transition between vertical and horizontal flight
Solution Approach 1:
The wing assembly employs dynamic reconfiguration through rotatable wing elements that can change their orientation relative to the fuselage. The first and second wing elements can be rotated to different angles and positions to optimize aerodynamic characteristics for different flight modes, enabling smooth transition between vertical and horizontal flight while maintaining pitch stability.
Solution Approach 2:
The wing is divided into multiple independent elements (first wing element and second wing element) that can be controlled separately. This segmentation allows each element to be optimized for specific flight phases - the first element for vertical flight and the second element for horizontal flight - thereby resolving the pitch control difficulties during transition.
2Adaptability or versatility
If the wing elements are fixed in position, then the structure is simple, but the aircraft cannot efficiently transition between vertical and horizontal flight modes
Solution Approach 1:
The wing assembly incorporates rotatable and slidable mechanisms that allow the wing elements to dynamically adjust their positions and orientations. The first wing element can rotate with the wing spar and slide relative to the fuselage, while the second wing element can pivot relative to the first, enabling efficient mode transition despite the added mechanical complexity.
Solution Approach 2:
The second wing element is positioned to overlap the first wing element, creating a nested configuration. This nesting arrangement allows both elements to be compact when not in use while still providing full aerodynamic surface area when deployed, balancing structural compactness with functional versatility.
3Stability of the object's composition
If a tail is used for pitch control, then pitch stability is improved, but the aircraft structure becomes more complex and heavier
Solution Approach 1:
The invention extracts the pitch control function from the traditional tail assembly and relocates it to the wing elements themselves. By making the wing elements rotatable and adjustable, they directly provide pitch control authority, eliminating the need for a separate tail and reducing overall structural complexity.
Solution Approach 2:
The wing elements serve multiple functions: they provide lift, generate drag for braking, and control pitch through their rotatable joints. This multi-functionality consolidates what would traditionally require separate components (tail, elevators, flaps) into a single integrated wing assembly, reducing structural complexity.
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
The wing assembly provides stable pitch and yaw control without a tail, allowing for efficient vertical takeoff and landing, as well as high-speed cruising, by dynamically balancing lift and drag forces, enabling seamless transition between flight modes without pitching the airframe.
Implementation Method 1
The wing assembly provides stable pitch and yaw control without a tail, allowing for efficient vertical takeoff and landing, as well as high-speed cruising, by dynamically balancing lift and drag forces
Implementation Method 2
The wing assembly provides stable pitch and yaw control without a tail, allowing for efficient vertical takeoff and landing, as well as high-speed cruising, by dynamically balancing lift and drag forces
Data Source
AI summary
In at least some implementations, an aircraft includes a fuselage, a wing spar rotatably carried by the fuselage, a first wing element and a second wing element. The first wing element is carried by the wing spar, rotatable with the wing spar, and slidably moveable relative to the fuselage and wing spar. The second wing element is connected to the first wing element for pivoted movement of the second wing element relative to the first wing element. The second wing element at least partially overlaps the first wing element and the first and second wing elements are moveable to a plurality of positions wherein the amount that the second wing element overlaps the first wing element varies to vary the effective combined wing area of the wing elements.