Aircraft Wing with Freely Rotating Tips
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Solution Overview
Problem
Conventional aircraft wing designs face challenges in maintaining stability and lift during low-speed maneuvers, leading to stall and spin accidents, as the wing tips stall, reducing lateral stability and increasing drag, especially during takeoff and landing.
Innovation Solution
A static aircraft wing with freely rotating wing tips, where the wing tips are rotatably mounted to the main wing section and can freely spin about a rotational center aligned with the mean lift line, allowing them to auto-rotate and maintain lift without stalling, enhancing lateral stability and reducing drag.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the wing tips are fixed in position, then the structure is simple and stable, but the wing tips stall during low-speed maneuvers reducing lateral stability and increasing drag
Solution Approach 1:
The wing tips are made dynamically adjustable through a rotation mechanism that allows them to change their angle of attack relative to the wing. This enables the wing tips to adapt their orientation based on flight conditions, preventing stalling during low-speed maneuvers while maintaining structural simplicity through a straightforward rotational joint design.
Solution Approach 2:
The invention changes the parameter of wing tip angle of attack dynamically. By allowing the wing tips to rotate and adjust their orientation, the system can optimize the angle of attack for different flight speeds, preventing stall conditions during takeoff and landing while maintaining simplicity in the overall structure.
2Reliability
If the wing tips are made freely rotating, then stall-spin conditions are prevented and lateral stability is maintained, but the structure becomes more complex
Solution Approach 1:
The wing tips are equipped with a rotational mounting that allows dynamic adjustment of their orientation. This dynamic capability enables the wing tips to freely rotate and adapt to varying flight conditions, preventing stall-spin conditions while using a relatively simple rotational joint rather than a complex active control system.
Solution Approach 2:
The freely rotating wing tips utilize the natural aerodynamic forces and gravity to automatically adjust their orientation and prevent stalling, without requiring external control systems. The wing tips self-regulate their angle of attack based on flight conditions, maintaining stability during low-speed maneuvers while avoiding complex mechanical control mechanisms.
3Force
If the angle of attack is increased to maintain lift at low speeds, then lift is restored, but the airflow detaches from the upper part of the wing causing stall
Solution Approach 1:
The wing tips can dynamically adjust their angle of attack through rotation, allowing them to operate at optimal angles even when the main wing is at high angles of attack. This dynamic adjustment prevents airflow detachment at the wing tips during low-speed maneuvers, maintaining lift while avoiding stall conditions.
Solution Approach 2:
The invention changes the operational parameters of the wing tips by allowing independent rotation and angle adjustment. This enables the wing tips to maintain optimal airflow attachment and generate lift even when the overall wing is at high angles of attack, preventing the harmful effect of airflow detachment and stall.
4Ease of operation
If large control surfaces are used to compensate for reduced lift at low speeds, then lateral control is maintained, but aerodynamic drag increases
Solution Approach 1:
The rotating wing tips provide dynamic lateral control capability, allowing the aircraft to maintain lateral stability and control during low-speed maneuvers without requiring large fixed control surfaces. The ability to adjust wing tip orientation provides efficient control with minimal additional surface area, reducing aerodynamic drag.
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 freely rotating wing tips prevent stall-spin conditions, maintaining lift and stability during low-speed maneuvers, reducing the risk of accidents and improving control, while also reducing the need for large control surfaces and minimizing drag at high speeds.
Implementation Method 1
the wing tip is rotatably mounted at the proximal end to the outboard end of the main wing section and arranged to freely spin with respect to the main wing section in response to airflow incident on the at least one wing tip about a wing tip rotational centre that is parallel to or coaxially aligned with the mean lift line of the wing
Data Source
AI summary
The present invention relates to a wing for an aircraft. The wing includes a main wing section extending from an inboard end to an outboard end along a lateral axis of the wing, the inboard end for connecting the main wing section to the aircraft. The wing also includes a wing tip having a proximal end and a distal end, the wing tip being rotatably mounted at the proximal end to the outboard end of the main wing section and arranged to freely rotate about a wing tip rotational center with respect to the main wing section.