Pivoting Wingtip Effector Control for Aircraft Stability
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Solution Overview
Problem
Aircraft face challenges in maintaining control and stability due to dynamic environments, requiring enhanced control authority over changing aerodynamic conditions.
Innovation Solution
The aircraft design incorporates pivotably connected fore and aft winglets at the wing tips, which can be independently operated, allowing for symmetrical or anti-symmetrical deflection, and are controlled by a processor to manage roll, yaw, and roll-yaw hybrid modes, enhancing control and stability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If traditional fixed wingtip structures are used, then the aircraft structure is simple, but the control authority over changing aerodynamic conditions is insufficient
Solution Approach 1:
The patent applies the dynamics principle by transforming the static wingtip structure into a dynamic, actively controllable system. The winglets are equipped with actuators that enable real-time adjustment of their deflection angles, allowing the structure to adapt to changing aerodynamic conditions during flight. This dynamic capability provides variable control authority while managing structural complexity through controlled articulation points.
Solution Approach 2:
The patent segments the traditional monolithic wingtip into multiple independent controllable elements (fore winglet and aft winglet). Each winglet can be independently actuated and controlled, allowing differential deflection to achieve various flight control modes. This segmentation enables enhanced adaptability without requiring complete redesign of the entire wingspan structure.
2Adaptability or versatility
If multiple independently operable winglets are added to enhance control, then control authority improves, but device complexity increases
Solution Approach 1:
The patent implements multi-functionality by designing the fore and aft winglets to serve multiple control purposes simultaneously. The same winglet structure and actuation system enable roll control, yaw control, and coordinated maneuvers depending on the deflection pattern. This universal approach allows enhanced lateral-directional control capability without proportionally increasing system complexity, as a single actuator system achieves multiple control functions.
Solution Approach 2:
The patent merges the functions of multiple control surfaces into a unified winglet system. By combining fore and aft winglets on the same wing, and coordinating their movement with opposite wing's winglets, the system achieves enhanced control authority while consolidating actuation and control mechanisms. This merging reduces the need for separate control systems for each function.
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 configuration provides greater control authority, stability, and the ability to perform coordinated maneuvers by varying winglet deflections, achieving improved lateral-directional control and reducing induced drag.
Implementation Method 1
The winglets can be deflected symmetrically as well as anti-symmetrically... to produce a desired effect on the aircraft
Data Source
AI summary
An aircraft can include a first wing and a second wing. The first wing can extend laterally from an aircraft body to a first tip, and the second wing can extend laterally from the aircraft body to a second tip. The aircraft can include a first end effector and a second end effector, each including a fore winglet and an aft winglet. The fore and aft winglets of the first end effector can be pivotably connected to the first tip. The fore and aft winglets of the second end effector can be pivotably connected to the second tip. The fore and aft winglets of the first and second end effectors can be independently operable. The first and second end effectors can be independently operable. A processor can be operatively connected to control movement of the fore and aft winglets of the first and second end effectors.