Wingtip Deflector Yaw Control Mechanism
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current yaw control systems for aircraft are inefficient in balancing aerodynamic forces, often requiring multiple actuators and disrupting the aerodynamic profile of the wing, leading to potential instability and reduced performance.
Innovation Solution
A yaw control device comprising a common shaft with two deflectors positioned at the wingtip, which pivot from a closed to an open position to counteract yaw moments, minimizing aerodynamic moment and allowing for continuous leading and trailing edges, thus enhancing stability and aerodynamics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple actuators are used for yaw control, then yaw control effectiveness is improved, but device complexity and actuator load increase
Solution Approach 1:
The patent combines multiple deflector surfaces (top and bottom deflectors on each wing) onto a single common shaft, allowing them to be actuated simultaneously by one actuator. This merging approach maintains yaw control effectiveness while reducing the number of actuators from multiple to a single actuator per wing, thereby reducing device complexity and actuator load.
2Force
If deflectors are deployed for yaw control, then yaw moment is generated, but aerodynamic profile of the wing is disrupted
Solution Approach 1:
The patent positions deflectors at the wingtip region, concentrating the yaw control function locally at the wingtip rather than across the entire wing span. This local placement allows the deflectors to generate the necessary yaw moment while minimizing disruption to the overall aerodynamic profile of the wing, as the majority of the wing surface maintains its streamlined configuration.
3Loss of energy
If deflectors are positioned at wingtip, then aerodynamic moment is minimized, but yaw control effectiveness may be reduced
Solution Approach 1:
The patent employs asymmetric deflector deployment where deflectors on opposite wings can be positioned at different angles or deployed independently. This asymmetry allows one wing's deflector to generate a yaw moment that counteracts external yaw disturbances, while the other wing's deflector remains retracted or positioned differently, thereby maintaining aerodynamic efficiency while achieving effective yaw control.
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 solution provides effective yaw control with reduced actuator load, maintains continuous wing edges for improved aerodynamics, and allows for fuel storage in thicker wing regions, enhancing the aircraft's range and structural stiffness.
Implementation Method 1
impart an unbalanced drag force on one wing, thereby imparting the desired yaw moment
Implementation Method 2
the extended deployed surfaces are given an angle of attack to the free stream flow to produce a lift force
Data Source
Figure 1
Figure 2
Figure 3A
AI summary
A first deflector (250) configured to couple to a shaft of a wing (120) of an aircraft (100) and form part of a top surface (242) of the wing (120) when in a first closed position, and a second deflector (260) configured to couple to the shaft (310) and form part of a bottom surface (244) of the wing (120) when in a second closed position. The first deflector (250) and the second deflector (260) may be configured to be positioned proximate to the tip (220) of the wing (120). The first deflector (250) and the second deflector (260) may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft (310).