Variable Power Transfer for Flight Control Surfaces
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Solution Overview
Problem
Existing high-lift systems for fixed-wing aircraft limit the ability to tailor wing performance during different phases of flight since they can only actuate flight control surfaces simultaneously and in unison, restricting flexibility in lift distribution and wing camber adjustment.
Innovation Solution
The system employs a common movable driving member with variable power transfer devices, including clutches with magneto-rheological or electro-rheological fluids, to independently adjust power transfer to multiple flight control surfaces, allowing differential actuation and independent control of leading edge slats and trailing edge flaps, enabling variable deployment, retraction, and speed adjustment without reversing the driving member's direction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If flight control surfaces are mechanically coupled to a common actuator for simultaneous actuation, then the system structure is simple and reliable, but the ability to tailor wing performance during different phases of flight is limited
Solution Approach 1:
The patent divides the previously unified actuation system into multiple independent actuation channels. Each flight control surface (leading edge slats and trailing edge flaps) is equipped with its own actuator and control system, allowing independent adjustment of each surface. This segmentation enables differentiated actuation of various control surfaces during different flight phases, resolving the contradiction between system simplicity and performance adaptability.
Solution Approach 2:
The patent implements dynamic control capabilities by allowing the actuation parameters (deployment angle, speed, timing) of each flight control surface to be adjusted independently based on real-time flight conditions. The control system can dynamically modify the actuation commands sent to each actuator, enabling the wing configuration to be optimized for different flight phases such as takeoff, cruise, and landing.
2Adaptability or versatility
If a common actuator is used for multiple flight control surfaces, then the number of components is reduced, but the flexibility in lift distribution and camber adjustment is restricted
Solution Approach 1:
The patent segments the actuation system so that each flight control surface has its own dedicated actuator. This allows the leading edge slats and trailing edge flaps to be actuated independently with different deployment angles and speeds, providing flexible control over lift distribution across the wing span. The segmentation comes at the cost of increased component quantity but enables superior performance tailoring.
Solution Approach 2:
The patent applies local quality control by allowing different actuation parameters to be applied to different parts of the wing. Each flight control surface can have its own deployment angle, speed, and timing optimized for specific flight conditions. This local customization of control parameters enables precise control over the camber and lift characteristics of different wing sections.
3Ease of operation
If flight control surfaces are actuated in unison, then the control system is simplified, but the ability to independently adjust camber and lift force positioning is lost
Solution Approach 1:
The patent divides the control system into multiple independent control channels, each responsible for a specific flight control surface. This segmentation allows the control system to send independent commands to each actuator, enabling differential actuation of leading edge slats and trailing edge flaps. The increased control complexity is offset by the significant gain in operational flexibility and performance tailoring capability.
Solution Approach 2:
The patent implements dynamic control strategies where the actuation parameters of each flight control surface can be independently adjusted in real-time based on flight conditions. The control system can dynamically modify deployment angles, speeds, and timing for each surface, enabling optimized wing configuration for different flight phases while maintaining manageable control complexity through automated control algorithms.
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 approach enhances the flexibility in tailoring lift distribution along the wing span, allowing for selective adjustment of camber and lift force positioning, improving wing performance during various flight phases and conditions by enabling independent actuation of flight control surfaces.
Implementation Method 1
The disclosure also describes systems, components, apparatus and methods useful in the transfer of power to one or more flight control surfaces via magneto-rheological fluid or electro-rheological fluid
Implementation Method 2
The disclosure also describes systems, components, apparatus and methods useful in the transfer of power to one or more flight control surfaces via magneto-rheological fluid or electro-rheological fluid
Data Source
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AI summary
Apparatus and methods for actuating flight control surfaces (16A-C) of fixed-wing aircraft are disclosed herein. An exemplary apparatus disclosed includes a common movable driving member (20) for actuating a plurality of flight control surfaces; a first power transfer device (24A) configured to variably adjust power transfer from the common movable driving member to a first of the plurality of flight control surfaces; and a second power transfer device (24B) configured to variably adjust power transfer from the common movable driving member to a second of the plurality of flight control surfaces. The power transferred to the second flight control surface may be adjusted independently of the power transferred to the first flight control surface. Apparatus and methods for actuating flight control surfaces using magneto-rheological fluid or electro-rheological fluid are also disclosed.