Aircraft Flight Control Surface Assembly Wireless Energy Transfer
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Solution Overview
Problem
Existing flight control surface assemblies for aircraft are complex and costly due to high-reliability mounting structures needed to handle deviations from predetermined synchronous movement, such as skewing of slats, which increases weight and complexity.
Innovation Solution
A flight control surface assembly with a connection assembly and drive arrangement for synchronous movement, incorporating pairs of electrical components for wireless energy transfer and detection circuits to monitor deviations from the nominal path, allowing for early detection of faults like skewing and automatic stoppage of movement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If high-reliability mounting structures are constructed to handle fault states, then reliability is improved, but device complexity and weight increase
Solution Approach 1:
The patent replaces complex mechanical mounting structures with electromagnetic coupling between rotor and stator. The rotor generates a rotating magnetic field that induces currents in the stator, creating electromagnetic forces for linear motion without mechanical contact. This eliminates mechanical complexity while maintaining reliability through non-contact coupling.
Solution Approach 2:
The patent uses electromagnetic fields as the working medium instead of mechanical connections. The rotating magnetic field penetrates through the gap between rotor and stator, transmitting force wirelessly across the air gap, similar to how pneumatic or hydraulic systems transmit force through fluids without direct mechanical contact.
2Reliability
If high-reliability mounting structures are constructed to handle fault states, then reliability is improved, but weight increases
Solution Approach 1:
The patent replaces heavy mechanical mounting structures with lightweight electromagnetic coupling. The rotor and stator components are connected only through magnetic fields, eliminating the need for heavy mechanical linkages, bearings, and mounting brackets, thereby significantly reducing weight while maintaining reliability.
Solution Approach 2:
The patent uses a thin air gap between rotor and stator as the coupling medium. This gap allows electromagnetic field penetration while maintaining structural integrity, replacing what would otherwise require thick mechanical connection structures, thus reducing weight while preserving reliability.
3Adaptability or versatility
If spherical bearings and multiple links are used in joints, then adaptability is improved, but device complexity increases
Solution Approach 1:
The patent replaces spherical bearings and mechanical links with electromagnetic coupling. The rotating magnetic field can accommodate positional variations and maintain coupling effectiveness, providing adaptability without mechanical complexity. The magnetic field naturally adjusts to minor misalignments, eliminating the need for complex mechanical joints.
Solution Approach 2:
The patent uses a dynamically rotating magnetic field that can adapt to changing positions and orientations. The rotating field maintains effective coupling even when there are variations in the gap or relative positioning between rotor and stator, providing adaptability through dynamic electromagnetic interaction rather than static mechanical joints.
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 a cost-efficient and lightweight assembly capable of reliably detecting and preventing deviations from the predetermined synchronous movement, reducing the need for complex mechanical structures and maintaining high reliability with minimal maintenance.
Implementation Method 1
The first and second electrical components of each pair are adapted or configured to wirelessly transfer electrical energy over the gap from the first electrical component to the second electrical component
Data Source
AI summary
A flight control surface assembly for mounting to a main wing of an aircraft includes flight control surfaces side by side with a gap between each two of them, a connection assembly for movably connecting the flight control surfaces to the main wing to be selectively movable in a predetermined synchronous movement between retracted and extended positions, a drive arrangement operable to effect predetermined synchronous movement, and a control unit connected to the drive arrangement to control the drive arrangement. The flight control surface assembly includes for each gap a separate pair of electrical components with a first electrical component and a second electrical component fixedly mounted to a another one of the two flight control surfaces separated by the gap. The first and second electrical components of each pair are configured to wirelessly transfer electrical energy over the gap.