Aircraft Flap Drive Assembly with Independent Windings for Lower Complexity
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Solution Overview
Problem
Existing high-lift systems for aircraft wings require complex mechanical components and centralized drive units, leading to increased mechanical complexity, weight, and reduced efficiency.
Innovation Solution
A drive assembly with independent windings, motor control electronics, and flexible transmission shafts for each movable flow body, allowing differential flap settings without a central drive unit, enhancing redundancy and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a centralized drive unit (PCU) is used to drive movable flow bodies, then the drive system can be consolidated in one location, but the mechanical complexity increases due to long transmission shaft systems, numerous bearings, cardan joints and couplings
Solution Approach 1:
The patent divides the centralized drive system into multiple distributed drive assemblies, with each assembly independently driving a specific movable flow body. This segmentation eliminates the need for long transmission shafts, numerous bearings, cardan joints and couplings that connect a centralized PCU to multiple flaps, thereby reducing mechanical complexity and weight while maintaining drive functionality.
Solution Approach 2:
The invention extracts the drive function from the centralized PCU and distributes it to individual drive assemblies located at each movable flow body. By taking out the drive function from the central location and placing it locally at each flap, the patent eliminates the complex transmission shaft system that would otherwise connect the centralized drive to multiple flaps.
2Object-affected harmful factors
If a centralized drive unit with long transmission shaft systems is used, then all flow bodies can be driven from one location, but drag increases due to the extensive mechanical components inside the wings
Solution Approach 1:
The patent segments the drive system into distributed units located at each movable flow body, eliminating the need for extensive transmission shaft systems running through the wings. This segmentation removes the mechanical components that would generate drag, while still providing comprehensive drive capability for all flaps.
Solution Approach 2:
The invention replaces the mechanical transmission shaft system with electrical connections and control systems. Each distributed drive assembly receives electrical power and control signals independently, substituting the mechanical transmission infrastructure that would otherwise be required to transmit mechanical power from a centralized location, thereby reducing drag.
3Reliability
If independent drive assemblies with dual windings and control electronics are used for each movable flow body, then redundancy and reliability are improved, but the device complexity at the component level increases
Solution Approach 1:
The patent segments the drive system into independent drive assemblies, each with its own dual windings and control electronics. This segmentation provides redundancy at the system level - if one drive assembly fails, others continue to operate - while keeping each individual component relatively simple in design.
Solution Approach 2:
The invention applies local quality by providing each movable flow body with its own dedicated drive assembly featuring dual windings and control electronics. This local redundancy ensures that each flap can be reliably controlled independently, with the complexity distributed locally rather than concentrated centrally, improving overall system reliability.
4Stability of the object's composition
If a centralized drive system with transmission shafts is used, then synchronization between flaps can be achieved, but the system requires numerous bearings, cardan joints and couplings increasing mechanical complexity
Solution Approach 1:
The patent replaces the mechanical synchronization system (transmission shafts, bearings, cardan joints, couplings) with an electrical control system. Each distributed drive assembly receives synchronized control signals electronically, eliminating the need for mechanical synchronization infrastructure while maintaining precise coordination between multiple movable flow bodies.
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
Reduces mechanical complexity, weight, and drag while maintaining efficient operation and synchronization of movable flow bodies, enabling differential flap settings and improved integration feasibility.
Implementation Method 1
an electric motor (22) having a first set of windings (24) and a second set of windings (26)
Data Source
AI summary
A drive assembly for driving a movable flow body of an aircraft comprises an electric motor having a two sets of independent windings, two motor control electronics units coupled with the windings and a control computer, two actuators couplable with a first or second section of the flow body, a first and a second transmission shaft, wherein the transmission shafts each have a first and a second end, wherein the electric motor is coupled with the first ends of the transmission shafts, wherein the second ends of the transmission shafts are coupled with the respective actuator, and wherein the drive assembly is designed to selectively move and hold the movable flow body into a plurality of extended positions and a retracted position relative to a fixed structural component of the aircraft by selectively moving and holding the first actuator and the second actuator.