Aircraft Flow Body Drive Assembly for Differential Flap Control
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Solution Overview
Problem
Existing high-lift systems for aircraft wings are mechanically complex, requiring centralized drive units and extensive transmission shaft systems, which complicate synchronization and increase weight and drag.
Innovation Solution
A drive assembly with independent sets of windings and actuators, connected by flexible transmission shafts, allows for differential flap settings with reduced mechanical complexity and redundancy, eliminating the need for centralized units.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a centralized drive unit with transmission shaft systems is used to drive movable flow bodies, then synchronization between flaps can be achieved, but the mechanical complexity and number of components (bearings, cardan joints, couplings) increase significantly
Solution Approach 1:
The invention divides the centralized drive system into multiple independent distributed drive units, each responsible for driving a specific movable flow body. This segmentation eliminates the need for extensive transmission shaft systems connecting all flaps to a single central unit, thereby reducing mechanical complexity while maintaining synchronization through independent control of each segment.
2Reliability
If extensive transmission shaft systems with multiple bearings, cardan joints and couplings are used, then flap synchronization is achieved, but the weight of the drive system increases
Solution Approach 1:
The invention extracts and removes the heavy transmission shaft systems, bearings, cardan joints, and couplings from the drive architecture. By placing drive units directly at the flow bodies, the patent eliminates the need for these intermediate transmission components, significantly reducing the overall weight of the drive system while preserving synchronization capability through electronic control.
3Ease of operation
If a centralized drive unit is used, then control of multiple flaps is simplified, but drag increases due to extensive mechanical linkages inside the wings
Solution Approach 1:
The invention segments the mechanical linkages by placing independent drive units directly at each flow body location. This eliminates the need for extensive transmission shafts running through the wing structure, thereby reducing aerodynamic drag caused by these mechanical linkages while maintaining control capability through electronic coordination of the distributed units.
4Adaptability or versatility
If an active differential gear box is added between inboard and outboard flaps to enable differential flap settings, then versatility is improved, but device complexity increases
Solution Approach 1:
The invention applies segmentation by providing independent drive units for inboard and outboard flaps, each capable of independent control. This eliminates the need for complex differential gear boxes while achieving differential flap settings functionality, as each segmented drive unit can be controlled independently to achieve the desired differential configuration.
Solution Approach 2:
The invention replaces the mechanical differential gear box with an electronic control system that independently actuates the distributed drive units. This substitution eliminates complex mechanical components while achieving the same differential flap settings functionality through electronic coordination, thereby reducing device complexity.
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 design reduces mechanical complexity, weight, and drag while maintaining synchronization, enabling efficient and precise control of movable flow bodies with improved integration and reliability.
Implementation Method 1
an electric motor (22) having a first set of windings (24) and a second set of windings (26)
Data Source
Figure 1
Figure 2
Figure 3
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.