Integrated Landing Flap Drive System with Redundant Motors
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Solution Overview
Problem
Current landing flap drive systems for aircraft require extensive installation and structural leadthroughs due to central shaft arrangements, leading to increased complexity and cost, and lack redundancy, which can compromise system safety and reliability.
Innovation Solution
The integration of the landing flap drive system into the track of the landing flap, including a step-down gear arrangement, redundant drive motors, a brake device, and a safety load path, allows for reduced installation effort, enhanced safety, and improved operational efficiency by eliminating the need for central shafts and mechanical couplings, with electronic synchronization of motors.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a central shaft arrangement is used to transmit drive power from the fuselage to the landing flap, then the drive system can be controlled centrally, but the installation complexity increases significantly due to required structural leadthroughs, deflection gear arrangements, and universal joints
Solution Approach 1:
The patent divides the drive system into modular units, with each landing flap equipped with its own integrated drive system including motor, gear arrangement, and actuator. This segmentation eliminates the need for complex central shaft arrangements and universal joints, as each module operates independently while maintaining centralized control through electronic coordination.
Solution Approach 2:
The patent replaces the mechanical central shaft transmission system with electronically controlled independent drive units. Instead of mechanical power transmission through shafts and universal joints, the system uses electrical motors and electronic control signals, substituting mechanical complexity with electrical simplicity.
2Power
If a central drive arrangement with shafts and universal joints is implemented, then power transmission to distributed drive stations is achieved, but production expenditure and installation cost increase considerably
Solution Approach 1:
The drive system is segmented into independent modular units, with each landing flap having its own complete drive system. This eliminates the need for expensive central shaft arrangements and reduces installation complexity, thereby lowering production and installation costs while maintaining full power transmission capability to each flap.
Solution Approach 2:
The patent replaces expensive mechanical power transmission components (shafts, universal joints, deflection gears) with electronically controlled electric motors. This substitution dramatically reduces production expenditure and installation cost while achieving the same power transmission function through electrical means.
3Device complexity
If a single drive motor is used for each landing flap, then the system is simple, but system safety and reliability are compromised due to lack of redundancy
Solution Approach 1:
The patent implements redundant drive motors in each landing flap drive system as a preventive safety measure. This beforehand cushioning ensures that if one motor fails, the second motor can take over, preventing complete system failure and maintaining reliability without significantly increasing operational complexity.
Solution Approach 2:
The patent changes the system configuration from a single motor to a dual motor arrangement, altering the redundancy parameter. This parameter change enhances system safety and reliability by providing backup capability, while the modular design keeps the added complexity manageable.
4Adaptability or versatility
If drive components are installed separately during final assembly, then flexibility is maintained, but installation effort and time are significantly increased
Solution Approach 1:
The patent merges multiple drive components (motor, gear arrangement, actuator, brake device) into a single integrated drive system unit that is pre-assembled as one complete module. This merging maintains assembly flexibility for different aircraft configurations while dramatically improving installation efficiency, as the entire drive system can be installed in one operation rather than assembling multiple separate components.
Solution Approach 2:
The patent performs preliminary assembly of the complete drive system within the track structure before final installation on the aircraft. This preliminary action allows for factory pre-assembly and testing of the integrated drive system, reducing on-site installation effort and time while maintaining the ability to adapt to different aircraft configurations.
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 significantly simplifies the installation process, reduces production costs, enhances system safety through redundancy, and optimizes operational performance by integrating all drive components into the track, eliminating the need for structural leadthroughs and deflection gears, while ensuring structural integrity and efficient motor synchronization.
Implementation Method 1
a step-down gear arrangement to reduce the operational speed of the landing flap
Implementation Method 2
the brake device may be used in a supportive manner in that it absorbs, or compensates for, a compressive force that acts on the landing flap
Data Source
AI summary
A landing flap drive system, in one example, includes a first drive motor for operating a landing flap. In this arrangement, the landing flap drive system is integrated in a track of the landing flap such that final assembly and integration of the system are facilitated to a significant extent.