Single Flap Drive System With Flex Shafts
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Solution Overview
Problem
Decentralized flap systems in aircraft face challenges in synchronizing flap surfaces and detecting failure cases, leading to complexity, weight, and energy inefficiency compared to centrally driven systems.
Innovation Solution
A simplified drive assembly for aircraft flaps using a single power drive unit with a power-off brake, flex shafts, and position feedback sensors, controlled by a redundant flight control computer, which eliminates the need for differential gears and redundant motors, allowing for weight and cost savings while enhancing power efficiency and failure detection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If a centralized flap actuation system with mechanical transmission shafts is used, then symmetry and uniform movement of all flap surfaces are guaranteed, but the system becomes complex and heavy due to long transmission shafts, supporting bearings, and routing direction changing gear boxes
Solution Approach 1:
The patent divides the centralized drive system into decentralized drive units, with each flap or flap group having its own independent motor and drive mechanism. This segmentation eliminates the need for long transmission shafts and complex mechanical linkages, reducing overall system complexity while maintaining controlled movement of each flap surface independently
Solution Approach 2:
The patent replaces traditional mechanical transmission shafts and gear boxes with electric motors directly coupled to flaps or drive stations. This substitution of mechanical systems with electric drives eliminates the need for complex mechanical transmission components, reducing weight and complexity while achieving the desired flap movement control
2Weight of moving object
If a decentralized flap system is used, then weight and cost are reduced with fewer components, but synchronization of different flap surfaces and detection of failure cases becomes challenging
Solution Approach 1:
The patent incorporates position feedback sensors at each drive station or flap to monitor the actual position and status of flap surfaces. This feedback mechanism enables the control system to synchronize flap movements by adjusting individual drive units based on real-time position data and to detect failure cases by identifying deviations from expected behavior, thereby maintaining reliability despite the decentralized architecture
Solution Approach 2:
The patent employs a universal control architecture where a single control unit or flight control computer manages multiple decentralized drive stations through standardized communication protocols. This multi-functional control approach simplifies synchronization and failure detection across different flap surfaces by using统一的 control logic and monitoring procedures
3Use of energy by moving object
If a decentralized flap system with individual drive units is used, then energy efficiency is improved, but the ability to detect and prevent additional failure cases is compromised
Solution Approach 1:
The patent equips each decentralized drive unit with position feedback sensors and monitoring systems that continuously report status to the control unit. This feedback network enables energy-efficient operation by allowing individual drive units to operate independently while simultaneously providing the control system with real-time data to detect failure cases such as motor failures, gear failures, or flap position deviations, thus maintaining comprehensive monitoring despite the distributed architecture
Data Source
AI summary
A drive assembly for driving a movable flow body of an aircraft, includes: a power drive unit, a flight control computer, a first flex shaft connecting the power drive unit to an inboard drive station, a second flex shaft connecting the inboard drive station to an outboard drive station, a first actuator connected to the inboard drive station and being couplable with the movable flow body, a second actuator connected to the outboard drive station and being couplable with the movable flow body. The second actuator includes a redundant position feedback sensor. The power drive unit includes a power-off brake, wherein the position feedback sensor is configured to send a position feedback signal to the flight control computer, and the flight control computer is configured to control the power drive unit.