Aircraft Flap Actuation with Independent Drive Units
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Solution Overview
Problem
Existing aircraft high-lift systems face challenges in maintaining safety and reliability, particularly when individual actuators fail, as they often rely on secondary structural elements and sensors to prevent flap position deviations, which can be complex and costly to implement.
Innovation Solution
A system and method for actuating positioning flaps on aircraft wings using electrically controlled servo actuators and hydraulic systems, with a mechanical drive transmission device and coupling mechanism that allows independent operation of each flap, enabling fault compensation and reconfiguration without a secondary flap connecting strut, utilizing brake mechanisms and sensors for real-time evaluation and control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a central motor drives a drive shaft that extends along the wing to transmit driving torque to individual flap actuators, then the high-lift system can be controlled centrally, but the system complexity increases and safety is compromised upon actuator failure
Solution Approach 1:
The patent divides the centralized drive shaft into multiple independent drive units, each responsible for specific flap actuators. This segmentation allows individual units to fail independently without compromising the entire system, while maintaining centralized control capability through the coordinated arrangement of these modular units
Solution Approach 2:
The patent incorporates redundant actuator mechanisms and alternative load paths that are pre-configured to compensate for potential actuator failures. These cushioning measures ensure that if one actuator fails, the system can still maintain flap positioning through alternative mechanisms, preventing catastrophic failure
2Reliability
If brakes and sensors are installed for error detection and to hold high-lift surfaces in defined position, then safety is improved, but device complexity and cost increase
Solution Approach 1:
The patent designs the drive units and coupling mechanisms to serve multiple functions: they provide both the primary actuation function and the fail-safe positioning function. The coupling mechanisms between drive units and actuators are designed to inherently maintain position upon failure without requiring additional dedicated braking or sensing components for each function
Solution Approach 2:
The system employs self-monitoring capabilities where the drive units and coupling mechanisms automatically detect and respond to failure conditions through their inherent mechanical and electrical feedback. This self-service approach eliminates the need for separate complex monitoring systems while maintaining safety through automatic fault detection and isolation
3Reliability
If secondary flap connecting struts are provided to couple positioning flaps and transfer load from defective flaps, then fault compensation is improved, but structural complexity increases
Solution Approach 1:
The patent segments the load-bearing structure into independent drive units, each capable of isolating and compensating for failures locally. This segmentation eliminates the need for long-span secondary connecting struts by distributing the load compensation function across multiple independent modular units along the wing span
Solution Approach 2:
The patent introduces intermediate coupling mechanisms between drive units and flap actuators that serve as mediators for fault isolation and load transfer. These coupling mechanisms provide the necessary fault compensation functionality without requiring additional secondary structural elements like flap connecting struts, as they integrate the compensation function into the existing actuation path
Data Source
AI summary
A method for actuating at least one positioning flap on each wing of an aircraft, which positioning flap is actuated by at least two flap coupling devices each including a flap actuator device, where at least on one flap actuator device for each positioning flap a brake mechanism is arranged by means of whose actuation an adjustment state of the respective flap actuator device can be locked, including the steps of: actuating each brake mechanism of a positioning flap individually, subsequently actuating the flap actuator device by means of the drive motor, in the case of a change in the adjustment state of the positioning flap by a predetermined extent, terminating actuation of the positioning flap concerned, and a system for implementing the method.