Synchronized Hydraulic Flap Actuation with Position Hold Backup
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Solution Overview
Problem
Existing flight control actuation systems for aircraft rely on hydraulic actuators, which can be inefficient and lack precise control, especially when hydraulic pressure is unavailable, leading to inconsistent movement and potential loss of control.
Innovation Solution
The system employs synchronized hydraulic actuators with meshing worm gears and gears, along with brakes and motors, to ensure consistent movement and positioning of flight control members, using an actuation control unit to manage hydraulic fluid flow and adjust valves based on sensor signals, allowing for independent control of inboard and outboard flight control members.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If hydraulic actuators are used for flight control members, then the actuation system can provide sufficient force for control surface movement, but the system lacks precise control and consistency when hydraulic pressure is unavailable
Solution Approach 1:
The patent combines hydraulic actuators with electrical motors in a hybrid actuation system. Each flight control member has both a hydraulic actuator and an electric motor that can independently or simultaneously provide actuation force. This merging ensures reliable control consistency through hydraulic power while maintaining precise control capability through electric motor control, resolving the contradiction between reliability and ease of operation.
Solution Approach 2:
The system changes the actuation parameter from purely hydraulic pressure-dependent to a dual-mode system that can operate in hydraulic mode, electric mode, or hybrid mode. The control system dynamically selects the appropriate actuation parameter based on available hydraulic pressure and control precision requirements, ensuring both reliability and precise control across different operating conditions.
2Adaptability or versatility
If individual control of flight control members is implemented, then differential operation for optimizing wing loading is achieved, but the system complexity increases
Solution Approach 1:
The patent divides the actuation system into independent modular units, with each flight control member having its own hybrid actuator assembly. This segmentation allows each control surface to be independently controlled with its own hydraulic actuator and electric motor, enabling differential operation for optimizing wing loading while keeping each module's complexity manageable and standardized.
Solution Approach 2:
The hybrid actuator design provides multi-functionality by enabling each flight control member to be actuated independently through either hydraulic or electric means. This universal actuation capability allows the system to achieve differential operation for various flight conditions while using standardized components, reducing overall system complexity despite the increased adaptability.
3Manufacturing precision
If synchronization members are added to coordinate actuator movement, then consistent positioning is achieved, but the device complexity increases
Solution Approach 1:
The patent incorporates feedback control mechanisms where sensors monitor the position of flight control members and provide real-time data to the control system. The control system processes this feedback and adjusts the actuation commands to both hydraulic actuators and electric motors to ensure they reach and maintain the desired synchronized position, achieving precise positioning without overly complex mechanical synchronization linkages.
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 solution provides consistent and precise control of flight control members, maintaining position even when hydraulic pressure is unavailable, and allows for differential operation of inboard and outboard flight control members, optimizing wing loading during flight.
Implementation Method 1
The slave hydraulic actuator includes meshing first and second worm gears
Implementation Method 2
A pump moves the hydraulic fluid through the supply and to the actuators. The hydraulic fluid then is directed into different sections of the hydraulic actuators to move the hydraulic actuator
Implementation Method 3
the pacing hydraulic actuator including meshing first and second gears with a same efficiency in both operating directions
Data Source
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AI summary
An actuation system for controlling flight control members of a vehicle. Each flight control member (101) is controlled by two or more linear hydraulic actuators (20). Synchronization members (40) extend between the hydraulic actuators (20) on the same flight control members (101) to synchronize the movements of the hydraulic actuators (20) for consistent movement across the length of the flight control members (101). Brakes (50) can maintain the positions of the synchronization members (40) and thus the flight control members. Motors (60) can provide for moving the synchronization members to control the positioning of the hydraulic actuators (20) and flight control members.