Aircraft Wing Trailing Edge Torque Tube for Flutter Suppression
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Solution Overview
Problem
Existing systems face challenges in quickly moving trailing edge elements of aircraft wings to react to gusts and suppress flutter while minimizing the negative impact on aerodynamic performance.
Innovation Solution
A trailing edge system with a torque element, such as a torque tube, connects movable flap devices to transmit torque for synchronized rotational movement, using an actuator to drive the torque element, with the torque element positioned off-center to minimize aerodynamic interference.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If quickly movable trailing edge elements are added to react to gusts and suppress flutter, then the response speed and flutter suppression capability are improved, but the device complexity and aerodynamic interference increase
Solution Approach 1:
The patent combines multiple flap devices (first and second flap devices) into a single integrated flap device arrangement, actuated by one common actuator through a torque element. This merging approach reduces the number of independent actuators and simplifies the overall control system while maintaining the capability for quick response to gusts and flutter suppression.
Solution Approach 2:
The single actuator serves multiple functions by actuating both the first and second flap devices simultaneously through the torque element. This multi-functional actuator design reduces system complexity while enabling the trailing edge system to perform both gust response and flutter suppression functions.
2Speed
If quickly movable trailing edge elements are added to react to gusts and suppress flutter, then the response speed and flutter suppression capability are improved, but the aerodynamic performance deteriorates
Solution Approach 1:
The patent positions the torque element off-center relative to the axis of rotation of the flap devices. This asymmetric local positioning minimizes the aerodynamic interference of the torque element itself while still effectively transmitting actuation forces to both flap devices, thereby reducing overall aerodynamic drag and interference.
Solution Approach 2:
The torque element is deliberately designed with asymmetric positioning (off-center mounting) rather than symmetric central positioning. This asymmetric configuration reduces the windage drag and aerodynamic interference caused by the torque element, while maintaining effective mechanical coupling to both flap devices for quick response operation.
3Productivity
If multiple movable flap devices are used for quick response, then the gust response capability is improved, but the actuation effort required increases
Solution Approach 1:
The patent merges the actuation of multiple flap devices into a single integrated system where one actuator controls both the first and second flap devices through a common torque element. This combined actuation approach distributes the actuation effort efficiently and reduces the total force requirement compared to independent actuation of each flap device.
Solution Approach 2:
The torque element acts as an intermediary mechanical component that efficiently transmits actuation force from the single actuator to both flap devices. This intermediary mechanism enables coordinated movement of multiple flap devices with reduced actuation effort by providing mechanical advantage and force distribution.
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
Enables quick movement of trailing edge elements to react to gusts and suppress flutter with minimal aerodynamic disruption, optimizing aerodynamic performance and simplifying actuation mechanisms.
Implementation Method 1
a torque element connecting the movable flap devices for transmitting a torque to the movable flap devices in order to actuate a rotational movement of the movable flap devices
Implementation Method 2
an actuator for rotationally driving the torque element
Implementation Method 3
the torque element positioned off-center to minimize aerodynamic interference
Data Source
AI summary
A trailing edge system for a wing of an aircraft comprises a flap device arrangement configured for being mounted at a trailing edge of an aircraft wing, wherein at least two movable flap devices of the flap device arrangement are spaced apart from each other. A torque element is connecting the movable flap devices for transmitting a torque to the movable flap devices in order to actuate a rotational movement of the movable flap devices. An actuator for rotationally driving the torque element is provided. Also a method of operating control surfaces of an aircraft wing and an aircraft and aircraft wing with such a system.