Distributed Trailing Edge Wing Flap Actuation with Dual Power Sources
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Solution Overview
Problem
Conventional trailing edge wing flap systems are vulnerable to failure when there is a partial or complete failure of hydraulic or electrical systems, leading to the inability to change or control wing flap positions, which can result in asymmetry and loss of control during flight.
Innovation Solution
The distributed trailing edge wing flap system incorporates at least one hydraulically driven actuator powered by both the aircraft's hydraulic system and a local power unit connected to the electrical system, ensuring continuous operation and maintaining wing flap position control even in the event of system failures, using a fly-by-wire flight control system and a 2H2E power architecture.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional hydraulic or electrical systems are used to power wing flap actuators, then the system structure is simple, but the system becomes vulnerable to failure when hydraulic or electrical systems fail, leading to loss of control
Solution Approach 1:
The patent divides the actuator power system into multiple independent power sources (hydraulic system and electrical system) that can operate separately. Each actuator can be powered by either hydraulic motors or electrical motors, allowing the system to segment the power supply function across different energy sources to maintain reliability when one system fails.
Solution Approach 2:
The patent changes the power supply parameter from single-source to dual-source by incorporating both hydraulic and electrical power systems. This parameter change allows the actuators to accept different power inputs based on system availability, transforming the power architecture from vulnerable single-source to resilient multi-source configuration.
2Reliability
If distributed trailing edge wing flap systems with multiple actuators are implemented, then redundancy and control reliability are improved, but the device complexity and number of components increase
Solution Approach 1:
The patent creates universal actuators that can accept both hydraulic and electrical power inputs. These multi-functional actuators can operate in different modes (hydraulic-only, electrical-only, or combined) depending on system conditions, reducing the need for completely separate redundant systems while maintaining reliability through flexible power source selection.
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 maintains the ability to control wing flap positions, prevents asymmetry, and ensures safe flight operations by providing independent power to each actuator, even if one or more hydraulic or electrical systems fail, thereby enhancing aircraft stability and control.
Implementation Method 1
a hydraulic module located at and operatively coupled to the actuator. The hydraulic module includes a supply line and a return line, each having selective fluid communication with a first port and a second port of the actuator
Data Source
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Figure 2A~2B
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AI summary
Distributed trailing edge wing flap systems (300) are described. An example wing flap system (300) for an aircraft (100) includes a flap (112), an actuator (302, 402, 502), a first hydraulic module (318, 424, 506), and a second hydraulic module (334, 510). The flap is movable between a deployed position (204) and a retracted position (202) relative to a fixed trailing edge (110) of a wing (102) of the aircraft. The actuator is to move the flap relative to the fixed trailing edge. The first hydraulic module is located at the actuator. The second hydraulic module is located remotely from the first hydraulic module and includes a local power unit (554). The actuator is hydraulically drivable via first pressurized hydraulic fluid to be supplied from a hydraulic system (346, 518) of the aircraft to the actuator via the second hydraulic module and further via the first hydraulic module. The actuator is also hydraulically drivable via second pressurized hydraulic fluid to be supplied from the local power unit to the actuator via the second hydraulic module and further via the first hydraulic module.