Distributed Trailing Edge Flaps With Local Hydraulic Power Backup
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Solution Overview
Problem
Conventional trailing edge wing flap systems become inoperable in the event of a partial or complete failure of the hydraulic system, leading to the inability to control or maintain the positions of wing flaps, which is critical for aircraft operation.
Innovation Solution
The distributed trailing edge wing flap system incorporates actuators that can be hydraulically driven by both the aircraft's hydraulic system and a local power unit (LPU) connected to the electrical system, allowing the LPU to supply pressurized hydraulic fluid independently and maintain wing flap positions even if the primary hydraulic system fails.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the aircraft uses a centralized hydraulic system to drive wing flap actuators, then the system structure is simple and easy to control, but the system becomes inoperable in the event of hydraulic system failure
Solution Approach 1:
The patent divides the centralized hydraulic system into distributed modular units, with each wing flap actuator equipped with its own local power unit (LPU) containing hydraulic pump and motor. This segmentation ensures that failure of the main hydraulic system does not render all flaps inoperable, as each module can potentially operate independently using its local power source.
Solution Approach 2:
The patent implements local power units at each actuator location along the wing span, providing localized hydraulic power generation. This local quality approach allows each actuator to have its own backup power capability, ensuring that wing flaps can be controlled even when the centralized hydraulic system fails, thereby improving overall system reliability.
2Reliability
If the aircraft equips each actuator with a local power unit for backup, then the reliability is improved, but the device complexity and weight increase
Solution Approach 1:
The local power units are designed to serve multiple functions: they can operate as backup power sources during main hydraulic system failure, and can also function as primary power sources or supplement the main system during normal operation. This multi-functionality justifies the added complexity by providing versatile operational capabilities.
Solution Approach 2:
The local power units are pre-configured and pre-charged with hydraulic fluid in the compensators before failure occurs. This preliminary action ensures that when the main hydraulic system fails, the LPUs can immediately take over without requiring time-consuming setup or fluid transfer, thus maintaining reliability while managing complexity through advance preparation.
3Speed
If the local power unit uses compensators to store hydraulic fluid, then the response time is improved, but the volume and weight of the power unit increase
Solution Approach 1:
The compensators are sized to provide sufficient hydraulic fluid for critical backup operations rather than full continuous operation. This partial action approach provides adequate response time for emergency flap control while minimizing the volume and weight penalty of oversized compensators.
Solution Approach 2:
The compensators are pre-charged with hydraulic fluid during normal operation, storing energy in advance. This preliminary action allows the system to respond immediately during failure conditions without requiring large compensator volumes, as the fluid is already in place and ready for rapid deployment when needed.
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 ensures the aircraft can maintain and control wing flap positions, preventing asymmetry and ensuring safe operation by providing a backup power source for the actuators, thus restoring the ability to actuate wing flaps to their last commanded positions in case of hydraulic system failure.
Implementation Method 1
a hydraulic pump in fluid communication with the compensator, and an electrical motor operatively coupled to the hydraulic pump
Implementation Method 2
the local power unit includes a compensator, a hydraulic pump in fluid communication with the compensator
Data Source
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AI summary
Distributed trailing edge wing flap systems are described. An example wing flap system for an aircraft (100) includes a flap (112, 114, 118, 120) and an actuator (402). 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 (402) is to move the flap relative to the fixed trailing edge (110). The actuator (402) is hydraulically drivable via first pressurized hydraulic fluid to be supplied by a hydraulic system (930) of the aircraft. The actuator is also hydraulically drivable via second pressurized hydraulic fluid to be supplied by a local power unit (902). The local power unit (902) is selectively connectable to an electrical system (918) of the aircraft. The electrical system (918) is to power the local power unit (902) to supply the second pressurized hydraulic fluid.