Distributed Wing Flap Actuation With Local Hydraulic Backup
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Conventional trailing edge wing flap systems become inoperable in the event of a partial or complete failure of the hydraulic system, leaving aircraft without the ability to change or control wing flap positions.
Innovation Solution
The distributed trailing edge wing flap system incorporates actuators that can be hydraulically driven by the aircraft's hydraulic systems and independently powered by local power units (LPUs) connected to the electrical system, allowing for the restoration and maintenance of wing flap positions even in the event of hydraulic system failure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional hydraulic systems are used to drive wing flap actuators, then the system structure is simple and easy to operate, but the system becomes inoperable in the event of hydraulic system failure
Solution Approach 1:
The patent divides the actuator power system into multiple independent segments: each actuator can be powered by either the central hydraulic system or its own local power unit (LPU), allowing independent operation of each flap actuator even when other segments fail
Solution Approach 2:
The system changes the power source parameter from a single hydraulic source to dual power sources (hydraulic and electrical), enabling the actuators to switch between different energy states and maintain operation under varying system conditions
2Reliability
If local power units are added to each actuator for independent operation, then the system reliability is improved, but the device complexity and weight increase
Solution Approach 1:
Local power units are pre-installed at each actuator location and pre-filled with hydraulic fluid, enabling immediate independent operation when central hydraulic system failure occurs without requiring complex real-time switching mechanisms
Solution Approach 2:
Each local power unit is designed to be self-contained and self-sufficient, capable of independently powering its associated actuator without requiring complex coordination or control from other system components
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 asymmetries and ensuring safe operation by providing a backup power source for the actuators, thus overcoming the limitations of conventional systems.
Implementation Method 1
first local power unit configured to generate third pressurized hydraulic fluid to independently power the first actuator
Implementation Method 2
first actuator configured to move the first flap relative to the first fixed trailing edge... configured to be hydraulically driven via third pressurized hydraulic fluid supplied by the first local power unit
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A wing flap system (300) for an aircraft, comprising four flaps (112,114,118,120) configured to be moved between respective deployed positions and respective retracted positions, the flaps being configured to be moved relative to fixed trailing edges (110,116) of the wings (102,104) of the aircraft, eight actuators (302,304,306,308,310,312,314,316) configured to move the flaps relative to the fixed trailing edges, respective ones of the actuators being configured to be hydraulically driven via first pressurized hydraulic fluid to be supplied by a first hydraulic system (334) of the aircraft, respective ones of the actuators being configured to be hydraulically driven via second pressurized hydraulic fluid to be supplied by a second hydraulic system (338) of the aircraft; and four local power units, four of the actuators being configured to be independently hydraulically driven via pressurized hydraulic fluid to be supplied by the local power units.