Distributed Trailing Edge Actuation for Aircraft Wings
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Solution Overview
Problem
Conventional trailing edge actuation systems for aircraft require significant space and multiple sub-assemblies, leading to thicker, less efficient wings, and lack redundancy for continuous operation in case of component failures.
Innovation Solution
The development of distributed trailing edge actuation systems with hybrid hydraulic-electric actuators and redundant control electronics, allowing independent control of flap actuators and switching between modes (hydraulic, electric, and hybrid) to maintain functionality in case of failures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If conventional trailing edge actuation systems are used, then flaps can be moved to generate lift, but the system requires significant space and multiple sub-assemblies leading to thicker wings
Solution Approach 1:
The actuation system is divided into multiple independent modular units distributed along the trailing edge of the wing. Each module contains its own actuator and control electronics, allowing independent operation. This segmentation reduces the space required per module compared to a centralized system, enabling thinner wing design while maintaining full flap control capability.
Solution Approach 2:
The patent replaces conventional purely mechanical actuation systems with a hybrid electro-hydraulic system. Electric motors provide primary actuation force, while hydraulic components assist during high-load conditions. This substitution reduces the mechanical complexity and space requirements compared to traditional mechanical linkages and actuators.
2Reliability
If redundant control electronics are implemented, then continuous operation during failures is enabled, but system complexity increases
Solution Approach 1:
Each modular actuation unit contains its own dedicated control electronics and actuator, creating local redundancy. If one module fails, others continue operating independently. This distributed architecture provides fault tolerance without requiring a single complex centralized control system, as each local unit is relatively simple and self-contained.
Solution Approach 2:
The system incorporates redundant control electronics and multiple actuation paths before failures occur. Each module is designed with backup capabilities so that if one component fails, the system can seamlessly switch to alternative actuation paths, cushioning against the impact of failures and ensuring continuous operation.
3Adaptability or versatility
If hybrid hydraulic-electric actuators are used, then mode switching for continuous operation is enabled, but actuator complexity increases
Solution Approach 1:
The actuator design integrates both electric and hydraulic actuation capabilities within a single universal unit. The electric motor serves as the primary actuator for normal operations, while hydraulic components provide assist or alternative actuation during high-load or emergency conditions. This multi-functional design allows the same actuator to operate in multiple modes (electric-only, hydraulic-assist, hydraulic-only) without requiring separate actuator systems.
Solution Approach 2:
The actuator system dynamically switches between electric and hydraulic modes based on real-time operational requirements. Control electronics monitor load conditions, available hydraulic pressure, and system state to automatically select the optimal actuation mode. This dynamic adaptability allows the system to handle varying flight conditions efficiently while maintaining a relatively compact actuator design.
4Length of stationary object
If distributed actuation modules are implemented, then wing thickness is reduced, but manufacturing complexity increases
Solution Approach 1:
The actuation system is manufactured as separate modular units that can be produced independently using standardized processes. Each module contains integrated electric and hydraulic components assembled in a compact configuration. This segmentation allows parallel manufacturing of multiple identical modules, reducing overall manufacturing complexity compared to building a single large centralized actuation system.
Solution Approach 2:
The actuator design nests hydraulic components within or alongside electric motor assemblies, creating compact integrated modules. The hydraulic reservoir, pumps, and control valves are arranged to fit within the space envelope of the electric actuator housing. This nesting approach minimizes the overall volume of each module, enabling thinner wing design while keeping manufacturing processes manageable through modular assembly.
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 the construction of thinner, lighter, and more efficient wings with improved fault tolerance, allowing continuous operation even if components fail, reducing installation time and overall aircraft weight.
Implementation Method 1
a hydraulic powered actuator coupled to the crank arm. The hydraulic powered actuator is to rotate the crank arm when activated
Implementation Method 2
an electric powered actuator coupled to the crank arm. The electric powered actuator is to rotate the crank arm when activated
Data Source
AI summary
Distributed trailing edge actuation systems and methods for aircraft are described herein. An example aircraft includes a wing, a flap coupled to the wing, the flap movable between a stowed position and a deployed position, and a distributed trailing edge (DTE) actuation system including a flap actuator coupled to the wing to move the flap. The flap actuator includes an integrated hydraulic powered actuator and electric powered actuator. The flap actuator is operable in a hydraulic powered mode in which the hydraulic powered actuator is activated to move the flap, an electric powered mode in which the electric powered actuator is activated to move the flap, and a hybrid mode in which the hydraulic powered actuator and the electric powered actuator are activated simultaneously to move the flap.