More Electric Flight Control System with Local Electro-Hydraulic Generation
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Solution Overview
Problem
Current flight control systems face challenges with thermal transfer issues due to carbon structures, increased system mass, complex installation and maintenance of hydraulic systems, reduced reliability due to thermal constraints and mechanical stresses on power electronics, and higher risks of seizure in electro-mechanical actuators.
Innovation Solution
A more electric flight control system utilizing local electro-hydraulic generation to power hydraulic servocontrols, featuring induction motors powered by fixed frequency AC voltage, reducing the need for power electronics and integrating power electronics into a single module for improved reliability and maintenance accessibility.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If electro-hydrostatic actuators (EHA) with independent hydraulic systems are used, then thermal management is improved, but device complexity increases
Solution Approach 1:
The patent merges multiple independent hydraulic systems into a single centralized hydraulic system that serves all flight control actuators. Instead of each actuator having its own independent hydraulic pump and fluid system (as in EHA), the invention uses one centralized hydraulic source that distributes pressurized fluid to multiple actuators through a network of pipes and manifolds. This consolidation reduces the number of hydraulic pumps from multiple to one, eliminates redundant hydraulic fluid volumes, and simplifies the overall system architecture while maintaining effective thermal management through the centralized hydraulic fluid circulation.
2Reliability
If local electro-hydraulic generation with power electronics is used, then system reliability is improved, but manufacturing complexity increases
Solution Approach 1:
The patent extracts and removes power electronics from the distributed actuator-level systems and consolidates them into a single centralized power electronic system at the hydraulic source. Instead of each actuator requiring its own power electronic converter to drive an electric motor and pump, the invention uses one centralized power electronic system that drives a single hydraulic pump. This extraction simplifies manufacturing by reducing the total number of power electronic components from multiple distributed units to one centralized unit, while maintaining system reliability through centralized control and monitoring capabilities.
3Ease of operation
If electro-mechanical actuators are used, then electrical control is improved, but seizure risk increases
Solution Approach 1:
The patent replaces electro-mechanical actuators that use electric motors and mechanical linkages with hydraulic actuators that use fluid pressure directly. Instead of converting electrical energy to mechanical rotation and then to linear motion through complex mechanical mechanisms (which are prone to seizure), the invention uses hydraulic fluid pressure to directly actuate the control surfaces. This substitution eliminates the mechanical components (gears, belts, linkages) that are susceptible to seizure, while maintaining precise electrical control through electronic control of the centralized hydraulic system's valve and flow control.
4Reliability
If multiple independent hydraulic circuits are used, then system reliability is improved, but system mass increases
Solution Approach 1:
The patent combines multiple independent hydraulic circuits into a single centralized hydraulic system that serves all flight control functions. Instead of having separate hydraulic pumps, fluid reservoirs, and control systems for each flight control surface (ailerons, elevators, rudders, spoilers), the invention uses one centralized hydraulic system with a single pump and fluid source that distributes pressurized hydraulic fluid to all actuators through a shared network. This merging reduces the total mass of hydraulic components (pumps, reservoirs, hoses) compared to multiple independent systems, while maintaining system reliability through centralized monitoring and the ability to isolate individual actuators if 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 reduces power electronic failures, simplifies maintenance, optimizes costs, and enhances system reliability by eliminating the need for additional cooling devices and electro-hydrostatic actuators, while minimizing hydraulic pipe lengths and improving integration with the aircraft structure.
Implementation Method 1
an induction motor powered by a fixed frequency AC voltage with a constant rms value so as to operate at a constant speed
Data Source
AI summary
An electric flight control system onboard an aircraft provided with flight control surfaces and controllers for controlling these surfaces, that include at least one local electro-hydraulic generator to supply hydraulic servocontrols connected to flight control surfaces.