Electro-mechanically biased actuator for flight control surface loading
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Solution Overview
Problem
Existing aircraft flight control systems face challenges with high-pressure hydraulic cycles, which complicate design and increase energy consumption, particularly at high speeds, due to the need for high-pressure hydraulic fluid to operate flight control members.
Innovation Solution
An actuator assembly comprising a support strut, a hydraulic actuator, and an electro-mechanical actuator (EMA) with a biasing member that moves between compressed and expanded states in response to varying biasing loads, reducing the need for high-pressure hydraulic cycles and current consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If high-pressure hydraulic fluid is used to operate flight control members at high speeds, then the flight control members can be effectively actuated against high aerodynamic loads, but the hydraulic system complexity and energy consumption increase
Solution Approach 1:
The patent replaces the traditional hydraulic actuation system with an electro-mechanical actuator (EMA) that uses electrical motors and mechanical components to drive the flight control members. This substitution eliminates the need for high-pressure hydraulic systems while maintaining the ability to overcome high aerodynamic loads, thereby reducing system complexity and energy consumption.
Solution Approach 2:
The patent changes the operating parameters of the actuation system by transitioning from high-pressure hydraulic operation to electro-mechanical operation with variable speed motors. This allows the system to adapt to different flight conditions without requiring high-pressure hydraulic infrastructure, reducing both complexity and energy requirements while maintaining adequate force output.
2Force
If high-pressure hydraulic cycles are used to control flight control members, then adequate force is provided to overcome aerodynamic loads, but energy consumption and heat generation increase
Solution Approach 1:
The patent substitutes the energy-intensive high-pressure hydraulic system with an electro-mechanical actuator that uses electrical energy more efficiently. The EMA converts electrical energy directly to mechanical work without the energy losses associated with hydraulic pressure generation, fluid compression, and heat dissipation, thereby reducing overall energy consumption while maintaining adequate actuator force.
Solution Approach 2:
The patent employs variable speed motors in the electro-mechanical actuator that can dynamically adjust their operating speed and torque output to match the actual aerodynamic loads on the flight control members. This dynamic adaptation allows the system to use only the necessary energy at any given moment, avoiding the continuous high-energy operation required by fixed high-pressure hydraulic systems.
3Stress or pressure
If new or additional features are incorporated in hydraulic valves to handle high-pressure gain operations, then high-pressure operation capability is improved, but device complexity increases
Solution Approach 1:
The patent eliminates the hydraulic valve system entirely by replacing it with an electro-mechanical actuator that uses electrical control to drive the flight control members. This substitution removes the need for complex high-pressure hydraulic valves and their associated features, significantly reducing valve complexity while maintaining the capability to operate against high aerodynamic loads through direct mechanical actuation.
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 the number of high-pressure hydraulic cycles and current required to drive the EMA, enhancing system efficiency and reliability by allowing a distributed hydraulic system to operate at lower pressures, thereby reducing energy consumption and heat generation.
Implementation Method 1
a biasing member configured to move between a compressed state and an expanded state in response to a varying biasing load exerted on a surface of the flight control member
Data Source
AI summary
An actuator assembly for an aircraft includes a support strut operatively coupled to a hinge axis of a flight control member of the aircraft, a hydraulic actuator operatively coupled to the flight control member via a pivot element, and an electro-mechanical actuator (EMA) having first and second opposing ends and a biasing member. The first end is operatively coupled to a support structure of the aircraft, and the second end is operatively coupled to both the support strut and the hydraulic actuator. The biasing member moves between a compressed state and an expanded state in response to a varying biasing load exerted on a surface of the flight control member, thereby reducing an amount of current needed to drive the EMA, as well as a number of high-pressure hydraulic cycles of the hydraulic actuator to control the flight control member.