Distributed Electromechanical Actuation System for Aircraft Flight Control Surfaces
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Solution Overview
Problem
Modern thin wing aircraft designs face challenges in routing mechanical drive shafts due to increased congestion along the spars, making traditional actuator and torque tube systems difficult to manage effectively.
Innovation Solution
A distributed electromechanical actuation system using multiple electromechanical actuators powered by induction motors or similar, controlled via a common bus with Volts per Hertz open loop control, ensuring synchronous or near synchronous operation and eliminating the need for torque tubes and multiple motor controllers.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional mechanical drive shafts (torque tubes) are used to connect central power drive units to actuators, then synchronous operation of multiple actuators can be achieved, but the system becomes increasingly difficult to manage and route due to wing spar congestion
Solution Approach 1:
The patent divides the actuation system into distributed electromechanical actuators, each with its own motor and control electronics, eliminating the need for centralized torque tubes. Each actuator is independently controlled through a common electrical bus, allowing synchronization without mechanical linkages across the wing structure.
Solution Approach 2:
The patent replaces the mechanical torque tube system with an electrical control system. Instead of transmitting mechanical power through physical shafts, the system uses electrical signals over a common bus to control multiple electromechanical actuators, thereby eliminating routing complexity while maintaining synchronous operation.
2Ease of operation
If multiple independent motor controllers are used for each actuator, then precise individual control is achieved, but the system complexity and number of components increases
Solution Approach 1:
The patent merges multiple individual motor controllers into a single controller that manages all electromechanical actuators. This single controller communicates with each actuator over a common electrical bus, reducing the total number of controllers while maintaining the ability to individually address and control each actuator through software-based control strategies.
3Force
If induction motors with high pullout torque and low slippage are used, then torque capability is improved, but the motors operate near the pullout point where synchronization becomes more difficult
Solution Approach 1:
The patent implements a control system that monitors the operational status of each induction motor and adjusts control signals accordingly. By using feedback from motor performance data, the single controller can compensate for slip variations and maintain synchronous operation even when motors operate near their pullout torque point, thereby resolving the conflict between torque capability and synchronization accuracy.
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 allows for efficient and synchronized control of aircraft flight control surfaces, optimizing fuel economy by reducing the complexity and congestion associated with traditional actuator systems, while maintaining low slip and high torque capabilities across varying loads.
Implementation Method 1
Each individual actuator is powered by one or more induction motors or other appropriate motor such as a stepper, switched reluctance, or other type of motor
Data Source
AI summary
A distributed electromechanical actuation system including multiple electromechanical actuators intended to operate together in a synchronous (or near synchronous) manner. Each individual actuator is powered by one or more induction motors or other appropriate motor such as a stepper motor. The induction motors are designed to have a very high pullout torque with very low slippage to the pull out point. The group of actuators is controlled from a single controller (e.g., an induction motor controller) that utilizes a Volts per Hertz type of open loop control where the bus voltage and frequency are controlled to assure that the motors always operate on the low slip side of the pull out point performance curve.