Aircraft Electromechanical Drive With Two-Way Torque Transmission
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Solution Overview
Problem
Existing aircraft control systems are bulky, heavy, and costly due to the inclusion of numerous units and active elements, leading to increased weight, electrical consumption, and heat dissipation, necessitating a reduction in components to enhance efficiency and reduce production and maintenance costs.
Innovation Solution
An electromechanical drive system with a two-way transmission and clutch assembly that allows torque transmission in both directions, incorporating a decoupling mechanism to manage reversibility load without additional active elements, and adjustable braking torque for pilot feedback, reducing the need for trim actuators and integrated systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If integrated control systems with additional active elements (actuators, solenoids) are used to perform manual and autopilot control, then control functionality is improved, but weight and electrical consumption increase
Solution Approach 1:
The patent merges manual control and autopilot control functions into a single integrated system that uses the same actuator for both modes. The actuator can operate in different modes (manual with mechanical feedback, autopilot with electrical control) without requiring separate active elements for each function, thereby reducing weight while maintaining versatility
Solution Approach 2:
The actuator is designed as a universal component that can perform both manual control operations and autopilot control operations. By making the actuator multi-functional rather than having separate actuators for each mode, the system reduces the number of active elements needed, thus reducing weight and electrical consumption while maintaining full control functionality
2Adaptability or versatility
If multiple active elements (actuators, solenoids) are included in the control system, then control versatility is improved, but device complexity increases
Solution Approach 1:
The patent combines multiple control functions (manual and autopilot) into a single actuator system with a unified mechanical and electrical architecture. This merging eliminates the need for multiple separate actuators and solenoids, reducing device complexity while preserving control versatility through mode-switching capability
Solution Approach 2:
The actuator is designed as a universal component that can perform both manual control operations and autopilot control operations. By making the actuator multi-functional rather than having separate actuators for each mode, the system reduces the number of active elements needed, thus reducing weight and electrical consumption while maintaining full control functionality
3Adaptability or versatility
If additional integrated electronics are added to enable mode switching between manual and autopilot control, then control adaptability is improved, but manufacturing and maintenance costs increase
Solution Approach 1:
The patent merges the control functions and electronics into a more integrated architecture where the same actuator serves both manual and autopilot modes. This reduces the total number of electronic control units needed, simplifying manufacturing and maintenance while maintaining mode switching capability through a streamlined electronic system
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
The system optimizes aircraft control by minimizing components and costs while maintaining operational efficiency and versatility, reducing weight and electrical consumption, and providing adjustable pilot feedback.
Implementation Method 1
an electric machine 3, such as an electric motor, configured to at least operate in an operating state in which it transforms electric energy in order to drag in rotation the transmission shaft 2
Implementation Method 2
a clutch assembly 9 configured to allow the transmission of a torque from the transmission assembly 7 to the transmission shaft 2
Data Source
AI summary
Electromechanical drive system (1) to control a transmission shaft (2) connected to the mechanical operating systems of an aircraft, comprising an electric machine (3), a two-way transmission rotation (8) and a clutch assembly (9) wherein the two-way transmission rotation (8) is configured, in any direction of rotation of the transmission shaft (2), to selectively allow the passage of torque either only between the electric machine (3) and the transmission shaft (2) when the torque is supplied by the electric machine (3) to the transmission shaft (2) or between the transmission shaft (2), the clutch assembly (9) and the electric machine (3) when the torque is supplied by the transmission shaft (2) to the electric machine (3).