Electric Actuator Release Mechanism for Aircraft Rudder Jamming
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Solution Overview
Problem
Existing electric actuator devices for aircraft rudder surfaces with ball screw mechanisms face mechanical jamming issues, leading to unintended rudder position fixation, which complicates aircraft control and increases weight due to the need for multiple components and a complex structure.
Innovation Solution
An electric actuator device with a simple structure featuring a support member that advances and retracts to release mechanical connection between the rudder surface and aircraft body, utilizing a holding member to prevent components from falling and a control unit to detect failures and initiate release, allowing for easy disengagement of the rudder surface from mechanical restraint.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If a ball screw mechanism is adopted in the electric actuator, then the actuator becomes lighter and has higher output, but mechanical jamming occurs where the ball nut is fixed on the rotating screw
Solution Approach 1:
The release mechanism is activated in advance to separate the ball nut from the screw shaft before mechanical jamming can occur or to release it when jamming is detected. The control unit monitors the operation state and triggers the release mechanism proactively, preventing the harmful effect of mechanical jamming while maintaining the lightweight ball screw mechanism.
2Reliability
If two systems of ball screw mechanisms with independent motors and clutch mechanisms are adopted to prevent mechanical jamming, then reliability improves, but device complexity and weight increase significantly
Solution Approach 1:
Instead of duplicating the entire ball screw mechanism system, the invention extracts only the essential release function by providing a separate release mechanism that can detach the ball nut from the screw shaft. This simplified approach achieves the same reliability benefit without the complexity and weight of dual systems, motors, and clutch mechanisms.
Solution Approach 2:
The release mechanism serves multiple functions: it can release the ball nut during normal operation for maintenance, automatically release during mechanical jamming, and provide emergency release capability. This multi-functional design replaces the need for complex dual systems while maintaining reliability.
3Reliability
If a release mechanism is added to separate the ball nut from the screw shaft, then mechanical jamming can be released, but device complexity increases
Solution Approach 1:
The release mechanism is integrated with the existing actuator structure, combining the release function with the housing or support components. The release groove and release pin are incorporated into the existing mechanical framework, adding minimal components while achieving the jamming release function.
Solution Approach 2:
A release pin or release groove acts as an intermediary element between the ball nut and screw shaft, enabling easy separation when needed. This simple intermediary component provides the release function without requiring complex mechanisms or multiple parts.
Data Source
AI summary
An electric actuator device is provided with: an electric actuator body that has a first fulcrum connected to a rudder surface side of an aircraft and a second fulcrum connected to the aircraft body side, and is driven by an electric motor such that the first fulcrum and the second fulcrum can be brought closer together and drawn further apart; a support member for advancing/retracting between a support position at which the support member supports the first fulcrum or the second fulcrum thereunder, and a retracted position at which the support member is retracted from under the first fulcrum or the second fulcrum; and a retention member for retaining the first fulcrum or the second fulcrum when the support member is located in the retracted position.