Actuating Device Locking Latches for Thrust Reverser Safety
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Solution Overview
Problem
Propulsion systems for aircraft are bulkier due to the need for separate actuation devices for thrust reversal and airflow regulation systems, which increases equipment size and complexity.
Innovation Solution
A single actuation device with a locking mechanism that allows selective actuation of both thrust reversal and airflow regulation systems by varying its deployment range, using a shaft, nut, and electromagnetically controlled locking latches to prevent untimely deployment of the thrust reversal system during flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate actuation devices are used for thrust reversal and airflow regulation systems, then reliability and safety are improved, but device complexity and bulkiness increase
Solution Approach 1:
The patent combines two separate actuation devices into a single integrated actuation device that can control both the thrust reversal system and airflow regulation system. The single device includes a motor, reduction gear, and actuation tube that can selectively actuate either system based on operational requirements, thereby reducing equipment bulkiness while maintaining functional separation and safety through controlled deployment ranges and locking mechanisms
Solution Approach 2:
The integrated actuation device is designed with multi-functionality to perform both thrust reversal actuation and airflow regulation actuation. It includes a first actuation range for airflow regulation and a second actuation range for thrust reversal, allowing one device to replace two separate devices while maintaining the reliability benefits of dedicated actuation for each system
2Device complexity
If a single actuation device is used for both systems, then device complexity is reduced, but the risk of untimely deployment increases
Solution Approach 1:
The actuation device incorporates dynamic control through a locking mechanism that can selectively lock or unlock the actuation tube based on the desired operational range. The locking device includes a locking latch that can be positioned to allow movement within the first actuation range (airflow regulation) while preventing movement into the second actuation range (thrust reversal), thereby dynamically controlling deployment safety based on operational requirements
Solution Approach 2:
The locking mechanism is designed to preemptively prevent unauthorized deployment into the thrust reversal range. Before the actuation tube can accidentally enter the second actuation range, the locking latch blocks this path, ensuring that thrust reversal can only occur when intentionally commanded through proper actuation sequences, thus preventing untimely deployment
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 solution reduces equipment bulkiness by integrating actuation for both systems, preventing untimely deployment of the thrust reversal system and optimizing fuel consumption through efficient airflow regulation.
Implementation Method 1
The locking device comprises an electromagnet, the electromagnet being able to be powered for driving the ring into rotation
Data Source
AI summary
The invention relates to an actuating device comprising: —a first element (7), —a second element (8) able to move translationally with respect to the first element (7), and —a locking device (6) comprising a catch (18, 20) able to move between a deployed position and a retracted position, the catch (18-20) being positioned with respect to the first element (7) in such a way that when the catch (18-20) is in a deployed position, the catch (18-20) allows the second element (8) to move with respect to the first element (7) in a first range of movement (A) and prevents the second element (8) from moving with respect to the first element (7) in a second range of movement (B), and when the catch (18-20) is in the retracted position, the catch (18-20) allows the second element to move with respect to the first element (7) in the second range of movement (B). This device is particularly suited to allowing actuation of a thrust reverser system and of a system that regulates air flow through an aircraft propulsion unit.