Aircraft Thrust Reverser Actuator Integration
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Solution Overview
Problem
The complexity and reliability issues of existing electric thrust reverser systems for aircraft engines, particularly due to the multitude of actuators and safety redundancy requirements, necessitate a simplification while maintaining safety standards.
Innovation Solution
An electric thrust reverser system architecture that integrates a primary lock into the drive cylinder, utilizing a 'lost motion' mechanism, and implements a three-line defense system with mechanical, electronic, and electrical redundancies, including a tertiary lock, to enhance reliability and safety without additional calculators.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple actuators and locking mechanisms are used to ensure safety redundancy, then reliability is improved, but device complexity increases
Solution Approach 1:
The patent integrates the primary locking mechanism directly into the actuator assembly, combining two previously separate systems (actuator and lock) into a single integrated unit. This reduces the total number of discrete components while maintaining the required safety redundancy through the integrated design, thereby improving reliability without proportionally increasing complexity
Solution Approach 2:
The integrated actuator-assembly serves multiple functions simultaneously: it provides both the actuation motion and the primary locking function. This multi-functionality reduces the need for separate dedicated locking mechanisms, simplifying the overall system architecture while maintaining reliability through the combined functionality
2Reliability
If redundancy organs are added to comply with safety standards, then safety is improved, but device complexity increases
Solution Approach 1:
The patent combines the primary lock with the actuator to form an integrated assembly, reducing the number of separate organs while maintaining safety redundancy. The integration allows the system to meet safety standards through the combined functionality rather than through multiplication of separate components
Solution Approach 2:
The patent segments the locking function into hierarchical levels (primary lock integrated in actuator, secondary lock, and tertiary lock), where each level provides a specific layer of safety redundancy. This segmentation allows compliance with safety standards while avoiding unnecessary multiplication of organs by assigning specific roles to each locking level
Data Source
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AI summary
An electric thrust reverser system for an aircraft engine nacelle and an aircraft engine nacelle provided with same. The invention concerns an electric thrust reverser system for an aircraft engine nacelle, comprising at least one mechanism (2 or 3) for actuating a thrust reverser mechanism like a reverser door. The actuating mechanism (2 or 3) comprises first (6) and second (7) drive cylinders. Each cylinder comprises a mechanical connection casing (9), a primary lock (8) and a mobile rod (10) rigidly connected to a point linked to the associated reverser mechanism, like a reverser door. A motorised drive unit (11) is connected mechanically by flexible shafts (12) to the mechanical connection casings (9) of each cylinder (6, 7) of the actuating mechanism (2 or 3) and set in motion under the control of a control unit (1) by means of an electrical connection (16, 17). A tertiary lock (13) is disposed to secure the associated thrust reverser mechanism like a thrust reverser door to a fixed structure of the nacelle.