Aircraft Electric Braking LRU Integration
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Solution Overview
Problem
Current electrically actuated aircraft braking systems face reliability issues due to the potential for simultaneous failure of electro-mechanical actuator controllers (EMACs), leading to partial or full loss of braking control, and are complex and costly to maintain.
Innovation Solution
The integration of an electro-mechanical brake actuator (EMAbrake), an electro-mechanical actuator controller (EMAC), and a braking control unit within a common line replaceable unit (LRU) reduces wiring complexity, enhances reliability, and provides weight and cost savings by incorporating redundant motor controllers for normal and emergency modes, including anti-skid control functionality.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If EMACs are distributed separately to minimize common mode failures, then system reliability improves, but device complexity and wiring complexity increase
Solution Approach 1:
The patent combines the EMAC and BCU into a single integrated unit, merging previously separate components. This integration reduces wiring complexity while maintaining reliability through internal redundancy architecture, directly resolving the contradiction between distributed reliability and wiring complexity
2Reliability
If redundant BCUs are provided for fault tolerance, then system reliability improves, but device complexity and maintenance cost increase
Solution Approach 1:
The patent segments the braking control system into modular LRUs that can be independently replaced. Each LRU contains integrated EMAC and BCU functionality with internal redundancy, allowing fault isolation and simplified maintenance while maintaining overall system reliability
3Ease of manufacture
If EMACs are made identical for part commonality, then manufacturing cost decreases, but simultaneous failure risk increases
Solution Approach 1:
The patent implements local quality by providing dissimilar redundant controllers within each LRU while maintaining identical LRU designs across the system. This allows part commonality for manufacturing efficiency while ensuring reliability through architectural diversity at the controller level
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 configuration enhances the reliability and reduces the complexity and cost of the braking system, providing effective braking control even in emergency situations by minimizing the risk of common mode failures and simplifying maintenance through digital communication and redundant channels.
Implementation Method 1
the EMAbrake including a motor
Data Source
Figure 1
Figure 2
Figure 3~4
AI summary
An electrically actuated braking system for an aircraft, comprising: an electro-mechanical brake actuator (EMAbrake) proximate a wheel of the aircraft, the EMAbrake including a motor; an electro-mechanical actuator controller (EMAC) including a motor controller for generating a drive signal for the EMAbrake; and a braking control unit for generating a braking force command signal for the EMAC; wherein the braking control unit and the EMAC are disposed together with the EMAbrake in a common line replaceable unit (LRU).