Aircraft Electric Brake Control Architecture via Digital Bus
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Solution Overview
Problem
Aircraft braking systems face issues with weight, performance, and reliability in traditional cable and hydraulic connections, and there is a need for a redundant electric brake system that prevents inadvertent brake applications.
Innovation Solution
An electric brake system architecture with two or more electrical braking subsystems, each controlled by a brake system control unit and electric brake actuator controller, utilizing remote data concentrators and a digital data communication bus for independent brake activation, reducing weight and preventing error propagation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional cable or hydraulic connections are used for aircraft braking control, then the system structure is simple, but the system suffers from weight issues, performance limitations, and reliability problems
Solution Approach 1:
The braking control system is divided into multiple independent braking subsystems (first braking subsystem, second braking subsystem), each capable of independently controlling different wheel groups. This segmentation provides redundancy and reliability while maintaining manageable complexity through modular architecture.
Solution Approach 2:
A digital data communication bus is introduced as an intermediary between the braking subsystems and the landing gear wheel groups. This mediator enables reliable electrical control signals to be transmitted without direct mechanical or hydraulic connections, improving reliability while allowing complex control logic to be managed through standardized communication protocols.
2Reliability
If electric brake systems are implemented to improve reliability and performance, then braking performance and reliability are improved, but the system complexity increases
Solution Approach 1:
The electrical brake system is segmented into multiple independent braking subsystems with separate control units and actuator controllers. Each subsystem can operate independently to provide redundancy, improving reliability while keeping individual subsystem complexity manageable.
Solution Approach 2:
The digital data communication bus serves multiple functions: transmitting brake control signals, wheel data, and status information between various subsystems. This multi-functional communication infrastructure reduces overall system complexity by consolidating multiple communication channels into a single standardized bus system.
3Reliability
If redundant braking subsystems are implemented to prevent inadvertent brake applications, then safety and reliability are improved, but system weight increases
Solution Approach 1:
Traditional mechanical cable connections and hydraulic systems are replaced with electrical control systems that communicate through a digital data bus. This substitution eliminates heavy mechanical linkages and fluid systems while providing equivalent or superior control reliability through electronic redundancy.
4Reliability
If independent brake activation of wheel groups is implemented through digital communication bus, then error propagation between subsystems is prevented, but system complexity increases
Solution Approach 1:
The control architecture is segmented into independent braking subsystems that can operate autonomously. Each subsystem has its own control unit and actuator controller, preventing errors in one subsystem from propagating to others. This modular segmentation isolates potential failures while maintaining overall system reliability.
Solution Approach 2:
The digital data communication bus enables bidirectional communication between braking subsystems and landing gear wheel groups, allowing each subsystem to receive feedback about wheel status and adjust control accordingly. This feedback mechanism ensures independent error handling while maintaining coordinated braking performance across all wheel groups.
Data Source
AI summary
An electric brake system architecture for an aircraft with two or more electrical braking subsystems including brake system controls configured to communicate pilot pedal commands to electric brake actuator controllers that apply or release brakes in wheel groups. The system allows independent brake activation of wheel groups through a plurality of brake system controls and electric brake actuator controllers. The electric braking system further includes remote data consolidators to collect and transmit wheel data to brake system controls through a digital data communication bus. The system reduces aircraft weight, prevents inadvertent braking, and prevents error propagation between subsystems.