Aircraft Brake Control Architecture Against Common Mode Failures
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing aircraft electrical brake systems face challenges in addressing common mode failures, which can lead to system downtime and increased mass due to redundant emergency equipment.
Innovation Solution
The proposed aircraft brake system incorporates a dual control device configuration with dissimilar hardware and software modules. Each control device has a primary and secondary software module, where the secondary module is simpler and designed to take over in case of primary module failure, without adding mass to the aircraft.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If dissimilar emergency equipment is implemented to avoid common mode failures, then system reliability is improved, but aircraft mass increases
Solution Approach 1:
The control software is segmented into multiple independent modules (first control software module, second control software module, third control software module, fourth control software module) with different functional responsibilities. This segmentation allows the system to maintain reliability through software redundancy without requiring additional hardware mass.
Solution Approach 2:
The patent implements software copying by creating multiple control software modules that replicate essential braking control functions. The second and fourth software modules serve as redundant copies that can take over when the primary modules fail, providing reliability without physical duplication of hardware components.
2Duration of action of stationary object
If redundant emergency equipment is added to the brake system, then system durability is improved, but device complexity increases
Solution Approach 1:
The dissimilar control devices share universal interfaces and communication protocols, allowing them to perform multiple functions. Each device can operate in both normal and emergency modes, and the software modules are designed to be interchangeable, reducing overall system complexity despite the presence of redundancy.
Solution Approach 2:
The system dynamically switches between different software modules based on operational status. The control system can transition from primary to secondary software modules in real-time without requiring physical reconfiguration, maintaining durability while managing complexity through dynamic adaptability.
3Reliability
If dissimilar control devices with multiple software modules are used, then common mode failures are mitigated, but control system complexity increases
Solution Approach 1:
The patent employs asymmetric dissimilarity between control devices and software modules. The first and second control devices have different architectures, and each contains software modules with different functional allocations. This asymmetric design ensures that a fault in one module cannot propagate to identical modules, mitigating common mode failures while maintaining manageable complexity through deliberate differentiation.
Data Source
AI summary
An aircraft brake system comprising:a first group of at least one electromechanical actuator,a second group of at least one electromechanical actuator,a first control device with a first software module and a second software module, the second software module being configured to control the first group of at least one actuator at least in the event of a fault of the first software module,a second control device with a third software module and a fourth software module, the fourth software module being configured to control the second group of at least one actuator at least in the event of a fault of the third software module,wherein the first device module and the second control device are dissimilar.The invention also relates to an aircraft equipped with this system.