Aircraft Electronic Brake Control System Emergency Overdrive
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Solution Overview
Problem
Conventional aircraft braking systems often compromise between stopping distance and component longevity, with a need for a system that can achieve a short stopping distance without causing damage to braking system components.
Innovation Solution
An electronic brake control system that includes a brake control unit capable of deriving output commands from pilot inputs to apply a high, emergency-level braking force by placing electromechanical brake actuators into an overdrive condition, allowing for a short stopping distance while accepting potential component destruction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of time
If conventional braking systems are used to achieve short stopping distance, then stopping distance is reduced, but brake components may be damaged or destroyed
Solution Approach 1:
The brake control system dynamically switches between normal braking mode and emergency maximum braking mode based on detected conditions. In emergency mode, the system places electromechanical brake actuators into an overdrive condition, dynamically changing their operational characteristics to achieve maximum braking force despite potential component destruction
Solution Approach 2:
The system changes the operational parameters of the brake actuators by applying voltages that exceed normal operating ranges. The brake control unit derives output commands that place actuators in an overdrive condition, changing electrical and mechanical parameters to achieve emergency braking performance
2Force
If high emergency-level braking force is applied to achieve short stopping distance, then stopping distance is reduced, but brake components may be destroyed
Solution Approach 1:
The system applies excessive braking force beyond normal operational limits by placing actuators in an overdrive condition. This partial or excessive action is intentionally used in emergency situations where maximum braking force is required, accepting that some component damage may occur
Solution Approach 2:
The system accepts that brake components may be destroyed during emergency maximum braking and are designed to be replaceable. The focus is on preserving the aircraft and occupants, with the understanding that brake components may need replacement after such events
Data Source
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AI summary
Systems and methods for reducing the speed of an aircraft (100) are disclosed herein. An electronic brake control system (200) may include a first braked wheel (132,134) of a landing gear system, a brake pedal (161,16r) electronically coupled to the first braked wheel (132,134), and a first actuator (26). The first actuator (26) may be configured to deliver a scalable clamping force on the first braked (132,134) wheel via a brake stack (31). The first actuator (26) may be configured to deliver an emergency maximum clamping force on the first braked wheel (132,134) in response to the electronic brake control unit (210) being in an emergency condition braking mode and a signal being received proportional to the brake pedal displacement. The emergency maximum clamping force results in the first actuator (26) being driven in an overdriven state.