Emergency Autoland Braking With Force-Balanced Electromechanical Actuation
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Solution Overview
Problem
Existing emergency autoland braking systems for aircraft often require multiple actuators in the hydraulic system, which can complicate design and installation across different aircraft models, and fail to account for varying tire and runway conditions that affect equal braking force application.
Innovation Solution
An emergency autoland braking system using a single or dual electromechanical actuator system with a force equalizing mechanism via pulleys and cables, applying equal or differential braking forces to the rudder pedals, compatible with both open and closed loop control, and compatible with traditional hydraulic and electronic brake-by-wire systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple actuators are used in the hydraulic system for emergency autoland braking, then braking force control is improved, but design complexity and installation difficulty increase
Solution Approach 1:
The patent combines multiple actuator functions into a single integrated electromechanical actuator that can apply differential braking force to the left and right rudder pedals. This single actuator replaces what would traditionally require multiple hydraulic actuators, thereby reducing design complexity while maintaining reliable braking force control through electronic control mechanisms.
Solution Approach 2:
The patent replaces traditional hydraulic actuators with an electromechanical actuator system. This substitution eliminates the need for complex hydraulic piping and multiple hydraulic actuators, reducing overall system complexity while providing precise control over braking force application to each brake pedal through electronic control.
2Reliability
If traditional hydraulic actuators are used for braking, then braking force application is reliable, but adaptability to varying tire and runway conditions is insufficient
Solution Approach 1:
The electromechanical actuator system incorporates feedback control mechanisms that monitor braking conditions and adjust braking force application in real-time. This feedback capability enables the system to adapt to varying tire and runway conditions while maintaining reliable braking force application, as the control system can dynamically adjust based on sensor input regarding wheel speed, runway conditions, and aircraft state.
Solution Approach 2:
The patent implements a dynamic braking control system where the electromechanical actuator can vary braking force application based on real-time operating conditions. The system transitions from static hydraulic braking to dynamic electronic control, allowing continuous adjustment of braking force to accommodate changing tire and runway conditions while maintaining reliable braking performance.
3Device complexity
If a single actuator system is used with force equalizing mechanism, then device complexity is reduced, but precision in applying equal braking force to both brake arms may be compromised
Solution Approach 1:
The patent replaces mechanical force equalization mechanisms with electronic control precision. Instead of relying on mechanical linkages and pulleys to equalize force, the electromechanical actuator uses electronic control to precisely apply equal or differential braking force to each brake pedal, achieving higher manufacturing precision while maintaining reduced device complexity.
Solution Approach 2:
The system changes the control parameter from mechanical force transmission to electronic control signals. By controlling the electromechanical actuator through electronic parameters rather than mechanical linkages, the system achieves precise control over braking force equality to both brake arms while maintaining a simpler single-actuator architecture.
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
The system ensures consistent braking force application across different aircraft models, accommodating varying conditions, while maintaining compatibility with existing braking systems and pilot operation, and providing safe and efficient deceleration.
Implementation Method 1
a linear actuator operatively coupled to the pulley for adjusting a position of the pulley, wherein actuation of the linear actuator applies equal tension to the first and second ends of the cable via the pulley
Implementation Method 2
a first cam operatively coupled to the first end of the cable, wherein the first cam is configured to rotate via pulling of the cable thereby actuating a left brake arm
Data Source
AI summary
An emergency autoland braking system for aircraft includes an electromechanical actuator configured to provide a braking force to rudder pedals for actuating a braking system without altering the existing braking system of the aircraft. An equalized braking force may be applied to both rudder pedals via a force balancing mechanism and a single linear actuator, or differential braking force may be applied via independent linear actuators. The system is compatible with both open and closed loop control for commanding a braking force.