Aircraft Brake Yaw Compensation Using Pilot Intent Feedback
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Solution Overview
Problem
Aircraft braking systems face challenges in reducing unintended yaw during landing and braking, particularly in 'brake-by-wire' systems, which increases pilot workload and safety risks due to increased aerodynamic lift, reduced drag, and weight savings efforts, leading to sensitivity in braking torque and controllability issues.
Innovation Solution
A yaw reduction system and method that differentiates between intentional and unintentional yaw by employing sensors like the inertial reference unit (IRU) and feedback mechanisms to adjust wheel braking, integrating with existing brake control systems to provide active yaw control, reducing unwanted yaw and accommodating intentional differential braking for steering.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If ground spoilers are reduced or eliminated to save weight and reduce drag, then fuel efficiency is improved, but braking system yaw sensitivity increases and controllability deteriorates
Solution Approach 1:
The patent implements a feedback control system that continuously monitors aircraft yaw rate during braking and automatically adjusts brake torque distribution between left and right wheels. The control system processes yaw rate signals and generates compensating differential brake commands to counteract unintended yaw, thereby maintaining controllability despite the removal of ground spoilers.
Solution Approach 2:
The patent replaces the mechanical/aerodynamic yaw control function of ground spoilers with an electronic control system that uses sensors (inertial reference unit, yaw rate sensors) and electronic brake control. This substitution eliminates the need for heavy mechanical ground spoiler systems while providing precise electronic yaw management during braking.
2Use of energy by moving object
If thrust reversers are eliminated to save weight, then fuel efficiency is improved, but braking effectiveness deteriorates and yaw sensitivity increases
Solution Approach 1:
The patent replaces the mechanical thrust reverser system with an electronic brake control system that provides equivalent or superior deceleration performance. The electronic control system manages brake torque distribution to achieve effective stopping without the yaw-inducing effects of asymmetric thrust reversal, thereby maintaining reliability while eliminating heavy mechanical components.
Solution Approach 2:
The patent dynamically adjusts brake torque parameters based on aircraft speed, weight, and desired deceleration rate. The control system modulates brake pressure and torque distribution in real-time to optimize braking effectiveness across different flight conditions, replacing the fixed mechanical thrust reverser system with adaptive electronic control.
3Use of energy by moving object
If brake wear material is reduced to save weight, then fuel efficiency is improved, but controllability deteriorates
Solution Approach 1:
The patent implements feedback control that monitors brake performance and aircraft response to automatically adjust brake torque distribution. This electronic control compensates for the reduced mechanical advantage from lighter brake materials, maintaining precise controllability despite using less wear material and reducing overall brake system weight.
4Use of energy by moving object
If mechanical and hydraulic components are reduced to save weight, then fuel efficiency is improved, but system complexity in electrical controls increases
Solution Approach 1:
The patent implements a multi-functional electronic control system that performs multiple tasks: monitoring yaw rate, determining pilot intent, calculating compensating brake commands, and actuating brakes. This universal control architecture consolidates what would otherwise require separate systems, reducing overall complexity despite the transition from mechanical to electrical controls.
Solution Approach 2:
The control system automatically determines pilot intent by analyzing brake pedal inputs and aircraft state, then self-adjusts brake torque distribution without requiring additional pilot inputs or complex mechanical linkages. The system serves itself by using sensor data and algorithms to autonomously manage yaw control, simplifying the interface while maintaining sophisticated control capabilities.
Data Source
AI summary
An aircraft brake control system accommodates desired yaw for steering, while substantially eliminating undesired yaw. The system assesses brake command signals from the pilot, signals corresponding to aircraft parameters, and signals based on brake control parameters, and determines therefrom an amount of yaw desired by the pilot. The instantaneous yaw rate is monitored and compared to the desired yaw rate. An error signal corresponding to the difference between instantaneous and actual yaw rates is calculated and that error signal is employed to modify a braking differential between right and left brakes to eliminate or substantially reduce the undesired yaw.