Variable Gain Nose Wheel Steering Control
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Solution Overview
Problem
Existing aircraft nose wheel steering systems lack a seamless relationship between aircraft speed and maximum steering angle, particularly during parking and taxiing, which can lead to instability and difficulty in controlling the aircraft.
Innovation Solution
A method and system that determine a target steering angle for the nose landing gear by calculating a normal gain and a parking gain based on rudder pedal input and aircraft speed, integrating these gains to provide a non-step relationship between speed and steering angle, ensuring optimal control across various conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a two-stage steering mode with different steering angles for the same pedal stroke is used, then the steering angle can be simplified for different conditions, but the relationship between aircraft speed and maximum steering angle becomes discontinuous and non-seamless
Solution Approach 1:
The patent applies dynamics by making the steering gain continuously variable based on aircraft speed rather than using fixed two-stage modes. The normal gain and parking gain are dynamically adjusted according to the actual speed, creating a seamless transition between different steering requirements at different speeds.
Solution Approach 2:
The patent changes the parameter of steering gain from discrete values in two-stage modes to continuous values that vary with aircraft speed. By calculating normal gain and parking gain as continuous functions of speed, the system achieves a non-step relationship between speed and maximum steering angle, eliminating discontinuities.
2Device complexity
If a fixed steering angle for the same pedal stroke is used across different speeds, then the control system is simplified, but the aircraft becomes unstable during transitions between parking and taxiing speeds
Solution Approach 1:
The system uses dynamic gain adjustment based on real-time speed feedback to maintain stability during transitions. The normal gain and parking gain are continuously updated according to aircraft speed, ensuring smooth and stable steering control during speed transitions without requiring complex mechanical systems.
Solution Approach 2:
The patent implements feedback by continuously monitoring aircraft speed and adjusting the steering gain accordingly. The control system receives speed data, calculates the appropriate normal gain and parking gain based on the current speed, and applies the correct gain to maintain stable and predictable steering behavior across all speed ranges.
3Measurement precision
If separate normal gain and parking gain calculations are implemented, then precise control across different speed ranges is achieved, but the calculation complexity increases
Solution Approach 1:
The patent merges the normal gain and parking gain calculations into a unified control framework where both gains are calculated simultaneously based on the same speed input. The total steering angle is the sum of normal gain and parking gain components, allowing precise control while sharing common calculation resources and avoiding redundant computations.
Data Source
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AI summary
A method for determining a target steering angle for nose landing gear of an aircraft includes receiving rudder pedal input data into a steering control unit, receiving aircraft speed data into the steering control unit, calculating a normal gain, calculating a parking gain, and adding the normal gain and the parking gain to determine the target steering angle. The normal gain is a positive quantity in all aircraft speed and pedal stroke ranges. The parking gain is a positive quantity in parking and taxiing speed ranges. A nose wheel steering system is also disclosed.