Aircraft Landing Gear Steering Angle Detection Using Lidar Centroids
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Solution Overview
Problem
Existing methods for determining the steering angle of an aircraft landing gear are intrusive and computationally intensive, leading to latency and reduced accuracy.
Innovation Solution
A computer-implemented method using an imaging device to obtain position data points, calculate a centroid, and determine the steering angle through an intersection angle, minimizing sensor intrusion and computation by employing techniques like clustering and using a lidar device for precise data acquisition.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional intrusive sensors are used to measure steering angle, then measurement reliability is improved, but device complexity and intrusiveness increase
Solution Approach 1:
The patent replaces traditional mechanical/intrusive sensors with an imaging device (optical system) to capture position data points of landing gear components. This substitution eliminates physical contact with moving parts, reducing device complexity and intrusiveness while maintaining measurement reliability through non-contact optical measurement.
Solution Approach 2:
The patent creates a digital representation (point cloud) of the landing gear component positions through imaging, rather than using physical sensors mounted on the components. This copying approach allows accurate measurement of steering angle without adding physical sensors that would increase device complexity.
2Measurement precision
If complex computational algorithms are used to determine steering angle, then measurement precision is improved, but processing time increases
Solution Approach 1:
The patent extracts only the essential position data points of key landing gear components from the full point cloud, rather than processing all captured data. By focusing computation on relevant points only, the system achieves high measurement precision while significantly reducing processing time and latency.
Solution Approach 2:
The patent segments the landing gear component into key feature points that define its position and orientation. By identifying and processing only these critical points rather than the entire component geometry, the system achieves accurate steering angle determination with minimal computational overhead.
3Measurement precision
If multiple sensors are deployed to monitor landing gear, then measurement precision is improved, but device complexity increases
Solution Approach 1:
The patent employs a single imaging device that performs multiple functions: capturing position data of landing gear components, generating point clouds, and enabling steering angle determination. This multi-functional approach achieves measurement precision equivalent to multiple specialized sensors while reducing the total sensor count and overall system complexity.
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
Enables non-intrusive, accurate, and rapid determination of the steering angle, reducing latency and improving maneuverability feedback for pilots and enabling remote operation.
Implementation Method 1
The set of position data points may be obtained from a sensor which is monitoring other properties of the aircraft landing gear... Obtaining the set of position data points may comprise scanning the aircraft landing gear assembly with an imaging device to generate the set of position data points. The imaging device may comprise at least one of: a lidar device, a radar device, a sonar device, time-of-flight sensors or an ultrasonic rangefinder.
Implementation Method 2
Obtaining the set of position data points may comprise scanning the aircraft landing gear with a lidar device to generate the set of position data points.
Data Source
AI summary
A computer-implemented method of determining a steering angle of an aircraft landing gear is disclosed including obtaining a set of position data points, wherein the set of position data points comprises position data points of a component of the aircraft landing gear and calculating a centroid of the set of position data points. The method also includes determining an angle of an intersection between a straight line that passes through both the centroid and an axis of rotation of the aircraft landing gear and an axis that is orthogonal to a strut of the aircraft landing gear when the aircraft landing gear is at a previously known steering angle, and determining the steering angle of the aircraft landing gear based on the determined angle of intersection.