Aircraft Force Detection via Velocity Vector Analysis
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Solution Overview
Problem
Existing systems for detecting impact forces on aircraft, such as landing gear, are cumbersome and lack fidelity due to the use of multiple sensors, increasing weight and complexity while providing limited accurate feedback to control systems.
Innovation Solution
A method and system that utilize a processor connected to sensors to define velocity vectors, an instant axis of rotation, and calculate distances to determine if a force has been exerted on an aircraft portion, outputting an indication of force application by comparing distances to threshold values, thereby identifying landing gear contact without additional sensors.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If sensors are located on each landing assembly to determine weight application, then force detection capability is provided, but aircraft weight and complexity increase
Solution Approach 1:
The patent combines multiple sensor inputs (accelerometers, gyroscopes, magnetometers) into a single integrated system that processes data collectively to detect landing gear contact, rather than using separate sensors on each landing assembly. This merging approach reduces overall system complexity while maintaining detection capability.
Solution Approach 2:
The sensor system is designed to perform multiple functions: detecting rotation motion, determining aircraft orientation, and identifying landing gear contact events. By making the sensor system multi-functional, fewer dedicated sensors are needed, reducing overall system complexity.
2Measurement precision
If multiple sensors are used on landing assemblies, then force detection is enabled, but aircraft weight increases
Solution Approach 1:
The patent merges the functionality of multiple separate sensors into a single sensor system that collects and processes data from multiple sensing elements simultaneously. This consolidation maintains detection accuracy while reducing the total weight compared to installing individual sensors on each landing assembly.
Solution Approach 2:
The system uses an intermediary processing approach where sensor data from multiple sources (accelerometers, gyroscopes, magnetometers) is processed collectively to infer landing gear contact, rather than using direct force sensors on each assembly. This intermediary method reduces weight while preserving detection capability.
3Reliability
If traditional sensor systems are used on landing assemblies, then contact detection is possible, but measurement fidelity is limited
Solution Approach 1:
The patent replaces direct mechanical force sensors on landing assemblies with an indirect sensing system using accelerometers, gyroscopes, and magnetometers that measure motion and orientation changes. This substitution provides more faithful measurement of actual contact events by capturing the dynamic characteristics of landing gear contact rather than relying on simple weight threshold detection.
Solution Approach 2:
The system continuously monitors sensor data and provides feedback about aircraft motion and orientation to determine landing gear contact status. This feedback mechanism enhances measurement fidelity by using multiple data points and temporal patterns to accurately distinguish actual contact events from other motion conditions.
Data Source
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AI summary
A system for sensing a force applied to an aircraft includes a first sensor (106), a second sensor (107), and a processor (102) operative to define a first velocity vector as a function of a first velocity due to a rotation motion of the aircraft, define a second velocity vector as a function of a second velocity due to the rotation motion of the aircraft, define an instant axis of rotation of the aircraft as a function of the first velocity vector and the second velocity vector, determine whether a force has been exerted on a first portion of the aircraft, and output an indication that a force has been exerted on the first portion of the aircraft responsive to determining that the force has been exerted on the first portion of the aircraft.