Dynamic Landing Gear Detection Using Flight Data
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Solution Overview
Problem
Aircraft pilots often fail to deploy landing gear during landing, leading to potential damage and safety risks, as existing sensor-based systems are expensive and operationally limited, providing a short time window for reaction.
Innovation Solution
A method and system that dynamically manage landing gear deployment by generating and comparing flight measurements such as altitude, distance to destination, and airspeed to produce a landing scenario indication, converting this into a landing gear protocol to ensure timely deployment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If sensor-based systems (radar altimeters) are used for landing gear configuration warning, then detection reliability is improved, but system cost increases and device complexity increases
Solution Approach 1:
The patent replaces complex sensor-based mechanical detection systems with a computational approach that uses existing flight data (altitude, distance to destination, airspeed) processed by a computer system. This substitutes physical sensor complexity with software-based logic that achieves similar detection reliability at lower cost and complexity.
Solution Approach 2:
The patent creates a virtual model of landing scenarios by copying and processing existing flight measurement data through computational algorithms. Instead of using physical sensors to directly detect landing gear status, the system copies flight parameters and analyzes them to infer landing scenarios, reducing hardware complexity while maintaining detection capability.
2Reliability
If sensor-based systems are used for landing gear detection, then detection reliability is improved, but the time window for pilot reaction is reduced
Solution Approach 1:
The patent performs preliminary analysis of flight scenarios by continuously monitoring altitude, distance to destination, and airspeed before the actual landing occurs. The system proactively identifies potential landing scenarios and triggers warnings early in the approach phase, giving pilots sufficient reaction time rather than waiting for last-minute sensor alerts.
Solution Approach 2:
The patent implements continuous monitoring and evaluation of flight parameters throughout the approach phase, maintaining constant detection and warning capability from the moment landing becomes possible until gear deployment is confirmed. This continuous action ensures no time window is lost and provides ongoing pilot awareness throughout the critical approach period.
3Reliability
If existing landing gear warning systems are used, then they can detect improper configuration, but they are rarely used in small aircraft due to cost
Solution Approach 1:
The patent employs a cost-effective approach by using readily available flight data from existing aircraft systems (altitude sensors, GPS, airspeed indicators) rather than requiring expensive specialized landing gear detection hardware. The computational analysis software acts as a disposable, low-cost layer that enhances safety without requiring expensive hardware investments, making it suitable for small aircraft.
Solution Approach 2:
The patent makes the existing multi-functional flight data systems serve an additional safety function. The same altitude, distance, and airspeed data used for navigation and flight control are also utilized for landing gear configuration warning, eliminating the need for separate dedicated sensors and reducing overall system cost while maintaining comprehensive safety coverage.
Data Source
AI summary
The embodiments described herein relate to dynamically detecting landing gear deployment of an aerial vehicle. A set of flight measurements is dynamically generated and stored. The set of measurements may include altitude, distance to a destination, and airspeed. Each of these measurements is compared to a respective threshold value to produce a landing scenario indication. The comparison includes ascertaining that the vehicle is within a defined above ground level based on the altitude measurement, ascertaining that the vehicle is within a defined distance to a destination based on the distance to a destination measurement, and ascertaining that the airspeed measurement is below a maximum gear extension speed. The produced indication is converted into a landing gear protocol.