Aircraft Landing Site Localization for Real-Time Flight Path Control
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Solution Overview
Problem
Current navigation systems for aircraft landing are expensive, lack precision, are unreliable, and prone to interference, making them inadequate for automated landing procedures.
Innovation Solution
A system that processes sensor-derived data from aircraft components and remote stations to dynamically generate updated analyses of the aircraft's position and orientation relative to a landing site, providing real-time flight control instructions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If current navigation systems are used for aircraft landing, then the system is already established and operational, but the precision and reliability are insufficient for automated landing procedures
Solution Approach 1:
The patent combines multiple independent navigation systems (GPS, inertial navigation, visual approach slope indicator, and other sensor systems) into an integrated navigation system. This merging allows the system to cross-validate data from multiple sources, significantly improving both measurement precision and reliability for automated landing procedures by eliminating the weaknesses of individual systems.
Solution Approach 2:
The integrated navigation system is designed to perform multiple functions simultaneously: providing position information, velocity information, orientation information, and guidance cues to the flight director system. This multi-functionality ensures that a single system can meet all navigation requirements for automated landing, improving reliability by reducing the need for multiple separate systems.
2Measurement precision
If expensive navigation apparatus are installed and maintained, then navigation coverage is provided, but the cost is high and precision for automated landing is still insufficient
Solution Approach 1:
The navigation system is segmented into distinct functional modules: GPS receiver for position, inertial measurement unit for velocity and orientation, visual approach slope indicator for glide path information, and a processor that integrates data from all modules. This segmentation allows each component to be optimized independently while maintaining overall system precision, reducing complexity through modular design.
Solution Approach 2:
The patent replaces traditional mechanical navigation aids with electronic and optical systems. The visual approach slope indicator uses optical lights to provide glide path information, eliminating the need for mechanical instruments. The integrated electronic navigation system processes and combines data digitally, providing higher precision with reduced mechanical complexity.
3Reliability
If traditional navigation systems are used, then basic navigation is possible, but the systems are prone to interference and lack the reliability required for automated landing
Solution Approach 1:
The system continuously receives feedback from multiple sensor systems and uses this feedback to adjust and validate navigation solutions in real-time. The processor monitors data from GPS, inertial sensors, and visual indicators, comparing results to detect inconsistencies or interference. This feedback mechanism enables the system to identify and compensate for interference, maintaining high reliability for automated landing.
Data Source
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Figure 2A
AI summary
A system having components coupled to an aircraft and components remote from the aircraft processes sensor-derived data, transmits information between aircraft system components and remote system components, and dynamically generates updated analyses of position and orientation of the aircraft relative to a desired landing site, while the aircraft is in flight toward the desired landing site. Based on the position and orientation information, the system generates instructions for flight control of the aircraft toward a flight path to the landing site, and can update flight control instructions as new data is received and processed.