Altitude Data Generation System for Aviation
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Solution Overview
Problem
Current navigation systems, particularly in aviation, face challenges in achieving high navigational accuracy due to path definition errors, navigation system errors, and flight technical errors, especially during low-visibility instrument approach procedures, which require precise altitude determination independent of terrain variations and aircraft descent rate.
Innovation Solution
A system that integrates data from SBAS-aided satellite navigation, inertial systems, air-data computers, radar altimeters, terrain data, and runway data to generate inertially-smoothed altitude and height information, reducing noise and providing a consistent decision height for pilots, independent of terrain changes, by correlating altitude changes with the aircraft's descent rate and a fixed reference point.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If radar altimeter system is used to measure height above terrain, then altitude measurement is independent of aircraft descent rate, but the measurement changes quickly due to noise and terrain elevation variations
Solution Approach 1:
The patent combines multiple independent navigation systems (GPS, inertial navigation, barometric altimeters, radar altimeters) to create a integrated navigation system. By merging these systems, the patent achieves both stability (from inertial and barometric systems) and accuracy (from GPS and radar altimeter corrections), resolving the contradiction between measurement stability and accuracy.
Solution Approach 2:
The patent implements feedback mechanisms where the navigation system continuously monitors and corrects altitude measurements from multiple sources. The system uses feedback loops to filter noise from radar altimeter readings and compensate for drift in inertial navigation, maintaining both stability and precision in altitude determination.
2Reliability
If radar altimeter system is included in IAP to determine DH, then height measurement is independent of terrain, but routine ground maintenance is required to prevent false readings from obstacles
Solution Approach 1:
The patent creates a universal navigation system that can operate across different terrain types and conditions using multiple complementary systems. The integrated system provides height measurement consistency through GPS and inertial navigation while reducing dependence on radar altimeter maintenance by using multiple redundant measurement methods.
Solution Approach 2:
The navigation system performs self-diagnosis and self-correction by continuously monitoring data from multiple independent sources. The system can automatically detect and compensate for potential false readings from any single source, reducing the need for manual ground maintenance and obstacle clearance verification.
3Measurement precision
If GPS-based navigation is used to achieve lower DH, then navigational accuracy is improved, but more than 2,700 GPS IAPs require survey preparations to implement
Solution Approach 1:
The patent develops a universal integrated navigation system that can be applied to all GPS-based IAPs regardless of specific terrain characteristics. By creating a multi-functional system that combines GPS with inertial navigation, barometric altimetry, and radar altimetry, the system can be implemented across thousands of airports without requiring individualized survey preparations for each location.
Solution Approach 2:
The patent performs preliminary integration and validation of multiple navigation systems in a unified framework before deployment. By pre-establishing the integrated system architecture and validation protocols, the patent enables rapid implementation across numerous GPS IAPs without requiring extensive site-specific survey preparations for each airport.
4Measurement precision
If multiple navigation systems are integrated to reduce TSE, then navigational accuracy is improved, but system complexity increases
Solution Approach 1:
The patent segments the navigation system into distinct functional modules (GPS receiver, inertial navigation unit, barometric altimeter, radar altimeter) that can be independently developed, tested, and maintained. This modular segmentation reduces integration complexity while maintaining the navigational accuracy benefits of the multi-system approach.
Solution Approach 2:
The patent introduces an intermediary integration layer that standardizes data exchange between different navigation systems. This intermediary layer provides a common interface and data fusion algorithm that simplifies the integration of heterogeneous systems, reducing overall system complexity while preserving the accuracy improvements from multi-system integration.
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
This integration enhances navigational accuracy, reduces pilot workload, and simplifies training by providing a common decision height for all approaches, independent of terrain, thereby improving operational efficiency and safety.
Implementation Method 1
The radar altimeter system produces radar altimeter reading that are independent of aircraft decent rate
Data Source
AI summary
Present novel and non-trivial system, device, and method for generating altitude data and/or height data are disclosed. A processor receives navigation data from an external source such as a global positioning system (“GPS”); receives navigation data from multiple internal sources; receives object data representative of terrain or surface feature elevation; determines an instant measurement of aircraft altitude as a function of these inputs; and generates aircraft altitude data responsive to such determination. In an additional embodiment, the processor receives reference point data representative of the elevation of the stationary reference point (e.g., a landing threshold point); determines an instant measurement of aircraft height as a function of this input and the instant measurement of aircraft altitude; and generates aircraft height data responsive to such determination.