Satellite Augmentation Supplemental System for Low Visibility
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Solution Overview
Problem
Current satellite-based navigation systems are limited in providing approach guidance below 200ft during low visibility conditions, leading to flight delays, diversions, and cancellations at smaller airports, as they require costly ground infrastructure for CAT II and CAT III operations.
Innovation Solution
Integration of an independent onboard supplemental navigation sensor with satellite-based augmentation systems (SBAS) to enhance navigation integrity monitoring, allowing LPV guidance without the need for expensive airport ground equipment, thereby enabling safer approaches below LPV250 or LPV200 decision heights.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If airport ground equipment is implemented for CAT II and CAT III operation, then navigation reliability during low visibility conditions is improved, but system cost increases significantly
Solution Approach 1:
The patent replaces ground-based mechanical/electronic navigation equipment with an airborne system combining satellite-based augmentation system (SBAS) and inertial navigation system (INS). This substitution eliminates the need for expensive ground infrastructure while maintaining navigation reliability through integrated onboard sensors and processing.
Solution Approach 2:
The patent creates a virtual copy of ground-based navigation capabilities by implementing equivalent navigation functions onboard the aircraft using SBAS and INS. The airborne system replicates the functionality of ground equipment through software-based navigation solution integration, providing the same CAT II/III approach capabilities without physical ground installation.
2Device complexity
If satellite based augmentation system is used for LPV guidance, then system cost is reduced, but navigation reliability below 200ft during low visibility conditions deteriorates
Solution Approach 1:
The patent merges satellite-based augmentation system (SBAS) with inertial navigation system (INS) to create an integrated navigation solution. The combination allows the system to maintain SBAS cost-effectiveness while achieving CAT II/III level reliability below 200ft by fusing GPS/Loran-C data with inertial sensor measurements through Kalman filtering and integrity monitoring.
Solution Approach 2:
The patent creates a composite navigation solution by combining multiple navigation sources (SBAS, INS, integrity monitoring) into a unified system. The hybrid architecture integrates satellite-based positioning with onboard inertial sensors, leveraging the strengths of each system to achieve reliable low-visibility approach guidance at reduced cost.
3Adaptability or versatility
If approach guidance is provided below LPV200 decision height, then airport accessibility during low visibility conditions is improved, but risk of undetected faults increases
Solution Approach 1:
The patent implements continuous feedback through autonomous integrity monitoring that compares SBAS and INS navigation solutions in real-time. The system monitors for inconsistencies, detects potential faults, and provides feedback to maintain navigation safety. This closed-loop monitoring enables extended approach below LPV200 while maintaining fault detection capability through ongoing solution validation.
Data Source
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AI summary
A method of supplementing a satellite based augmentation system approach during low visibility conditions is provided. The method includes acquiring satellite range measurements and additional measurements from at least one additional onboard independent sensor. Core sigma values are assigned for satellite range measurements and for each additional measurement from the at least one additional onboard independent sensor. A weighted position solution is determined using the acquired satellite range measurements, the acquired additional measurements and the assigned core sigma values. A discriminator is applied that utilizes vehicle positions derived from the acquired satellite range measurements and from the additional measurements to determine if a fault is present in the weighted positon solution. An alert is generated if an output of the discriminator is outside a set tolerance value needed for low visibility operation.