Aircraft GNSS Positioning via Link 16 Correction
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Solution Overview
Problem
Satellite-based positioning systems for aircraft approach and landing lack accuracy, necessitating correction terms derived from known reference objects and satellite signals, which can be complex and require additional hardware, increasing weight and assembly count.
Innovation Solution
An aircraft design incorporating a mission computer, GNSS receiver, and data transmission unit with a Link 16 interface, allowing decentralized processing of satellite signals and correction terms to determine accurate position values without separate assemblies, utilizing existing components for precision approach and landing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If correction terms are derived from known reference objects and satellite signals to improve positioning accuracy, then measurement precision is improved, but device complexity increases due to additional hardware and assembly requirements
Solution Approach 1:
The patent applies multi-functionality by enabling the GNSS receiver to serve dual purposes: standard navigation functionality and precision approach/landing operations. By utilizing existing components (GNSS receiver, data transmission unit, mission computer) for multiple functions, the system achieves high positioning accuracy without adding dedicated specialized hardware assemblies.
Solution Approach 2:
The patent merges the precision approach and landing functionality into the existing GNSS receiver system by integrating correction term processing within the mission computer. This combines multiple functions (navigation, correction application, position determination) into existing components rather than adding separate assemblies, thereby reducing overall device complexity while maintaining measurement precision.
2Measurement precision
If correction terms are applied to satellite signals to determine corrected position values, then measurement precision is improved, but weight increases due to additional components
Solution Approach 1:
The existing GNSS receiver and data transmission unit are utilized for multiple purposes including receiving satellite signals, obtaining correction terms, and determining corrected positions. This multi-functional use eliminates the need for additional dedicated hardware, thereby avoiding weight increase while achieving improved position determination accuracy.
Solution Approach 2:
The system uses the aircraft's existing communication and navigation infrastructure to obtain and process correction terms. The data transmission unit already present in the aircraft is utilized to receive correction data, and the mission computer processes these corrections, making the system self-sufficient without requiring external added components that would increase weight.
3Device complexity
If decentralized processing is implemented using existing components, then device complexity is reduced, but reliability may be affected
Solution Approach 1:
The system implements feedback by continuously receiving correction terms from ground stations via the data transmission unit and applying them in real-time through the mission computer. This closed-loop feedback mechanism ensures that the decentralized processing architecture maintains reliability by constantly updating position calculations with the latest correction data, compensating for any potential errors in the distributed system.
Data Source
AI summary
An aircraft with a mission computer, a GNSS receiver with a first air interface and a first receiver and a data transmission unit with a second air interface and a second receiver. The data transmission unit can receive data via an encrypted, bidirectional communication path. The mission computer determines a position value for the aircraft based on satellite signals from the GNSS receiver to which a correction term has been applied, which is transmitted to the aircraft by the data transmission unit to determine corrected satellite signals. The corrected satellite signals are the basis for determining corrected position value. The mission computer uses a GNSS receiver and data transmission unit as part of the aircraft. A ground arrangement is provided with an associated ground station and optionally a test unit for checking correct determination of the corrected position value.