Aircraft Navigation System Radar-Augmented Drift Correction
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Solution Overview
Problem
Current aircraft navigation systems lack precision, reliability, and are prone to accuracy drift, especially during low-altitude flights, and are not designed to operate continuously when subsystems are unavailable.
Innovation Solution
A survey-augmented navigation system that combines radar, IMU, and GPS data to dynamically determine aircraft location and state, correcting for accuracy drift and allowing continuous operation by transitioning between different navigation modes based on altitude and subsystem availability, using a non-traditional navigation architecture that includes radar-augmented data processing and remote system communication.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If traditional navigation systems are used, then the system is simple to operate, but the measurement precision and reliability deteriorate due to accuracy drift and interference
Solution Approach 1:
The patent combines multiple navigation subsystems (GPS, inertial navigation, radar altimeter, terrain reference navigation) into a unified integrated navigation system. This merging allows the system to leverage the strengths of each subsystem while compensating for their individual weaknesses, achieving high precision location determination through data fusion and mutual correction of measurements.
Solution Approach 2:
The integrated navigation system performs multiple functions simultaneously: position determination, velocity measurement, attitude calculation, and terrain mapping. The system can operate in various modes (GPS-dependent, GPS-independent, radar-augmented) and provides redundant navigation capabilities, making it universally applicable across different flight conditions and environments.
2Reliability
If traditional navigation systems are used, then the device complexity is low, but the reliability deteriorates when subsystems become unavailable
Solution Approach 1:
The system implements beforehand cushioning by pre-configuring multiple independent navigation subsystems and establishing backup pathways for navigation functionality. When the primary GPS subsystem becomes unavailable, the system has pre-prepared alternative navigation modes (inertial navigation with terrain reference, radar-augmented navigation) that can immediately take over, ensuring continuous operation without interruption.
Solution Approach 2:
The navigation system dynamically adapts its configuration based on the availability of different subsystems. The system can transition between GPS-dependent mode, GPS-degraded mode, and GPS-independent mode, adjusting its operational characteristics in real-time. This dynamic reconfiguration allows the system to maintain reliability under varying conditions while managing complexity through adaptive rather than static redundancy.
3Measurement precision
If radar-augmented navigation is implemented, then the measurement precision improves at low altitudes, but the use of energy increases due to additional radar operations
Solution Approach 1:
The system implements partial action by selectively activating radar augmentation only when needed - specifically when operating at low altitudes where GPS precision deteriorates or when enhanced terrain correlation is required. The radar subsystem operates intermittently rather than continuously, providing precision enhancement only in the specific operational regime where it is most beneficial, thereby reducing overall energy consumption while maintaining high precision when required.
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
The system provides precise location and state determination, improves navigation decision-making, and ensures continuous operation even when traditional navigation subsystems fail, enhancing flight safety and accuracy, especially at low altitudes.
Implementation Method 1
a radar subsystem including a radar signal transmitter configured to transmit radar signals, and a radar signal receiver configured to receive the radar signals
Implementation Method 2
an inertial measurement unit (IMU) configured to output inertial measurement unit data associated with a dynamic state of the aircraft
Implementation Method 3
a GPS receiver configured to receive global positioning system (GPS) signals
Data Source
AI summary
A system having components coupled to an aircraft and components remote from the aircraft processes radar-augmented data, transmits information between aircraft system components and/or remote system components, and dynamically determines locations and states of the aircraft, while the aircraft is in flight. Based on the locations and states of the aircraft, the system generates instructions for flight control of the aircraft toward a flight path appropriate to the locations of the aircraft, and can update flight control instructions as new data is received and processed.