GNSS Interference Detection via Satellite Tracking Table Comparison

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Solution Overview

Problem

Global Navigation Satellite System (GNSS) receivers are vulnerable to interference from spoofing and jamming attacks, which can deceive positioning calculations by broadcasting false or blocking signals, compromising the accuracy of location determination.

Innovation Solution

A method involving the creation of a satellite tracking table for Access Points (APs) to monitor and compare derived satellite parameters from received GNSS signals with expected parameters, detecting interference events when significant deviations occur, and using spoof detection logic to identify and locate the source of the interference.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If GNSS receivers use traditional signal reception methods, then the device complexity is low, but the reliability is compromised due to vulnerability to spoofing and jamming attacks

Engineering Contradiction:
ImprovereliabilityVSAvoiddevice complexity
Core Design Contradiction:
ReliabilityVSDevice complexity

Solution Approach 1:

The system performs preliminary actions by creating a satellite tracking table in advance that contains expected parameters for legitimate satellites. This table is generated before interference detection occurs, establishing a baseline for comparison with received signals. The preliminary creation of this reference data structure enables the system to quickly identify spoofing or jamming attacks without requiring complex real-time analysis of satellite ephemeris data.

Inventive Principle:
Principle #10Preliminary action

Solution Approach 2:

The satellite tracking table acts as an intermediary between the complex satellite orbital mechanics and the simple signal comparison process. Instead of directly analyzing complex satellite position and timing data, the system uses this intermediate table to store pre-calculated expected parameters, which then serve as a reference for detecting interference. This intermediary structure simplifies the detection process while maintaining high reliability.

Inventive Principle:
Principle #24Intermediary (Mediator)

2Reliability

If GNSS receivers implement interference detection mechanisms, then the reliability improves, but the device complexity increases due to additional processing requirements

Engineering Contradiction:
ImprovereliabilityVSAvoiddevice complexity
Core Design Contradiction:
ReliabilityVSDevice complexity

Solution Approach 1:

The system extracts only the essential parameters needed for interference detection from the complete satellite data set. Instead of processing all satellite ephemeris information, the system extracts and stores only the critical expected parameters (such as signal arrival time, frequency, and code phase) in the satellite tracking table. This extraction approach enables reliable interference detection while minimizing processing complexity by focusing only on the most relevant data elements.

Inventive Principle:
Principle #2Taking out (Extraction)

Solution Approach 2:

The system changes parameters by comparing derived parameters from received signals against expected parameters stored in the tracking table. When significant deviations are detected in these parameters, the system identifies potential interference. This parameter comparison approach transforms the complex problem of interference detection into a simpler parameter matching task, improving reliability without proportionally increasing device complexity.

Inventive Principle:
Principle #35Parameter changes

3Measurement precision

If the system monitors and compares satellite parameters in real-time, then the measurement precision improves for detecting interference, but the loss of time increases due to processing requirements

Engineering Contradiction:
Improvemeasurement precisionVSAvoidloss of time
Core Design Contradiction:
Measurement precisionVSLoss of time

Solution Approach 1:

The system performs preliminary computation of expected satellite parameters and stores them in the satellite tracking table before real-time detection begins. This preliminary action eliminates the need for complex real-time calculations, allowing the system to achieve high measurement precision by simply comparing received signal parameters against pre-computed expected values. The time-consuming computational work is done in advance, not during real-time operation.

Inventive Principle:
Principle #10Preliminary action

Solution Approach 2:

The system replaces complex mechanical computation processes with a simpler data lookup and comparison mechanism. Instead of performing real-time orbital mechanics calculations to determine expected satellite parameters, the system substitutes this with a pre-computed table lookup approach. This substitution maintains high measurement precision for interference detection while dramatically reducing the processing time required during actual operation.

Inventive Principle:
Principle #28Mechanics substitution (Replace mechanical system)

Data Source

PatentUS20240345259A1Global navigational satellite system (GNSS) interference detection
Publication Date: 2024.10.17 CISCO TECHNOLOGY INC
  • US20240345259A1 patent drawing
  • US20240345259A1 patent drawing
  • US20240345259A1 patent drawing

AI summary

Global Navigation Satellite System (GNSS) interference detection may be provided. A satellite tracking table for a first Access Point (AP) may be created. The satellite tracking table may include a listing of a plurality of satellites of a Global Navigation Satellite System (GNSS) available for the first AP and expected satellite parameters for each of the plurality of satellites. A derived satellite parameter may be determined from a received GNSS signal. The derived satellite parameter may be compared with an corresponding expected satellite parameter. The corresponding expected satellite parameter may be determined from the satellite tracking table. An interference event may be determined when the derived satellite parameter differs from the corresponding expected satellite parameter by at least a predetermined amount.