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Global Positioning System (GPS) technology has revolutionized navigation and positioning, but its accuracy is often compromised by various errors. These errors, stemming from environmental, satellite, and receiver-related factors, require careful mitigation to ensure reliable performance across applications.Atmospheric ErrorsGPS signals travel through the Earth’s ionosphere and troposphere, introducing delays which affect accuracy. The ionosphere is strongly influenced by charged particles,...
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Updated: Aug 10, 2025

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Research on Algorithm of Airborne Dual-Antenna GNSS/MINS Integrated Navigation System.

Ming Xia1, Pengfei Sun2, Lianwu Guan2

  • 1Department of Intelligent Manufacturing and Industrial Security, Chongqing Vocational Institute of Safety & Technology, Chongqing 404020, China.

Sensors (Basel, Switzerland)
|February 11, 2023
PubMed
Summary
This summary is machine-generated.

A new dual-antenna Global Navigation Satellite System (GNSS) and Micro-Inertial Navigation System (MINS) offers high-precision, reliable airborne navigation. This system addresses import reliance and high costs of current aviation navigation equipment.

Keywords:
GNSS initial alignmentGNSS/MINS integrated navigationdiscrete Kalman filtererror analysisstrapdown inertial navigation algorithm

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Area of Science:

  • Aerospace Engineering
  • Navigation Systems
  • Control Systems

Background:

  • Airborne navigation equipment in China heavily relies on imports.
  • Existing domestic high-precision navigation systems are prohibitively expensive for aircraft manufacturing.
  • There is a critical need for indigenous, high-performance navigation solutions.

Purpose of the Study:

  • To develop a high-precision and high-reliability integrated airborne navigation system.
  • To overcome the limitations of imported and expensive domestic navigation equipment.
  • To provide a cost-effective and reliable solution for Chinese navigable aircraft.

Main Methods:

  • Developed a dual-antenna Global Navigation Satellite System (GNSS) and Micro-Inertial Navigation System (MINS) integrated navigation system.
  • Established state and measurement equations using discrete Kalman filter principles.
  • Implemented attitude initial alignment using magnetometers, accelerometers, and dual-antenna GNSS, leveraging MEMS IMU's insensitivity to Earth's rotation for self-alignment.
  • Utilized flight status identification based on satellite data and inertial sensor parameters.

Main Results:

  • Achieved root mean square (RMS) pitch and roll angle errors below 0.05° under indoor static conditions.
  • Demonstrated heading angle error RMS below 0.15° in static tests.
  • Validated system effectiveness through UAV flight tests covering various flight phases (take-off, climb, turn, cruise).

Conclusions:

  • The developed dual-antenna GNSS/MINS integrated navigation system meets high-precision and reliability requirements for airborne applications.
  • The system effectively addresses the challenges of import dependency and high costs in domestic aviation navigation.
  • The algorithm's performance is validated across diverse flight conditions, confirming its practical applicability.