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In-flight alignment using H ∞ filter for strapdown INS on aircraft.

Fu-Jun Pei1, Xuan Liu1, Li Zhu1

  • 1Beijing University of Technology, Beijing 100124, China.

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Summary
This summary is machine-generated.

This study introduces a new method for strapdown inertial navigation system (INS) in-flight alignment, improving accuracy during dynamic aircraft movements. The novel approach enhances initial alignment by addressing disturbances effectively.

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Area of Science:

  • Navigation Systems
  • Control Theory
  • Signal Processing

Background:

  • Strapdown inertial navigation systems (INS) require accurate initial alignment.
  • In-flight alignment is crucial for improving INS accuracy and speed.
  • Aircraft dynamic movements during flight disturb the alignment process.

Purpose of the Study:

  • To investigate a novel alignment method for strapdown INS (SINS) to overcome dynamic disturbances.
  • To establish an initial alignment error model for SINS in the inertial frame.
  • To enhance the accuracy and speed of initial alignment under dynamic conditions.

Main Methods:

  • Establishing an initial alignment error model for SINS in the inertial frame.
  • Analyzing system observability using piece-wise constant system (PWCS) theory.
  • Computing observable degree via singular value decomposition (SVD) theory.
  • Designing an H ∞ filter to manage measurement noise uncertainty.

Main Results:

  • Demonstrated complete system observability.
  • Confirmed that all system state parameters can be estimated by an optimal filter.
  • Simulation results show the proposed algorithm achieves better accuracy under dynamic disturbance conditions.

Conclusions:

  • The novel alignment method effectively addresses dynamic disturbances in SINS initial alignment.
  • The system's observability is proven, enabling accurate state parameter estimation.
  • The H ∞ filter design contributes to robust performance in the presence of measurement noise.