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Modeling the Functional Network for Spatial Navigation in the Human Brain
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Research on In-Flight Alignment for Micro Inertial Navigation System Based on Changing Acceleration using Exponential

Yun Xu1, Tong Zhou2

  • 1School of Mechanical Engineering & Automation, Zhejiang Sci-Tech University, Hangzhou 310018, China. ntxuyun@126.com.

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|January 2, 2019
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Summary
This summary is machine-generated.

This study proposes a novel method for in-flight alignment of micro inertial navigation systems (MINS) in guided projectiles. The technique utilizes changing acceleration to achieve accurate initial attitude estimation, crucial for stable flight.

Keywords:
changing accelerationexponential functionguided projectilemicro inertial navigation system

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Area of Science:

  • Aerospace Engineering
  • Navigation Systems
  • Guidance and Control

Background:

  • Stable flight of guided projectiles requires precise initial attitude determination.
  • In-flight alignment of micro inertial navigation systems (MINS) is challenging due to short flight times.
  • Existing methods struggle to achieve sufficient accuracy within the limited flight duration.

Purpose of the Study:

  • To develop an effective in-flight alignment method for MINS in guided projectiles.
  • To improve the accuracy of initial attitude estimation for enhanced flight stability.
  • To address the limitations of current alignment techniques in short-duration flights.

Main Methods:

  • Proposed a novel method employing changing acceleration with an exponential function for in-flight alignment.
  • Derived double-vector observations to facilitate attitude estimation.
  • Utilized the regressive quaternion estimation (QUEST) algorithm for initial attitude determination.
  • Analyzed estimation errors and justified the use of changing acceleration.

Main Results:

  • Achieved accurate initial attitude estimation for guided projectiles.
  • Demonstrated effectiveness through simulation and semi-physical experiments.
  • Reported initial attitude errors: rolling angle ~0.35°, pitch angle ~0.1°, heading angle ~0.6° for shooting angles between 15° and 55°.

Conclusions:

  • The proposed changing acceleration method is effective for in-flight alignment of MINS in guided projectiles.
  • The method provides accurate initial attitude estimation, contributing to stable projectile flight.
  • Future work includes field experiments to validate stability in real-world conditions.