Effect of acceleration switching during INS in-flight alignment
Author:
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
General Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.19744
Reference3 articles.
1. Azimuth Observability Enhancement During Inertial Navigation System In-Flight Alignment
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1. Inertial Measurement Unit Error Modeling Tutorial: Inertial Navigation System State Estimation with Real-Time Sensor Calibration;IEEE Control Systems;2022-12
2. Enhancement of GPS/INS Navigation System Observability Using a Triaxial Magnetometer;TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES;2019
3. Observability Degree-Based AUV Single Beacon Navigation Trajectory Optimization with Range-Only Measurements;Complexity;2018-10-03
4. On the Error State Selection for Stationary SINS Alignment and Calibration Kalman Filters—Part II: Observability/Estimability Analysis;Sensors;2017-02-23
5. Stochastic observability-based analytic optimization of SINS multiposition alignment;IEEE Transactions on Aerospace and Electronic Systems;2015-07
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