An accurate calibration of inertial sensors, loses its validity over time. In this paper, a practical method is proposed to compensate the modeling error of a strapdown inertial navigation system (INS) in order to resolve the requirement for re-calibration. Since strapdown INS needs a specific turntable for its calibration, this method improves the availability of flying object that equipped with strapdown INS. In this process, using the Earth’s gravity and rotation rate, deviation of calibration coefficients will be compensated. To verify effectiveness of suggested method, three different tests are performed, and it is proved that the proposed technique decreases the part of navigation error that is related to calibration deviation.
Taghavi,S. H. and Abdoli Hosseinabadi,A. (2014). Improvement of Accuracy by Pre-launch Compensation with Earth’s Gravity and Rotation Rate for SINS. Journal of Aeronautical Engineering, 16(1), 95-104.
MLA
Taghavi,S. H. , and Abdoli Hosseinabadi,A. . "Improvement of Accuracy by Pre-launch Compensation with Earth’s Gravity and Rotation Rate for SINS", Journal of Aeronautical Engineering, 16, 1, 2014, 95-104.
HARVARD
Taghavi S. H., Abdoli Hosseinabadi A. (2014). 'Improvement of Accuracy by Pre-launch Compensation with Earth’s Gravity and Rotation Rate for SINS', Journal of Aeronautical Engineering, 16(1), pp. 95-104.
CHICAGO
S. H. Taghavi and A. Abdoli Hosseinabadi, "Improvement of Accuracy by Pre-launch Compensation with Earth’s Gravity and Rotation Rate for SINS," Journal of Aeronautical Engineering, 16 1 (2014): 95-104,
VANCOUVER
Taghavi S. H., Abdoli Hosseinabadi A. Improvement of Accuracy by Pre-launch Compensation with Earth’s Gravity and Rotation Rate for SINS. JoAE, 2014; 16(1): 95-104.
