Calibration and Compensation of Scale Factor Non-linearity and Non-Orthogonality Errors for Dynamically Tuned Gyroscope (DTG)

Hegazy, Salem Abd El-Hakem; Mahmoud, A Attia; Kamel, Ahmed M.; Arafa, Ibrahim I.; Elhalwagy, Yehia Z.

doi:10.1109/iceeng45378.2020.9171734

Cited by 5 publications

(4 citation statements)

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“…This has drawbacks due to neglecting the scale factors at low rates. To overcome this downside, a calibration approach is proposed by this work's author and presented in Hegazy et al (2020a).…”

Section: Scale Factormentioning

confidence: 99%

“…In light of this problem, the work presented in Hegazy et al (2020a) introduced an approach for the calculation of a pure non-orthogonal error by removing the irrelevant lateral coupling signal that is measured using a lateral accelerometer in position and rate tests. This irrelevant signal is directly proportional to the centripetal acceleration and is caused by the rates applied.…”

Section: Non-orthogonalitymentioning

confidence: 99%

“…The goal of IMU calibration is to estimate the intrinsic value of the IMU and compensate for errors in IMU measure-ments to enhance INS efficiency. The precision of the IMU intrinsic calibration will also have a direct impact on the effects of motion estimation (Hegazy et al, 2020a).…”

Section: Introductionmentioning

confidence: 99%

“…Stochastic analysis is performed using several techniques such as the autocorrelation function, power spectral density, and Allan variance (AVR). The core of the analysis process is the calculation of the effect of specific noise sources on sensor output and sensor accuracy (Hegazy et al, 2020a).…”

Section: Introductionmentioning

confidence: 99%

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INS Stochastic Noise Impact on Circular Error Probability of Ballistic Missiles

Hegazy

Kamel

Arafa

et al. 2022

navi

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A circular error probability (CEP) metric in ballistic missile science is an experimental indicator of the accuracy of a missile system. There are a lot of error sources that cause a ballistic missile to deviate from its ideal trajectory, and that causes a deviation from required CEP. This work discusses the problems of dispersion of ballistic missiles due to inertial navigation system (INS) errors. INS deterministic errors are usually calibrated and compensated using some proper techniques. However, INS stochastic errors can be modeled and analyzed. In this study, a chosen missile is thoroughly analyzed using the six degrees-of-freedom missile flight trajectory simulator. A Monte Carlo simulation is used to generate a large number of flight trajectories to inspect the effect of INS stochastic noise on missile CEP. Moreover, a strategy for selecting an adequate sensor according to mission requirements and its corresponding sensor errors is introduced.

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Section: Scale Factormentioning

confidence: 99%

Section: Non-orthogonalitymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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