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Correction of a Strapdown Inertial Navigation System During Descent in the Atmosphere
Mechanics of Solids, 2023The article deals with the problem on determining the angular position during descent on an apparatus with low lift-drag ratio. A solution is presented using the least squares method, which reduces to determining the orientation quaternion using a system of linear algebraic equations.
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In-Motion Filter-QUEST Alignment for Strapdown Inertial Navigation Systems
IEEE Transactions on Instrumentation and Measurement, 2018By analyzing the error models of the measured vectors of the gravitational apparent motion, an in-motion filter-QUEST alignment method only with the inertial measurement unit is presented in this paper. The contribution of the proposed method lies in constructing the in-motion model of the measured vectors of the gravitational apparent motion and ...
Xiang Xu 0004 +3 more
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Initial Alignment by Attitude Estimation for Strapdown Inertial Navigation Systems
IEEE Transactions on Instrumentation and Measurement, 2015This paper derives a novel initial alignment method for the strapdown inertial navigation system (SINS), which transforms the attitude alignment into an attitude estimation problem. The process model of the proposed initial alignment method by attitude estimation is established by decomposition of the attitude matrix.
Lubin Chang, Jingshu Li, Shengyong Chen
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Strapdown inertial navigation system of pendulum type
Mechanics of Solids, 2014We consider two implementations of an isotropic oscillator to be used in the construction of a strapdown inertial system of new type [1]. The first implementation is a contact-free suspension of an electrically conductive ball used in electrostatic gyros, and the second implementation is a 3D combination of elastic constraints holding a mass point.
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Strapdown Inertial Navigation System Algorithms Based on Geometric Algebra
Advances in Applied Clifford Algebras, 2012zbMATH Open Web Interface contents unavailable due to conflicting licenses.
Wu, Dimin, Wang, Zhengzhi
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Strapdown inertial navigation system of a rotating carrier
2017 24th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS), 2017The paper deals with a strapdown inertial navigation system (SINS) of a rotating carrier (RC) characterized by a high roll speed and rather slow oscillations in the yaw and pitch angles. It is shown that it is expedient for an RC to develop four orientation parameters: traditional yaw angles, pitch and trigonometric functions of the sine, cosine of the
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Application of Neural Network to the Alignment of Strapdown Inertial Navigation System
2007In this paper, a strapdown inertial navigation system (SINS) error model is introduced, and the model observability is analyzed. Due to the weak observability of SINS error model, the azimuth error can not be estimated quickly by Kalman filter. To reduce the initial alignment time, a neural network method for the initial alignment of SINS on stationary
Meng Bai, Xiaoguang Zhao, Zeng-Guang Hou
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Basic principles of strapdown inertial navigation systems
2004The previous chapter has provided some insight into the basic measurements that are necessary for inertial navigation. For the purposes of the ensuing discussion, it is assumed that measurements of specific force and angular rate are available along and about axes which are mutually perpendicular.
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Research on the Vibration Control for Strapdown Inertial Navigation System
2010 Second International Conference on Intelligent Human-Machine Systems and Cybernetics, 2010This paper investigates the vibration control for strap down inertial navigation system (SINS) based on the theoretical analysis and the simulation confirmation. Firstly, the disadvantage of passive vibration control technique commonly used for SINS at present is pointed out that it is only effective at high frequency.
Fan Li, Yinghui Yan
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A strapdown inertial navigation system for the flat-Earth model
IEEE Transactions on Aerospace and Electronic Systems, 1997The development of a strapdown inertial navigation system (SINS) for aerodynamically controlled vehicles, which are limited to altitudes below 30 km (that is, a small distance compared with the Earth's radius of about 7000 km), or using the so-called flat-Earth model (FEM), is the principal objective of this work. In dealing with the FEM equations, the
N. Lovren, J.K. Pieper
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