Small-sized integrated navigation system

Veremeenko, K. K.; Антонов, Д. А.; Zharkov, M. V.; Zimin, R. Yu.; Tchernodoubov, A Y

doi:10.1109/maes.2011.5746184

Cited by 5 publications

(3 citation statements)

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“…Strapdown inertial navigation systems (SINS) are widely used in various applications [1][2][3][4][5][6][7]. The key task of SINS design is the development of attitude determination algorithm providing attitude angles (heading, pitch, and roll) calculation within required accuracy and output rate [8].…”

Section: Introductionmentioning

confidence: 99%

“…The Moscow Aviation Institute MAI has been carrying out research and development in the field of INS since the middle of the last century. Currently, MAI has created a line of various accuracy grade SINS, depending on the type of gyroscopes used: from MEMS to laser gyroscopes [2,3]. Due to the increasing capabilities of embedded computers in the latest modifications of SINS, the attitude algorithm is based on a transformation matrix.…”

Section: Introductionmentioning

confidence: 99%

“…The comparison of attitude errors mean values and RMS are given in Table 1. 2 Direct angles calculation approach, 3 Transformation matrix approach using GNSS data, and 4 Direct angles calculation approach using GNSS data.…”

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confidence: 99%

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Experimental Results of Attitude Determination Functional Algorithms Implementation in Strapdown Inertial Navigation System

Zharkov

Veremeenko

Kuznetsov

et al. 2022

Sensors

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Strapdown inertial navigation system (SINS) software developers are usually mainly focused on the attitude determination algorithm design and characteristics. Such an algorithm can be based on different mathematical apparatus. An approach to the derivation of attitude determination algorithm equations in strapdown inertial navigation system is proposed. This algorithm is based on direct heading, pitch, and roll calculation. The qualitative differences between the proposed algorithm and the one using a transformation matrix are noted. The main objective of the paper is direct attitude angles calculation algorithm application possibilities analysis in real SINS operating conditions. The analysis is based on a comparison of the proposed algorithm with another frequently used attitude determination algorithm based on the transformation matrix. Attitude determination algorithms performance investigation results based on car and helicopter experimental tests are presented.

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