SINS/CNS Integrated Navigation System for Ballistic Missile based on Maximum Correntropy Kalman Filter

Hou, Bowen; He, Zhangming; Zhou, Hongyan; Zhou, Xuanying; Sun, Baohong; Xu, Shuqing; Wang, Jiongqi

doi:10.23919/acc.2018.8431551

Cited by 4 publications

(5 citation statements)

References 26 publications

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“…In all attitude determination algorithms, the aim is finding matrix A so that the defined expense function L minimizes in form of relation (15). [2] In this equation, W i and V i are unit vectors of stars of image and unit vectors of catalog stars and a i are the positive weight coefficients of these vectors.…”

Section: Quaternionsmentioning

confidence: 99%

“…If e = e 1 e 2 e 3 T is the eigenvector of the largest eigenvalue of transfer matrix A and is the rotation angle, the quaternions are defined based on following relation (16). [2] The transfer matrix can be obtained in form of relation (17) by quaternions.…”

Section: Quaternionsmentioning

confidence: 99%

“…Also, it can be proved that cost function can be rewritten in form of relation (18). [2] In above equation, 0 and B are calculated by relations of (19).…”

Section: Wahba Cost Functionmentioning

confidence: 99%

“…One of the most important requirements of all satellites, since its inception, is the sub-system of control and determination of the situation, because without it, use of the satellite to carry out missions is not possible. The status determination system, an integral part of the satellite control system, plays a significant role in satellite control algorithms [1][2][3].…”

Section: Introductionmentioning

confidence: 99%

“…In relation (23), matrix K is defined as (24) in which matrices B, S, Z are calculated based on relations of (20). [2] To maximize relation (25) and also because of |q| = 1 , the optimal quaternion is the special proper with the largest eigenvalue of matrix K. [2] (23)…”

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confidence: 99%

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Modification and hardware implementation of star tracker algorithms

2019

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In this paper, a laboratory model is designed to evaluate the performance of star tracker algorithms for attitude determination of a satellite. Star tracker is the most accurate attitude sensor that determines satellite direction by applying centroiding algorithm, star identification and attitude determination. To utilize such algorithms, first, high quality of star images are needed which should be provided through the star tracker camera. Then, such images are given to processors and it determines the attitude of camera and satellite in three axes based on mentioned algorithms. First, in preliminary design, we define important star tracker parameters, like accuracy, detector, processor and field of view. In this paper, we have considered the range accuracy in yaw/pitch axis less than 20 arcsec and for roll axis less than 100 arcsec. To improve the attitude determination accuracy, we have applied an adaptive structure in centroiding algorithm, as only brightness stars are selected and identification algorithm is done based on them. Another important parameter is speed of identification algorithm which is handled by an ARM processor and improving pyramid algorithm, we reached less than 25 ms. Duo to this time, updating rate would be desired. Also knowing the coordination of bore sight direction that is distance between focal lens and imager is another important parameter that affects the accuracy of attitude and by ground calibration of camera, this parameter could be estimated carefully. Finally, implementation results on real images that are captured by a star tracker demonstrate optimum performance of algorithms.

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Section: Quaternionsmentioning

confidence: 99%

Section: Quaternionsmentioning

confidence: 99%

“…Also, it can be proved that cost function can be rewritten in form of relation (18). [2] In above equation, 0 and B are calculated by relations of (19).…”

Section: Wahba Cost Functionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

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