2018
DOI: 10.3390/s18061724
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Maximum Correntropy Unscented Kalman Filter for Ballistic Missile Navigation System based on SINS/CNS Deeply Integrated Mode

Abstract: Strap-down inertial navigation system/celestial navigation system (SINS/CNS) integrated navigation is a high precision navigation technique for ballistic missiles. The traditional navigation method has a divergence in the position error. A deeply integrated mode for SINS/CNS navigation system is proposed to improve the navigation accuracy of ballistic missile. The deeply integrated navigation principle is described and the observability of the navigation system is analyzed. The nonlinearity, as well as the lar… Show more

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Cited by 35 publications
(25 citation statements)
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“…Considering only one fixed point iteration, the Equation (36) can be solved by using the modified measurement covariance matrix in the update process as [ 34 , 35 ]: …”
Section: Derivation Of Mcupfmentioning
confidence: 99%
See 3 more Smart Citations
“…Considering only one fixed point iteration, the Equation (36) can be solved by using the modified measurement covariance matrix in the update process as [ 34 , 35 ]: …”
Section: Derivation Of Mcupfmentioning
confidence: 99%
“…The existing PF [ 14 ], UPF [ 14 ], Huber unscented particle filter (HRUPF) [ 24 ], MCUKF [ 34 ], iterated VB based cubature Kalman filter (IVBCKF) [ 21 ], and the proposed MCUPF are compared, where the simple random resampling is employed in PF and UPF. In order to obtain a better performance of MCUKF, the kernel bandwidth in MCUKF and MCUPF are set as following the advice of [ 34 , 35 ]. Besides, the turning parameter and iterated times in HRUPF are commonly used and [ 24 , 27 ], respectively.…”
Section: Lake-water Filed Trialmentioning
confidence: 99%
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“…Being highly precise and highly reliable, a star sensor is one of the main devices of a celestial navigation system [ 1 ]. It is widely used in spacecraft attitude control [ 2 ], missile guidance [ 3 ], and ship and aircraft navigation [ 4 , 5 ], and is small in size and light in weight [ 6 , 7 ]. By executing star centroid extraction, star identification, and attitude estimation, the attitude information can be determined [ 8 ].…”
Section: Introductionmentioning
confidence: 99%