Stellar Refraction–Based SINS/CNS Integrated Navigation System for Aerospace Vehicles

Yang, Shujie; Yang, Ge; Zhu, Zhiying; Li, Jing

doi:10.1061/(asce)as.1943-5525.0000536

Cited by 24 publications

(14 citation statements)

References 17 publications

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“…7). Algorithm 1: Off-line training the dictionaries A and C. Parameters: The error threshold (γσ) 2 . Initialisation: The off-line training samples must be prepared in advance.…”

Section: Algorithm Flowmentioning

confidence: 99%

“…The field of the simulated star sensor was 9 × 9°a nd the pixel size was 8 × 8 μm. There are three important parameters in the setup of the proposed method: the sizes of training samples, the size of image patches n, and the error threshold (γσ) 2 . First, we fixed σ = 10, n = 8, the probability distributions of Poisson-Gaussian noise e and d to 1/4 and 0.04, respectively.…”

Section: Experiments Setupmentioning

confidence: 99%

“…The celestial navigation system (CNS) is one of the most accurate navigation systems currently available [1][2][3]. The navigation performance of CNS is directly affected by the reliability of star image pre-processing procedures such as de-noising and stellar centroid extraction [4][5][6][7].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Automatic centroid extraction method for noisy star image

Gou

Chen

2018

IET Image Processing

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“…7). Algorithm 1: Off-line training the dictionaries A and C. Parameters: The error threshold (γσ) 2 . Initialisation: The off-line training samples must be prepared in advance.…”

Section: Algorithm Flowmentioning

confidence: 99%

Section: Experiments Setupmentioning

confidence: 99%

See 1 more Smart Citation

Automatic centroid extraction method for noisy star image

Gou

Chen

2018

IET Image Processing

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“…The SINS/CNS integrated navigation system can correct the attitude error and the gyro drift using the starlight information and greatly improve navigation accuracy [ 11 ]. At present, it is an important developing direction for missile, airplane, and spacecraft navigation technology [ 12 ]. Nevertheless, the traditional system only makes use of the information of star sensors to reckon the gyro drift, but it cannot estimate the accelerometer bias, which leads to position divergence.…”

Section: Introductionmentioning

confidence: 99%

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

Hou

Liu³

et al. 2018

Sensors

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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 large outliers and the Gaussian mixture noises, often exists during the actual navigation process, leading to the divergence phenomenon of the navigation filter. The new nonlinear Kalman filter on the basis of the maximum correntropy theory and unscented transformation, named the maximum correntropy unscented Kalman filter, is deduced, and the computational complexity is analyzed. The unscented transformation is used for restricting the nonlinearity of the system equation, and the maximum correntropy theory is used to deal with the non-Gaussian noises. Finally, numerical simulation illustrates the superiority of the proposed filter compared with the traditional unscented Kalman filter. The comparison results show that the large outliers and the influence of non-Gaussian noises for SINS/CNS deeply integrated navigation is significantly reduced through the proposed filter.

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“…Inertial navigation systems (INSs) can provide position, velocity, and attitude independently [ 1 ]. Thus, they are used extensively in land [ 2 , 3 ], marine [ 4 , 5 ], and aerospace navigation [ 6 ]. A direct and effective way to improve the navigation accuracy of an INS is to increase the accuracy of its inertial sensors.…”

Section: Introductionmentioning

confidence: 99%

Economical High–Low Temperature and Heading Rotation Test Method for the Evaluation and Optimization of the Temperature Control System for High-Precision Platform Inertial Navigation Systems

Yang

Zhang

2018

Sensors

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Inertial navigation systems (INSs) use the temperature control system to ensure the stability of the temperature of the inertial sensors for improving the navigation accuracy of the INSs. That is, the temperature control accuracy affects the performance of the INSs. Thus, the performance of temperature control systems must be evaluated before their application. However, nearly all high-precision INSs are large and heavy and require long-term testing under many different experimental conditions. As a result, conducting an outdoor navigation experiment, which involves high–low temperature and heading rotation tests, is time consuming, laborious, and costly for researchers. To address this issue, an economical high–low temperature and heading rotation test method for high-precision platform INSs is proposed, and an evaluation system based on this method is developed to evaluate the performance of the temperature control systems for high-precision platform INSs indoors. The evaluation system uses an acrylic chamber, exhaust fans, temperature sensors, and an air conditioner to simulate the environment temperature change. The outer gimbals of the platform INSs are utilized to simulate the heading rotation. The temperature control system of a high-precision platform INS is evaluated using the proposed evaluation method. The temperature difference of the gyros is obtained in the high–low temperature test, and the temperature fluctuation of the temperature control system is observed in the rotation test. These tests verify the effectiveness of the proposed evaluation method. Then, the corresponding optimization method for the temperature control system of this high-precision platform INS is put forward on the basis of the test results of the evaluation system. Experimental results show that the maximum temperature differences of the two gyros between high- and low-temperature tests are decreased from 1.51 °C to 0.50 °C, and the maximum temperature fluctuation value of the temperature control system is decreased from 0.81 °C to 0.27 °C after the proposed evaluation and optimization processes. Therefore, the proposed methods are cost effective and useful for evaluating and optimization of the temperature control system for INSs.

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Stellar Refraction–Based SINS/CNS Integrated Navigation System for Aerospace Vehicles

Cited by 24 publications

References 17 publications

Automatic centroid extraction method for noisy star image

Automatic centroid extraction method for noisy star image

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

Economical High–Low Temperature and Heading Rotation Test Method for the Evaluation and Optimization of the Temperature Control System for High-Precision Platform Inertial Navigation Systems

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