Classification of Methods in the SINS/CNS Integration Navigation System

Yang, Yanqiang; Zhang, Chunxi; Lu, Jiazhen; Zhang, Hao

doi:10.1109/access.2017.2787424

Cited by 17 publications

(4 citation statements)

References 13 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The corresponding observation equation for the star vector can be written as (Yang et al, 2018) where is the star vector information in the platform navigation frame (s-frame). is the star vector information in the computer navigation frame (c-frame).…”

Section: Star Vector Observation Principle Of Stellar-insmentioning

confidence: 99%

The Stellar-INS Navigation Performance Influence Mechanism of Star Vector Orientation in the Field of View

et al. 2020

Self Cite

View full text Add to dashboard Cite

The star sensor field of view varies from several arc-minutes to 20 degrees, which directly determines the star vector orientation in the field of view (FOV). Although the relationship between star vector orientation in the FOV and attitude accuracy has been revealed, the influence mechanism of star vector orientation on the integrated navigation performance of a stellar inertial navigation system has not been analysed. In order to improve the integrated accuracy, the main errors such as star sensor installation error, gyro error and initial platform angle error should be estimated online. It is significant to study the influence mechanism of star vector orientation on estimation of the above errors. In this paper, the star sensor sensitivity and the geometry factor are defined to feature the difference between the optical axis direction and the non-optical axis direction. The formulised mechanism and quantification results between star vector orientation and integration attitude and error estimation accuracy are clearly given. Simulation and ground testing were conducted and it was found that the larger the star vector orientation along the optical axis, the better the error estimation accuracy. In contrast, the attitude accuracy is weakly sensitive to the orientation of the star vector in conditions of appropriate posture adjustment and star observation scheme. This conclusion can offer universal guidance for the design and evaluation of stellar inertial navigation systems with narrow field of view or large field of view star sensors.

show abstract

Section: Star Vector Observation Principle Of Stellar-insmentioning

confidence: 99%

The Stellar-INS Navigation Performance Influence Mechanism of Star Vector Orientation in the Field of View

et al. 2020

Self Cite

View full text Add to dashboard Cite

show abstract

“…where ε 0 is the constant bias of the gyroscopic drift, A, f , and θ 0 are the amplitude, frequency, and initial phase of the periodical part of the gyroscopic drift, respectively, k is the coefficient of its linear part, ∇ (t) is the colored noise, and (t) is the white noise [27]- [29]. We analyzed the error characteristics of FOG by calculating the Allan variance of the output of FOG, which was obtained by sampling for 8 h in a state of rest and at a sampling frequency of 300 Hz.…”

Section: ) Analysis Of Gyroscopic Driftmentioning

confidence: 99%

Algorithms and Instrument for Rapid Detection of Rail Surface Defects and Vertical Short-Wave Irregularities Based on FOG and Odometer

et al. 2019

View full text Add to dashboard Cite

Defects and vertical short-wave irregularities significantly influence the maintenance of the railway tracks and the train safety, and hence, they need to be detected and eliminated in the early stages of formation. We studied the principles and algorithms to detect the defects and to measure the vertical shortwave irregularities by using a fiber optical gyroscope and an odometer, and the associated software was also developed. The principles of deformation index, namely, the ratio of angular rate to velocity and the method to determine the threshold of defects detection, are expatiated. The influence of the transfer function in measuring the vertical irregularities has long been a tough issue. The relation between the characteristics of deformation index and the wavelength of irregularities is studied by converting the deformation index from the time domain to the spatial domain. The post-processing module utilizes the results of the spectrum analysis of the deformation index to determine the wavelength of the track irregularities and eliminate the influence of the transfer function. To improve the accuracy of the calculation results, we analyzed the characteristics of the output of the gyroscope and the odometer and designed a series of targeted error-elimination methods. The forward and reverse dead-reckoning method is utilized to reduce the error accumulation, especially a high frequency noise when calculating the magnitude of the vertical short-wave irregularities. The experimental results show that the repeatability is 0.038 mm when the chord length is 1 m and 0.65 mm when the chord length is 10 m. The accuracy is 0.05 mm when compared with the results obtained using a ruler of 1 m. The moving speed of the instrument was approximately 0.6-1.2 m/s during the experiment. Both the accuracy and the efficiency can fulfill the requirements for the measurement of the short-wave irregularities.INDEX TERMS Fiber optical gyro, short-wave irregularity, deformation index, transfer function, dead reckoning.CUIJUN DONG received the B.E. degree in surveying and mapping engineering from the Uni-

show abstract

“…The commonly used navigation systems for hypersonic vehicles include the inertial navigation system (INS), global navigation satellite system (GNSS), and celestial navigation system (CNS) [3]. The INS are self-contained and are more accurate in the short term and they can supply data continuously at a very high rate.…”

Section: Introductionmentioning

confidence: 99%

Tightly Coupled Integrated Navigation Algorithm for Hypersonic Boost-Glide Vehicles in the LCEF Frame

et al. 2021

View full text Add to dashboard Cite

According to the trajectory characteristics of hypersonic boost-glide vehicles, a tightly coupled integrated navigation algorithm for hypersonic vehicles based on the launch-centered Earth-fixed (LCEF) frame is proposed. First, the strapdown inertial navigation mechanization algorithm and discrete update algorithm in the LCEF frame are introduced. Subsequently, the attitude, velocity, and position error equations of strapdown inertial navigation in the LCEF frame are introduced. The strapdown inertial navigation system/global positioning system (SINS/GPS) pseudo-range and pseudo-range rate measurement equations in the LCEF frame are derived. Further, the tightly coupled SINS/GPS integrated navigation filter state equation and the measurement equation are presented. Finally, the tightly coupled SINS/GPS integrated navigation algorithm is verified in the hardware-in-the-loop (HWIL) simulation environment. The simulation results indicate that the precision of tightly coupled integrated navigation is better than that of loosely coupled integrated navigation. Moreover, even when the number of effective satellites is less than four, tightly coupled integrated navigation functions well, thus verifying the effectiveness and feasibility of the algorithm.

show abstract

Classification of Methods in the SINS/CNS Integration Navigation System

Cited by 17 publications

References 13 publications

The Stellar-INS Navigation Performance Influence Mechanism of Star Vector Orientation in the Field of View

The Stellar-INS Navigation Performance Influence Mechanism of Star Vector Orientation in the Field of View

Algorithms and Instrument for Rapid Detection of Rail Surface Defects and Vertical Short-Wave Irregularities Based on FOG and Odometer

Tightly Coupled Integrated Navigation Algorithm for Hypersonic Boost-Glide Vehicles in the LCEF Frame

Contact Info

Product

Resources

About