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Journal articles on the topic 'Autonomous satellite navigation'

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Published: 4 June 2021
Last updated: 18 February 2022

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1

Gao, Youtao, Tanran Zhao, Bingyu Jin, Junkang Chen, and Bo Xu. "Autonomous Orbit Determination for Lagrangian Navigation Satellite Based on Neural Network Based State Observer." International Journal of Aerospace Engineering 2017 (2017): 1–10. http://dx.doi.org/10.1155/2017/9734164.

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In order to improve the accuracy of the dynamical model used in the orbit determination of the Lagrangian navigation satellites, the nonlinear perturbations acting on Lagrangian navigation satellites are estimated by a neural network. A neural network based state observer is applied to autonomously determine the orbits of Lagrangian navigation satellites using only satellite-to-satellite range. This autonomous orbit determination method does not require linearizing the dynamical mode. There is no need to calculate the transition matrix. It is proved that three satellite-to-satellite ranges are needed using this method; therefore, the navigation constellation should include four Lagrangian navigation satellites at least. Four satellites orbiting on the collinear libration orbits are chosen to construct a constellation which is used to demonstrate the utility of this method. Simulation results illustrate that the stable error of autonomous orbit determination is about 10 m. The perturbation can be estimated by the neural network.
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2

Wang, Haihong, Zhonggui Chen, Jinjun Zheng, and Haibin Chu. "A New Algorithm for Onboard Autonomous Orbit Determination of Navigation Satellites." Journal of Navigation 64, S1 (October 14, 2011): S162—S179. http://dx.doi.org/10.1017/s0373463311000397.

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Autonomous orbit determination of a navigation constellation is the process by which the orbit parameters of navigation satellites are autonomously calibrated onboard the satellites without the need for external aids. It commonly uses a satellite onboard data processing unit and a filtering method to process the measurements of inter-satellite ranges. The onboard data processing unit is the main module of autonomous navigation systems. In this paper, the two main factors that affect the accuracy of autonomous orbit determination for a navigation constellation are discussed first, and then a distributed onboard algorithm for autonomous orbit determination of navigation satellites is proposed. This method is based on a long-term ephemeris prediction and is suitable for the satellite hardware capability. The main feature of this method is that both the distributed computing method and an onboard analytical state transition matrix are used to process inter-satellite range measurements. One of the main advantages of this approach is high-speed computing since the amount of calculations needed is significantly less than that of the centralised computing method and those distributed methods that need to use an onboard numerical integrator. Another advantage of this approach is that the use of the onboard analytical state transition matrix algorithm can save a great amount of resources for both ground-to-satellite data transmissions and data storage units in satellites’ hardware. This could result in substantial cost reduction for space missions. Finally, a simulation method used for testing the proposed algorithm is presented. Results of tests over a period of 90 days show that the user range error of autonomous orbit determination derived from the proposed method is less than three metres.
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3

YongZhi, Wen, Zhang ZeJian, and Wu Jie. "High-Precision Navigation Approach of High-Orbit Spacecraft Based on Retransmission Communication Satellites." Journal of Navigation 65, no. 2 (March 12, 2012): 351–62. http://dx.doi.org/10.1017/s0373463311000671.

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Many countries have presented new requirements for in-orbit space services. Space autonomous rendezvous and docking technology could speed up the development of in-orbit spacecraft and reduce the threat of increasing amounts of space debris. The purpose of this paper is to provide real-time high-precision navigation data for high-orbit spacecraft, thus reducing the cost of ground monitoring for high-orbit spacecraft autonomous rendezvous operations, and to provide technical support for high-orbit spacecraft in-orbit services. This paper proposes a new high-orbit spacecraft autonomous navigation approach, based on a communication satellite transmitting ground navigation signals. It proposes an overall navigation system design, sets up the system information integration model and analyses the precision of the navigation system by simulation research. Through simulation of this navigation method, the positional precision of a spacecraft at an altitude of 40 000 km, can be within 2·6 m with a velocity precision of 0·0011 m/s. The transponding satellite navigation method greatly reduces the development costs by using communication satellites in high-orbit spacecraft navigation instead of launching special navigation satellites. Moreover, the signals of transponding satellite navigation are generated on the ground, which is very convenient and cost-effective for system maintenance. In addition, placing atomic clocks on the ground may also help improve the clock accuracy achieved. In this study, the satellite-based navigation method is for the first time applied in high-orbit spacecraft navigation. The study's data could improve the present lack of effective high-orbit spacecraft navigation methods and provide strong technical support for autonomous rendezvous and docking of high orbital spacecraft, as well as other application fields.
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Hua, Bing, Zhiwen Zhang, Yunhua Wu, and Zhiming Chen. "Autonomous navigation algorithm based on AUKF filter about fusion of geomagnetic and sunlight directions." International Journal of Intelligent Computing and Cybernetics 11, no. 4 (November 12, 2018): 471–85. http://dx.doi.org/10.1108/ijicc-07-2017-0087.

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Purpose The geomagnetic field vector is a function of the satellite’s position. The position and speed of the satellite can be determined by comparing the geomagnetic field vector measured by on board three-axis magnetometer with the standard value of the international geomagnetic field. The geomagnetic model has the disadvantages of uncertainty, low precision and long-term variability. Therefore, accuracy of autonomous navigation using the magnetometer is low. The purpose of this paper is to use the geomagnetic and sunlight information fusion algorithm to improve the orbit accuracy. Design/methodology/approach In this paper, an autonomous navigation method for low earth orbit satellite is studied by fusing geomagnetic and solar energy information. The algorithm selects the cosine value of the angle between the solar light vector and the geomagnetic vector, and the geomagnetic field intensity as observation. The Adaptive Unscented Kalman Filter (AUKF) filter is used to estimate the speed and position of the satellite, and the simulation research is carried out. This paper also made the same study using the UKF filter for comparison with the AUKF filter. Findings The algorithm of adding the sun direction vector information improves the positioning accuracy compared with the simple geomagnetic navigation, and the convergence and stability of the filter are better. The navigation error does not accumulate with time and has engineering application value. It also can be seen that AUKF filtering accuracy is better than UKF filtering accuracy. Research limitations/implications Geomagnetic navigation is greatly affected by the accuracy of magnetometer. This paper does not consider the spacecraft’s environmental interference with magnetic sensors. Practical implications Magnetometers and solar sensors are common sensors for micro-satellites. Near-Earth satellite orbit has abundant geomagnetic field resources. Therefore, the algorithm will have higher engineering significance in the practical application of low orbit micro-satellites orbit determination. Originality/value This paper introduces a satellite autonomous navigation algorithm. The AUKF geomagnetic filter algorithm using sunlight information can obviously improve the navigation accuracy and meet the basic requirements of low orbit small satellite orbit determination.
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5

Liao, Shilong, Zhaoxiang Qi, and Zhenghong Tang. "A Differential Measurement Method for Solving the Ephemeris Observability Issues in Autonomous Navigation." Journal of Navigation 68, no. 6 (May 25, 2015): 1133–40. http://dx.doi.org/10.1017/s0373463315000417.

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The autonomous navigation of navigation and positioning systems such as the Global Positioning System (GPS) and other Global Navigation Satellite Systems (GNSS) was motivated to improve accuracy and survivability of the navigation function for 180 days without ground contact. These improvements are accomplished by establishing inter-satellite links in the constellation for pseudo-range observations and communications between satellites. But observability issues arise for both ephemeris and clock since the pseudo-range describes only the relative distance between satellites. A differential measurement method is proposed to measure the rotation of the constellation as a whole for the first time. The feasibility of the proposed method is verified by simulations.
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6

Baohua, Li, Lai Wenjie, Chen Yun, and Liu Zongming. "An Autonomous Navigation Algorithm for High Orbit Satellite Using Star Sensor and Ultraviolet Earth Sensor." Scientific World Journal 2013 (2013): 1–7. http://dx.doi.org/10.1155/2013/237189.

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An autonomous navigation algorithm using the sensor that integrated the star sensor (FOV1) and ultraviolet earth sensor (FOV2) is presented. The star images are sampled by FOV1, and the ultraviolet earth images are sampled by the FOV2. The star identification algorithm and star tracking algorithm are executed at FOV1. Then, the optical axis direction of FOV1 at J2000.0 coordinate system is calculated. The ultraviolet image of earth is sampled by FOV2. The center vector of earth at FOV2 coordinate system is calculated with the coordinates of ultraviolet earth. The autonomous navigation data of satellite are calculated by integrated sensor with the optical axis direction of FOV1 and the center vector of earth from FOV2. The position accuracy of the autonomous navigation for satellite is improved from 1000 meters to 300 meters. And the velocity accuracy of the autonomous navigation for satellite is improved from 100 m/s to 20 m/s. At the same time, the period sine errors of the autonomous navigation for satellite are eliminated. The autonomous navigation for satellite with a sensor that integrated ultraviolet earth sensor and star sensor is well robust.
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7

Albukerque, J., J. L. Lair, B. Govin, G. Muller, P. Riant, D. Berton, and D.-F. Godart. "Autonomous Satellite Navigation Using Optico-Inertial Instruments." IFAC Proceedings Volumes 18, no. 4 (June 1985): 183–88. http://dx.doi.org/10.1016/s1474-6670(17)60887-5.

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8

Popov, Sergey, Vladimir Zaborovsky, Leonid Kurochkin, Maksim Sharagin, and Lei Zhang. "Method of Dynamic Selection of Satellite Navigation System in the Autonomous Mode of Positioning." SPIIRAS Proceedings 18, no. 2 (April 12, 2019): 302–25. http://dx.doi.org/10.15622/sp.18.2.302-325.

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Today, the list of applications that require accurate operational positioning is constantly growing. These tasks include: tasks of managing groups of Autonomous mobile robots, geodetic tasks of high-precision positioning, navigation and monitoring tasks in intelligent transport systems. Satellite navigation systems are a data source for operational positioning in such tasks. Today, global and local satellite navigation systems are actively used: GPS, GLONASS, BeiDou, Galileo. They are characterized by different completeness of satellite constellation deployment, which determines the accuracy of operational positioning in a particular geographical point, which depends on number of satellites available for observation, as well as the characteristics of the receiver, landscape features, weather conditions and the possibility of using differential corrections. The widespread use of differential corrections at the moment is not possible due to the fact that number of stable operating reference stations is limited - the Earth is covered by them unevenly; reliable data networks necessary for the transmission of differential corrections are also not deployed everywhere; budget versions of single-channel receivers of the navigation signal are widely used, which do not allow the use of differential corrections. In this case, there is a problem of operational choice of the system or a combination of satellite positioning systems, providing the most accurate navigation data. This paper presents a comparison of static and dynamic methods for selecting a system or a combination of satellite positioning systems that provide the most accurate definition of the object's own coordinates when using a single-channel receiver of navigation signals in offline mode. The choice is made on the basis of statistical analysis of data obtained from satellite positioning systems. During the analysis, the results of post-processing of data obtained from satellite navigation systems and refined with the use of differential corrections of navigation data were compared.
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9

Gao, Youtao, Junkang Chen, Bo Xu, and Jianhua Zhou. "Research on the Effectiveness of Different Estimation Algorithm on the Autonomous Orbit Determination of Lagrangian Navigation Constellation." International Journal of Aerospace Engineering 2016 (2016): 1–8. http://dx.doi.org/10.1155/2016/8392148.

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The accuracy of autonomous orbit determination of Lagrangian navigation constellation will affect the navigation accuracy for the deep space probes. Because of the special dynamical characteristics of Lagrangian navigation satellite, the error caused by different estimation algorithm will cause totally different autonomous orbit determination accuracy. We apply the extended Kalman filter and the fading–memory filter to determinate the orbits of Lagrangian navigation satellites. The autonomous orbit determination errors are compared. The accuracy of autonomous orbit determination using fading-memory filter can improve 50% compared to the autonomous orbit determination accuracy using extended Kalman filter. We proposed an integrated Kalman fading filter to smooth the process of autonomous orbit determination and improve the accuracy of autonomous orbit determination. The square root extended Kalman filter is introduced to deal with the case of inaccurate initial error variance matrix. The simulations proved that the estimation method can affect the accuracy of autonomous orbit determination greatly.
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10

Zhang, Lei, and Bo Xu. "A Universe Light House — Candidate Architectures of the Libration Point Satellite Navigation System." Journal of Navigation 67, no. 5 (March 12, 2014): 737–52. http://dx.doi.org/10.1017/s0373463314000137.

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In view of the shortcomings of existing satellite navigation systems in deep-space performance, candidate architectures which utilise libration point orbits in the Earth-Moon system are proposed to create an autonomous satellite navigation system for lunar missions. Three candidate constellations are systematically studied in order to achieve continuous global coverage for lunar orbits: the Earth-Moon L1,2 two-satellite constellation, the Earth-Moon L2,4,5 three-satellite constellation and the Earth-Moon L1,2,4,5 four-satellite constellation. After a thorough search for possible configurations, the latter two constellations are found to be the simplest feasible architectures for lunar navigation. Finally, an autonomous orbit determination simulation is performed to verify the autonomy of the system and two optimal configurations are obtained in a comprehensive consideration of coverage and autonomous orbit determination performance.
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11

Janschek, K., and S. Dyblenko. "Satellite Autonomous Navigation Based on Image Motion Analysis." IFAC Proceedings Volumes 34, no. 15 (September 2001): 111–16. http://dx.doi.org/10.1016/s1474-6670(17)40713-0.

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12

Xiaolin, Ning, and Fang Jiancheng. "An Autonomous Celestial Navigation Method for Geosychronous Satellite." IFAC Proceedings Volumes 37, no. 6 (June 2004): 179–83. http://dx.doi.org/10.1016/s1474-6670(17)32170-5.

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13

Shorshi, Gil, and Itzhack Y. Bar-Itzhack. "Satellite autonomous navigation based on magnetic field measurements." Journal of Guidance, Control, and Dynamics 18, no. 4 (July 1995): 843–50. http://dx.doi.org/10.2514/3.21468.

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14

Carnebianca, C., G. Solari, A. Cramarossa, G. Rondinelli, J. Deza, and C. Reines. "Satellite autonomous navigation using navsat GEO + HEO configuration." Acta Astronautica 16 (January 1987): 143–50. http://dx.doi.org/10.1016/0094-5765(87)90102-0.

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15

Ning, Xiaolin, Longhua Wang, Xinbei Bai, and Jiancheng Fang. "Autonomous satellite navigation using starlight refraction angle measurements." Advances in Space Research 51, no. 9 (May 2013): 1761–72. http://dx.doi.org/10.1016/j.asr.2012.12.008.

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16

Ma, Pengbin, Fanghua Jiang, and Hexi Baoyin. "Autonomous Navigation of Mars Probes by Combining Optical Data of Viewing Martian Moons and SST Data." Journal of Navigation 68, no. 6 (April 13, 2015): 1019–40. http://dx.doi.org/10.1017/s0373463315000272.

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Autonomous navigation has become a key technology for deep space exploration missions. Phobos and Deimos, the two natural moons of Mars, are important optical navigation information sources available for Mars missions. However, during the phase of the probe orbiting close to Mars, the ephemeris bias and the difference between the barycentre and the centre of brightness of a Martian moon will result in low navigation accuracy. On the other hand, Satellite-to-Satellite Tracking (SST) can achieve convenient and high accuracy observation for autonomous navigation. However, this cannot apply for a Mars mission during the Mars orbit phase only by SST data because of a rank defect problem of the Jacobian matrix. To improve the autonomous navigation accuracy of Mars probes, this paper presents a new autonomous navigation method that combines SST radio data provided by two probes and optical measurement by viewing the natural Martian moons. Two sequential orbit determination algorithms, an Extended Kalman Filter (EKF) and Unscented Kalman Filter (UKF) are compared. Simulation results show this method can obtain high autonomous navigation accuracy during the probe's Mars Orbit phase.
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17

Nowak, Aleksander. "Dynamic GNSS Mission Planning Using DTM for Precise Navigation of Autonomous Vehicles." Journal of Navigation 70, no. 3 (October 17, 2016): 483–504. http://dx.doi.org/10.1017/s0373463316000679.

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Nowadays, the most widely used method for estimating location of autonomous vehicles in real time is the use of Global Navigation Satellite Systems (GNSS). However, positioning in urban environments using GNSS is hampered by poor satellite geometry due to signal obstruction created by both man-made and natural features of the urban environment. The presence of obstacles is the reason for the decreased number of observed satellites as well as uncertainty of GNSS positioning. It is possible that in some sections of the vehicle route there might not be enough satellites necessary to fix position. It is common to use software for static GNSS measurement campaign planning, but it is often only able to predict satellite visibility at one point. This article presents a proposal for dynamic GNSS mission planning using a Digital Terrain Model (DTM) and dead reckoning. The methodology and sample results of numerical experiments are also described. They clearly show that proper dynamic GNSS mission planning is necessary in order to complete a task by an autonomous vehicle in an obstructed environment.
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Wang, Huibin, Yongmei Cheng, Cheng Cheng, Song Li, and Zhenwei Li. "Research on Satellite Selection Strategy for Receiver Autonomous Integrity Monitoring Applications." Remote Sensing 13, no. 9 (April 29, 2021): 1725. http://dx.doi.org/10.3390/rs13091725.

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Satellite selection is an effective way to overcome the challenges for the processing capability and channel limitation of the receivers due to superabundant satellites in view. The satellite selection strategies have been widely investigated to construct the subset with high accuracy but deserve further studies when applied to safety-critical applications such as the receiver autonomous integrity monitoring (RAIM) technique. In this study, the impacts of subset size on the accuracy and integrity of the subset and computation load are analyzed at first to confirm the importance of the satellite selection strategy for the RAIM process. Then the integrated performance impact of a single satellite on the current subset is evaluated according to the performance requirement of the flight phase. Subsequently, a performance-requirement-driven fast satellite selection algorithm is proposed based on the impact evaluation to construct a relatively small subset that satisfies the accuracy and integrity requirements. Comparison simulations show that the proposed algorithm can keep similar accuracy and better integrity performances than the geometric algorithm and the downdate algorithm when the subset size is fixed to 12, and can achieve an average 1.0 to 2.0 satellites smaller subset in the Lateral Navigation (LNAV) and approach procedures with vertical guidance (APV-I) horizontal requirement trial. Thus, it is suitable for real-time RAIM applications and low-cost navigation devices.
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Johannessen, R. "External Ground Monitoring v. Receiver Monitoring." Journal of Navigation 44, no. 1 (January 1991): 11–24. http://dx.doi.org/10.1017/s0373463300009681.

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The transmissions from GPS and GLONASS navigation satellites include information about the state of those transmissions as perceived by the control centre. In the case of GPS, for example, this information is contained in the data stream in Subframe 1 Word 3. However, with some of the failure conditions that can arise there is a delay of the order of half an hour before this message is altered to signal that a failure exists. A situation can therefore arise when the satellite signals that all is well, whereas in fact it is not. The very high levels of integrity which civil aviation require before satellite navigation can be used with confidence therefore means that the warning messages from the satellite must be augmented by some other form of monitoring. Two alternatives exist: (1) to have a monitor at some fixed and surveyed ground location which broadcasts a warning to the navigating aircraft when there is a malfunction (ground monitoring), or (2) to arrange for the navigating receiver to perform its own internal monitoring, known as receiver autonomous integrity monitoring (RAIM). Each alternative is beneficial in its own way.
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20

Chang, Jiansong, Yunhai Geng, Jianxin Guo, and Wei Fan. "Calibration of Satellite Autonomous Navigation Based on Attitude Sensor." Journal of Guidance, Control, and Dynamics 40, no. 1 (January 2017): 188–94. http://dx.doi.org/10.2514/1.g000684.

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21

YAO Xiang, 姚. 翔., 吴盘龙 WU Pan long, and 陈尚敏 CHEN Shang min. "Autonomous Navigation for Lunar Satellite Using X Ray Pulsars." Electronics Optics & Control 22, no. 9 (2015): 87–90. http://dx.doi.org/10.3788/m0005220152209.0087.

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22

Jianxin, Guo, and Xie Yongcbun. "Observability Analysis of a Geostationary Satellite Autonomous Navigation System." IFAC Proceedings Volumes 37, no. 6 (June 2004): 281–85. http://dx.doi.org/10.1016/s1474-6670(17)32187-0.

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23

Jiancheng, Fang, and Zhang Yu. "An Information Fusion Method for Satellite Autonomous Celestial Navigation." IFAC Proceedings Volumes 37, no. 6 (June 2004): 287–91. http://dx.doi.org/10.1016/s1474-6670(17)32188-2.

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24

WHITE, ROBERT L., SAM W. THURMAN, and FRANK A. BARNES. "Autonomous Satellite Navigation Using Observations of Starlight Atmospheric Refraction." Navigation 32, no. 4 (December 1985): 317–33. http://dx.doi.org/10.1002/j.2161-4296.1985.tb00914.x.

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25

He, Lina, Hairui Zhou, and Gongyuan Zhang. "Improving extended Kalman filter algorithm in satellite autonomous navigation." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 4 (August 6, 2016): 743–59. http://dx.doi.org/10.1177/0954410016641708.

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With the goal of reducing dependence on ground tracking systems, satellite autonomous navigation technologies are developed quickly in the recent several decades. However, precise orbit determination at high orbital altitudes is an important and challenging problem. In this paper, the nonlinear real-time orbit determination problem is investigated. Combined with satellite dynamical model, extended Kalman filter is explored to estimate satellite orbit parameters. Further, considering errors occur in linearization processing, two improvements for the extended Kalman filter algorithm, i.e. extended Kalman filter-I and extended Kalman filter-II, are proposed based on Lagrange’s mean value theorem, and respectively focus on choosing better linear expansion point and Jacobian matrix calculation point. Extensive simulations show that extended Kalman filter-I and extended Kalman filter-II significantly enhance orbit accuracy, compared with extended Kalman filter. And the increases in calculation complexity are acceptable. Finally, the robustness of extended Kalman filter-I and extended Kalman filter-II is analyzed by given different initial position errors, and results show that extended Kalman filter-I and extended Kalman filter-II have better robustness than extended Kalman filter.
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26

Wiegand, Matthias. "Autonomous satellite navigation via kalman filtering of magnetometer data." Acta Astronautica 38, no. 4-8 (February 1996): 395–403. http://dx.doi.org/10.1016/0094-5765(96)00052-5.

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27

Zheng, Xueen, Ye Liu, Guochao Fan, Jing Zhao, and Chengdong Xu. "Analyses of the sensitivity of multi-constellation advanced receiver autonomous integrity monitoring vertical protection level availability to error parameters and a failure model over China." Advances in Mechanical Engineering 10, no. 6 (June 2018): 168781401877619. http://dx.doi.org/10.1177/1687814018776191.

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The availability of advanced receiver autonomous integrity monitoring for vertical guidance down to altitudes of 200 ft (LPV-200) is discussed using real satellite orbit/ephemeris data collected at eight international global navigation satellite system service stations across China. Analyses were conducted for the availability of multi-constellation advanced receiver autonomous integrity monitoring and multi-fault advanced receiver autonomous integrity monitoring, and the sensitivity of availability in response to changes in error model parameters (i.e. user range accuracy, user range error, Bias-Nom and Bias-Max) was used to compute the vertical protection level. The results demonstrated that advanced receiver autonomous integrity monitoring availability based on multiple constellations met the requirements of LPV-200 despite multiple-fault detections that reduced the availability of the advanced receiver autonomous integrity monitoring algorithm; the advanced receiver autonomous integrity monitoring availability thresholds of the user range error and Bias-Nom used for accuracy were more relevant to geographic information than the user range accuracy and Bias-Max used for integrity at the eight international global navigation satellite system service stations. Finally, the possibility of using the advanced receiver autonomous integrity monitoring algorithm for a Category III navigation standard is discussed using two sets of predicted errors, revealing that the algorithm could be used in 79% of China.
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Gao, She Sheng, Wen Hui Wei, and Li Xue. "Near Space Pseudolite Navigation System Design and High-Performance Filtering Algorithm." Applied Mechanics and Materials 411-414 (September 2013): 931–35. http://dx.doi.org/10.4028/www.scientific.net/amm.411-414.931.

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This paper analyzes the defects of satellite navigation systems that exist in positioning and precision-guided weapons and pointes out the advantages and military needs of pseudolite. The autonomous navigation nonlinear mathematical model of Near Space Pseudolite SINS/CNS/SAR autonomous navigation system is established. Based on the merits of fading filter, robust adaptive filtering and particle filter, we propose a fading adaptive Unscented Particle Filtering algorithm. The proposed filtering algorithm is applied to SINS/CNS/SAR autonomous navigation system and conducted simulation calculation with the Unscented Kalman filter and particle filter comparison. The results show that the new algorithm that is proposed meets the needs of pseudolite autonomous navigation, and the navigation accuracy is significantly higher than the Unscented Kalman filter and particle filter algorithm.
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Li, Jiang, Ma, Lv, Yuan, and Li. "LEO Precise Orbit Determination with Inter-Satellite Links." Remote Sensing 11, no. 18 (September 11, 2019): 2117. http://dx.doi.org/10.3390/rs11182117.

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Traditional precise orbit determination (POD) for low Earth orbit (LEO) satellites relies on observations from ground stations and onboard receivers. Although the accuracy can reach centimeter level, there are still problems such as insufficient autonomous operation capability. The inter-satellite link (ISL) is a link used for communication between satellites and has a function of dual-way ranging. Numerous studies have shown that observational data using ISLs can be adopted for POD of navigation satellites. In this contribution, we mainly focus on LEO satellites POD with ISLs. First, we design LEO constellations with different numbers of satellites and ISL measurements, based on which the constellations are simulated. Then rough tests of POD using different link topologies are carried out. The results show that in the 60-LEO constellation the average 3-dimensional (3D) orbital errors are 0.112 m using “4-connected” link topology with constant 4 links per satellite and 0.069 m using “all-connected” link topology with theoretically maximum numbers of links. After that, we carry out refined POD experiments with several sets of satellite numbers and different observation accuracy. The results show the higher link ranging accuracy and the more numbers of links bring higher POD precision. POD with ISLs gets bad performance in the case of center of gravity reference when link ranging accuracy is poor and numbers of links are small. When the link accuracy is 40 cm, average 3D orbital errors of 60-LEO constellation are 0.358 m, which can only meet the demand of autonomous navigation. With the constraint of the right ascension of the ascending node (RAAN), POD using ISLs reaches an extremely high precision when adopting a spatial reference provided by navigation satellites. For 120-LEO constellation, the average 3D orbital errors are 0.010 m; for 192-LEO constellation, the errors are 0.006 m.
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Sarma, Achanta D., Quddusa Sultana, and Vemuri Satya Srinivas. "Augmentation of Indian Regional Navigation Satellite System to Improve Dilution of Precision." Journal of Navigation 63, no. 2 (February 23, 2010): 313–21. http://dx.doi.org/10.1017/s037346330999035x.

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The Indian Regional Navigation Satellite System (IRNSS) is an autonomous and independent navigational system being developed by India. IRNSS will provide position, navigation and timing services for national applications. To improve accuracy, it can be augmented using GPS and pseudolites (pseudo-satellites). In this paper, the effect on DOP (Dilution of Precision) due to augmentation of the proposed constellation of IRNSS with pseudolites is investigated. GDOP is reduced to 1·75 (max) from 3·63 (max) due to augmentation of IRNSS with two airport pseudolites (APLs). Due to augmentation of IRNSS with GPS, GDOP is reduced to 2·4 (max). When IRNSS is augmented with an APL as well as with GPS, GDOP is further decreased to 1·65 (max). The regional effect on DOP due to IRNSS is also investigated at different locations in the Indian region.
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Suzuki, Taro, Mitsunori Kitamura, Yoshiharu Amano, and Nobuaki Kubo. "Autonomous Navigation of a Mobile Robot Based on GNSS/DR Integration in Outdoor Environments." Journal of Robotics and Mechatronics 26, no. 2 (April 20, 2014): 214–24. http://dx.doi.org/10.20965/jrm.2014.p0214.

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This paper describes the development of a mobile robot system and an outdoor navigationmethod based on global navigation satellite system (GNSS) in an autonomous mobile robot navigation challenge, called the Tsukuba Challenge, held in Tsukuba, Japan, in 2011 and 2012. The Tsukuba Challenge promotes practical technologies for autonomous mobile robots working in ordinary pedestrian environments. Many teams taking part in the Tsukuba Challenge used laser scanners to determine robot positions. GNSS was not used in localization because its positioning has multipath errors and problems in availability. We propose a technique for realizing multipath mitigation that uses an omnidirectional IR camera to exclude “invisible” satellites, i.e., those entirely obstructed by a building and whose direct waves therefore are not received. We applied GPS / dead reckoning (DR) integrated based on observation data from visible satellites determined by the IR camera. Positioning was evaluated during Tsukuba Challenge 2011 and 2012. Our robot ran the 1.4 km course autonomously and evaluation results confirmed the effectiveness of our proposed technique and the feasibility of its highly accurate positioning.
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32

Huang, He, Jun Zhou, and Ying Ying Liu. "How to Get the Solar Direction from Skylight Polarization for Satellite Autonomous Navigation." Applied Mechanics and Materials 577 (July 2014): 434–37. http://dx.doi.org/10.4028/www.scientific.net/amm.577.434.

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The solar direction is an important clue for satellite autonomous navigation. A new method for obtaining the solar direction from skylight polarization for satellite navigation is discussed. The new method is using two E-vector polarization sensors to get solar direction, and the view field of the polarization sensor is discussed.
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33

Hesar, Siamak G., Jeffrey S. Parker, Jason M. Leonard, Ryan M. McGranaghan, and George H. Born. "Lunar far side surface navigation using Linked Autonomous Interplanetary Satellite Orbit Navigation (LiAISON)." Acta Astronautica 117 (December 2015): 116–29. http://dx.doi.org/10.1016/j.actaastro.2015.07.027.

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34

Gao, Youtao, Zhicheng You, and Bo Xu. "Integrated Design of Autonomous Orbit Determination and Orbit Control for GEO Satellite Based on Neural Network." International Journal of Aerospace Engineering 2020 (January 21, 2020): 1–13. http://dx.doi.org/10.1155/2020/3801625.

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In order to improve the autonomy of a maneuvered GEO satellite which is a member of a navigation satellite system, an integrated design method of autonomous orbit determination and autonomous control was proposed. A neural network state observer was designed to estimate the state of the GEO satellite, with only the intersatellite ranging information as observations. The controller is determined autonomously by another neural network based on the estimated state and the preset correction trajectory. A gradient descent learning method with a forgetting factor was used to derive the weight updating strategy which can satisfy the system’s stability and real-time performance. A Lyapunov method was used to prove the stability of both the observer and the controller. The neural network observer can reduce the influence of control on autonomous orbit determination. The neural network controller can improve the robustness of the maneuvered GEO satellite. The simulation results show the effectiveness of this method.
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35

Durand, J. M. "Satellite Navigation: GPS Inadequacies: Comparative Study into Solutions for Civil Aviation." Journal of Navigation 43, no. 1 (January 1990): 8–17. http://dx.doi.org/10.1017/s037346330001376x.

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The Global Positioning System (GPS) will be an extremely high-performance satellite-based navigation system which is expected to provide a sole means air navigation service for most aeronautical flight phases. It will be particularly suitable for ‘en route’, ‘terminal’ and ‘non-precision approach’ phases, thus providing substantial savings on aircraft operating costs.However, GPS has three major disadvantages for civil aviation: (1) Insufficient system integrity, since satellites can transmit erroneous information for two hours before being repaired or neutralized. In such an event, the many simultaneous users of the satellite that has lost its integrity can derive false positions and remain unaware of the problem. (2) Availability constrained by the limited number of satellites. Users are then unable to obtain a position fix or else obtain a result with significantly degraded performance. (3) Deliberate spatio-temporal degradation (selective availability) of system performance, the characteristics of which are not fully known or defined.Many solutions to these problems have been put forward. One concept uses the redundancy of the GPS system itself (receiver autonomous integrity monitoring). Another set of solutions is based on complementary information from autonomous navigation equipment (altimeter, clock, inertial system) or external navigation systems already available or being developed (Omega, Loran-C, GLONASS). A third type of solution is to implement a system by which to monitor the status of the GPS satellites and broadcast the information to users.This paper reports on the different techniques put forward and uses different qualitative criteria (technical feasibility, cost, political independence, etc.) to assess their suitability for civil aviation applications. The comparison leads to the recommendation of a system to monitor the status of the GPS satellites and broadcast the information to users. The characteristics of such messages would be as similar as possible to those of GPS messages.
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36

Strachan, Victor F. "Inertial Measurement Technology in the Satellite Navigation Environment." Journal of Navigation 53, no. 2 (May 2000): 247–60. http://dx.doi.org/10.1017/s0373463300008808.

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Inertial measurement technology can make a valuable contribution to the development of autonomous, sole-means Satellite Navigation Systems. The integration of inertial measurement technology and GPS can enable a significant performance improvement to the various configurations of GPS, WAAS and LAAS. This paper provides a conceptual discussion of the safety and performance benefits that inertial measurement and integration technology can bring to the satellite navigation environment.
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37

Yu, Ziyuan, Jin Liu, Chao Pan, Lvqian Guo, Zhiwei Kang, and Xin Ma. "Solar TDOA measurement and integrated navigation for formation flying." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 12 (February 2019): 4635–45. http://dx.doi.org/10.1177/0954410019827148.

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To improve the positioning accuracy of autonomous celestial navigation systems when flying in formation, we exploit the fact that the sole light source in the solar system is the Sun to directly provide positioning information for relative navigation. We term this solar Time Difference of Arrival (TDOA) navigation for formation flying. Solar light has the potential to provide a solar Time of Arrival (TOA) because of its unstable intensity. However, the solar TOA cannot be used for navigation because it has no baseline. To solve this problem, we took the difference between the solar TOAs of two spacecraft (the solar TDOA) as the basis for navigational measurement. The solar TDOA represents the relative distance between two spacecraft in a radial direction. However, whilst the solar TDOA is insensitive to solar direction errors, a free-standing solar TDOA navigation system is not observable. We therefore combined the solar TDOA with the Mars direction and inter-satellite link navigation system, to form an integrated solar TDOA/Mars direction/inter-satellite link navigation method for formation flying. Simulation results indicate that solar TDOA-based integrated navigation for formation flying can provide highly accurate navigation information, especially under relative conditions.
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38

HAN, Ke, Hao WANG, Binjie TU, and Zhonghe JIN. "Pico-satellite Autonomous Navigation with Magnetometer and Sun Sensor Data." Chinese Journal of Aeronautics 24, no. 1 (February 2011): 46–54. http://dx.doi.org/10.1016/s1000-9361(11)60006-x.

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39

Peng, Jian-hang, Xiang-lei Wang, Jian-min Fang, and Zhi-ping Wang. "Analysis of Time Scale Algorithm in Satellite Autonomous Navigation Mode." IOP Conference Series: Earth and Environmental Science 310 (September 5, 2019): 042053. http://dx.doi.org/10.1088/1755-1315/310/4/042053.

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40

JIA, XiaoLin, Yue MAO, XianBing WU, XiaoYong SONG, XiaoGong HU, and YanLing CHEN. "Satellite autonomous navigation algorithm analysis based on broadcast ephemeris parameters." SCIENTIA SINICA Physica, Mechanica & Astronomica 45, no. 7 (June 1, 2015): 079512. http://dx.doi.org/10.1360/sspma2015-00126.

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41

Drozd, O. V., V. S. Tutatchikov, and D. V. Kapulin. "Simulation modelling of autonomous navigation support for small satellite constellation." Journal of Physics: Conference Series 1661 (November 2020): 012002. http://dx.doi.org/10.1088/1742-6596/1661/1/012002.

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42

Wen, Yuanlan, Jun Zhu, Youxing Gong, Qian Wang, and Xiufeng He. "Distributed Orbit Determination for Global Navigation Satellite System with Inter-Satellite Link." Sensors 19, no. 5 (February 28, 2019): 1031. http://dx.doi.org/10.3390/s19051031.

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To keep the global navigation satellite system functional during extreme conditions, it is a trend to employ autonomous navigation technology with inter-satellite link. As in the newly built BeiDou system (BDS-3) equipped with Ka-band inter-satellite links, every individual satellite has the ability of communicating and measuring distances among each other. The system also has less dependence on the ground stations and improved navigation performance. Because of the huge amount of measurement data, the centralized data processing algorithm for orbit determination is suggested to be replaced by a distributed one in which each satellite in the constellation is required to finish a partial computation task. In the present paper, the balanced extended Kalman filter algorithm for distributed orbit determination is proposed and compared with the whole-constellation centralized extended Kalman filter, the iterative cascade extended Kalman filter, and the increasing measurement covariance extended Kalman filter. The proposed method demands a lower computation power; however, it yields results with a relatively good accuracy.
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43

Ivanov, A. V., D. V. Boykov, O. V. Trapeznikova, A. P. Pudovkin, and E. V. Trapeznikov. "Autonomous navigation data integrity monitoring of satellite radio navigation systems based on residual method." Journal of Physics: Conference Series 1546 (May 2020): 012016. http://dx.doi.org/10.1088/1742-6596/1546/1/012016.

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44

Kai, Xiong, Wei Chunling, and Liu Liangdong. "Autonomous navigation for a group of satellites with star sensors and inter-satellite links." Acta Astronautica 86 (May 2013): 10–23. http://dx.doi.org/10.1016/j.actaastro.2012.12.001.

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45

Feng, Lei, and Guotong Li. "Research on Self-Monitoring Method for Anomalies of Satellite Atomic Clock." International Journal of Aerospace Engineering 2016 (2016): 1–16. http://dx.doi.org/10.1155/2016/1759512.

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Atomic clock is the core component of navigation satellite payload, playing a decisive role in the realization of positioning function. So the monitoring for anomalies of the satellite atomic clock is very important. In this paper, a complete autonomous monitoring method for the satellite clock is put forward, which is, respectively, based on Phase-Locked Loop (PLL) and statistical principle. Our methods focus on anomalies in satellite clock such as phase and frequency jumping, instantaneous deterioration, stability deterioration, and frequency drift-rate anomaly. Now, method based on PLL has been used successfully in China’s newest BeiDou navigation satellite.
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46

Yang, Yang, Yong Li, Chris Rizos, Andrew G. Dempster, and Xiaokui Yue. "Inter-satellite Ranging Augmented GPS Relative Navigation for Satellite Formation Flying." Journal of Navigation 67, no. 3 (November 26, 2013): 437–49. http://dx.doi.org/10.1017/s0373463313000763.

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An Augmented Relative Navigation System (ARNS) is proposed for autonomous satellite formation flying in low-Earth-orbit (LEO). Inter-satellite ranging systems such as those based on radio frequency transmissions can provide additional observation information, e.g. inter-satellite distance measurement, which can be used to increase the Global Positioning System (GPS) stand-alone observation dimension, or treated as a non-linear equality constraint within a smoothly-constrained Kalman filter. Both approaches are implemented in the proposed ARNS described in this paper. An innovative phase integer ambiguity fixing and feedback scheme is implemented to increase the ambiguity fix rate of the GPS carrier phase measurements. A set of Gravity Recovery and Climate Experiment (GRACE) flight data is used to test and validate the relative navigation performance of the proposed methods. Results indicate that the augmented system can improve relative positioning accuracy by an order of magnitude.
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47

KOZOREZ, Dmitriy A., and Dmitriy M. KRUZHKOV. "Autonomous navigation of the space debris collector." INCAS BULLETIN 11, S (August 1, 2019): 105–13. http://dx.doi.org/10.13111/2066-8201.2019.11.s.10.

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The article discusses potential use of proposed by the authors configuration of onboard system of autonomous navigation and movement control of space debris collector to operate at GSO. The relevance of this research is that the problem of space debris is acute because of a large number of spent spacecraft that may damage other equipment. The purpose of the article is to analyses the launch of the work of navigation system for autonomous space debris collector. The solution of this problem is possible by applying the previously created the semi-natural modelling stands and simulation mathematical models implemented in software. The modelling results showed that during the formation of scenarios for the work of the debris collector at GSO, there was a significant number of time intervals during the year, when favorable conditions for receiving satellite signals remained at a given target longitude of GSO and, as a result, performed a high-precision solution for the navigation task.
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48

Volkova, A., and P. W. Gibbens. "SATELLITE IMAGERY ASSISTED ROAD-BASED VISUAL NAVIGATION SYSTEM." ISPRS Annals of Photogrammetry, Remote Sensing and Spatial Information Sciences III-1 (June 2, 2016): 209–17. http://dx.doi.org/10.5194/isprs-annals-iii-1-209-2016.

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There is a growing demand for unmanned aerial systems as autonomous surveillance, exploration and remote sensing solutions. Among the key concerns for robust operation of these systems is the need to reliably navigate the environment without reliance on global navigation satellite system (GNSS). This is of particular concern in Defence circles, but is also a major safety issue for commercial operations. In these circumstances, the aircraft needs to navigate relying only on information from on-board passive sensors such as digital cameras. An autonomous feature-based visual system presented in this work offers a novel integral approach to the modelling and registration of visual features that responds to the specific needs of the navigation system. It detects visual features from Google Earth<sup>*</sup> build a feature database. The same algorithm then detects features in an on-board cameras video stream. On one level this serves to localise the vehicle relative to the environment using Simultaneous Localisation and Mapping (SLAM). On a second level it correlates them with the database to localise the vehicle with respect to the inertial frame. <br><br> The performance of the presented visual navigation system was compared using the satellite imagery from different years. Based on comparison results, an analysis of the effects of seasonal, structural and qualitative changes of the imagery source on the performance of the navigation algorithm is presented. <br><br> <sup>*</sup> The algorithm is independent of the source of satellite imagery and another provider can be used
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49

Elghamrawy, Haidy Y. F., Mohamed Tamazin, and Aboelmagd Noureldin. "Investigating the Benefits of Vector-Based GNSS Receivers for Autonomous Vehicles under Challenging Navigation Environments." Signals 1, no. 2 (October 1, 2020): 121–37. http://dx.doi.org/10.3390/signals1020007.

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There is a growing demand for robust and accurate positioning information for various applications, including the self-driving car industry. Such applications rely mainly on the Global Navigation Satellite System (GNSS), including the Global Positioning System (GPS). However, GPS positioning accuracy relies on several factors, such as satellite geometry, receiver architecture, and navigation environment, to name a few. In urban canyons in which there is a significant probability of signal blockage of one or more satellites and/or interference, the positioning accuracy of scalar-based GPS receivers drastically deteriorates. On the other hand, vector-based GPS receivers exhibit some immunity to momentary outages and interference. Therefore, it is becoming necessary to consider vector-based GPS receivers for several applications, especially safety-critical applications, including next-generation navigation technologies for autonomous vehicles. This paper investigates a vector-based receiver’s performance and compares it to its scalar counterpart in signal degraded conditions. The realistic simulation experiments in this paper are conducted on GPS L1 C/A signals generated using the SpirentTM simulation system to create a fully controlled environment to examine and validate the performance. The results show that the vector tracking system outperforms the scalar tracking in terms of position and velocity estimation accuracy in signal-degraded environments.
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50

Volkova, A., and P. W. Gibbens. "SATELLITE IMAGERY ASSISTED ROAD-BASED VISUAL NAVIGATION SYSTEM." ISPRS Annals of Photogrammetry, Remote Sensing and Spatial Information Sciences III-1 (June 2, 2016): 209–17. http://dx.doi.org/10.5194/isprsannals-iii-1-209-2016.

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There is a growing demand for unmanned aerial systems as autonomous surveillance, exploration and remote sensing solutions. Among the key concerns for robust operation of these systems is the need to reliably navigate the environment without reliance on global navigation satellite system (GNSS). This is of particular concern in Defence circles, but is also a major safety issue for commercial operations. In these circumstances, the aircraft needs to navigate relying only on information from on-board passive sensors such as digital cameras. An autonomous feature-based visual system presented in this work offers a novel integral approach to the modelling and registration of visual features that responds to the specific needs of the navigation system. It detects visual features from Google Earth&lt;sup&gt;*&lt;/sup&gt; build a feature database. The same algorithm then detects features in an on-board cameras video stream. On one level this serves to localise the vehicle relative to the environment using Simultaneous Localisation and Mapping (SLAM). On a second level it correlates them with the database to localise the vehicle with respect to the inertial frame. &lt;br&gt;&lt;br&gt; The performance of the presented visual navigation system was compared using the satellite imagery from different years. Based on comparison results, an analysis of the effects of seasonal, structural and qualitative changes of the imagery source on the performance of the navigation algorithm is presented. &lt;br&gt;&lt;br&gt; &lt;sup&gt;*&lt;/sup&gt; The algorithm is independent of the source of satellite imagery and another provider can be used
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