Navigation in GEO, HEO, and Lunar Trajectory Using Multi-GNSS Sidelobe Signals

Guan, Meiqian; Xu, Tianhe; Li, Min; Gao, Fan; Mu, Dapeng

doi:10.3390/rs14020318

Cited by 18 publications

(9 citation statements)

References 25 publications

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“…The Global Navigation Satellite System (GNSS) has played an important role in ground navigation and low orbit (LEO) spacecraft navigation since its establishment. With the increase of space missions such as deep space exploration, GNSS navigation of high-orbit spacecraft has become a new way to achieve autonomous navigation of space-craft [1,2]. High orbit spacecraft mainly include lunar and planetary probes, relay satellites, geostationary earth orbit satellites and so on.…”

Section: Introductionmentioning

confidence: 99%

Orbit Determination of High Orbit Spacecraft based on BDS-3 using Extended Kalman Filter

Ma,

Hu,

et al. 2024

J. Phys.: Conf. Ser.

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The positioning of highly elliptical orbit (HEO) spacecraft is very important in deep space exploration and other missions. The Beidou Navigation Satellite System (BDS-3), which was completed in 2020, has put forward new ideas for using GNSS technology to make up for the lack of earth-based TT&C systems. At the same time, the selection of the gravity field order and the perturbation forces must be considered when using dynamical methods for HEO spacecraft positioning. In this paper, simulation experiments are carried out based on the Two-Line Orbital Element (TLE) data of BDS. Two HEO satellites with different semimajor-axis (67509.6 km, 212857.3 km) are selected as the target spacecraft orbits. The single point positioning (SPP) method and Extended Kalman Filter (EKF) method are used for HEO spacecrafts positioning respectively. The experiments show that a 20×20 order gravity field model can be chosen for the orbital integral of HEO spacecraft orbits, and the integration error caused by solar gravity and lunar gravity should be taken into account with the change of orbital altitude. Adding Geostationary Orbit (GEO) and Inclined GeoSynchronous Orbit (IGSO) navigation satellites improved the visibility of these two orbits by 19.45% and 16.64%, respectively, and improved the GDOP value by 14.1% and 3.8%, respectively, compared to observing MEO satellites only. The use of the EKF method can effectively improve the positioning accuracy of the HEO spacecraft compared to the SPP method. For the spacecraft in HEO-1, the RMS value of the positioning errors of the EKF method was 67.82 m, and the accuracy of each direction was improved by 44.28%, 38.85%, and 38.62%, respectively. For the spacecraft in HEO-2, the positioning errors in the x direction of EKF method was within 12 km and within 2 km in the y and z directions. The accuracy of these three directions was improved by 84.91%, 79.24%, and 58.64%, respectively.

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Section: Introductionmentioning

confidence: 99%

Orbit Determination of High Orbit Spacecraft based on BDS-3 using Extended Kalman Filter

Ma,

Hu,

et al. 2024

J. Phys.: Conf. Ser.

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“…Recent years have witnessed mankind accelerating into a new era of lunar exploration and development [1], and there will be more and more cislunar activities [2,3]. In the future, the number of unmanned lunar probes and manned lunar spacecraft will increase and take more and more "one small step for individuals and one giant step for humankind" [4][5][6].…”

Section: Introductionmentioning

confidence: 99%

A Measurement Method for Cislunar Spacecraft Based on Connected Element Interferometry and BeiDou-3 Interplanetary Link in Future Lunar Exploration

Gao

Yang

et al. 2023

Remote Sensing

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To meet the urgent need for high-precision tracking and reliable cataloging of non-cooperative targets in the Earth–Moon space, this paper proposes a GNSS Inter-Satellite Link and Connected Element Interferometry (CEI)-based measurement method for high-value cislunar space targets. Firstly, the general flow and basic scenario of the proposed method are given, followed by the mathematical model which, mainly includes four parts: (i) dynamical constraint equations for targets; (ii) GNSS-based interplanetary link for irradiation of targets; (iii) transmission loss equation of GNSS inter-satellite link signal in Earth–Moon space; (iv) CEI-based precision measurements of targets. On this basis, the full process link budget analysis is carried out, followed by the performance evaluation, which includes the reception performance of CEI receiving arrays and the measurement accuracy of targets. The feasibility of the proposed method is evaluated and verified in experiments, and it is illustrated that (i) for inter-satellite link visibility analysis, at least 20 satellites can simultaneously provide inter-satellite link signals to the Earth–Moon space targets, with a single GEO satellite up to 8.5 h continuously, while the chain access can be available at up to 73,000 km, with the angle ranging from −80∘ to 360∘; (ii) the Max Duration of Chain Access for BD3-lunarprobe-CEI (from 24 March 2023 04:00:00.000 to 31 March 2023 10:00:00.000) is 50,998.804 s/day, with a Total Duration of 358,408.797 s in 7 days; (iii) for link budget and measurement accuracy analysis, even beyond the farthest Earth–Moon Lagrangian point, the C/N0 will be above 56.1 dBHZ, while even approaching the distances of 4.5×105km, the σDLL and σFLL will be below 5.345 m and 3.475×10−4 m/s, respectively, and the final measurement error will remain at 62.5 m with the proposed method. The findings of this paper could play a key role in future increasingly serious space missions, such as Earth–Moon space situational awareness, and will have a broad application prospect, if put into actual testing and operations.

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“…When a vehicle orbits at an altitude higher than that of GNSS satellites, nadir antennae can be used to receive unobscured GNSS side lobe signals from the other side of the Earth [1]. Although these signals are quite weak, as the transmitting antenna gain of the side lobe tends to be about 10-15 dB lower than the main lobe, these signals have proven to be usable [2][3][4][5]. The concept of space service volume (SSV) was introduced early in this century as a standard for describing the service performance of the Global Positioning System (GPS) in space applications from 3000 to 36,000 km above the Earth's surface (geostationary orbit altitude, GEO) [6].…”

Section: Introductionmentioning

confidence: 99%

Acquisition of Weak BDS Signal in the Lunar Environment

Chen

Yan

2023

Remote Sensing

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Autonomous navigation using the GNSS has been increasingly used in lunar exploration missions, as it is considered an efficient method for spacecraft to operate without relying on ground facilities. However, so far, only GPS and Galileo have been studied and implemented in lunar missions, whereas the potential of BDS-3 for such missions remains largely unexplored. This paper presents an analysis and evaluation of the navigation service capabilities for spacecraft at lunar altitudes by utilizing existing GNSS satellite resources in orbit. In detail, we investigate the number of GNSS signals received by low lunar orbit (LLO) receivers, as well as the carrier-to-noise ratio (C/N0), Doppler shift, and geometric dilution of precision (GDOP) of the received signal. Additionally, a digital intermediate frequency (IF) signal simulation program to emulate the BDS B1I signal is utilized, which allows to freely set the carrier-to-noise ratio, Doppler shift, and code phase. Based on this framework, we discussed a high-sensitivity BDS B1I signal receiver and validated its performance with simulated signals. We verified the capabilities of coherent integration, non-coherent integration, differential integration, and semi-bit methods to detect weak BDS B1I signals in a lunar environment. The results indicate that the semi-bit coherent differential integration method is still capable of acquiring signals at a C/N0 of 15 dB-Hz and can effectively suppress the navigation data bit sign transition.

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Navigation in GEO, HEO, and Lunar Trajectory Using Multi-GNSS Sidelobe Signals

Cited by 18 publications

References 25 publications

Orbit Determination of High Orbit Spacecraft based on BDS-3 using Extended Kalman Filter

Orbit Determination of High Orbit Spacecraft based on BDS-3 using Extended Kalman Filter

A Measurement Method for Cislunar Spacecraft Based on Connected Element Interferometry and BeiDou-3 Interplanetary Link in Future Lunar Exploration

Acquisition of Weak BDS Signal in the Lunar Environment

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