The research on system error of Inter-Satellite-Link (ISL) measurements for autonomous navigation of Beidou system

Chang, Jianbo; Shang, Liang; Li, Guotong

doi:10.1016/j.asr.2017.03.016

Cited by 13 publications

(4 citation statements)

References 26 publications

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“…The main principles of the four-way ranging are as follows. The inter-satellite link (ISL) forwards signal, modulated by a specific piece of pseudo-code for ranging, is transmitted by the ground station [4,5]. The TDRS then relays the signal to the user spacecraft, which demodulates the ranging pseudo-code and sends it back to the ground station via TDRS.…”

Section: Introductionmentioning

confidence: 99%

“…Large satellites in geosynchronous orbit (GEO), such as TDRS, usually have a lifespan of one to two decades and are subject to various space environment factors like illumination conditions, equipment ages, and bias, which can significantly differ from ground-based lab environment. Moreover, although the time delay of the TDRS ISL transponder can be tested in a ground-based laboratory before launch, calibrating it in orbit can be very challenging [3,4]. In summary, while the utilization of TDRS via four-way ranging can significantly enhance the accuracy of user spacecraft orbit determination, the systematic bias introduced by the TDRS ISL transponder must be accurately calibrated in orbit to avoid substantial systematic errors and ensure accurate orbit determination of user spacecraft.…”

Section: Introductionmentioning

confidence: 99%

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An on‐orbit calibration method for time delay of inter‐satellite link transponder in tracking and data relay satellite

Wang¹,

Tong²,

Yang³

et al. 2023

Electronics Letters

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The tracking and data relay satellite (TDRS) in geosynchronous orbit (GEO) can provide ranging and communication services for user spacecraft in low Earth orbit (LEO) through the inter‐satellite link (ISL). The time delay of TDRS ISL transponder in orbit differs from its pre‐launch state and changes due to the complex space environment, adding significant errors to the user spacecraft's orbit determination based on four‐way ranging data. The authors have developed a calibration system and proposed an efficient on‐orbit calibration method for the ISL transponder's time delay in TDRS. Experimental results demonstrate the effectiveness of the authors’ method, and the RMS of calibration residuals is less than 0.5 m.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

An on‐orbit calibration method for time delay of inter‐satellite link transponder in tracking and data relay satellite

Wang¹,

Tong²,

Yang³

et al. 2023

Electronics Letters

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“…Inter-satellite links (ISLs) can be used as a bridge between navigation satellites to connect the satellites as a whole and form a three-dimensional crossover network through mutual communication and ranging [1], [2]. ISLs can shorten the update cycle of ephemeris, realize joint-orbit determination of the navigation constellation, and notably improve the orbit determination accuracy [3]; Moreover, ISLs improve the integrity of a global navigation satellite system (GNSS) by providing an independent means to assess ephemeris and clock parameters. The establishment of ISLs enables the navigation constellation to attain a short routing delay and high communication capacity, which can considerably improve the measurement and control performance of the satellite navigation system [4].…”

Section: Introductionmentioning

confidence: 99%

A Novel Chip Pulse Employed by Ranging Code Based on Simultaneous Transmitting CPM Modulation and PN Ranging in Inter-Satellite Links of GNSS

Xue

Wang

Tang³

2020

IEEE Access

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The construction of a navigation constellation with inter-satellite links (ISLs) has become one of the important development trends for new-generation global navigation satellite systems (GNSSs), and ISLs currently realize navigation and communication functions through separate low-rate omnidirectional telemetry, tracking, command and high-rate data service channels, respectively. If the above two functions are integrated into one channel, this will result in simplification of the onboard equipment, improvement of the electromagnetic compatibility, power consumption reduction and frequency resources savings, and we speculate that autonomous navigation will be achieved by ISLs with navigation and communication fusion. In this paper, a system capable of simultaneous high-data rate communication transmission and precision ranging is investigated, and a specific scheme is introduced by combining continuous phase modulation (CPM) and a pseudonoise (PN) ranging code denoted as CPM+PN. The chip pulse is one of the key factors to design the ranging code, which not only affects the ranging performance but also influences the properties of the CPM+PN scheme, such as its spectral characteristics, communication reliability, and acquisition time. To consider the above performance indexes, a new chip pulse based on a normally distributed wave is proposed. Theoretical analysis and simulation results show that compared to squarewave and half-sine wave cases, the normally distributed wave attains great advantages in the ranging accuracy and communication reliability, which become more notable with reasonable selection of the energy distribution index. Moreover, the proposed chip pulse achieves a similar acquisition time as the traditional wave. As a result, the normally distributed wave can be used as a better alternative to the ranging chip pulse for the CPM+PN waveform.

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“…However, the use of GPS does not make the satellite completely autonomous, since it is related to the constellation of the GPS satellites and the constellation is mostly navigated from ground stations [6]. On the other hand, relative states of two (or more) satellites can be utilized for an orbit estimation, independent of GPS satellites and/or ground stations [7,8,9,10,11]. Additionally, natural properties of a planet, like its magnetic field [12,13], atmosphere [14,15], or moons [16], can help to build an autonomous orbit estimation procedure.…”

Section: Introductionmentioning

confidence: 99%

Orbit estimation using a horizon detector in the presence of uncertain celestial body rotation and geometry

2018

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This paper presents an orbit estimation using non-simultaneous horizon detector measurements in the presence of uncertainties in the celestial body rotational velocity and its geometrical characteristics. The celestial body is modelled as a tri-axial ellipsoid with a three-dimensional force field. The non-simultaneous modelling provides the possibility to consider the time gap between horizon measurements. An unscented Kalman filter is used to estimate the spacecraft motion states and estimate the geometric characteristics as well as the rotational velocity of the celestial body. A Monte-Carlo simulation is implemented to verify the results. Simulations showed that using non-simultaneous horizon vector measurements, the spacecraft state errors converge to zero even in the presence of an uncertain geometry and rotational velocity of the celestial body.

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The research on system error of Inter-Satellite-Link (ISL) measurements for autonomous navigation of Beidou system

Cited by 13 publications

References 26 publications

An on‐orbit calibration method for time delay of inter‐satellite link transponder in tracking and data relay satellite

An on‐orbit calibration method for time delay of inter‐satellite link transponder in tracking and data relay satellite

A Novel Chip Pulse Employed by Ranging Code Based on Simultaneous Transmitting CPM Modulation and PN Ranging in Inter-Satellite Links of GNSS

Orbit estimation using a horizon detector in the presence of uncertain celestial body rotation and geometry

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