Orbit and tracking data evaluation of Chang’E-4 relay satellite

Qin, Songhe; Huang, Yong; Li, Peijia; Shan, Qiuli; Mo, Fan; Hu, Xiaogong; Wang, Guangli

doi:10.1016/j.asr.2019.05.028

Cited by 15 publications

(6 citation statements)

References 12 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…These errors represent the residual error the user receiver will experience after application of the LCNS navigation message, applying the same concept as Earth GNSS. Studying the current state-of-the-art of orbit determination and time synchronization (ODTS) techniques (Bauer et al, 2017;Exertier et al, 2013;Maier & Baur, 2016;Mazarico et al, 2018;Qin et al, 2019), it is clear that there is not yet an ultimate approach to achieve accurate LCNS ephemerides when used as part of a real-time broadcast in a lunar navigation system. However, using a combination of existing techniques and technologies, the authors consider that the assumed LCNS orbit and clock errors at maximum age-of-data (AOD) are achievable.…”

Section: Lunar Communication and Navigation Servicementioning

confidence: 99%

Positioning and Velocity Performance Levels for a Lunar Lander using a Dedicated Lunar Communication and Navigation System

Grenier

Giordano

Bucci

et al. 2022

navi

View full text Add to dashboard Cite

With the Moon becoming the next long-term objective in space for both agencies (ESA, 2021; NASA, 2021) and private actors (NASA, 2020), the number of expected missions to Earth's natural satellite might exceed, already in this decade, the overall number reached in the 1960s-1970s (Euroconsult, 2020).In the past, lunar missions have almost entirely relied on direct-to-Earth (DTE) communications, whilst using ranging radiometric measurements from Earth for navigation. The benefits of a lunar relay infrastructure were already envisaged in the early years of the Apollo missions (Farquhar, 1971) and were also demonstrated by the recent far-side landing of the Chinese Chang'E 4 mission (Gao et al., 2019; the latter focused on relaying telemetry to ground rather than providing an independent orbit determination and navigation solution). The growing trend in the number of missions to the Moon is creating demand for the deployment of a lunar communication and navigation infrastructure to support the international community. This, in turn, can act as a catalyst for additional public and private worldwide cislunar initiatives.

show abstract

Section: Lunar Communication and Navigation Servicementioning

confidence: 99%

Positioning and Velocity Performance Levels for a Lunar Lander using a Dedicated Lunar Communication and Navigation System

Grenier

Giordano

Bucci

et al. 2022

navi

View full text Add to dashboard Cite

show abstract

“…However, the landing site was on the far side of the Moon. Before that, a communication relay satellite was launched into a halo orbit near the Earth-Moon L2 point for communication between lander/rover and ground stations [4]. As a sample return mission, CE-5 consists of four modules: lander, ascender, orbiter and returner.…”

Section: Introductionmentioning

confidence: 99%

Trajectory Determination of Chang’E-5 during Landing and Ascending

Yang

Huang

et al. 2021

Remote Sensing

Self Cite

View full text Add to dashboard Cite

Chang’E-5 (CE-5) is China’s first lunar sample return mission. This paper focuses on the trajectory determination of the CE-5 lander and ascender during the landing and ascending phases, and the positioning of the CE-5 lander on the Moon. Based on the kinematic statistical orbit determination method using B-spline and polynomial functions, the descent and ascent trajectories of the lander and ascender are determined by using ground-based radiometric ranging, Doppler and interferometry data. The results show that a B-spline function is suitable for a trajectory with complex maneuvers. For a smooth trajectory, B-spline and polynomial functions can reach almost the same solutions. The positioning of the CE-5 lander on the Moon is also investigated here. Using the kinematic statistical positioning method, the landing site of the lander is 43.0590°N, 51.9208°W with an elevation of −2480.26 m, which is less than 200 m different from the LRO (Lunar Reconnaissance Orbiter) image data.

show abstract

“…As part of China's lunar and deep-space missions, similar to the navigation techniques employed in Chinese Lunar exploration missions (Qin et al 2019), very long baseline interferometry (VLBI) and ranging/velocity data are adopted for the accurate orbit determination in the TW-1 mission, with TW-1 orbiter's orbit accuracy of kilometer level (Yang et al 2022). The Chinese VLBI Network (CVN) and the deep-space tracking stations are responsible for tracking TW-1 and providing essential VLBI and ranging/velocity data required for determining the orbiter's orbit.…”

Section: Introductionmentioning

confidence: 99%

An in-beam Source-frequency Phase Referencing VLBI Positioning Method for China’s First Martian Rover

Tong,

Zheng,

Zhang

2024

PASP

View full text Add to dashboard Cite

Very long baseline interferometry (VLBI) plays a crucial role in geodesy and astrometry, and it is also being successfully used in spacecraft tracking. Phase referencing VLBI is a technique that uses phase information rather than the traditional VLBI group time delay to achieve higher measurement accuracy. The newly developed source-frequency phase referencing (SFPR) VLBI has been proven to be a powerful method to eliminate errors, but for positioning purposes, only “core shifts” are left in SFPR. Therefore, in this paper, an in-beam SFPR (IB-SFPR) VLBI method based on SFPR is proposed to overcome the positioning deficiency in SFPR, and to achieve high positioning accuracy. The proposed IB-SFPR method is further researched in more detail and shown to have the ability to achieve high positioning accuracy. For the first Martian rover of China, the IB-SFPR is first applied in its positioning. The positioning results of the rover have shown that the 1σ formal position error is hundreds of meters, with a formal error of post-fitted phase time delay of about 1.3 ps. However, the position discrepancies among the results of IB-SFPR, the guidance, navigation and control system, and the visual localization are at kilometer level, which are mainly affected by the orbit error of the orbiter. Therefore, considering the external reference’s (the obiter) orbit error, the final positioning accuracy of the Martian rover is at the kilometer level.

show abstract

Orbit and tracking data evaluation of Chang’E-4 relay satellite

Cited by 15 publications

References 12 publications

Positioning and Velocity Performance Levels for a Lunar Lander using a Dedicated Lunar Communication and Navigation System

Positioning and Velocity Performance Levels for a Lunar Lander using a Dedicated Lunar Communication and Navigation System

Trajectory Determination of Chang’E-5 during Landing and Ascending

An in-beam Source-frequency Phase Referencing VLBI Positioning Method for China’s First Martian Rover

Contact Info

Product

Resources

About