Observational Arc-Length Effect on Orbit Determination for KPLO Using a Sequential Estimation Technique

Kim, Young-Rok; Song, Young Woong; Bae, Jonghee; Choi, Seok-Weon

doi:10.5140/jass.2018.35.4.295

Cited by 2 publications

(2 citation statements)

References 24 publications

(27 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…For normal cases, measurement noise values of the DSN range and Doppler are set to 13 m and 0.003 Hz, respectively. It is assumed that the KDSA has noise values of 22 m and 0.15 Hz for range and Doppler measurements, respectively (Kim et al 2018a).…”

Section: Measurement Simulationmentioning

confidence: 99%

See 1 more Smart Citation

Ground Tracking Support Condition Effect on Orbit Determination for Korea Pathfinder Lunar Orbiter (KPLO) in Lunar Orbit

Kim¹,

Song²,

Park³

et al. 2020

Journal of Astronomy and Space Sciences

View full text Add to dashboard Cite

The ground tracking support is a critical factor for the navigation performance of spacecraft orbiting around the Moon. Because of the tracking limit of antennas, only a small number of facilities can support lunar missions. Therefore, case studies for various ground tracking support conditions are needed for lunar missions on the stage of preliminary mission analysis. This study analyzes the ground supporting condition effect on orbit determination (OD) of Korea Pathfinder Lunar Orbiter (KPLO) in the lunar orbit. For the assumption of ground support conditions, daily tracking frequency, cut-off angle for low elevation, tracking measurement accuracy, and tracking failure situations were considered. Two antennas of deep space network (DSN) and Korea Deep Space Antenna (KDSA) are utilized for various tracking conditions configuration. For the investigation of the daily tracking frequency effect, three cases (full support, DSN 4 pass/day and KDSA 4 pass/day, and DSN 2 pass/day and KDSA 2 pass/day) are prepared. For the elevation cut-off angle effect, two situations, which are 5 deg and 10 deg, are assumed. Three cases (0%, 30%, and 50% of degradation) were considered for the tracking measurement accuracy effect. Three cases such as no missing, 1-day KDSA missing, and 2-day KDSA missing are assumed for tracking failure effect. For OD, a sequential estimation algorithm was used, and for the OD performance evaluation, position uncertainty, position differences between true and estimated orbits, and orbit overlap precision according to various ground supporting conditions were investigated. Orbit prediction accuracy variations due to ground tracking conditions were also demonstrated. This study provides a guideline for selecting ground tracking support levels and preparing a backup plan for the KPLO lunar mission phase.

show abstract

Section: Measurement Simulationmentioning

confidence: 99%

“…Numerous studies of KPLO OD has been progressed and delivered useful results for both Earth-Moon translunar trajectory and lunar mission orbits. Arc-length selection strategies for both phases were investigated for better orbit accuracy (Kim et al 2018a;. The OD simulations for the total KPLO mission duration were established .…”

Section: Introductionmentioning

confidence: 99%

Ground Tracking Support Condition Effect on Orbit Determination for Korea Pathfinder Lunar Orbiter (KPLO) in Lunar Orbit

Kim¹,

Song²,

Park³

et al. 2020

Journal of Astronomy and Space Sciences

View full text Add to dashboard Cite

show abstract

Overview of the Flight Dynamics Subsystem for Korea Pathfinder Lunar Orbiter Mission

et al. 2021

View full text Add to dashboard Cite

Korea’s first lunar mission, the Korea Pathfinder Lunar Orbiter (KPLO), aims to launch in mid-2022 via the Space-X Falcon-9 launch vehicle. For the successful flight operation of KPLO, the Korea Aerospace Research Institute (KARI) has designed and developed the Flight Dynamics Subsystem (FDS). FDS is one of the subsystems in the KPLO Deep-Space Ground System (KDGS), which is responsible for the overall flight dynamics-related operation. FDS is currently successfully implemented and meets all of the requirements derived from the critical design phases. The current work addresses the design and implementation results for the KPLO FDS. Starting from overviews on KPLO payloads, bus systems, and mission trajectory characteristics, a review on KDGS is also treated briefly. Details on the design philosophy, unique characteristics, and functionalities of all six different modules nested inside the FDS with its Graphical User Interface (GUI) design are discussed. Moreover, efforts currently devoted to the flight operation preparation of the KPLO are summarized, including many collaborative works between KARI and the National Aeronautics and Space Administration (NASA) teams.

show abstract

Observational Arc-Length Effect on Orbit Determination for KPLO Using a Sequential Estimation Technique

Cited by 2 publications

References 24 publications

Ground Tracking Support Condition Effect on Orbit Determination for Korea Pathfinder Lunar Orbiter (KPLO) in Lunar Orbit

Ground Tracking Support Condition Effect on Orbit Determination for Korea Pathfinder Lunar Orbiter (KPLO) in Lunar Orbit

Overview of the Flight Dynamics Subsystem for Korea Pathfinder Lunar Orbiter Mission

Contact Info

Product

Resources

About