Autonomous orbit determination for future GEO and HEO missions

Lorga, J.F.M.; Silva, P. F.; Dovis, Fabio; Cintio, A. Di; Kowaltschek, S.; Jiménez, David González; Jansson, R.

doi:10.1109/navitec.2010.5708028

Cited by 21 publications

(9 citation statements)

References 2 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In this study, the +Z direction antenna gain Gr(ϕ) is set to 10 dB at 0° and approximately − 0.75 dB at 40°. To simplify the model, the gain for the receiving angle greater than 40° is considered as − 1.8 dB (Lorga et al 2010). Considering that the EIRP of each GNSS satellite is different due to different generations and various years in orbit, according to the references (Liu et al 2016(Liu et al , 2017Steigenberger et al 2017;Thoelert et al 2019), the EIRP settings of each GNSS in the paper are given in Fig.…”

Section: Figmentioning

confidence: 99%

“…Palmerini (2014) pointed out that under the combination of dual navigation systems, the signals obtained are usually extremely weak and have a short duration for the receiver at very high altitude so that the receiver needs to work in snapshot mode and the operation is highly dependent on its software algorithm and hardware resources. Due to a limited number of visible satellites with double GNSSs, most researches focused on the method of orbit filtering or satellite selection algorithm to analyze the autonomous navigation of GEO or High Elliptic Orbit (HEO) spacecraft for improving its accuracy (Lorga et al 2010;Zou et al 2019). Wang (2019) also developed GNSS receiver based on GPS and BDS and focused on the processing of navigation signals, e.g.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Performance evaluation of multi-GNSSs navigation in super synchronous transfer orbit and geostationary earth orbit

2021

View full text Add to dashboard Cite

The autonomous navigation of the spacecrafts in High Elliptic Orbit (HEO), Geostationary Earth Orbit (GEO) and Geostationary Transfer Orbit (GTO) based on Global Navigation Satellite System (GNSS) are considered feasible in many studies. With the completion of BeiDou Navigation Satellite System with Global Coverage (BDS-3) in 2020, there are at least 130 satellites providing Position, Navigation, and Timing (PNT) services. In this paper, considering the latest CZ-5(Y3) launch scenario of Shijian-20 GEO spacecraft via Super-Synchronous Transfer Orbit (SSTO) in December 2019, the navigation performance based on the latest BeiDou Navigation Satellite System (BDS), Global Positioning System (GPS), Galileo Navigation Satellite System (Galileo) and GLObal NAvigation Satellite System (GLONASS) satellites in 2020 is evaluated, including the number of visible satellites, carrier to noise ratio, Doppler, and Position Dilution of Precision (PDOP). The simulation results show that the GEO/Inclined Geo-Synchronous Orbit (IGSO) navigation satellites of BDS-3 can effectively increase the number of visible satellites and improve the PDOP in the whole launch process of a typical GEO spacecraft, including SSTO and GEO, especially for the GEO spacecraft on the opposite side of Asia-Pacific region. The navigation performance of high orbit spacecrafts based on multi-GNSSs can be significantly improved by the employment of BDS-3. This provides a feasible solution for autonomous navigation of various high orbit spacecrafts, such as SSTO, MEO, GEO, and even Lunar Transfer Orbit (LTO) for the lunar exploration mission.

show abstract

Section: Figmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Performance evaluation of multi-GNSSs navigation in super synchronous transfer orbit and geostationary earth orbit

2021

View full text Add to dashboard Cite

show abstract

“…While the defined space service volume and hardware with space flight heritage are GPS-only, making use of the other constellations has already been shown to have significant benefits for GEO and HEO navigation [6][7][8]. One possible source of navigation signals that has yet to be explored for use in HEO and GEO is the satellite-based the future, L5 frequencies.…”

Section: Introductionmentioning

confidence: 99%

An Analysis of SBAS Signal Reception in Space

2016

View full text Add to dashboard Cite

WAAS, EGNOS, GAGAN, and MSAS data have been collected from the CanX‐2 CubeSat. The suitability of SBAS for navigation in geostationary orbits (GEO), where SBAS satellites may be permanently in view, was assessed. The analysis revealed that all tracked SBAS transmit enough power to be tracked over Earth's limb. GAGAN has the narrowest gain pattern, WAAS has a similar pattern to EGNOS but a 2–4 dB higher transmit power, and MSAS has the lowest signal power but more even global coverage, with stronger power transmitted towards the edge of the Earth. SBAS ranging typically agrees with GPS single‐point positions to within +/−10 m for WAAS and +/−20 m for MSAS and GAGAN. It was determined that the SBAS ranging capability is useable in GEO and other high orbits, provided that fast correction data are applied to the broadcast ephemeris, and the lower accuracies are accounted for. Copyright © 2016 Institute of Navigation

show abstract

“…In a study completed for the European Space Agency, Lorga [63] concluded that successful GPS-based navigation on HEO would require the reception of side-lobe signals. Such reception has been demonstrated in GEO [64] and in HEO [65].…”

Section: Refining the Link Budget: Side-lobesmentioning

confidence: 99%

“…• a 2010 simulation study by Lorga et al [63] which incorporated advanced tracking algorithms and signals from the Galileo constellation to achieve 20 m (3D 1σ) accuracy in HEO; and…”

Section: Kalman Flight Heritagementioning

confidence: 99%

Nonlinear Filtering for Autonomous Navigation of Spacecraft in Highly Elliptical Orbit

Vigneron¹

View full text Add to dashboard Cite

To fill a gap in satellite services for the Canadian Arctic, the Canadian Space Agency has proposed a Polar Communication and Weather (PCW) mission to be flown in a highly elliptical Molniya orbit. In an era of increasingly capable space hardware, autonomous satellite navigation has become a standard means by which satellites in low Earth orbit can increase their independence and functionality. This study examined the accuracy to which autonomous navigation might be realized in a Molniya orbit.Using appropriate physical force models and simulated pseudorange signals from the Global Positioning System (GPS), a navigation algorithm based on the Extended Kalman Filter was demonstrated to achieve a three-dimensional root-mean-square accuracy of 58.9 m over a 500 km ¢ 40 000 km Molniya orbit. This accuracy satisfied the requirements of the PCW mission and demonstrated the utility of GPS signal reception at high altitudes. Algorithms based on the Unscented Kalman Filter and the Cubature Kalman Filter were not found to improve this result; this was due to a high frequency of measurements during periods of highly nonlinear dynamics.During this study, detailed models were developed for GPS pseudorange errors, including ephemeris errors, transmitter clock errors, and ionospheric delay. Receiver clock bias error was shown to be a significant source of navigation solution error; for reasons of geometry, the navigation algorithm is not able to differentiate between this error and a radial position error. GPS sidelobe signals were shown to be an effective means to acquire additional GPS signals over the highly elliptical orbit. Finally, an exploratory study found ground-based radio beacons to be a useful navigation aid for this orbital regime.

show abstract

Autonomous orbit determination for future GEO and HEO missions

Cited by 21 publications

References 2 publications

Performance evaluation of multi-GNSSs navigation in super synchronous transfer orbit and geostationary earth orbit

Performance evaluation of multi-GNSSs navigation in super synchronous transfer orbit and geostationary earth orbit

An Analysis of SBAS Signal Reception in Space

Nonlinear Filtering for Autonomous Navigation of Spacecraft in Highly Elliptical Orbit

Contact Info

Product

Resources

About