Continuous communications for the lunar farside: How do we get there? A differentially corrected halo transfer orbit

1996 ◽  
Author(s):  
Paul Merritt
Keyword(s):  
Lunar Farside ◽  
Transfer Orbit

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

2021 ◽  
Vol 2 (1) ◽  
Author(s):  
Tao Shi ◽  
Xuebin Zhuang ◽  
Liwei Xie
Keyword(s):  
Global Navigation Satellite System ◽  
Autonomous Navigation ◽  
Satellite System ◽  
Earth Orbit ◽  
Navigation Satellite ◽  
Geostationary Earth Orbit ◽  
Beidou Navigation Satellite System ◽  
Transfer Orbit ◽  
High Orbit ◽  
Global Navigation Satellite

AbstractThe 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.

Optimal Reentry Time Estimation of an Upper Stage from Geostationary Transfer Orbit

2010 ◽  
Vol 47 (4) ◽  
pp. 686-690 ◽  
Author(s):  
M. Mutyalarao ◽  
Ram Krishnan Sharma
Keyword(s):  
Time Estimation ◽  
Transfer Orbit ◽  
Upper Stage

Application and Research of Data Interface Synchronization on Web Maintenance

2014 ◽  
Vol 1049-1050 ◽  
pp. 1803-1807
Author(s):  
Xiao Yang Liu ◽  
Jian Ping Zhao ◽  
Qing Mei Li ◽  
Wei Wang ◽  
Ran Ding ◽  
...  
Keyword(s):  
Data Processing ◽  
Real Time ◽  
Incremental Maintenance ◽  
Synchronization Mechanism ◽  
Materialized View ◽  
Maintenance System ◽  
Transfer Orbit ◽  
Database Technology ◽  
Orbit Segment ◽  
The Web

To adapt to the changing requirement of task data interface under the situation of far distance, multiple segment, multiple circle, multiple satellite and multi-station visibility for satellite misson in transfer orbit segment, the web incremental maintenance system based on materialized view was achieved through applying incremental maintenance principle, database technology, synchronization mechanism and maintenance proxy, and realizing the synchronization and consistency of data interface about the distributed experiment information surveillance software system. The result shows that web incremental maintenance system can ensure the real-time and consistency of data processing and transmission.

scholarly journals The Hipparcos Mission: Will it be a Scientific Success?

1990 ◽  
Vol 123 ◽  
pp. 27-33
Author(s):  
M.A.C. Perryman
Keyword(s):  
Routine Data ◽  
High Energy ◽  
High Energy Particle ◽  
Scientific Success ◽  
Ground Station ◽  
Solar Arrays ◽  
Transfer Orbit ◽  
The One ◽  
Scientific Value ◽  
Data Reductions

AbstractThe Hipparcos astrometry satellite was launched on 8 August 1989, and after spacecraft and payload commissioning, commenced the routine data acquisition phase on 26 November 1989. Having failed to reach its planned geostationary orbit, major revisions in the mission operations were made, and the post-launch expectations of the mission were strongly degraded with respect to the original goals - principally due to the greatly reduced observational efficiency (caused by the lack of ground station coverage) and the anticipated degraded mission lifetime (as a result of the high-energy particle degradation of the solar arrays in the geostationary transfer orbit).The final astrometric accuracies attainable by the Hipparcos mission will be influenced by the spacecraft and payload performances on the one hand, and by fraction of useful data and mission lifetime on the other. It will be shown that the elemental observational measurements correspond very closely to the predictions, and the data recovery fraction now stands at around 60–70 per cent, so that the ultimate scientific value of the Hipparcos results will be tied directly to the satellite lifetime. A measurement duration of at least 18 months is mandatory if the astrometric parameters (parallaxes and proper motions) are to be decoupled through the data reductions procedures. A somewhat longer lifetime (2.5–3 years) is necessary in order to reduce the errors on the astrometric parameters to the astrophysically-significant accuracies of around 2 milli-arcsec.It will be shown that the present indications of the satellite performances, and the significant progress already made in the data reductions, indicate that the difficulties of the ‘revised’ Hipparcos mission have been largely overcome, and that these target accuracies could still be achievable.

Orbit Plan Method for General Rendezvous Problems

2014 ◽  
Vol 543-547 ◽  
pp. 1385-1388
Author(s):  
Xu Min Song ◽  
Yong Chen ◽  
Qi Lin
Keyword(s):  
Optimization Problem ◽  
Planning Problem ◽  
Shooting Technique ◽  
Lambert Problem ◽  
Orbit Perturbation ◽  
Eccentric Orbits ◽  
Rendezvous Problem ◽  
Transfer Orbit ◽  
Adaptive Simulated Annealing ◽  
Annealing Method

The orbit plan method of rendezvous mission was studied in this paper. We are concerned with the general rendezvous problem between two satellites which may be in non-coplanar, eccentric orbits, considering orbit perturbation and rendezvous time limitation. The planning problem was modeled as a nonlinear optimization problem, and the adaptive simulated annealing method was used to get the global solution. The Lambert algorithm was used to compute the transfer orbit, so that the endpoint constraint of rendezvous was eliminated. A shooting technique was used to solve the perturbed lambert problem. The method was validated by simulation results.

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