Robust Simulation and Visualization of Satellite Orbit Tracking System

Author(s):  
Kadry Ali Ezzat ◽  
Lamia Nabil Mahdy ◽  
Aboul Ella Hassanien ◽  
Ashraf Darwish
2013 ◽  
Vol 353-356 ◽  
pp. 3456-3459 ◽  
Author(s):  
Qiao Li Kong ◽  
Jin Yun Guo ◽  
Li Tao Han

DORIS is a kind of advanced space-geodetic techniques applied in satellite orbit tracking and measuring. As the first ocean dynamic environmental satellite in China, the HY-2 satellite is equipped with the Doppler orbitography and radiopositioning integrated by satellite (DORIS) tracking system for the precise orbit determination. In particular, the investigation of our work has focused on accuracy analysis of orbit determination using simulated DORIS data given different observation noises, besides the relationship is investigated between accuracy and computation time and the number of ground beacons evenly distributed around the world. Experiment results show that observation noises can affect the accuracy of orbit determination directly, and the number of DORIS ground beacons decides the accuracy and computation time of obit determination in the condition of ground beacons are evenly distributed around the world, therefore, during the process of obit determination, we should optimize the ground beacon station distribution to achieve the best accuracy of obit determination using DORIS tracking data.


The announcement by President Eisenhower in August, 1955 that the United States were including in their programme for the International Geophysical Year the launching of artificial earth satellites, was received with great interest in this country and elsewhere. There was some disappointment felt when, some months later, the proposed inclination (40°) of the satellite orbit was announced, for it was realized that there would be few opportunities available for observation of such satellites from Britain. The satellite subcommittee set up by the British National Committee for the International Geophysical Year to deal with all matters concerned with satellites, did not feel justified in planning any considerable observa­tional activities in relation to the proposed American satellites, at least as far as stations in Britain were involved. The possibility of using radar detection was examined and development began of radio-interferometers operating on the fre­quency 108 Mc/s chosen by the Americans for their satellite radio beacons. Meanwhile, at the I. G. Y. conference at Barcelona in September 1956 the Russian delegation made the official announcement that the U. S. S. R. also proposed to launch satellites containing scientific instruments during the I. G. Y. No other details were given, but a recommendation was approved at the conference that the beacon frequencies of all satellites should be chosen to be compatible with the American tracking system. By June of 1957 it became known that the proposed inclinations of the Russian satellite orbits would be much greater (about 65°) than that of the American so observation would certainly be possible from Britain. Information about the beacon frequencies was not immediately forthcoming but by the end of July it was confirmed that these could be 20 and 40 Mc/s, quite different from that chosen by the U. S. A. As this entailed considerable changes in the design of receiving equipment it was decided to wait until after the forthcoming I. G. Y. conference on Rockets and Satellites planned to be held in Washington from 30 September to 5 October 1957. In fact, as we all know, the first satellite was launched by the Russians on 4 October, the evening of the last full day of the conference—the announcement was actually made by Dr Berkner, the American organizer of the conference and I. G. Y. reporter for Rockets and Satellites, at a cocktail party given by the Russian delegates in the Soviet Embassy at Washington.


1966 ◽  
Vol 25 ◽  
pp. 363-371
Author(s):  
P. Sconzo

In this paper an orbit computation program for artificial satellites is presented. This program is operational and it has already been used to compute the orbits of several satellites.After an introductory discussion on the subject of artificial satellite orbit computations, the features of this program are thoroughly explained. In order to achieve the representation of the orbital elements over short intervals of time a drag-free perturbation theory coupled with a differential correction procedure is used, while the long range behavior is obtained empirically. The empirical treatment of the non-gravitational effects upon the satellite motion seems to be very satisfactory. Numerical analysis procedures supporting this treatment and experience gained in using our program are also objects of discussion.


Author(s):  
Paul A. Wetzel ◽  
Gretchen Krueger-Anderson ◽  
Christine Poprik ◽  
Peter Bascom

1993 ◽  
Vol 9 (2) ◽  
pp. 96-100 ◽  
Author(s):  
Thomas Payne ◽  
Susan Kanvik ◽  
Richard Seward ◽  
Doug Beeman ◽  
Angela Salazar ◽  
...  

2018 ◽  
Vol 2 (1) ◽  
Author(s):  
Fatima Ameen ◽  
Ziad Mohammed ◽  
Abdulrahman Siddiq

Tracking systems of moving objects provide a useful means to better control, manage and secure them. Tracking systems are used in different scales of applications such as indoors, outdoors and even used to track vehicles, ships and air planes moving over the globe. This paper presents the design and implementation of a system for tracking objects moving over a wide geographical area. The system depends on the Global Positioning System (GPS) and Global System for Mobile Communications (GSM) technologies without requiring the Internet service. The implemented system uses the freely available GPS service to determine the position of the moving objects. The tests of the implemented system in different regions and conditions show that the maximum uncertainty in the obtained positions is a circle with radius of about 16 m, which is an acceptable result for tracking the movement of objects in wide and open environments.


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