Development of a computer model for calculating the elements of an unperturbed orbit based on satellite observations from a point on the Earth's surface
Автор: Dastanbek Rakhmetbekov • Октябрь 3, 2023 • Контрольная работа • 695 Слов (3 Страниц) • 167 Просмотры
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PROJECT
on the discipline: "Spacecraft dynamics and control"
on the topic: "Development of a computer model for calculating the elements of an unperturbed orbit based on satellite observations from a point on the Earth's surface"
Done:
Rakhmetbekov D.T.
Supervisor:
Sukhenko A.S.
Almaty, 2021
Contents of the project report
№ | Contents | |
1 | Introduction | |
2 | Method of research | |
2.1 | Execution of the work | |
2.2 | Results of the research | |
3 | Conclusion | |
4 | List of references |
- Introduction
Problem statement. Observations of the satellite were made, distances to its three instantaneous positions and topocentric directions from the point of the earth's surface were determined. It is necessary to calculate the elements of the satellite's orbit and develop a computer model in the MATLAB application packages.
- Method of research
2.1. Execution of the work
I step. Calculation of satellite orbit elements. To do this, we use a modification of the classical Gauss method.
Initial data
1) Time point (36000 s)
Position of the Artificial Earth Satellite (AES):
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2) Time point (36300 s)
Position of the Artificial Earth Satellite (AES):
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2) Time point (36600 s)
Position of the Artificial Earth Satellite (AES):
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Solution
1. Right ascension (Fig. 1):
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Fig. 1
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2. Inclination (Fig. 2):
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Fig. 2
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3. Distance of AES (Fig. 3):
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Fig. 3
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4. Angle of inclination of the orbit plane to the equator plane (Fig. 4):
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Fig. 4
5. Longitude of the ascending node (Fig. 5):
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Fig. 5
6. Latitude argument (Fig. 6):
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Fig. 6
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7. Focal parameter (Fig. 7):
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Fig. 7
8. True anomaly (Fig. 8):
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Fig. 8
9. Orbital eccentricity (Fig. 9):
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Fig. 9
10. Pericenter argument (Fig. 10):
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Fig. 10
11. Major semi-axis (Fig. 11):
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Fig. 11
12. Mean motion (Fig. 12):
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Fig. 12
13. Eccentric anomaly (Fig. 13):
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Fig. 13
14. Moment of passing through the pericenter (Fig. 14):
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Fig. 14
15. Initial value of the average anomaly (Fig. 15):
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Fig. 15
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Fig. 16. A fragment of the code for calculating the elements of the satellite's orbit on the MATLAB application software package
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