Flight dynamic model for low earth orbit satellites
Alshamy, H., Makled, A., Elhalwagy, Y., Hendy, H. (2019). Flight dynamic model for low earth orbit satellites. EKB Journal Management System, 18(18), 1-12. doi: 10.1088/1757-899X/610/1/012100
Hossam Mohamed Alshamy; Ah. El-S. Makled; Y Elhalwagy; Hossam Hendy. "Flight dynamic model for low earth orbit satellites". EKB Journal Management System, 18, 18, 2019, 1-12. doi: 10.1088/1757-899X/610/1/012100
Alshamy, H., Makled, A., Elhalwagy, Y., Hendy, H. (2019). 'Flight dynamic model for low earth orbit satellites', EKB Journal Management System, 18(18), pp. 1-12. doi: 10.1088/1757-899X/610/1/012100
Alshamy, H., Makled, A., Elhalwagy, Y., Hendy, H. Flight dynamic model for low earth orbit satellites. EKB Journal Management System, 2019; 18(18): 1-12. doi: 10.1088/1757-899X/610/1/012100

Flight dynamic model for low earth orbit satellites

International Conference on Aerospace Sciences and Aviation Technology
Article 101, Volume 18, Issue 18, April 2019, Page 1-12  XML PDF (1.32 MB)
Document Type: Original Article
DOI: 10.1088/1757-899X/610/1/012100
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Authors
Hossam Mohamed Alshamy1; Ah. El-S. Makled2; Y Elhalwagy3; Hossam Hendy3
1Egyptian Armed Forces Space Technology Center
2Space Technology Center, Cairo, Egypt.
3Guidance Department, Military Technical College, Cairo, Egypt.
Abstract
Low Earth Orbit satellite(LEO) missions have potentially attractive features such as low launch cost, and wide remote sensing applications.
There are three vital missions during the satellites life time including orbit transfer from the parking to the operating orbit, maintaining the operating orbit and de-orbiting mission to a disposal orbit at the end of the satellite lifetime according to the standard disposal orbit law. The mathematical model has been implemented to study various LEO mission orbits including the three vital missions.
The mathematical model evaluates the required performance parameters, velocity budget, number of manoeuvers, duration and consumed propellant mass for each mission.
The mathematical algorithm is carried out using Matlab/Simulink, the complete mathematical flight dynamic model has been verified through comparisons with the generated mission scenarios from Satellite Tool kit (STK), the graphical user interface is designed to display the model.
The carried out algorithm can be applied in satellite mission design to help predicting the parameters for each mission to minimize the risks and intensive tests. it can be considered as powerful tool to design and analysis LEO satellite missions
Keywords
Satellite dynamic; flight dynamic model; space mission; deorbiting; orbit transfer
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