Meysam Mahooti
University of Tehran
MATLAB
Spoken Languages:
English
Professional Interests:
Numerical Integration and Differential Equations, Least Squares, Aerospace and Defense, Satellite and Orbital Mechanics
Statistics
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Download any 10 unique submissions
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Awarded to Meysam Mahooti on 16 Nov 2017
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Feeds
Submitted
Jacchia-Bowman Atmospheric Density Model
Computation of the total mass density of the atmosphere using the Jacchia-Bowman model
2 days ago | 21 downloads |
Submitted
High Precision Orbit Propagator
Precise modeling of satellite's perturbed motion (special perturbations approach)
2 days ago | 59 downloads |
Submitted
Satellite Orbit Modeling
Precise modeling of satellite's perturbed motion (special perturbations approach)
2 days ago | 40 downloads |
Submitted
Real-Time Orbit Determination
Real-Time Orbit Determination based on GPS Navigation Data
3 days ago | 22 downloads |
Submitted
Relay Satellite Orbit Determination
Orbit Determination from Tracking and Data Relay Satellite Measurements
5 days ago | 16 downloads |
Submitted
NASA JPL Development Ephemerides (DE430)
DE430 spans from 1549-12-21 to 2650-01-25 and is based on the International Celestial Reference Frame (version 2.0).
18 days ago | 20 downloads |
Submitted
Runge-Kutta-Fehlberg (RKF78)
Fehlberg's 7th and 8th Order Embedded Method
20 days ago | 19 downloads |
Submitted
NRLMSISE-00 Atmosphere Model
Computation of neutral temperature and densities in Earth's atmosphere from ground to thermospheric heights.
21 days ago | 53 downloads |
Submitted
SGP8
The SGP8 model to calculate orbital state vectors of near-Earth satellites
4 months ago | 13 downloads |
Submitted
Sun Position (VSOP87)
VSOP87 defines the analytical solutions to the motions of the solar system planets
4 months ago | 2 downloads |
Submitted
Moon Position
Position of the Moon referred to the mean equator and equinox of J2000
4 months ago | 4 downloads |
Submitted
ECI2ECEF & ECEF2ECI Transformations
The transformation from celestial to terrestrial reference system and vice versa
4 months ago | 20 downloads |
Submitted
Sun Position
Geocentric equatorial position of the Sun (in [m]), referred to the ICRF
4 months ago | 12 downloads |
Submitted
Radau IIA
Variable-order Radau IIA integrator with step-size control
6 months ago | 7 downloads |
Submitted
Satellite Visibility
Propagation of the satellite's state vector using SGP4 and checking its visibility for future
8 months ago | 10 downloads |
Submitted
NASA JPL Development Ephemerides (DE405)
DE405 covers 1599-12-09 to 2201-02-20. Referred to the International Celestial Reference Frame.
8 months ago | 10 downloads |
Submitted
Initial orbit determination
Initial orbit determination (two sets of range and angle measurements of a satellite)
8 months ago | 6 downloads |
Submitted
Initial Orbit Determination (Least Squares Method)
Initial orbit determination applying the Least Squares method
10 months ago | 17 downloads |
Submitted
Initial Orbit Determination (Angles-Only Method)
Angles-only approach applying the Least Squares method
10 months ago | 6 downloads |
Submitted
NASA JPL Development Ephemerides (DE440)
High precision planetary ephemerides
10 months ago | 7 downloads |
Submitted
NASA JPL Development Ephemerides (DE441)
High-precision computation of planetary ephemerides
12 months ago | 11 downloads |
Submitted
Lambert's Problem
Lambert’s problem is the orbital boundary-value problem constrained by two points and elapsed time.
1 year ago | 17 downloads |
Submitted
Sunrise Sunset
Rising and setting times of the Sun and the Moon and twilight times
1 year ago | 4 downloads |
Submitted
Sunrise Sunset
Rising and setting times of the Sun and the Moon and twilight times
1 year ago | 5 downloads |
Submitted
Initial Orbit Determination (Extended Kalman Filter)
Initial orbit determination applying the Extended Kalman Filter
1 year ago | 19 downloads |
Submitted
Double-r Initial Orbit Determination
Double-r method is utilized to determine the initial orbit.
1 year ago | 3 downloads |
Submitted
Gauss Initial Orbit Determination
Gauss's method is utilized to determine the initial orbit.
1 year ago | 15 downloads |
Submitted
SGP4
The SGP4 model to calculate orbital state vectors of near-Earth satellites
1 year ago | 87 downloads |
Submitted
Moon Phases
Determination of lunar phases and checking for eclipses
1 year ago | 7 downloads |
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