This code simulates a small satellite in orbit around the Earth. It currently includes orbital dynamics described by Kepler's Laws and attitude dynamics for a rigid body.
A Python 2 distribution is required, along with the packages numpy, matplotlib, mpl_toolkits, tqdm and math. Something like Anaconda is recommended for Windows users.
To run the simulation, run RunSim.py in the Python console. This will define an orbit using the specified orbital elements, simulate it, and plot the results. Orbital elements can be specified manually on line 20 by commenting out lines 27 and 28 or by specifying presets in the file Presets.py.
Executing RunSim without changes will simulate a satellite in the Molniya orbit, producing the following plots.
Earth properties can be edited in EarthProps.py, satellite properties in SatProps.py and universal properties in UniversalProps.py. The file OrbitModel.py describes the behaviour of the satellite in orbit and will likely break if played with. Plots.py produces the output plots and will also probably break.
- Orbital dynamics
- Attitude dynamics
- Basic plots
- 3D orbital path
- 2D ground track plot
- Time histories for satellite attitude
- Environmental disturbances
- Aerodynamic moment
- Magnetic torque
- Gravity gradient torque
- J2 gravitational effects
- Sensor systems
- Rate gyroscopes
- Magnetometer
- Sun sensor
- Control actuators
- Thrusters
- Magnetotorquer
- Reaction wheels
- Permamagnets
- Software
- Control system
- Animations
- Orbit animation
- POV near satellite animation
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