main.py : contains main loop of the simulation

constants.py : contains all constants

frames.py : contains frame conversions

qnv.py : contains functions of attitude kinematics

satellite.py : contains declaration of satellite object

constants_1U.py: contains constants for 1U satellite simulation

constants_2U.py: contains constants for 2U satellite simulations

dynamics.py : contains quaternion kinematics equation and euler dynamics equation for body-ecif frames

getorbitdata.py : contains code for generating position and velocity data for orbit in eci frame using SGP4 model

test_--.py : The test codes for respective .py files.

Python Code to use IGRF

  from pyigrf12 import runigrf12
  z1 = 0
  z2 = 1
  B = runigrf12(day,z1,z2,height,lat,lon)
  #B : in nano tesla in NED frame. first 3 components are Bn, Be, Bd and fourth is 2-norm of B
  #day declared using datetime module in python
  #z1 : indicates we want magnetic field (we can also get the secular variation using 1 instead of 0 here)
  #z2 : indicates the height is given in km above sea level
  #height : height in km above sea level i.e. altitude
  #lat : latitude
  #lon : longitude