Initial Conditions

This class InitialConditions serves as a centralized configuration for initial conditions and physical constants related to a satellite orbital simulation.

index = 1 # keeping track when running different
dragCoeff = 2
crossSec = 10
satMass = 60

  • dragCoeff: Drag coefficient (dimensionless), used in atmospheric drag force calculations.

  • crossSec: Cross-sectional area of the satellite in square meters.

  • satMass: Mass of the satellite in kilograms.

earthMass = 6E+24
earthRadius = 6.37E+6
gravConstant = 6.67E-11

  • earthMass: Earth’s mass in kilograms.

  • earthRadius: Earth’s radius in meters.

  • gravConstant: Gravitational constant G.

deltaV = 80.0
initSatAlt = 400000
initSatTheta = 0.0
initSatPhi = np.pi / 2
initSatLam = 0.0
initSatRdot = 0.0
initSatPhidot = np.radians(0.0) / 1.0

  • deltaV: Initial velocity change applied to the satellite (in m/s), typically for deorbiting.

  • initSatAlt: Initial satellite altitude above Earth’s surface (in meters).

  • initSatTheta: Initial 2D angle θ (in radians).

  • initSatPhi: Initial 3D polar angle φ (in radians).

  • initSatLam: Initial 3D azimuthal angle λ (in radians).

  • initSatRdot: Initial radial velocity (ṙ) in meters per second.

  • initSatPhidot: Initial angular velocity in the φ direction (in radians per second).

populatedRadius = 50000
populatedCenters = [
    (np.radians(51.5074), np.radians(-0.1278)),
    (np.radians(40.7128), np.radians(-74.0060)),
    (np.radians(48.8566), np.radians(2.3522)),
    (np.radians(34.0522), np.radians(-118.2437)),
]
hThrust = 100000
deltaV_from_thrust = 200

  • populatedRadius: Radius of populated area on Earth’s surface (in meters).

  • populatedCenters: List of major city coordinates (latitude, longitude) in radians representing populated regions (four examples, should add more).

  • hThrust: Altitude at which additional thrust is applied (in meters).

  • deltaV_from_thrust: Increase in velocity due to thrust (in m/s).