This is a simplified model for a rocket trajectory going into LEO (Low Earth Orbit) in python, taking as reference the Electron from RocketLab.
From the Figure 1, the trajectory in relation to the Earth, for simplicity as said, we will ignore the Earth´s rotation and write the equations respect to a non rotating earth.
T direction:
N direction:
Drag Force
Atmospheric Density
Gravity Acceleration
LiftOff Mass (Kg) | First Stage (kN) | Second Stage (kN) | Payload (Kg) |
---|---|---|---|
13500 | 218.982 | 29.22 | 300 |
This is an early version and some values havent been modified, next updates will make this in a more realistic orbit for the Electron Rocket.