Launch simulation of a launch vehicle
Trajectory to low Earth orbit
First overview by ScienceInsight
Article SI16
The stability of a rocket during its flight into space is crucial for a successful launch and reaching the desired orbit. Here are some important design features that help ensure a rocket’s stability.
Center of Mass (CoM):
The center of mass is the point where the entire mass of the rocket is concentrated. It must be located in front of the center of pressure (aerodynamics) to ensure stability. A forward-biased center of mass ensures that the rocket remains nose-first during flight.
Aerodynamic Stability:
The rocket is aerodynamically designed to be stabilized by air resistance. This is often achieved through the shape of the fuselage and nose cone.
Stabilizing fins at the rear of the rocket also contribute to aerodynamic stability.
Thrust vectoring:
Modern launch vehicles have swiveling nozzles (thrust vectoring) to direct thrust in different directions. This allows control over the flight direction.
Physical implementation
Physical model:: 2-stage launch vehicle. Physically plausible scaling and visually practical. The simulation will be written in Python.
Scaling
- Simulation window: 1920 x 1080 px
- Scaling: 1.3 meters = 10 pixels ⇒ 1 meter = 7.69 pixels
- Rocket height = 28 meters
- Visibility*: max. visible height = 1080 px / 7.69 px/m ≈ 140 meters
- v(t) : interpolated
*) This is sufficient for the landing approach and first-stage maneuvers (usually stabilized at <100 m altitude)
- Constants:
- Gravitation: g = 9.81 m/s²