Launch Location
Launch Latitude (deg)
Orbit Inclination (deg)
Calculated:
Orbit Parameters
Target Orbit Height (km)
Calculated: Circular Orbit Speed m/s
Min Orbit Drag (mN)
Integration Step
dt (ms)
Time Scale
Graphics
max ALT (km)
Notes:
Specific Impulse Isp (s) - typically 250 s for H2/O2 propellant and 320 s for hypergolic (OMS) N Engine NE - number of individual engines based on maximum fuel flow of 350 kg/s per engine Stage Delay Tss (s) - delay between engine cut off and stage separation Stage Fire Tsf (s) - delay between engine cut off and engine start of next stage Tsiolkovsky ΔV (m/s) - theoretical change in velocity without atmospheric drag Trajectory Δγ (deg) - estimated pitchover angle. Try to keep near, but less than, 90 degrees for orbit insertion minimum fuel.
Rocket Simulator
This is a rocket simulation using Newtonian mechanics.
Press launch to go - starting at T - 10 s.
The simulation uses the gravity trajectory and is very sensitive to pitchover velocity, and thrust/weight ratio of each stage.
These parameters can be set in the DESIGN section. Aerodynamic drag and heating is predicted.
Atmospheric properties are the US Standard 1976. Default fuel is liquid H2 and O2 with a specific impulse (Isp)
= 250 s. Use the OMS system to adjust orbit altitude and velocity - or leave under computer guidance Automatic OMS.
Orbit acceleration r̈ should be near zero for circular orbit.
The default setup should get you into orbit in about 8 minutes. Most of the OMS fuel will be used up. Click the DESIGN button for details.
To change orbit - turn off Automatic OMS after reaching initial orbit, adjust throttle, and apply thrusters as desired.