Loading STEMORIA content
Construct an orbit from position and velocity, change that orbit with explicit delta-v burns, then move into Earth-Moon dynamics where multiple gravitating bodies shape the trajectory.
Simulation loop
Set the state, predict the path, apply a physical intervention, then audit what the equations and integrator produced.
01
Set
02
Predict
03
Burn / Run
04
Audit
STEMORIA orbital mechanics simulation
scientific model · impulsive maneuvers · time integration · 3D diagnostics
Simulation mode
One orbital-mechanics family: orbit construction, impulsive transfer, then multi-body dynamics.
Elapsed
0 s
Altitude
400 km
Speed
7.6726 km/s
Trajectory
Circular bound orbit
Energy drift
0 ppm
h drift
0 ppm
Orbital diagnostics
Eccentricity e
2.22045e-16
Periapsis
400 km
altitude above model surface
Apoapsis
400 km
altitude above model surface
Period
92.41 min
Inclination
28.5°
Specific energy
-29.434 MJ/kg
Numerical audit & model contract
Energy conservation
0 ppm
drift from the launch-state specific orbital energy
Angular momentum conservation
0 ppm
drift in |r × v| for the central-force model
a = −μr / |r|³
ε = v²/2 − μ/r
e⃗ = (v × h⃗)/μ − r⃗/|r|
Restricted Newtonian two-body model: the central spherical body is fixed at the origin and the satellite is a test particle. Integration uses velocity-Verlet. Energy and angular-momentum drift are shown live so numerical behavior is visible rather than hidden.
Atmosphere, drag, oblateness/J₂, central-body rotation, third bodies, thrust, collisions beyond the central surface, and relativistic effects are not represented in this slice. The default μ and radius are rounded Earth-scale teaching values, not a real-time ephemeris dataset.