ANALYZER / INTEGRATED PHYSICS ENGINE

Configure. Propagate. Inspect.

Define a serial-stage launch vehicle, choose the modeling assumptions, run the coupled ascent simulation, and inspect how the final orbital state was produced.

PHYSICS MODULES11

ORCHESTRATIONEvent-aware

OUTPUTOrbital state

01 / INPUT

Configuration

VEHICLE Definition Vehicle name

Payload mass kg Stages

AERODYNAMICS Mach-Cd model

The example curve is an assumed generic model, not vehicle-specific aerodynamic data. Replace it when real Cd information is available.

Mach	Cd	Remove row

GUIDANCE Open-loop profile Profile

ASSUMPTION

The generic profile is only a transparent simulator default. It is not calibrated to a real vehicle and is not operational launch guidance.

Advanced simulation settings Initial state, target orbit, solver, atmosphere

Initial state

Launch altitude m Initial tangential velocity m/s

Target orbit

Periapsis km Apoapsis km Tolerance km

Solver

Time step s Max time s Plot every N recorded states

Environment

Air velocity X m/s Air velocity Y m/s

Above 86 km atmosphere behavior

The simulation executes locally in your browser. No vehicle input is sent anywhere.

02 / OUTPUT

Analysis

Ready

TRAJECTORY

Downrange / altitude

Vehicle path Flight event

NO SIMULATION DATA Configure the vehicle and run the model.

STATUS: —
MAX ALT: —
MAX SPEED: —
MAX-Q: —
FINAL MASS: —

MAX ALTITUDE—

MAX SPEED—

MAX MACH—

MAX-Q—

PERIAPSIS—

APOAPSIS—

RESULT STATUS Awaiting simulation

The final orbital classification will appear here.

MODEL TRACE Input → model → result

01 Validate vehicle and model inputs
02 Propagate coupled state with event-safe integration
03 Analyze final position and velocity as an orbital state

Configure. Propagate. Inspect.

Analysis

Downrange / altitude

Altitude vs time

Stage-by-stage result