PHYSICS-BASED ASCENT & ORBITAL-STATE ANALYSIS
Launch Vehicle
Analyzer
A transparent framework for modeling launch vehicle ascent from the lower atmosphere to final orbital-state analysis, with assumptions, equations, and model boundaries kept visible.
- Dynamics
- 2D
- Atmosphere
- Lower model
- Integrator
- RK4
- Staging
- Serial
- Orbit
- Planar 2-body
02 / SYSTEM
HOW THE SIMULATION WORKS
A launch is a coupled physical system.
The vehicle state is propagated through interacting environment, force, guidance, numerical integration, staging, and orbital-analysis models.
03 / FLIGHT
FOLLOW THE VEHICLE
From dense atmosphere to orbital state.
01 / LIFTOFF
Propulsion begins changing the vehicle state.
Gravity, thrust, mass flow, and the lower atmosphere immediately interact.
- propulsion
- gravity
- atmosphere
02 / ATMOSPHERIC FLIGHT
Density and Mach shape aerodynamic loading.
Relative airspeed, speed of sound, dynamic pressure, and Cd determine drag.
- atmosphere
- aerodynamics
- guidance
03 / STAGE EVENT
Continuous integration meets a discrete event.
Burnout is detected, the step is split safely, and discarded stage mass is removed.
- integrator
- staging
- dynamics
04 / ORBITAL STATE
Position and velocity determine the resulting orbit.
Energy, angular momentum, eccentricity, periapsis, and apoapsis describe the final state.
- orbit
- state analysis
04 / PHYSICS
INSIDE THE PHYSICS ENGINE
Model scope, without pretending at false precision.
Select a model to inspect what it receives, what it computes, and where its assumptions stop.
01
IMPLEMENTED
GRAVITY MODEL
Central spherical-Earth gravity
- Relation
- g = μ / r²
- Input
- Earth-centred position
- Output
- Acceleration vector
- Module
gravity.js
MODEL BOUNDARY
J2, oblateness, third-body gravity, and local terrain effects are not modeled.
05 / TRACEABILITY
TRANSPARENT BY DESIGN
A value should never enter the model anonymously.
Vehicle data can distinguish published, derived, estimated, and assumed values, with confidence recorded separately.
06 / ARCHITECTURE
MODULAR BY RESPONSIBILITY
The numerical integrator does not know it is flying a rocket.
Physics remains replaceable and inspectable; continuous state propagation stays separate from discrete stage events.
DATAvehicle-model.js
MODELgravity.js
MODELatmosphere.js
MODELpropulsion.js
MODELaerodynamics.js
CONTROLguidance.js
COREdynamics.jsgravity + thrust + drag → state derivatives
SOLVERintegrator.js
EVENTSstaging.js
ANALYSISorbit.js
NEXT SYSTEM
From physical assumptions to orbital state.
The analyzer interface connects vehicle definition, trajectory telemetry, staging events, and final orbital analysis.