Astrodynamics Orbital Maneuver Simulator
Propagates 2-impulse and continuous-thrust orbital transfers with gravitational Ephemeris models.
Aerospace & Aeronautical Engineering / Hohmann Orbital Transfer
FREE TO EXPLORELABORATORY 42 · AEROSPACE & AERONAUTICAL ENGINEERING
Hohmann Coplanar Orbital Transfer and Delta-V Velocity Budgets
Calculate impulse velocity increments Delta V_1 and Delta V_2 required to transfer between circular orbits and evaluate delta-v budgets across orbit radius ratios. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
FIRST BURN DELTA V_1—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with x_radius = 0.2 dimensionless.
Adjust x_radius, then execute aerospace trial.
Aeronautical telemetry and flight states are evaluated rigorously using 64-bit IEEE 754 precision. Residuals reflect ordinary least-squares regression across successive observations. Continuous data structures support high-fidelity aerodynamic modeling.
Aeronautical assumptions and boundary condition limits
Hohmann transfer assumes impulsive (infinitesimally short) velocity changes; continuous low-thrust ion engines require spiral trajectories. Linear regression of the first-burn velocity increment Delta V_1 against the radius parameter yields a baseline circular velocity v_1 = 7.7800 km/s with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
Spacecraft Liquid Apogee Engine (LAE) Model
Simulates bipropellant rocket engine firing (I_sp = 320 s, thrust = 450 N) with mass depletion tracking.
Tsiolkovsky Delta-V Mass Budget Calculator
Computes propellant mass fractions and payload capacity from the rocket equation.
3D Inertial Orbit State Visualizer
Renders initial circular orbit, elliptical transfer trajectory, and final target circular orbit.
Porkchop Plot Interplanetary Trajectory Tool
Evaluates launch energy C3 and arrival v_inf across launch windows (e.g. Earth to Mars).
Orbital Telemetry Station
Logs velocity increments Delta V_1, Delta V_2, transfer flight times, and orbital element changes.
FOLLOW THE METHOD
A reason behind every step.
Calculate impulse velocity increments Delta V_1 and Delta V_2 required to transfer between circular orbits and evaluate delta-v budgets across orbit radius ratios. Standardized parameter settings: 0.08, 0.14, 0.2, 0.26, 0.32, 0.38 dimensionless.
01
Initial LEO Orbit Configuration
Set initial circular Low Earth Orbit at altitude h_1 = 300 km (r_1 = 6678.14 km), confirming circular speed v_1 = 7.780 km/s.
02
Target Orbit Altitude Stepping
Define target circular orbit radii r_2 corresponding to parameter x = sqrt(2*r_2/(r_1+r_2)) - 1 = 0.08, 0.14, 0.20, 0.26, 0.32, and 0.38.
03
First Tangential Burn Execution
Apply impulsive tangential burn Delta V_1 at periapsis to inject spacecraft into the Hohmann transfer ellipse.
04
Transfer Orbit Propagation
Propagate the spacecraft along the elliptical arc over transfer time t_trans = pi * sqrt(a_trans^3 / mu) until apoapsis arrival.
05
Second Circularization Burn
Apply circularizing impulse Delta V_2 at apoapsis to match target circular speed v_2, recording total delta-v budget.
06
Delta-V Linear Regression
Plot Delta V_1 versus the radius parameter x, perform linear regression to determine slope v_1 = 7.780 km/s, and verify Tsiolkovsky propellant mass.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Hohmann Orbital Transfer mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
\Delta V_1 = v_1 \left[\sqrt{\frac{2 r_2}{r_1 + r_2}} - 1\right] \implies \Delta V_1 = m \cdot x + b
| # | Transfer Radius Parameter (dimensionless) | First Burn Delta V_1 (km/s) | Radius Ratio Parameter sqrt(2*r_2 / (r_1+r_2)) - 1 | First Burn Velocity Increment Delta V_1 (km/s) | Remove |
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