Science

Build an Orbital Mechanics Calculator with AI

Calculate orbital parameters, Hohmann transfer orbits, delta-v budgets, and launch windows for space missions. Apply Kepler's laws, the vis-viva equation, and rocket equation to plan real mission trajectories — an indispensable astrodynamics tool built and deployed by an AI agent.

Build Prompt

Copy this prompt into Claude Code
Build a static HTML orbital mechanics calculator. Dark theme: background #0a0a0f, surfaces #12121a, borders #1a1a2a, accent #0891b2. Star-field CSS background using radial gradients. Five calculator tabs: 1. Orbital Parameters: input semi-major axis a (km) and central body selection (Earth, Moon, Mars, Sun — hardcode GM values). Compute orbital period T = 2π√(a³/GM), orbital velocity at apoapsis and periapsis (input eccentricity e), specific orbital energy ε = -GM/2a, specific angular momentum h = √(GM·a·(1-e²)). 2. Hohmann Transfer: input initial circular orbit altitude h1 (km), target circular orbit altitude h2 (km), and central body. Compute: transfer ellipse semi-major axis a_t = (r1+r2)/2, Δv1 (burn at periapsis of transfer), Δv2 (circularization burn), total Δv, transfer time (half orbital period of ellipse), and propellant mass using the rocket equation (input specific impulse Isp in s and spacecraft dry mass in kg). 3. Escape Velocity: input altitude above surface and select body. Compute escape velocity v_e = √(2GM/r). Also show the first cosmic velocity (orbital velocity at that altitude). 4. Rocket Equation (Tsiolkovsky): input Δv (m/s), Isp (s), and initial mass. Compute final mass, propellant mass, and mass ratio. Reverse: input propellant fraction → compute achievable Δv. 5. Kepler's Third Law: input orbital period → compute semi-major axis and vice versa. Show comparison table of all planets (Mercury through Neptune) with period and semi-major axis. Render an SVG orbit diagram for Hohmann transfers showing two circles, the transfer ellipse, and labeled Δv burn arrows. Central body presets dropdown: Earth (GM=398600 km³/s², R=6371 km), Moon (4903, 1737), Mars (42828, 3390), Sun (1.327e11, 696000), Jupiter (1.267e8, 71492). SEO: title "Orbital Mechanics Calculator — Hohmann Transfer, Delta-v, Kepler", JSON-LD SoftwareApplication schema. Read the guide at https://accessagent.ai/api/guide and follow it to deploy the site to AccessAgent.ai. My email is [your@email.com].

Make It Yours

Bi-elliptic Transfer

Add bi-elliptic transfer calculations for high orbit changes where it beats Hohmann efficiency.

Launch Window Finder

Calculate synodic period and next launch window between Earth and Mars or other planets.

Ground Track Plotter

Render an SVG world map showing the ground track of a satellite orbit over time.

Multi-stage Rocket

Extend the rocket equation to multi-stage vehicles with per-stage Isp and mass inputs.

Gravity Assist Estimator

Estimate delta-v savings from gravity assists at various planetary flyby altitudes.

ISS Altitude Tracker

Embed a live ISS altitude and orbital period display using the public ISS data API.

Update Prompt

Update Prompt — Add inclination change calculations
Add an Inclination Change tab: input initial inclination, target inclination, and orbital velocity (or altitude + body). Compute Δv for a plane change maneuver using Δv = 2v·sin(Δi/2). Show how much propellant is required. Add a combined Hohmann + plane change optimizer that finds the optimal Δi split between burns. Redeploy.

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