Programming for Aerospace Engineers

Learn Python by solving real aerospace problems, orbits, trajectories, and flight dynamics.

10 projects, 250 hands-on levels, run in your browser.

Syllabus

  • Orbital Mechanics: Model how spacecraft and satellites move. You'll build up from constants and units to functions, conditionals, data structures, iteration, and finally a small orbit propagator, the same math behind every mission.
  • Atmospheric Flight: Why aircraft fly and how the air changes with altitude. You'll pick up NumPy and Matplotlib while modelling the standard atmosphere, lift and drag, and a glider's performance.
  • Rocket Performance: What it takes to reach orbit. Work through the rocket equation, mass budgets, thrust, and staging, then design a two-stage rocket that makes orbit.
  • Signals & Telemetry: Spacecraft talk in signals. Sample a waveform, add and measure noise, filter it out, and use the FFT to find a hidden tone, the foundations of telemetry.
  • Trajectory Simulation: Numerically fly a spacecraft. Build state-vector integrators from Euler to Runge-Kutta 4, compare their accuracy, and check the conservation laws that prove a simulation is trustworthy.
  • Flight Data Analysis: Turn raw flight logs into insight. Load real CSV telemetry with pandas, explore and clean it, group it by flight phase, and produce a flight report.
  • Control Systems: Hold a spacecraft's attitude steady with feedback control. Build up a PID controller term by term, see why each one matters, and tune it to meet a spec.
  • Structures & Loads: Work out whether an aerospace structure survives its loads. Start with stress in a single rod, build through beam bending, buckling, and pressure vessels, then solve a whole truss with linear algebra.
  • Optimization: Let the computer find the answer. Use SciPy to solve equations that have no formula, fit models to data, and search design spaces for the best wing, the fastest cruise, and the lightest tank.
  • Mission Design: The finale: design a complete crewed-class mission from Earth to Mars. Build the delta-v budget, launch to orbit, plan the interplanetary transfer, capture at Mars, then optimize the whole vehicle. Every tool from the track comes together here.

Key concepts

  • Circular orbital speed: The speed needed to maintain a circular orbit at radius r: v = sqrt(mu/r). Faster and the orbit stretches; slower and it decays.
  • Delta-v: The change in velocity a maneuver requires, the currency of spaceflight. Every burn (launch, transfer, capture) has a delta-v cost; the total budget sizes the…
  • Dynamic pressure: q = 0.5 * rho * v^2, the pressure of air on a moving body. Lift and drag both scale with it, making it central to aerodynamics.
  • Escape velocity: The minimum speed to escape a body's gravity from radius r without further propulsion: v = sqrt(2*mu/r) = sqrt(2) times the circular speed.
  • Hohmann transfer: The most fuel-efficient two-burn transfer between two circular coplanar orbits, via an ellipse tangent to both. One burn raises apoapsis, a second circularizes.
  • Kepler's laws: Three laws describing planetary orbits: orbits are ellipses with the central body at one focus; a line to the body sweeps equal areas in equal times; and the o…
  • Lift and drag: The two aerodynamic forces: lift (perpendicular to motion, holds an aircraft up) and drag (opposing motion). Both equal coefficient * dynamic pressure * area;…
  • Orbital period: The time for one full orbit. For a circular orbit of radius r about a body of gravitational parameter mu, T = 2 pi sqrt(r^3/mu).
  • Runge-Kutta (RK4): A fourth-order numerical integrator that advances an ODE by sampling the derivative four times per step, far more accurate than Euler for orbit and trajectory…
  • Specific impulse (Isp): A measure of engine efficiency: thrust per unit propellant weight flow, in seconds. Higher Isp means more delta-v per kilogram of fuel (v_e = Isp * g0).
  • Staging: Discarding empty tanks/engines mid-flight so the rocket equation's mass ratio resets, dramatically increasing achievable delta-v versus a single stage.
  • Tsiolkovsky rocket equation: delta-v = v_e * ln(m0/mf): the achievable velocity change from exhaust velocity v_e and the wet/dry mass ratio. It dictates why staging exists, ratios grow exp…