From Bernoulli's equation to a flying quadcopter — and from the Tsiolkovsky rocket equation to a staged launch — AeroMaster Academy teaches the real theory behind aerodynamics, propulsion, avionics, flight control, and rocketry through worked equations, engineering diagrams, CAD labs, and simulation, distilled from the field's 69 foundational textbooks.
Each discipline pairs theory from the reference texts with a hands-on lab — you don't just read the equation, you compute it, model it, and eventually fly it.
Lift, drag, airflow, and the physics that keep a wing in the sky.
Frame layout, motor sizing, flight controllers, and autopilot logic.
Brayton-cycle turbomachinery, thrust, and specific impulse.
Staging, the rocket equation, launch dynamics, and orbital basics.
Conceptual sizing, structures, materials, and the design spiral.
IMUs, GPS, pitot-static systems, and sensor-fusion basics.
SolidWorks/Fusion 360 modeling, CFD, and control-loop design.
Portfolio builds, skill checks, and shareable certificates.
Progress in order — each tier assumes the math and mechanics of the one before it. Every module ends in a worked problem set, not just a reading.
Eight core concepts spanning aerodynamics, propulsion, structures, materials, orbital mechanics, and controls — each built the same way: the governing equation, an annotated engineering diagram, and the physical properties that drive the design.
Every wing balances four forces: lift and weight along the vertical axis, thrust and drag along the flight path. Lift is generated as the airfoil accelerates air over its curved upper surface, lowering local pressure relative to the underside — the pressure differential integrates into a net upward force.
Angle of attack (α) — the angle between the chord line and the oncoming flow — is the single variable a pilot actually controls to change lift. Increase it and C_L climbs in a straight line, right up until the flow can no longer follow the upper surface. Past that point it separates, and lift collapses even though the nose is still pointed higher. Step through the chain below to watch it happen.
A turbojet accelerates air through five stages — inlet, compressor, combustor, turbine, and nozzle. The compressor raises pressure, fuel burns at near-constant pressure in the combustor, and the turbine extracts just enough energy to drive the compressor before the nozzle accelerates the remaining high-energy gas rearward, producing thrust by Newton's third law.
An aircraft is statically stable only if its neutral point sits behind its center of gravity — a nose-up disturbance must generate a restoring nose-down moment. The distance between the two, normalized by mean chord, is the static margin: the single number that tells you whether a design wants to fly straight or tumble.
A quad in X-configuration controls roll, pitch, and yaw purely by varying the relative thrust of four fixed motors — diagonal pairs spin opposite directions to cancel reactive torque. The flight controller runs a PID loop hundreds of times per second, comparing the IMU's attitude estimate to the commanded setpoint and re-mixing motor speeds to correct the error.
Every certified aircraft flies inside a defined envelope of airspeed versus load factor. Push past the stall boundary at low speed and the wing simply can't generate enough lift; push past the structural limit at high speed and the airframe itself is the constraint. The V-n diagram is where those two limits meet.
Aerospace materials aren't chosen for raw strength — they're chosen for strength per unit mass, since every extra kilogram of structure is a kilogram that can't be payload or fuel. Just as important is fatigue: every flight is a stress cycle, and some materials have a safe stress level they can survive forever, while others don't.
Once a vehicle reaches orbital velocity, engines shut off and gravity alone takes over — the resulting path is always a conic section, usually an ellipse with the planet at one focus, not the center. The vis-viva equation is the single relation that gives orbital speed anywhere on that ellipse.
Beyond tuning PID gains by feel, control engineers describe a system's full dynamic behavior in the Laplace domain as a transfer function — then analyze stability with tools like root locus and Bode plots before anything is ever built or flown.
One tool, seven modes — a fast way to check any of the equations above against real numbers.
Eight questions, one per concept above.
Rockets are the one flying machine that carries its own atmosphere to push against. This lab walks the governing equations, the internal anatomy of a two-stage launch vehicle, the order it's actually built in, and an interactive flight from ignition to orbit.
A rocket has no air to push against, so it obeys conservation of momentum directly: it throws mass out the back at high velocity and accelerates forward in reaction. Nearly every design decision — how many stages, how much propellant, what engine — traces back to one equation.
| Symbol | Meaning | Typical Value |
|---|---|---|
| Δv | Mission velocity budget | ~9.4 km/s to LEO, with losses |
| Isp | Specific impulse | 250–320 s (kerolox), up to ~450 s (hydrolox, vacuum) |
| g₀ | Standard gravity | 9.80665 m/s² |
| m₀ / m_f | Wet mass / dry mass | Mass ratio typically 8–15 per stage |
| Ve | Effective exhaust velocity | Ve = Isp · g₀ |
| T/W | Thrust-to-weight ratio | 1.2–1.5 typical at liftoff |
| ζ | Propellant mass fraction | ζ = (m₀−m_f)/m₀, ~0.9 for a good stage |
A cutaway of a two-stage launch vehicle, nose to tail.
Aerodynamic tip that reduces drag during atmospheric ascent; shape trades drag against internal volume.
Protective shell shielding the payload from aerodynamic and thermal loads; splits and jettisons once air density is negligible.
Flight computer, IMU, and GPS that estimate the vehicle's state and steer it along the planned trajectory.
Ignites after separation; a smaller, often vacuum-optimized engine finishes accelerating the payload to orbital velocity.
Structural adapter joining the two stages; houses the separation system (pneumatic pushers or pyrotechnics).
Holds the oxidizer — liquid oxygen in most modern kerolox or hydrolox vehicles — kept separate from fuel until the injector.
Holds the fuel (RP‑1/kerosene, liquid hydrogen, or methane); tank walls often double as load-bearing structure.
Combusts propellant and expands exhaust through the nozzle to produce thrust; fins add aerodynamic stability during ascent.
The order a real launch vehicle comes together, from raw structure to flight-ready stack.
Body tubes are CNC-machined or filament-wound from carbon composite; fins are bonded and precisely aligned so they don't induce unwanted roll.
Fuel and oxidizer tanks are welded or filament-wound, then proof-pressure tested well above operating pressure before being cleared for propellant.
The engine is machined and assembled — injector, combustion chamber, regeneratively-cooled nozzle — then proven on a static-fire test stand before it ever flies.
Flight computer, IMU, GPS, and telemetry radios are integrated and run through hardware-in-the-loop simulation against the planned trajectory.
The second stage's own tank, engine, and separation/ignition sequencing are assembled and function-tested independently of the booster.
The payload is mated in a clean room, the fairing halves close around it, and separation springs or pneumatic pushers are armed.
Stages are stacked, wiring harnesses routed through the interstage, and every umbilical and separation connector is mated and continuity-checked.
Full propellant load without ignition (wet dress rehearsal), a final static fire where possible, then a flight readiness review clears the vehicle to count down.
Step through ignition, ascent, staging, fairing jettison, and orbit insertion.
A liquid rocket engine has seven functional systems. Here's what each one does and the physics governing it — the conceptual grounding a design would start from, not a build spec.
Gets fuel and oxidizer from the tanks to the injector at the right pressure and flow rate. Pressure-fed systems push propellant with high-pressure gas in the tanks themselves — simple and reliable, but the tanks must be heavy enough to hold that pressure. Pump-fed systems use a turbopump to raise pressure just before the chamber, so tanks stay thin-walled — the standard choice once an engine needs serious thrust.
Breaks the incoming liquid streams into fine droplets and mixes fuel with oxidizer so combustion is fast and complete. Common families: impinging-jet (opposing streams collide and atomize), coaxial swirl (fuel swirls around a central oxidizer jet), and pintle (a single, throttleable annular gap). Poor mixing shows up directly as lower combustion efficiency and rough, unstable burning.
Where the atomized propellants burn to a near-equilibrium hot gas. Performance here is captured by the characteristic velocity, a measure of how effectively chemical energy converts to chamber pressure — independent of the nozzle.
A converging-diverging (de Laval) shape that converts thermal and pressure energy into directed kinetic energy. Flow accelerates to exactly Mach 1 at the throat, then keeps accelerating supersonically as the nozzle diverges — the area ratio sets the exit Mach number.
Chamber walls face gas temperatures that exceed most materials' melting points, so heat has to go somewhere. Regenerative cooling routes propellant through channels in the wall before injection, carrying heat away and preheating the propellant. Ablative cooling uses a liner that chars and erodes, taking heat with the lost material — common on smaller or single-use engines.
Some propellant combinations are hypergolic — they ignite on contact, no spark needed. Others need an active igniter: a spark torch, a small pyrotechnic charge, or a hypergolic "slug" injected to kick off a non-hypergolic main combustion. Reliable ignition timing matters enormously — too slow and unburned propellant can pool and detonate.
Transmits the engine's thrust into the vehicle's airframe and, on many designs, lets the whole engine pivot a few degrees on a gimbal — that's how the vehicle steers during powered flight, by vectoring thrust rather than using aerodynamic control surfaces alone.
A small "engine within the engine" — a gas generator or preburner burns a fraction of the propellant to spin a turbine, which drives the fuel and oxidizer pumps. Two dominant cycles: gas-generator (burns propellant separately, dumps the turbine exhaust overboard — simpler, slightly less efficient) and staged combustion (turbine exhaust is fed back into the main chamber — more efficient, more complex).
Give it chamber pressure, expansion ratio, and a propellant pick; it solves the same isentropic-flow equations above for exit Mach number, thrust coefficient, thrust, and Isp — the standard first-pass performance check used in coursework, not a design tool for an actual chamber.
Six questions to check the theory actually landed before you move on.
A multirotor is inherently unstable — left alone it tips over. Everything from here down is how the airframe, sensors, and control loop work together hundreds of times a second to keep it upright. We'll go part by part, tier by tier, then watch the correction loop run.
A multirotor has no control surfaces — it steers entirely by varying thrust between motors. Hovering is a thrust/weight balance; staying level is a continuous correction loop running on that same thrust differential.
| Symbol | Meaning | Typical Value |
|---|---|---|
| T/W | Thrust-to-weight ratio | ≥2 for aerobatic control authority |
| Kp / Ki / Kd | PID gains | Tuned per airframe; Kp dominant, Kd damps oscillation |
| e(t) | Attitude error | Setpoint minus estimated angle, in degrees |
| IMU rate | Sensor sample rate | 1–8 kHz (gyro), fused down to loop rate |
| I | Moment of inertia | Higher on larger frames → slower response |
| Motor Kv | RPM per volt (unloaded) | ~900–2400 Kv for typical 5–7" props |
A top-down cutaway of a standard quadcopter, X configuration.
Converts motor rotation into thrust; fixed-pitch on most multirotors, matched pairs spin CW and CCW.
Brushless DC motor — spins the propeller; rated by Kv (RPM per volt) and matched to prop size and battery voltage.
Converts the flight controller's throttle command into the 3-phase power that drives each brushless motor.
Structural skeleton holding motors at a fixed geometry; stiffness here directly affects how "twitchy" or vibration-prone the craft is.
The onboard computer running the control loop — reads sensors, computes PID output, sends commands to each ESC.
Measures linear acceleration and angular rate; fused together to estimate the craft's current attitude.
Provides position, ground speed, and heading for navigation modes — not needed for basic stabilization, essential for autonomy.
LiPo battery feeds a distribution board that splits power to all four ESCs plus the FC and accessories.
The same question — "why doesn't it fall over?" — gets a deeper answer at each level.
The order a quadcopter actually comes together, frame to first hover.
Arms are mounted to the center plate, standoffs set the stack height, and everything is torqued to spec before anything electrical goes on.
Motors are bolted to each arm and ESCs mounted nearby; motor rotation direction (CW/CCW) is checked against the frame's diagonal layout.
Battery leads connect to a power distribution board that feeds all four ESCs; wire gauge is sized for the expected current draw.
The FC is mounted on vibration-damping standoffs at the true center of gravity; IMU orientation is set in firmware to match how it's physically mounted.
The radio receiver is bound to the transmitter, antennas are routed away from carbon (which blocks signal), and failsafe behavior is configured.
Props are balanced to reduce vibration, then fitted so each one pushes air downward when spinning in its assigned direction.
Motor order and directions are verified in software, sensor calibration is run, and PID gains are set from safe defaults before any flight.
Props-off motor test, then a low, tethered or props-on hover in open space, watching for oscillation before gains are fine-tuned.
Step through a gust knocking the craft off-level and the control loop bringing it back.
The first check on any build: will it even fly, and how much control authority will it have left over?
Six questions on drone anatomy and stability theory.
A modern airliner engine is a Brayton-cycle machine wrapped around a bypass fan. Air gets compressed, heated, and expanded through a precise sequence of stages — each one identified by a station number that shows up on every gas-turbine spec sheet.
Beyond the basic thrust equation, two efficiency metrics tell you almost everything about how good an engine design is: how well it turns fuel energy into thrust, and how well it turns exhaust energy into useful push rather than wasted kinetic energy in the jet wash.
| Symbol | Meaning | Typical Value |
|---|---|---|
| OPR (rp) | Overall pressure ratio | 30:1 – 60:1, modern turbofans |
| BPR | Bypass ratio | 0 (turbojet) to 12+ (high-bypass turbofan) |
| TSFC | Thrust-specific fuel consumption | ~0.5–0.6 lb/(lbf·hr) cruise, modern turbofan |
| TIT | Turbine inlet temperature | 1400–1700 K |
| N1 / N2 | Fan/LP spool, HP spool speed | Reported as %; redlines vary by engine |
| η_prop | Propulsive efficiency | Higher BPR → higher η_prop, lower η at high speed |
A high-bypass turbofan in cross-section, inlet to nozzle.
The large front-most blade disk; most of its airflow bypasses the core entirely, generating most of the engine's thrust directly.
Also called the booster — a few stages that further compress the core airflow before it reaches the high-pressure compressor.
Many stages of blades and stators raising pressure sharply; this is where most of the overall pressure ratio is built.
Fuel is injected and burned continuously at roughly constant pressure, raising gas temperature to the turbine inlet limit.
Extracts just enough energy from the hot gas to drive the high-pressure compressor on the same shaft.
Extracts further energy to drive the fan and LP compressor via a second, concentric shaft.
Accelerates the remaining core exhaust; on a turbofan it contributes far less thrust than the bypass fan stream.
Ducts fan air around the core, mixing with or exiting alongside the core exhaust — the source of most modern turbofan thrust and efficiency.
"Why does it produce thrust?" gets a deeper answer at each level.
The order a turbofan comes together on the assembly line.
Fan blades are individually balanced and mounted into the fan disk; the whole assembly is balanced as a unit before it ever sees the rest of the engine.
Compressor disks are stacked stage by stage, each with its own blade row, and match-checked for the tight tip clearances the design calls for.
Fuel nozzles and igniters are fitted into the combustor liner, which is checked for correct cooling-air hole pattern and liner alignment.
Turbine blades — some of the most heat-stressed parts in the whole engine — are installed and their internal cooling passages leak-checked.
The concentric LP and HP shafts are installed with their bearings, which is what lets the two spools rotate independently.
The accessory gearbox (driving oil, fuel, and electrical pumps) and the FADEC control unit are mounted and wired in.
All modules are joined into a complete engine, then fitted with the sensors (EGT, N1/N2, vibration) that will monitor it for its whole service life.
The finished engine runs on an instrumented test stand through its full power range before it's cleared to ship to an airframe.
Step through the Brayton cycle as air actually experiences it, station 0 to station 8.
From basic mass-flow and velocity numbers, the same first-pass performance check used in intro propulsion coursework.
Six questions on turbofan theory and station anatomy.
Conceptual aircraft design isn't a straight line — it's a spiral. Every discipline's numbers depend on every other discipline's numbers, so the whole thing gets estimated, refined, and re-estimated until it converges on a design that actually closes.
Two numbers set the shape of almost everything else: wing loading (how much weight each square meter of wing has to carry) and the Breguet range equation, which ties propulsion, aerodynamics, and structure together into a single mission result.
| Symbol | Meaning | Typical Value |
|---|---|---|
| W/S | Wing loading | 400–700 kg/m² transports, 50–150 GA |
| AR | Aspect ratio | 7–10 transports, 20+ gliders |
| e | Oswald efficiency factor | 0.70–0.85 typical |
| L/D | Lift-to-drag ratio | 15–20 cruise, modern airliners |
| TSFC | Thrust-specific fuel consumption | ~0.045–0.065 kg/(N·h), modern turbofan cruise |
| We/W0 | Empty weight fraction | 0.45–0.60 typical |
A top-down planform view of a conventional transport-category aircraft.
The main body — carries payload/passengers and ties every other structural component together.
Primary lifting surface; its area and aspect ratio are set almost entirely by the wing loading target.
Horizontal and vertical stabilizers that provide pitch and yaw stability, plus the surfaces to control them.
Retracts for cruise; its stowed position and geometry are often a surprisingly major driver of fuselage and wing layout.
Engine and its housing; placement (wing-mounted vs. fuselage-mounted) trades structural weight against noise and maintenance access.
Ailerons, elevator, and rudder — hinged trailing-edge surfaces that let the pilot (or autopilot) command roll, pitch, and yaw.
Flaps and slats that temporarily increase C_Lmax for takeoff and landing, letting the wing be sized smaller for efficient cruise.
Usually integral to the wing box — the wing structure itself forms the tank walls, saving weight versus separate tanks.
"Why does it look the way it does?" gets a deeper answer at each level.
Step through six passes of the iteration loop that turns a rough guess into a closed design.
The phases a conceptual design actually moves through, requirements to certified aircraft.
Payload, range, cruise speed, runway length, and certification category are fixed as hard design requirements before anything is drawn.
Historical regression gives a first weight estimate; wing loading and thrust-to-weight are chosen from the mission requirements.
Wing position, tail arrangement, engine placement, and fuselage cross-section are laid out into a coherent overall shape.
Drag polar and L/D are estimated (and later refined with CFD), feeding directly back into the fuel weight estimate.
Spar and rib layout, skin gauges, and material choice are set from the V-n diagram's limit loads.
Avionics, hydraulics, fuel, and electrical systems are routed through the airframe without conflicting for space.
FEA and CFD validate the converged conceptual design against every load case and flight condition before hardware is cut.
A prototype is built and flown through a certification test campaign before the design can carry passengers or cargo.
The first-pass sizing check every conceptual design starts from.
Six questions on aircraft design fundamentals.
Every sensor on a vehicle lies to you in its own particular way — gyros drift, accelerometers are noisy, GPS updates slowly. Avionics is the discipline of combining several imperfect measurements into one estimate that's better than any of them alone.
The simplest working version of sensor fusion is the complementary filter — trust the gyro right now, but slowly correct it back toward whatever a drift-free (but noisy or slow) reference says over time.
| Symbol | Meaning | Typical Value |
|---|---|---|
| α | Filter blend coefficient | 0.95–0.98 typical (favors gyro short-term) |
| ω | Gyro angular rate | deg/s or rad/s, direct sensor output |
| ρ | Pseudorange | Computed from signal time-of-flight |
| δt_bias | Receiver clock bias | Solved for using a 4th satellite |
| DOP | Dilution of precision | <2 excellent, 2–5 good, >10 poor |
| GPS rate | Typical fix update rate | 1–10 Hz consumer, up to 100 Hz RTK |
A typical avionics sensor suite, hub-and-spoke around the flight management computer.
Measures linear acceleration and angular rate — the fast, short-term-accurate core of any attitude estimate.
Senses Earth's magnetic field for an absolute heading reference, correcting gyro yaw drift over time.
Infers altitude from air pressure; fast-updating but drifts with weather, so it's usually fused with GPS altitude.
Provides absolute position, velocity, and time from satellites — slow to update but doesn't drift over time.
Measures airspeed and altitude from dynamic and static air pressure — the primary reference on airplanes, distinct from GPS ground speed.
Fuses every sensor input into one trusted state estimate and runs the guidance and control laws from it.
Streams live sensor and status data to a ground station for monitoring, logging, and remote command.
Where the fused state estimate actually gets presented to a pilot or operator for situational awareness.
"How does it know where it is?" gets a deeper answer at each level.
The order an avionics suite actually gets bench-tested and installed.
Each sensor is characterized on the bench against a known reference before it ever sees the vehicle — bias, noise, and scale-factor errors are all measured up front.
The IMU in particular is mounted on vibration-damping standoffs, since raw airframe vibration can swamp the actual signal.
Sensors are wired onto shared digital buses (I2C, SPI, or CAN) back to the flight computer, with addresses and priorities configured.
Firmware drivers for each sensor are brought up individually and checked against raw expected values before any fusion logic runs.
Complementary or Kalman filter gains are tuned — often first in simulation, then validated against logged real sensor data.
Compass calibration is done outdoors, away from magnetic interference, and GPS cold-start performance is verified in open sky.
Every fused and raw value is logged; the telemetry downlink is checked for dropout under realistic range and interference conditions.
The fused state estimate is checked in real flight against independent references (visual, GPS ground truth) before the system is trusted operationally.
Step through the same real attitude change as seen by three different estimators — and watch the fused one stay right.
How far can position estimate drift between GPS fixes, given your update rate and velocity uncertainty?
Six questions on sensors, fusion, and navigation.
Every calculator so far has lived inside one Lab. Real missions don't — they chain equations from several disciplines together. Pick a mission below and watch exactly which Lab each step borrows from.
Scoped to direct ascent into a circular low-Earth orbit. Higher-energy destinations like GEO need transfer-orbit maneuvers this simplified chain doesn't model — that's a deliberate scope limit, not an oversight.
Circular orbit speed at the target altitude — how fast you actually need to be going once you're there.
Orbital velocity plus a typical ~1.7 km/s for gravity and drag losses during ascent through the atmosphere.
Total Δv divided evenly across the stages — each stage only has to deliver its own share.
Rearranged for mass ratio: MR = e^(Δv/(Isp·g₀)) — this is the number that decides whether a stage is buildable.
Solves the Breguet range equation backwards — instead of computing range from a fuel fraction, it computes the fuel fraction a target range demands, then checks what's left over for payload.
Solved in reverse: R = (V/(TSFC·g))·(L/D)·ln(1/(1−ff)) rearranged for ff given a target range.
Payload fraction = 1 − empty weight fraction − fuel fraction. Whatever's left over is what you can actually carry.
Checks whether a delivery drone can even lift its payload, then whether its navigation is precise enough to actually land on target.
Total max thrust from all motors divided by total weight — below 1.0 and it can't leave the ground.
Simple distance over cruise speed — check this against your battery's rated endurance separately.
Position drift between GPS fixes, assuming ~10% velocity-estimate uncertainty — this is how close it can actually land to the target.
Every formula from every Lab, searchable and filterable — each one links straight back to where it's taught.
Force generated perpendicular to the flight path from dynamic pressure and the lift coefficient.
↳ Theory Lab — AerodynamicsForce opposing the flight path, same dynamic-pressure term with the drag coefficient.
↳ Theory Lab — AerodynamicsLinear relationship between lift coefficient and angle of attack, up to the critical angle.
↳ Theory Lab — Angle of AttackRatio of inertial to viscous forces — governs whether flow is laminar or turbulent.
↳ Theory Lab — CalculatorMomentum thrust plus a pressure term for any air-breathing or rocket engine.
↳ Theory Lab — PropulsionIdeal cycle efficiency as a function of overall pressure ratio.
↳ Jet Engine LabWhy high-bypass fans beat small fast jets — less wasted kinetic energy in the exhaust.
↳ Jet Engine LabFuel burned per unit thrust — the efficiency number airlines actually track.
↳ Jet Engine LabTotal velocity change available from burning all propellant — the master equation of rocketry.
↳ Rocket LabRocket-specific form of the thrust equation — no inlet velocity term since it carries its own oxidizer.
↳ Rocket LabChamber-only performance metric, independent of the nozzle — measures combustion efficiency.
↳ Rocket LabRelates exit Mach number to how much the nozzle diverges past the throat.
↳ Rocket LabOrbital speed at any point on an elliptical orbit, given radius and semi-major axis.
↳ Theory Lab — Orbital MechanicsOrbital period depends only on semi-major axis, never on eccentricity.
↳ Theory Lab — Orbital MechanicsRatio of lift to weight — the vertical axis of the V-n diagram.
↳ Theory Lab — StructuresStall speed rises with the square root of load factor — traces the V-n diagram's curved boundary.
↳ Theory Lab — StructuresApplied force distributed over cross-sectional area.
↳ Theory Lab — StructuresStiffness relating stress to strain in a material's elastic region.
↳ Theory Lab — StructuresStrength per unit density — the metric that matters when mass is the enemy.
↳ Theory Lab — MaterialsStress amplitude vs. cycles to failure — the S-N fatigue curve.
↳ Theory Lab — MaterialsDistance between neutral point and CG, normalized by mean chord — determines static stability.
↳ Theory Lab — Flight StabilityProportional, integral, and derivative terms combine into a correction signal from attitude error.
↳ Drone LabOutput over input in the Laplace domain — a system's complete dynamic response.
↳ Theory Lab — Control SystemsHow feedback H(s) reshapes the overall response of controller and plant G(s).
↳ Theory Lab — Control SystemsPer-motor thrust needed to hover, assuming even loading across n motors.
↳ Drone LabRotational analogue of F=ma — motor thrust differentials create the torque that rotates a frame.
↳ Drone LabBlends a gyro's fast short-term accuracy with an accelerometer's drift-free long-term reference.
↳ Avionics LabSatellite signal travel time converted to distance, corrected for receiver clock bias.
↳ Avionics LabSets the trade between stall speed and cruise efficiency for a given design.
↳ Aircraft Design LabTies propulsion, aerodynamics, and structure together into a single mission range result.
↳ Aircraft Design LabEvery lesson traces back to a primary source. Here's the working shelf — aerodynamics, design, propulsion, structures, avionics, rocketry, and the math underneath all of it — searchable and filterable by discipline.
Real progress, not a mockup — every quiz score and calculator you use here is saved to your account and reflected below automatically.
The tutor walks through equations step by step, checks your CAD dimensions against your stated design loads, and points back to the exact chapter of the source text — it explains the "why" behind the formula, not just the answer.
Join the Beginner path today — physics, math, and basic aerodynamics, structured so the next tier always makes sense.