6.6 KiB
6.6 KiB
Quick Start Guide
Get up and running with RocketTools in 5 minutes.
Installation
npm install
npm run dev
Open http://localhost:5173 in your browser.
Your First Rocket Design (10 minutes)
Step 1: Design an Engine (3 min)
- Click Design → Engine
- Select propellants:
- Fuel: RP-1
- Oxidizer: LOX
- Set chamber pressure: 200 bar
- Set nozzle diameter: 50 mm
- Set expansion ratio: 8
- → Results: Thrust ~150 kN, Isp ~310 s, burn time 60 s
- Export as JSON (save to file)
Step 2: Design a Rocket (4 min)
- Click Design → Rocket
- Import engine JSON (from step 1)
- Set tank configuration: Tandem
- Set outer radius: 1.0 m
- Set propellant volume: 5000 L
- Set payload: 50 kg
- → Results: Wet mass 1550 kg, dry mass 450 kg, TWR 10
- Adjust nose cone shape: Von Kármán (optimal)
- Export as JSON (save to file)
Step 3: Simulate Flight (3 min)
- Click Design → Trajectory
- Import rocket JSON (from step 2)
- Import engine JSON (from step 1)
- Set pitch start altitude: 1000 m
- Run Simulation
- Watch the animation (click Play button)
- Results: ~5000 m downrange, 50 km apogee
Key Pages Overview
🧮 Solver
Automatically solve rocket equations.
- Drag variables onto workspace
- Set constraints
- Solver computes unknowns
Try this: Set thrust = 100000 N, massFlowRate = 100 kg/s
→ Solver computes exitVelocity = 1000 m/s
🔥 Engine Design
Calculate combustion, erosion, and structure.
- Propellant selection
- Chamber pressure & nozzle geometry
- Ablative erosion prediction
- Wall thickness & mass
Try this: Increase chamber pressure from 200 → 500 bar → See thrust increase, wall thickness increase, mass increase
🚀 Rocket Design
Vehicle geometry and mass budget.
- Tank configuration (tandem/coaxial)
- Tank structure (hoop stress)
- Nose cone shapes
- Complete mass budget
- 3D visualization
Try this: Switch nose cone from Conical → Von Kármán → 3D model updates in real time
📈 Trajectory Simulation
Flight path prediction.
- RK4 physics integrator
- Atmosphere model (US Standard)
- Event detection (liftoff, apogee, landing)
- Playback controls
Try this: Run simulation, then scrub timeline to different times → See position, velocity, altitude change
📚 Knowledgebase
Material & equation references.
- Fuels / Oxidizers — propellant properties
- Ablative Materials — thermal protection specs
- Equations — physics reference
- Structural Materials — metal/composite properties
Try this: Look up LOX properties → Temperature: 3750 K, Isp: 310 s
Tips & Tricks
Save Your Work
- Engine JSON → use for multiple rocket designs
- Rocket JSON → use for trajectory simulations
- Keep both files for reference
Quick Iterations
- Modify one parameter (e.g., chamber pressure)
- Solver/simulator automatically updates
- Check results
- Adjust again
Understanding Mass
- Wet mass = total (with fuel)
- Dry mass = structure + engine + payload (no fuel)
- Propellant mass = wet − dry
- TWR = thrust / weight
-
5 is good for vertical launch
- < 2 struggles to lift off
-
Understanding Isp
- Higher Isp = more efficient (goes farther on same fuel)
- Vacuum Isp > Sea-level Isp (less atmospheric pressure at altitude)
- LOX/RP-1: ~310 s (workhorse)
- LOX/H2: ~450 s (high-perf, but cryogenic)
- MMH/N2O4: ~290 s (storable, easier operations)
Flight Path Basics
- Vehicle accelerates straight up (vertical hold)
- At ~1 km altitude, starts gravity turn (follows velocity)
- Thrust ends at ~60 s (Main Engine Cutoff)
- Coasts up to apogee (~50 km in example)
- Falls back down (lands ~5 km downrange)
Common Questions
Q: How do I get higher apogee?
- Increase fuel volume (larger tank)
- Reduce payload mass
- Higher Isp propellant (LOX/H2)
- More efficient rocket (lighter structure)
Q: Why is my rocket too heavy?
- Reduce tank radius (but check volume)
- Use stronger material (Al → Ti → CFRP)
- Lower safety factor (use 2.0 instead of 3.0)
- Reduce payload
Q: Can I design multiple stages?
- Not yet — current version is single-stage only
- Workaround: design each stage separately, estimate staging losses manually
Q: How accurate are the simulations?
- ±5–10% for well-designed vehicles
- Assumes no wind, perfect injection
- Doesn't include control/guidance errors
- Good for feasibility analysis, not flight prediction
Q: Can I export to CAD?
- Not yet — export rocket JSON for external processing
- 3D model data available in code (tank dimensions, nose cone profile)
Common Mistakes to Avoid
❌ Too small tank
- 5000 L seems big but isn't for LOX/RP-1 rockets
- Try 10,000+ L for real vehicle
❌ Forgot engine burn time
- Check engine design was properly simulated
- Engine JSON must include burn time
❌ Wrong reference area for drag
- Use actual cross-sectional area (πR²)
- Not wetted surface or planform area
❌ Unrealistic safety factor
- 2.0–3.0 is typical for engines
- < 1.5 is dangerous, > 5.0 is wasteful
❌ Ignoring pressurant mass
- Pressure-fed system helium adds ~100 kg
- Consider pump-fed for heavier vehicles
Next Steps
- Explore knowledgebase — understand propellants & materials
- Read equations — understand the physics
- Design variants — try different tank sizes, materials
- Optimize — see what makes vehicle lighter/faster
- Contribute — add new equations or materials
Learning Resources
- Rocket Propulsion Elements — textbook
- NASA SP-273: Combustion Instability — free PDF
- Everyday Astronaut — video explanations
Troubleshooting
| Problem | Solution |
|---|---|
| Nothing shows up | Refresh browser (Ctrl+F5) |
| Numbers look wrong | Check input units (bar vs MPa, mm vs m) |
| 3D model doesn't render | WebGL must be enabled in browser |
| Solver stuck | Ensure enough constraints set for system |
| Simulation runs forever | Reduce timestep or check inputs for infinity |
Keyboard Shortcuts
| Shortcut | Action |
|---|---|
| Space | Play/pause trajectory |
| → | Jump forward 10 seconds |
| ← | Jump backward 10 seconds |
| Home | Jump to start |
| End | Jump to end |
Happy rocket designing! 🚀
Next, dive into SOLVER.md to master the equation solver.