Trajectories
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docs/QUICKSTART.md
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# Quick Start Guide
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Get up and running with RocketTools in 5 minutes.
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## Installation
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```bash
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npm install
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npm run dev
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```
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Open **http://localhost:5173** in your browser.
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---
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## Your First Rocket Design (10 minutes)
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### Step 1: Design an Engine (3 min)
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1. Click **Design → Engine**
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2. Select propellants:
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- Fuel: **RP-1**
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- Oxidizer: **LOX**
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3. Set chamber pressure: **200 bar**
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4. Set nozzle diameter: **50 mm**
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5. Set expansion ratio: **8**
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6. **→ Results**: Thrust ~150 kN, Isp ~310 s, burn time 60 s
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7. **Export as JSON** (save to file)
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### Step 2: Design a Rocket (4 min)
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1. Click **Design → Rocket**
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2. **Import engine JSON** (from step 1)
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3. Set tank configuration: **Tandem**
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4. Set outer radius: **1.0 m**
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5. Set propellant volume: **5000 L**
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6. Set payload: **50 kg**
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7. **→ Results**: Wet mass 1550 kg, dry mass 450 kg, TWR 10
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8. Adjust nose cone shape: **Von Kármán** (optimal)
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9. **Export as JSON** (save to file)
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### Step 3: Simulate Flight (3 min)
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1. Click **Design → Trajectory**
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2. **Import rocket JSON** (from step 2)
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3. **Import engine JSON** (from step 1)
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4. Set pitch start altitude: **1000 m**
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5. **Run Simulation**
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6. **Watch the animation** (click Play button)
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7. **Results**: ~5000 m downrange, 50 km apogee
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---
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## Key Pages Overview
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### 🧮 Solver
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Automatically solve rocket equations.
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- Drag variables onto workspace
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- Set constraints
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- Solver computes unknowns
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**Try this**: Set `thrust = 100000 N`, `massFlowRate = 100 kg/s`
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→ Solver computes `exitVelocity = 1000 m/s`
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### 🔥 Engine Design
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Calculate combustion, erosion, and structure.
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- Propellant selection
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- Chamber pressure & nozzle geometry
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- Ablative erosion prediction
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- Wall thickness & mass
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**Try this**: Increase chamber pressure from 200 → 500 bar
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→ See thrust increase, wall thickness increase, mass increase
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### 🚀 Rocket Design
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Vehicle geometry and mass budget.
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- Tank configuration (tandem/coaxial)
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- Tank structure (hoop stress)
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- Nose cone shapes
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- Complete mass budget
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- 3D visualization
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**Try this**: Switch nose cone from Conical → Von Kármán
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→ 3D model updates in real time
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### 📈 Trajectory Simulation
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Flight path prediction.
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- RK4 physics integrator
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- Atmosphere model (US Standard)
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- Event detection (liftoff, apogee, landing)
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- Playback controls
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**Try this**: Run simulation, then scrub timeline to different times
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→ See position, velocity, altitude change
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### 📚 Knowledgebase
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Material & equation references.
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- **Fuels / Oxidizers** — propellant properties
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- **Ablative Materials** — thermal protection specs
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- **Equations** — physics reference
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- **Structural Materials** — metal/composite properties
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**Try this**: Look up LOX properties
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→ Temperature: 3750 K, Isp: 310 s
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---
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## Tips & Tricks
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### Save Your Work
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- Engine JSON → use for multiple rocket designs
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- Rocket JSON → use for trajectory simulations
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- Keep both files for reference
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### Quick Iterations
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1. Modify one parameter (e.g., chamber pressure)
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2. Solver/simulator automatically updates
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3. Check results
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4. Adjust again
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### Understanding Mass
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- **Wet mass** = total (with fuel)
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- **Dry mass** = structure + engine + payload (no fuel)
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- **Propellant mass** = wet − dry
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- **TWR** = thrust / weight
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- > 5 is good for vertical launch
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- < 2 struggles to lift off
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### Understanding Isp
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- **Higher Isp = more efficient** (goes farther on same fuel)
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- Vacuum Isp > Sea-level Isp (less atmospheric pressure at altitude)
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- LOX/RP-1: ~310 s (workhorse)
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- LOX/H2: ~450 s (high-perf, but cryogenic)
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- MMH/N2O4: ~290 s (storable, easier operations)
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### Flight Path Basics
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- Vehicle accelerates straight up (vertical hold)
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- At ~1 km altitude, starts gravity turn (follows velocity)
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- Thrust ends at ~60 s (Main Engine Cutoff)
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- Coasts up to apogee (~50 km in example)
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- Falls back down (lands ~5 km downrange)
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---
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## Common Questions
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**Q: How do I get higher apogee?**
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- Increase fuel volume (larger tank)
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- Reduce payload mass
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- Higher Isp propellant (LOX/H2)
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- More efficient rocket (lighter structure)
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**Q: Why is my rocket too heavy?**
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- Reduce tank radius (but check volume)
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- Use stronger material (Al → Ti → CFRP)
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- Lower safety factor (use 2.0 instead of 3.0)
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- Reduce payload
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**Q: Can I design multiple stages?**
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- Not yet — current version is single-stage only
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- Workaround: design each stage separately, estimate staging losses manually
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**Q: How accurate are the simulations?**
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- ±5–10% for well-designed vehicles
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- Assumes no wind, perfect injection
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- Doesn't include control/guidance errors
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- Good for feasibility analysis, not flight prediction
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**Q: Can I export to CAD?**
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- Not yet — export rocket JSON for external processing
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- 3D model data available in code (tank dimensions, nose cone profile)
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---
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## Common Mistakes to Avoid
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❌ **Too small tank**
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- 5000 L seems big but isn't for LOX/RP-1 rockets
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- Try 10,000+ L for real vehicle
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❌ **Forgot engine burn time**
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- Check engine design was properly simulated
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- Engine JSON must include burn time
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❌ **Wrong reference area for drag**
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- Use actual cross-sectional area (πR²)
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- Not wetted surface or planform area
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❌ **Unrealistic safety factor**
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- 2.0–3.0 is typical for engines
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- < 1.5 is dangerous, > 5.0 is wasteful
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❌ **Ignoring pressurant mass**
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- Pressure-fed system helium adds ~100 kg
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- Consider pump-fed for heavier vehicles
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---
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## Next Steps
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1. **Explore knowledgebase** — understand propellants & materials
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2. **Read equations** — understand the physics
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3. **Design variants** — try different tank sizes, materials
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4. **Optimize** — see what makes vehicle lighter/faster
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5. **Contribute** — add new equations or materials
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---
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## Learning Resources
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- [Rocket Propulsion Elements](https://www.amazon.com/Rocket-Propulsion-Elements-Sutton-Biblarz/dp/0470080728) — textbook
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- [NASA SP-273: Combustion Instability](https://ntrs.nasa.gov) — free PDF
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- [Everyday Astronaut](https://www.youtube.com/c/EverydayAstronaut) — video explanations
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---
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## Troubleshooting
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| Problem | Solution |
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|---------|----------|
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| Nothing shows up | Refresh browser (Ctrl+F5) |
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| Numbers look wrong | Check input units (bar vs MPa, mm vs m) |
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| 3D model doesn't render | WebGL must be enabled in browser |
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| Solver stuck | Ensure enough constraints set for system |
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| Simulation runs forever | Reduce timestep or check inputs for infinity |
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---
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## Keyboard Shortcuts
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| Shortcut | Action |
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|----------|--------|
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| **Space** | Play/pause trajectory |
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| **→** | Jump forward 10 seconds |
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| **←** | Jump backward 10 seconds |
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| **Home** | Jump to start |
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| **End** | Jump to end |
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---
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**Happy rocket designing! 🚀**
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Next, dive into [SOLVER.md](SOLVER.md) to master the equation solver.
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