Reducing orbital access costs by 90% through ground-based acceleration and aerodynamic efficiency.
This project operates under the ShaneTheBrain Constitution.
All thebardchat repositories run on local-first hardware:
| Component | Detail |
|---|---|
| Compute | Raspberry Pi 5 (16 GB RAM) |
| Chassis | Pironman 5-MAX by Sunfounder |
| Storage | 2x WD Blue SN5000 2 TB NVMe — RAID 1 via mdadm |
| Core path | /mnt/shanebrain-raid/shanebrain-core/ |
| Networking | Tailscale VPN across all nodes |
Pi before cloud. Privacy before convenience. — Pillar 4
Current space launch systems waste 85-95% of their mass on propellant to fight Earth's atmosphere and gravity well. The Tsiolkovsky Rocket Equation dictates that for every kilogram of payload, we must lift 20-50 kg of fuel. This fundamental inefficiency keeps space access at $2,000-10,000 per kilogram.
We propose a three-stage hybrid system that decouples the energy-intensive acceleration phase from the spacecraft:
┌─────────────────────────────────────────────────────────────────────┐
│ BGKPJR LAUNCH SEQUENCE │
├─────────────────────────────────────────────────────────────────────┤
│ │
│ STAGE 1: MAGLEV "JUMP" STAGE 2: ATMOSPHERIC ASCENT │
│ ════════════════════════ ═══════════════════════════ │
│ │
│ ▄▄▄▄▄▄▄▄▄▄▄▄▄▄▄▄▄▄▄▄▄▄▄▄ ● │
│ ████████████████████████ /\ ← Gryphon Wings Deploy │
│ ████ EVACUATED TUBE ████ / \ │
│ ████████████████████████ / \ Mach 3.5 → Mach 8 │
│ ▀▀▀▀▀▀▀▀▀▀▀▀▀▀▀▀▀▀▀▀▀▀▀▀ / \ Aerodynamic Lift │
│ 28.7 km / \ + Hybrid Propulsion │
│ 15-45° incline ●──────────● │
│ Exit: Mach 3.5-5.0 │
│ │
│ STAGE 3: ORBITAL INSERTION & SOLAR PROPULSION │
│ ═════════════════════════════════════════════ │
│ │
│ ☀ ─────────────────→ ◇─────────◇ │
│ \ KEPLER / │
│ Solar Pressure \ SAIL / 1,200 m² │
│ @ >300km altitude \ / CP1 Polyimide │
│ \ / │
│ \/ │
│ │
└─────────────────────────────────────────────────────────────────────┘
By providing the initial 1,200 m/s (Mach 3.5) from ground-based superconducting electromagnets rather than onboard propellant, we:
- Reduce propellant mass fraction by 40% (validated by Tsiolkovsky analysis)
- Eliminate first-stage recovery complexity (no landing legs, no return fuel)
- Enable aircraft-like reusability (Gryphon glides back unpowered)
| Parameter | Value | Rationale |
|---|---|---|
| Length | 28.7 km | Required for < 4g acceleration to Mach 3.5 |
| Inclination | 15° - 45° | Variable based on mission profile |
| Exit Velocity | Mach 3.5 - 5.0 | 1,190 - 1,700 m/s |
| Structure | Evacuated Tube | Partial vacuum (0.1 atm) eliminates drag |
| Magnets | Superconducting NbTi | 4.2K operating temp, 8T field strength |
Critical Physics:
Track Length = v²/(2a)
L = (1190 m/s)² / (2 × 4 × 9.81 m/s²)
L = 18.0 km (minimum at 4g)
L = 28.7 km (with safety margin and curved exit)
Stealth-inspired blended wing body optimized for:
- Minimum drag during hypersonic tube exit
- Maximum lift during atmospheric climb
- Thermal survival at Mach 3.5+ exit conditions
| Parameter | Value |
|---|---|
| Airframe | Ti-6Al-4V / Carbon Composite Hybrid |
| Mass (dry) | 15,000 kg |
| Payload | 5,000 kg to LEO |
| Wing Area | 120 m² (deployed) |
| TPS | Active Transpiration Cooling (nose cone) |
| L/D Ratio | 4.5 (hypersonic) / 8.0 (subsonic return) |
CRITICAL NOTE: Deployed ONLY at stable orbit (>300 km). Solar sails are NOT usable for atmospheric ascent due to negligible thrust-to-weight ratio in gravity well.
| Parameter | Value |
|---|---|
| Material | CP1 Polyimide |
| Thickness | 2.5 microns |
| Area | 1,200 m² (initial) |
| Thrust | ~9 mN/m² at 1 AU |
| Purpose | Orbit raising, station-keeping, deep space transit |
Without BGKPJR (Traditional):
- Required Δv to LEO: ~9,400 m/s
- Mass ratio: ~20:1 (95% propellant)
With BGKPJR:
- Maglev provides: 1,200 m/s (free)
- Aerodynamic lift assists: ~800 m/s equivalent
- Required onboard Δv: ~7,400 m/s
- Mass ratio: ~12:1 (92% → 75% propellant)
Standard lift equation with Prandtl-Glauert correction for high subsonic/transonic:
For supersonic (Ackeret linear theory):
At Mach 3.5 exit into 0.1 atm tube pressure:
Stagnation Temperature = T_∞ × (1 + (γ-1)/2 × M²)
T_stag = 288K × (1 + 0.2 × 12.25)
T_stag = 994K (721°C)
Conclusion: Manageable with titanium leading edges + transpiration cooling.
BGKPJR-Core-Simulations/
├── README.md # You are here
├── docs/
│ ├── aerodynamics/ # Lift, drag, compressibility theory
│ ├── propulsion/ # Rocket equations, hybrid systems
│ ├── flight_dynamics/ # Stability, control, trajectory
│ ├── thermal/ # Heat management, TPS design
│ ├── gnc/ # Guidance, Navigation, Control
│ └── system_specs/ # Gryphon, Kepler, Track specifications
├── simulation/
│ ├── src/ # Python physics engine
│ ├── notebooks/ # Jupyter analysis notebooks
│ ├── tests/ # Unit tests for physics validation
│ └── matlab/ # MATLAB/Simulink models
├── control_systems/
│ ├── lqr/ # Linear Quadratic Regulator (atmo phase)
│ ├── mpc/ # Model Predictive Control (maglev)
│ └── stabilization/ # Attitude control algorithms
├── design/
│ ├── airfoils/ # .dat files for wing profiles
│ ├── geometry/ # OpenVSP/FreeCAD models
│ └── cad/ # Detailed CAD exports
├── data/
│ ├── lift_drag_polars/ # Aerodynamic coefficient data
│ ├── trajectory_logs/ # Simulation output files
│ ├── monte_carlo/ # Statistical analysis results
│ └── thermal_analysis/ # Temperature distribution data
├── roadmap/ # 12-month verification plan
└── patents/ # IP documentation
| Phase | Months | Focus | Deliverables |
|---|---|---|---|
| I | 1-3 | Mathematical Validation | Trajectory model, Monte Carlo (10k runs), Economic ROI |
| II | 4-6 | Aerodynamics & Thermal | Gryphon CFD, Max-Q analysis, TPS design |
| III | 7-9 | GNC Development | MPC (maglev), LQR (atmospheric), Solar sail dynamics |
| IV | 10-12 | Iron Bird Integration | UE5 visualization, Disaster testing, Investor presentation |
See roadmap/ for detailed milestone breakdown.
# Clone the repository
git clone https://github.com/your-org/BGKPJR-Core-Simulations.git
cd BGKPJR-Core-Simulations
# Create virtual environment
python -m venv venv
source venv/bin/activate # Windows: venv\Scripts\activate
# Install dependencies
pip install -r requirements.txt
# Run basic trajectory simulation
python simulation/src/trajectory_sim.py
# Run Monte Carlo analysis (warning: computationally intensive)
python simulation/src/monte_carlo.py --runs 1000We welcome contributions from aerospace engineers, physicists, and software developers. See CONTRIBUTING.md for guidelines.
Priority Areas:
- CFD expertise for hypersonic analysis
- Control systems engineers for GNC
- Materials scientists for TPS optimization
Docket: BGKPJR-001 United States Patent and Trademark Office - Application Pending
Title: Brazelton Gryphon Kepler Propulsion Jump Revolution Launch Architecture
See patents/ for full application text.
This project is licensed under the Apache License 2.0 - see LICENSE for details.
Shane Brazelton - Lead Engineer & Architect Project BGKPJR Development Team
| Partner | Role |
|---|---|
| Claude by Anthropic · claude.ai | Co-built this entire ecosystem |
| Raspberry Pi 5 · raspberrypi.com | Local compute backbone |
| Pironman 5-MAX · pironman.com | NVMe RAID 1 chassis that made it real |
"I could not have done any of this without them."
"We choose to go to the Moon not because it is easy, but because it is hard." - JFK
"We choose to launch from a cannon not because it is conventional, but because it is efficient." - Project BGKPJR
@thebardchat · Hazel Green, Alabama
If what I'm building matters to you — local AI for real people, tools for the left-behind — here's how to help:
- Sponsor me on GitHub
- Buy the book — You Probably Think This Book Is About You
- Star the repos — visibility matters for projects like this
Built by Shane Brazelton · Co-built with Claude (Anthropic) · Hazel Green, Alabama
Part of the ShaneBrain Ecosystem · Built under the Constitution