Man-Portable Aerial Defense Systems
PRECISION ROCKETRY SOLUTIONS FOR THE MODERN BATTLESPACE
CRYSTAL RIVER, FL // EST. 2026 // PRIMARY FACILITY
Vertically integrated defense platform combining COTS electronics, additive manufacturing, and simulation-verified aerodynamic design.
The ESP32-S3 flight computer executes real-time guidance algorithms at 240 MHz with dual-core processing capability. Integrated MPU6050 6-axis inertial measurement unit provides three-axis accelerometer and three-axis gyroscope data at configurable sample rates up to 1 kHz, enabling closed-loop attitude determination and flight path correction throughout the boost and coast phases.
Four-fin folding canard assembly with servo-actuated control surfaces provides active pitch and yaw authority from launch through apogee. Spring-loaded deployment mechanism ensures reliable fin extension upon rail departure. Control surface deflection is governed by PID loop feedback from the IMU, achieving stable flight characteristics across the operational envelope.
Multi-sensor telemetry architecture integrating GPS position tracking, BMP280 barometric altimeter with 0.12 hPa resolution for precision altitude determination, and HMC5883L 3-axis digital magnetometer for heading reference. All sensor data is logged at 10 Hz to onboard storage with post-flight retrieval capability for comprehensive mission analysis.
All structural and aerodynamic components are produced via FDM additive manufacturing using PLA and PETG thermoplastics, enabling rapid design iteration with sub-24-hour prototype turnaround. Autodesk Fusion 360 parametric modeling ensures dimensional accuracy and repeatability across production runs, with full revision control maintained for every airframe component.
Every flight configuration undergoes rigorous OpenRocket computational simulation prior to physical testing. Simulation profiles model thrust curves, drag coefficients, stability margins, and recovery deployment timing across variable atmospheric conditions. Over 200 simulated flights have been executed, validating performance parameters before commitment to physical test articles.
Purpose-built rail-guided launch platform provides consistent departure angle and eliminates tip-off error during the initial acceleration phase. Electronic ignition system utilizes ESP32-controlled relay actuation with a three-position safety interlock and continuity verification. Ground support equipment includes dedicated blast deflection and a standardized pre-flight checklist protocol.
Formal system parameters as documented in the FM-PADS program technical baseline.
| Parameter | Specification |
|---|---|
| DESIGNATION | FM-PADS Mk. I ACTIVE |
| GUIDANCE | ESP32-S3 dual-core 240 MHz flight computer, MPU6050 6-axis IMU (3-axis gyro + 3-axis accelerometer), PID closed-loop attitude control |
| STABILIZATION | 4-fin folding canard, servo-actuated, spring-loaded deployment, active pitch/yaw authority |
| TELEMETRY | GPS position tracking, BMP280 barometric altimeter (0.12 hPa), HMC5883L 3-axis magnetometer, 10 Hz logging to onboard SD |
| PROPULSION | Commercial solid rocket motor, Estes E12 or equivalent. Peak thrust 22.2 N, total impulse 28.45 Ns, burn time 3.0s VERIFIED |
| ALTITUDE | Simulated apogee: 850 ft AGL (E12 motor, nominal conditions). Verified via BMP280 barometric data CONFIRMED |
| AIRFRAME | 3D-printed PETG/PLA, FDM additive manufacturing. Fusion 360 parametric CAD with full revision control |
| SIMULATION | OpenRocket verified flight profiles. Thrust curve analysis, drag coefficient modeling, stability margin validation |
| DESIGN SOFTWARE | Autodesk Fusion 360, parametric modeling with dimensional tolerances maintained across production iterations |
| LAUNCH SYSTEM | Rail-guided, electronic ignition via ESP32 relay actuation. 3-position safety interlock with continuity verification |
| RECOVERY | Electronically deployed parachute system. Ejection charge initiated by flight computer at apogee detection via barometric trigger |
| OPERATING TEMP | Qualified for subtropical environment: 25-40°C ambient, high humidity tolerance. PETG components rated to 80°C |
| REGULATORY | Compliant with FAA 14 CFR Part 101 (unmanned rockets). Operations conducted per NAR Safety Code guidelines COMPLIANT |
| UNIT COST | Approximately $47 per flight-ready airframe, excluding reusable ground support equipment and avionics |
Authorized FM-PADS program items. All merchandise is ITAR-free and available without export license.
100% cotton, military green. Features the FM-PADS insignia and program motto: "Per Ardua Ad Garage." Standard issue for all program personnel.
Structured 6-panel cap with embroidered "FLORIDA MANPADS - EST. 2026" and rocket silhouette. Mesh back panel for ventilation in subtropical operating environments.
Premium vinyl, UV-resistant, rated for prolonged Florida sun exposure. Mission patch design suitable for equipment cases, vehicles, and workstation identification.
Ceramic, 11 oz capacity. Features the program mission patch. Dishwasher safe. Standard issue for pre-flight briefings and extended design review sessions.
Technical program briefing covering development methodology, facility capabilities, and system architecture.
The Florida Man-Portable Aerial Defense System (FM-PADS) program was established in Q1 2026 to demonstrate that commercial off-the-shelf (COTS) electronics, combined with modern additive manufacturing and open-source simulation tools, can produce a precision-guided model rocketry platform with legitimate flight control capabilities. The program employs an iterative design methodology with simulation-verified performance at every stage, achieving guided flight through integrated IMU feedback and active aerodynamic control surfaces.
The primary R&D facility in Crystal River, FL houses dedicated electronics assembly, 3D printing production, and component testing infrastructure. The facility supports full-cycle development from CAD design through flight-ready hardware, with capacity for concurrent prototyping of multiple airframe configurations. All soldering, sensor calibration, and avionics integration are performed on-site.
All aerodynamic and structural components are designed in Autodesk Fusion 360 using parametric modeling techniques that allow rapid dimensional iteration without full redesign cycles. Stability margins are calculated analytically and validated computationally before any physical prototype is committed to production. Structural components undergo load testing to verify print orientation and layer adhesion under expected flight loads.
Prior to physical flight testing, all configurations are validated through OpenRocket computational simulation, modeling thrust curves, aerodynamic drag, center of pressure migration, and recovery deployment timing across a range of atmospheric conditions. The simulation database contains over 200 virtual flights across 14 design iterations. Physical test campaigns are conducted at designated launch sites in compliance with NAR safety guidelines, with full telemetry capture for post-flight performance analysis.
The flight computer is built on the ESP32-S3 microcontroller platform, selected for its dual-core 240 MHz Xtensa LX7 processor, integrated WiFi for pre-flight telemetry download, and extensive peripheral support. The MPU6050 inertial measurement unit provides 6-axis motion data with 16-bit ADC resolution across configurable full-scale ranges. The sensor suite is completed by a BMP280 barometric pressure sensor, HMC5883L magnetometer, and GPS module, delivering a comprehensive flight data package at a COTS price point.
Selected feedback from program-adjacent personnel and community observers.
"The engineering rigor on display here is not what I expected to find in a residential garage. I have no further comment at this time."
"He purchases schedule-40 PVC in quantities that suggest either a significant irrigation project or something else entirely. We do not ask follow-up questions."
"We reviewed the inquiry. It is a model rocket. We confirmed this twice. The caller seemed disappointed by that determination."
"The system does not fall under ITAR export controls. It is a model rocket constructed from 3D-printed thermoplastic and consumer electronics. This has been communicated clearly."
"The avionics integration is thorough. The documentation is detailed. The garage has been fully requisitioned for this purpose. These are observations, not endorsements."
"Telemetry indicates nominal flight performance with stable attitude throughout the boost phase. Recovery was successful. Local wildlife appeared briefly startled but otherwise unaffected."