Roshan Aerospace IndustriesContact ↗

RAI-AVN-001 / Bench prototype active

Mini Flight Computer V1

RAI / Evidence-led development

An ESP32-based learning avionics platform integrating pressure, inertial sensing, display, actuation, recovery indication, and flight-state logic.

GalleryTechnical recordMathematics3D modelDocuments

02 / Engineering record

What was actually done

Flight Computer V1 is a breadboard-level avionics prototype. OLED, BMP280, MPU6050, servo, buzzer, and ESP32 tests have been completed individually. The next work is combined logic, bench validation, data logging, apogee detection, deployment sequencing, filtering, and fail-safe behaviour.

Evidence available

  • Independent module tests completed
  • Locked I²C, servo, and buzzer pin mapping
  • Physical breadboard prototype
  • State-machine and recovery logic defined
  • Combined code and logging are active development tasks

Recorded dimensions & specifications

ControllerESP32 DevKit / WROOM-32
Pressure sensorBMP280
IMUMPU6050
I²C pinsSDA 21 / SCL 22
Servo outputGPIO 18
Buzzer outputGPIO 25

03 / Mathematics

Calculations, not decoration

Altitude estimateh = 44330[1 − (P/P₀)^0.1903]

Barometric approximation; requires baseline pressure and careful filtering.

Acceleration magnitude|a| = √(ax² + ay² + az²)

Useful for event detection and sensor-health checks.

Apogee logicv̄z < 0 after positive ascent + persistence gate

Conceptual detection rule; deployment must not rely on a single noisy sample.

04 / Interactive engineering model

3D release pending

No verified STL or browser-ready glTF file is currently available in the project archive. A fake model would damage credibility. This viewer area is intentionally locked until the real export is checked, versioned, and approved for public release.

RAI / MODEL GATESTL / GLB
NOT RELEASEDModel ownership and public-release review required

05 / Documentation

Reports & release record

Technical reportPublic file not yet availableRelease pending

Declared limitations

  • Not flight-qualified
  • No redundant sensors or power architecture
  • No environmental, vibration, EMI, drop, or launch testing
  • No calibrated altitude accuracy figure
  • No deployment safety certification
  • No released PCB, enclosure, report, or 3D model