Project brief
Designed the ice detection sensor electronics and de-icing protection control system for a light twin-engine piston aircraft. The system uses dual-technology ice detection (capacitive ice detector + ultrasonic thickness sensor) to detect ice formation on wing leading edges and activates protection systems automatically, including pneumatic de-icing boots, pitot/static heat, windshield heat, and engine inlet heat.
The project narrative describes detection electronics and protection control integration. Environmental coverage and qualification claims are not independently substantiated here.
The engineering challenge
Combine ice-sensing inputs with coordinated protection-zone control and cockpit status.
Engineering approach
- Use the stated capacitive and ultrasonic paths as complementary detection inputs.
- Map detection states to boot and heater control functions.
- Include startup test and annunciation in the control sequence.
Features & capabilities
- Dual-technology: capacitive ice detector + ultrasonic ice thickness sensor
- Detects ice accretion from 0.5mm – 50mm thickness
- Automatic activation of 4-zone pneumatic de-icing boot system
- Pitot/AOA/static heat control — 4 channels, 100W each element
- Engine inlet inlet lip heat (2 channels) and windshield heat
- ARINC 429 ice warning output to EICAS display
- FAR Part 25 Appendix C 14CFR Appendix O icing envelope coverage
- Built-in test (BIT) with cockpit pass/fail indication on startup
Software & engineering tools
STM32F446, AD7124 ADC, solid-state relay (SSR) module, Altium Designer (4-layer MIL-SPEC), ARINC 429