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Objective

Identifying the aerodynamic derivatives for small Fixed-wing model aircraft

Experimental Platform

Freewing F-22 Raptor scaled model
Model scale: 1/13
Wingspan: 1060mm
Length: 1500mm
Empty weight: 2.96kg

On-board Avionics
Pixhawk Autopilot (Pixhawk 4)
VN200 Inertial Measurement Unit
Custom built airdata computer
Airboom with AOA/AOS vane

In-house Airdata Computer

Specifications
USART interface to Flight control computer (Full duplex 115200 bps)
Two absolute encoders interface (SSI interface for digital encoder)
Two barbed pressure ports (Static and Dynamic)

Simulation-based parameter identification

PILS (Processor-in-the-loop Simulation) environment
Configuration: Pixhawk (processor) / Simulink (data interface) / X-plane (Dynamics model)

Flight experiments for parameter ID

Automated flight sequence design

Model comparison with the flight test data
Parameter identification using “Prediction Error Minimization Method”

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Researcher

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김수현(Kim Su Hyeon)
한국항공대학교 스마트항공모빌리티학과 무인시스템제어연구실(KAU USCL)
박사과정
10540 경기도 고양시 덕양구 항공대학로 76 전자관 322호
angelfive92@gmail.com

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