Stability Derivatives Estimation of Unmanned Aerial Vehicle

Abstract

The purpose of this research is to estimate the dimensional stability derivatives in linear dynamic model of a fixed-wing model-scale unmanned aerial vehicle (UAV) by real flight data logged by an onboard flight computer. The paper described the experimental setup, operation procedure of raw flight data, process of nonlinear least squares estimation, and cause-effect examination of impulse responses. The simulation-based results of the estimated model indicated a very good accuracy with real flight data. The linear longitudinal and lateral models are very helpful for designing the stability-augmentation system or autopilot for the UAV.

Pitch Attitude Control Design of Unmanned Aerial Vehicle via Hardware-in-the-Loop Simulation

“…The detailed description of hardware-in-the-loop simulation system and virtual instrumentation is presented in section 2. According to the mathematical model for the MP2000UAV by Sun et al [8], the PID controller and FLC for pitch angle hold mode are designed in section 3. The results in HILS are demonstrated and discussed in section 4 where unmodelled dynamics and nonlinear saturation of real servo and sensor are considered.…”