Longitudinal Mode System Identification of an Insect-like Tailless Flapping-Wing Micro Air Vehicle Using Onboard Sensors

• Published in: Applied sciences 2022-03, Vol.12 (5), p.2486
• Main Authors: Aurecianus, Steven, Ha, Gi-Heon, Park, Hoon-Cheol, Kang, Tae-Sam
• Format: Article
• Language: English
• Subjects: Birds; Cameras; Center of gravity; Closed loop systems; Controllers; Design; Dynamic models; Dynamical systems; Feedback control; Flapping wings; flapping-wing micro air vehicle; Frequency analysis; Frequency domain analysis; Frequency ranges; gray box model; Identification; Identification methods; Insects; Kinematics; longitudinal mode; Micro air vehicles (MAV); model refinement; Neural networks; Nonlinear dynamics; onboard sensors; Pitch (inclination); Pitching moments; Pitching motion; Robotics; Robots; Sensors; Stability derivatives; System identification; Transient response
• ISSN: 2076-3417; 2076-3417
• DOI: 10.3390/app12052486

In this paper, model parameter identification results are presented for a longitudinal mode dynamic model of an insect-like tailless flapping-wing micro air vehicle (FWMAV) using angle and angular rate data from onboard sensors only. A gray box model approach with indirect method was utilized with adaptive Gauss–Newton, Levenberg–Marquardt, and gradient search identification methods. Regular and low-frequency reference commands were mainly used for identification since they gave higher fit percentages than irregular and high-frequency reference commands. Dynamic parameters obtained using three identification methods with two different datasets were similar to each other, indicating that the obtained dynamic model was sufficiently reliable. Most of the identified dynamic model parameters had similar values to the computationally obtained ones, except stability derivatives for pitching moment with forward velocity and pitching rate variations. Differences were mainly due to certain neglected body, nonlinear dynamics, and the shift of the center of gravity. Fit percentage of the identified dynamic model (~49%) was more than two-fold higher than that of the computationally obtained one (~22%). Frequency domain analysis showed that the identified model was much different from that of the computationally obtained one in the frequency range of 0.3 rad/s to 5 rad/s, which affected transient responses. Both dynamic models showed that the phase margin was very low, and that it should be increased by a feedback controller to have a robustly stable system. The stable dominant pole of the identified model had a higher magnitude which resulted in faster responses. The identified dynamic model exhibited much closer responses to experimental flight data in pitching motion than the computationally obtained dynamic model, demonstrating that the identified dynamic model could be used for the design of more effective pitch angle-stabilizing controllers.