Flight Dynamics Modeling and Control of a Novel Catapult Launched Tandem-Wing Micro Aerial Vehicle With Variable Sweep

• Published in: IEEE access Vol. 6; pp. 42294 - 42308
• Main Authors: Gao, Liang, Jin, Hongzhe, Zhao, Jie, Cai, Hegao, Zhu, Yanhe
• Format: Journal Article
• Language: English
• Published: Piscataway IEEE 01-01-2018; The Institute of Electrical and Electronics Engineers, Inc. (IEEE)
• Subjects: Actuators; Aerodynamic characteristics; Aerodynamics; Aerospace control; Aircraft; Airframes; Atmospheric modeling; Automotive components; catapult launch; Control surfaces; Control theory; Couplings; dynamic coupling; Dynamic models; Elevons; Flight control; Fuselages; Kane method; Micro air vehicles (MAV); Morphing; morphing aircraft; Multibody systems; Nonlinear analysis; Nonlinear dynamics; Sweep angle; Tandem-wing; variable sweep; Vehicle dynamics; Yaw
• ISSN: 2169-3536; 2169-3536
• DOI: 10.1109/ACCESS.2018.2858293

In this paper, the variable sweep is used as a replacement for the conventional control surfaces for flight control on a tandem-wing micro aerial vehicle (MAV). This configuration allows the MAV to be folded into and launched from a tubular catapult while also retaining an adequately high effectiveness and a simple structure. As new control inputs, the four sweep angles of the MAV are planned as symmetric and asymmetric morphing to eliminate the reactive forces between the airfoils and fuselage during morphing. The aerodynamic characteristics of the MAV are presented through numerical simulations to study the effects of variable sweep morphing. An accurate nonlinear multibody dynamic model of the variable sweep MAV is established using the Kane method. Next, open-loop dynamic responses of sweep morphing based on the nonlinear dynamic model are analyzed and compared with the responses caused by the elevons control mode to examine the control effectiveness. Moreover, a flight control law based on sweep control is designed and verified using a height and yaw tracking simulation with different actuator response rates. The results show that the sweep control mode produces weaker coupling between the longitudinal and lateral dynamics than the elevons control mode and that the innovative approach for flight control is feasible and effective.