Modeling and Closed Loop Flight Testing of a Fixed Wing Micro Air Vehicle

作者：Kandath Harikumar^*; Pushpangathan Jinraj V; Bera Titas; Dhall Sidhant; Bhat M Seetharama

来源：Micromachines, 2018, 9(3): 111.

DOI：10.3390/mi9030111

• flight testing
• lateral dynamics
• longitudinal dynamics
• micro air vehicle
• propeller effects
• wind tunnel testing

This paper presents the nonlinear six degrees of freedom dynamic modeling of a fixed wing micro air vehicle. The static derivatives of the micro air vehicle are obtained through the wind tunnel testing. The propeller effects on the lift, drag, pitching moment and side force are quantified through wind tunnel testing. The dynamic derivatives are obtained through empirical relations available in the literature. The trim conditions are computed for a straight and constant altitude flight condition. The linearized longitudinal and lateral state space models are obtained about trim conditions. The variations in short period mode, phugoid mode, Dutch roll mode, roll subsidence mode and spiral mode with respect to different trim operating conditions is presented. A stabilizing static output feedback controller is designed using the obtained model. Successful closed loop flight trials are conducted with the static output feedback controller.

• 出版日期2018-3
• 单位南阳理工学院