Dynamic Modeling and Analysis of Fixed-Wing Micro Air Vehicle

Abstract

This paper describes the dynamic modeling and analysis of a fixed-wing micro air vehicle (MAV). A nonlinear model for the MAV motion with six degrees of freedom is formulated first. Next, an extended version of the linear-time-invariant model for the MAV is derived by applying small perturbation theory and linearizing around an equilibrium flight condition. This ad hoc extended model for the MAV retains more terms that are generally neglected in mathematic models of conventional airplanes. To explore the stability and control characteristics, the aerodynamic derivatives required by dynamic modeling are evaluated using low-Reynolds-number wind tunnel testing data and some theoretical/empirical formulas. A fixed-wing MAV with a 15-cm wingspan successfully flown in 2002 is used as a baseline prototype for dynamic modeling and analysis. The longitudinal and lateral dynamic responses of the MAV under various conditions are demonstrated. The performance of the present extended MAV model is investigated by comparing the flight dynamics for different models. The simulation results show that the proposed extended model is consistent with the nonlinear dynamics model for a wider range of flight conditions. The present analysis may aid a better understanding of flight characteristics as well as design and analysis of MAV systems.

A novel solution methodology for longitudinal flight characterization of a Flying-Wing Micro Aerial Vehicle

“…The classical longitudinal modes have been captured by all three methodologies (conventional, Kuo methodology, 52 and the proposed methodology). Results from conventional LTI and the proposed methodology converged to 0 magnitude after phugoid oscillations died down slowly.…”

“…51 These four states become variables for longitudinal dynamics with control inputs as elevon control and throttle control. Earlier, an extended LTI system was proposed by Kuo et al 52 , 53 where dimensional derivatives were assumed to be a summation of axial force (X-force) and vertical force (Z-force). The authors of this research believed, that the solution of high pitch maneuvers cannot be addressed using axial and vertical force.…”

“…The unit impulse response of the elevons in an elevator role was also analyzed at the same flight conditions as of a unit step input and is plotted in Figure 11. The response of the longitudinal state variable upon a unit impulse input can be seen in Figure 11 The classical longitudinal modes have been captured by all three methodologies (conventional, Kuo methodology, 52 and the proposed methodology). Results from conventional LTI and the proposed methodology converged to 0 magnitude after phugoid oscillations died down slowly.…”

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

“…The stall of the wing is delayed by 10 of an angle of attack ( ) with the aerodynamic effects of rotating propeller. In [ 15 ], a six degree of freedom nonlinear model for MAV is developed without including the propeller effects. Thereafter, a linear model which includes terms which are often neglected in the linear model of a bigger aircraft is constructed by linearizing the six degrees of freedom nonlinear model around a trim point.…”