The methods presented in this chapter are for use with hover-capable flapping wing vehicles in the conceptual design phase. The class of flapping wing vehicles considered are those that maneuver by making changes to the motion of flapping wings, rather than making use of conventional aerodynamic surfaces. Methods are presented that allow one to iterate between vehicle design, trim, and controllability analysis until closure is achieved. The motion of the flapping wings is characterized by seven wing motion parameters: wing stroke amplitude, symmetric and asymmetric frequency, bias, upstroke and downstroke angle-of-attack limits, and wing stroke plane inclination. This chapter presents a table of cycle-averaged control derivatives that can be used with the multivariable chain rule to produce control derivative estimates for a diverse set of wing beat generation and control mechanisms that might be encountered in flapping wing vehicle designs. A method is presented that will enable the designer to estimate how the seven wing motion parameters change in response to changes in the control mechanism position; a step that is necessary to make use of the chain rule. A method for estimating the combined effect of fuselage motion and flapping wing motion is presented as well. Control design considerations and simulation methods are also discussed.
Dynamics and Control of Flapping Wing MAVs
Handbook of Unmanned Aerial Vehicles ; Kapitel : 55 ; 329-346
09.08.2014
18 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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