Open loop pitch control of a flapping wing micro-air vehicle using a tail and control mass

Orlowski, Christopher T.; Girard, Anouck; Shyy, Wei

doi:10.1109/acc.2010.5530878

Cited by 23 publications

(7 citation statements)

References 10 publications

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“…The chosen method is a hybrid of Euler and Lagrange techniques and is akin to Kane's equations and the Gibbs-Appel Equations [35]. The flight dynamics model is previously presented in [36,37]. The model, presented here, is enhanced from previous work, including the inclusion of stroke plane dynamics, calculation of the aerodynamic forces and moments based on a quasi-steady/blade-element method, and a more accurate accounting of the angular velocity of the wings.…”

Section: A Methodsmentioning

confidence: 99%

“…In addition to the B frame, the stroke plane frames are two body-fixed frames originated at the wing joints. The stroke plane frames are denoted by R sp and L sp and have initial [10] Linear No CFD Honeybees Doman et al [13,14] Nonlinear No Quasi steady/blade element Robot Fly Deng et al [18] Nonlinear No Quasi steady/blade element Small wing mass Bolender [26] Nonlinear Yes (two degrees of freedom per wing) Berman and Wang [12] No limitations Sun et al [27] Nonlinear Derived (not simulated) Navier-Stokes No limitations Buler et al [23] Nonlinear Yes (two degrees of freedom per wing) Not specified Ornithopters Grauer and Hubbard [25] Nonlinear Yes (one degree of freedom per wing) Quasi steady Ornithopters Orlowski et al [36,37] Nonlinear Yes (three degrees of freedom per wing) Berman and Wang [12] No limitations orientation parallel to the B frame. The orientation is rotated by an angle about theb y axis of the B frame to the stroke plane.…”

Section: B Reference Framesmentioning

confidence: 99%

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Modeling and Simulation of Nonlinear Dynamics of Flapping Wing Micro Air Vehicles

2011

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Section: A Methodsmentioning

confidence: 99%

Section: B Reference Framesmentioning

confidence: 99%

Modeling and Simulation of Nonlinear Dynamics of Flapping Wing Micro Air Vehicles

2011

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“…25 and compared to a 'wingless' model in Ref. 3, a two wing FWMAV with a tail and control mass in Ref. 26, and a four wing FWMAV in Ref. 27.…”

Section: Multibody Flight Dynamics Modelmentioning

confidence: 99%

Averaging of the Nonlinear Dynamics of Flapping Wing Micro Air Vehicles for Symmetrical Flapping

Orlowski

Girard

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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First order equations of motion for a flapping wing micro-air vehicle are presented. The first order, longitudinal equations of motion are obtained from the second-order, strongly coupled, multi-body equations of motion using an approximate inverse. The nonlinear dynamics of the longitudinal equations of motion are averaged using two different methods: local averaging over a fully flapping cycle and local averaging over quarter-flapping cycles. Open loop simulations are presented, near a hover condition, for both averaged systems. The results for the locally averaged system are not consistent with the solution to the full system -suggesting that the neglecting of individual contributions to the dynamics, due to averaging over the entirety of a flapping cycle, is not a valid approach. Better results are obtained when the equations of motion are averaged over a quarter of a flapping cycle. The quarter-cycle results show a significant improvement in the accuracy of the position and orientation of the simulations versus the cycle averaged simulations.

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“…The method of derivation was previously used to develop the equations of motion for a two-wing flapping wing micro-air vehicle 9 and a flapping wing micro-air vehicle with a tail and a control mass. 10 Simulations will investigate four main kinematic configurations, two for the dragonfly configuration and two for the x-wing configuration. The dragonfly configuration will be investigated with biomimetic wing kinematics.…”

Section: Dynamic Model Developmentmentioning

confidence: 99%

Four Wing Flapping Micro Air Vehicles - Dragonies or X-Wings?

Orlowski

Girard

Shyy

2010

AIAA Guidance, Navigation, and Control Conference

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The aerodynamic feats of dragonflies are well documented. However, human beings have created flying vehicles that do not mimic nature, e.g. helicopters and quad-rotors. The paper presents initial investigations, via simulations, into the dynamics of a four wing, flapping wing micro-air vehicle. The paper attempts to answer the question of whether four wings in a traditional setup, akin to a dragonfly, is more, or less, beneficial than a 'x-wing' configuration. The micro-air vehicle is modeled as a system of five connected rigid bodies, a central body and four wings. The equations of motion are derived using D'Alembert's Principle for Multiple Rigid Bodies. Each wing is given three separate degrees of freedom relative to the central body. Open loop simulations are presented using the full nonlinear equations of motion, which include the inertial effects of the wings on the central body. Simulations show that an 'x-wing' configuration and a 'revised' dragonfly configuration may provide better, inherent stability than a biomimetic vehicle modeled after a dragonfly. Simulations of the two configurations show better pitch stability than a biomimetic simulation and the 'revised' dragonfly exhibits outstanding stability and lift characteristics.

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Open loop pitch control of a flapping wing micro-air vehicle using a tail and control mass

Cited by 23 publications

References 10 publications

Modeling and Simulation of Nonlinear Dynamics of Flapping Wing Micro Air Vehicles

Modeling and Simulation of Nonlinear Dynamics of Flapping Wing Micro Air Vehicles

Averaging of the Nonlinear Dynamics of Flapping Wing Micro Air Vehicles for Symmetrical Flapping

Four Wing Flapping Micro Air Vehicles - Dragonies or X-Wings?

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