Flapping Wing Multi-body Dynamic Simulation

Zhong, Jingyang; Song, Bifeng; Wang, Jin

doi:10.1016/j.proeng.2014.12.617

Cited by 2 publications

(2 citation statements)

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“…Orlowski et al (2009) derived the equations of motion for a FMAV using D'Alembert's principle extended to rigid bodies. Jingyang et al (2015) deduced the multi-body dynamic equation for a flapping-wing vehicle by applying Newton's laws and angular momentum theorem. Hassan and Taha (2017) coupled together the longitudinal flapping-flight dynamic model consisting of the full, multi-body equations of motion and the analytical aerodynamic model to understand the mutual interaction.…”

Section: Flight Dynamics Of Fmav 249mentioning

confidence: 99%

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Aerodynamic and flight dynamic parametric studies of a flapping wing

Chetia

Rajaram

Sreejalekshmi

2022

IJIUS

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PurposeFlapping-wing vehicles show various advantages as compared to fixed wing vehicles, making flapping-wing vehicles' study necessary in the current scenario. The present study aims to provide guidelines for fixing geometric parameters for an initial engineering design by a simple aerodynamic and flight dynamic parametric study.Design/methodology/approachA mathematical analysis was performed to understand the aerodynamics and flight dynamics of the micro-air vehicle (MAV). Only the forces due to the flapping wing were considered. The flapping motion was considered to be a combination of the pitching and plunging motion. The geometric parameters of the flapping wing were varied and the aerodynamic forces and power were observed. Attempts were then made to understand the flight stability envelope of the MAV in a forward horizontal motion in the vertical plane with similar parametric studies as those conducted in the case of aerodynamics.FindingsFrom the aerodynamic study, insights were obtained regarding the interaction of design parameters with the aerodynamics and feasible ranges of values for the parameters were identified. The flapping wing was found to have neutral static stability. The flight dynamic analysis revealed the presence of an unstable oscillatory mode, a stable fast subsidence mode and a neutral mode, in the forward flight of the MAV. The presence of unstable modes highlighted the need for active control to restore the MAV to equilibrium from its unstable state.Research limitations/implicationsThe study does not take into account the effects of control surfaces and tail on the aerodynamics and flight dynamics of the MAV. There is also a need to validate the results obtained in the study through experimental means which shall be taken up in the future.Practical implicationsThe parametric study helps us to understand the extent of the impact of the design parameters on the aerodynamics and stability of the MAV. The analysis of both aerodynamics and dynamic stability provides a holistic picture for the initial design. The study incorporates complex mathematical equations and simplifies such to understand the aerodynamics and flight stability of the MAV from an engineering perspective.Originality/valueThe study adds to already existing knowledge on the design procedures of a flapping wing.

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Section: Flight Dynamics Of Fmav 249mentioning

confidence: 99%

“…(2009) derived the equations of motion for a FMAV using D'Alembert's principle extended to rigid bodies. Jingyang et al . (2015) deduced the multi-body dynamic equation for a flapping-wing vehicle by applying Newton's laws and angular momentum theorem.…”

Section: Introductionmentioning

confidence: 99%