Aerodynamic modelling of flapping flight using lifting line theory

Bhowmik, Joydeep; Das, Debopam; Ghosh, Saurav Kumar

doi:10.1108/20496421311298134

Cited by 5 publications

(4 citation statements)

References 12 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…As per the lifting line theory, the lift produced by the wing is proportional to the horseshoe vortex. It is the combination of a bound vortex and a free vortex (Bhowmik et al , 2013).…”

Section: Resultsmentioning

confidence: 99%

Effect of chord-wise flexibility in the lift generation of flapping MAV with membrane wing

S.¹,

R.²

2022

AEAT

View full text Add to dashboard Cite

Purpose The purpose of this study is to experimentally analyse the effect of flexible and stiffened membrane wings in the lift generation of flapping micro air vehicle (MAV). Design/methodology/approach This is analysed by the rectangle wing made up of polyethylene terephthalate sheets of 100 microns. MAV is tested for the free stream velocity of 2 m/s, 4 m/s, 6 m/s and k* of 0, 0.25, 1, 3, 8. This test is repeated for flapping MAV of the free flapping frequency of 2 Hz, 4 Hz, 6 Hz, 10 Hz and 12 Hz. Findings This study shows that the membrane wing with proper stiffeners can give better lift generation capacity than a flexible wing. Research limitations/implications Only a normal force component is measured, which is perpendicular to the longitudinal axis of the model. Practical implications In MAVs, the wing structures are thin and light, so the effect of fluid-structure interactions is important at low Reynold’s numbers. This data are useful for the MAV developments. Originality/value The effect of chord-wise flexibility in lift generation is the study of the effect of a flexible wing and rigid wing in MAV. It is analysed by the rectangle wing. The coefficient of normal force at different free stream conditions was analysed.

show abstract

“…As per the lifting line theory, the lift produced by the wing is proportional to the horseshoe vortex. It is the combination of a bound vortex and a free vortex (Bhowmik et al , 2013).…”

Section: Resultsmentioning

confidence: 99%

Effect of chord-wise flexibility in the lift generation of flapping MAV with membrane wing

S.¹,

R.²

2022

AEAT

View full text Add to dashboard Cite

show abstract

“…This is something the present study tries to achieve by observing the aerodynamic and flight dynamic characteristics of a wing subjected to change in wing twist during flapping. Bhowmik et al (2013) describes an aerodynamic model for flapping-wing flight based on the lifting line theory, which assumes a quasi-steady behavior. This model takes into account different geometrical twists for upstroke and downstroke, much like natural fliers.…”

Section: Flight Dynamics Of Fmav 249mentioning

confidence: 99%

Aerodynamic and flight dynamic parametric studies of a flapping wing

Chetia

Rajaram

Sreejalekshmi

2022

IJIUS

View full text Add to dashboard Cite

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.

show abstract

“…Grauer 6 modeled a Hawk inspired wingspan of 1.22 m and showed the importance of flapping wing geometry. Bhowmik et al 7 designed a flight prototype of 50 cm long wingspan, which includes an integrated gear box along with four bar mechanism, whose lift generation capability was improved by flapping and twisting operation. Kumar et al 8 proposed a prototype of black headed Gull comprising servo powered mechanism.…”

Section: Introductionmentioning

confidence: 99%

Bioinspired flapping wing UAV and its kinematic analysis—a novel approach

Dewangan

Pradhan

Roy

2022

Proceedings of the Institution of Mechanical Engineers, Part K:

View full text Add to dashboard Cite

A rich development in the domain of flapping wing Unmanned Aerial Vehicle (FWUAV) is not yet entirely sufficient to implement the findings of real-life situations. Using the limited knowledge of this domain, this work enlightens the scientific community by introducing a homegrown, patented flapping mechanism of foldable wing aerial vehicle. The synchronized dual wing flapping mechanism consists of a crank slotted lever, a gear train and a special type of 4 bar kinematic chain. The entire sets are powered by a DC motor through crank connected motor shaft. Flapping cycle works on quick return principle generated by crank slotted lever mechanism and foldable wing structure by the special type 4 bar chain with gear train ensure the controlled flapping frequency, twist angle, altitude gain and attitude parameters (Pitch, roll, yaw). This work majorly focuses on the kinematics of the developed bio mimic mechanism by observing the variation of flapping wing orientation, angular velocity and angular acceleration with respect to the crank rotation as well as different crank speeds. These analytically obtained kinematic parameters are further validated after developing a three-dimensional model of the said mechanism as well as multibody analysis by MSC ADAMS. The patterns of the kinematic parameters such that angular displacement, angular velocity and angular acceleration between output and input links are similar and its validation guarantees the correctness of developed mechanism. The kinematic analyzes of linkages are also essential for dynamic study as well as fabrication of prototype.

show abstract

Aerodynamic modelling of flapping flight using lifting line theory

Cited by 5 publications

References 12 publications

Effect of chord-wise flexibility in the lift generation of flapping MAV with membrane wing

Effect of chord-wise flexibility in the lift generation of flapping MAV with membrane wing

Aerodynamic and flight dynamic parametric studies of a flapping wing

Bioinspired flapping wing UAV and its kinematic analysis—a novel approach

Contact Info

Product

Resources

About