scholarly journals Wing Design, Fabrication, and Analysis for an X-Wing Flapping-Wing Micro Air Vehicle

Drones ◽  
2019 ◽  
Vol 3 (3) ◽  
pp. 65 ◽  
Author(s):  
Boon Hong Cheaw ◽  
Hann Woei Ho ◽  
Elmi Abu Bakar
Keyword(s):  
Insect Flight ◽  
Micro Air Vehicles ◽  
Flapping Wing ◽  
Indoor Environments ◽  
Wing Design ◽  
Thrust Generation ◽  
Thrust Measurement ◽  
Glue Method ◽  
Controller Board ◽  
Full Throttle

Flapping-wing Micro Air Vehicles (FW-MAVs), inspired by small insects, have limitless potential to be capable of performing tasks in urban and indoor environments. Through the process of mimicking insect flight, however, there are a lot of challenges for successful flight of these vehicles, which include their design, fabrication, control, and propulsion. To this end, this paper investigates the wing design and fabrication of an X-wing FW-MAV and analyzes its performance in terms of thrust generation. It was designed and developed using a systematic approach. Two pairs of wings were fabricated with a traditional cut-and-glue method and an advanced vacuum mold method. The FW-MAV is equipped with inexpensive and tiny avionics, such as the smallest Arduino controller board, a remote-control receiver, standard sensors, servos, a motor, and a 1-cell battery. Thrust measurement was conducted to compare the performance of different wings at full throttle. Overall, this FW-MAV produces maximum vertical thrust at a pitch angle of 10 degrees. The wing having stiffeners and manufactured using the vacuum mold produces the highest thrust among the tested wings.

Four-Bar Linkage Mechanism for Insectlike Flapping Wings in Hover: Concept and an Outline of Its Realization

2005 ◽  
Vol 127 (4) ◽  
pp. 817-824 ◽  
Author(s):  
Rafał Z˙bikowski ◽  
Cezary Galin´ski ◽  
Christopher B. Pedersen
Keyword(s):  
Insect Flight ◽  
Micro Air Vehicles ◽  
Flapping Wing ◽  
Flapping Wings ◽  
Test Bed ◽  
Linkage Mechanism ◽  
Actual Design ◽  
Straight Line Mechanism ◽  
Four Bar Linkage ◽  
Air Vehicles

This paper describes the concept of a four-bar linkage mechanism for flapping wing micro air vehicles and outlines its design, implementation, and testing. Micro air vehicles (MAVs) are defined as flying vehicles ca. 150 mm in size (handheld), weighing 50–100 g, and are developed to reconnoiter in confined spaces (inside buildings, tunnels, etc.). For this application, insectlike flapping wings are an attractive solution and, hence, the need to realize the functionality of insect flight by engineering means. Insects fly by oscillating (plunging) and rotating (pitching) their wings through large angles, while sweeping them forward and backward. During this motion, the wing tip approximately traces a figure eight and the wing changes the angle of attack (pitching) significantly. The aim of the work described here was to design and build an insectlike flapping mechanism on a 150 mm scale. The main purpose was not only to construct a test bed for aeromechanical research on hover in this mode of flight, but also to provide a precursor design for a future flapping-wing MAV. The mechanical realization was to be based on a four-bar linkage combined with a spatial articulation. Two instances of idealized figure eights were considered: (i) Bernoulli’s lemniscate and (ii) Watt’s sextic. The former was found theoretically attractive, but impractical, while the latter was both theoretically and practically feasible. This led to a combination of Watt’s straight-line mechanism with a drive train utilizing a Geneva wheel and a spatial articulation. The actual design, implementation, and testing of this concept are briefly described at the end of the paper.

scholarly journals Insect-like flapping wing mechanism based on a double spherical Scotch yoke

2005 ◽  
Vol 2 (3) ◽  
pp. 223-235 ◽  
Author(s):  
Cezary Galiński ◽  
Rafał Żbikowski
Keyword(s):  
Insect Flight ◽  
Micro Air Vehicles ◽  
Flapping Wing ◽  
Controlled Study ◽  
Concept Design ◽  
Test Bed ◽  
Insect Wing ◽  
Flying Insects ◽  
Adjustable Mechanism ◽  
Air Vehicles

We describe the rationale, concept, design and implementation of a fixed-motion (non-adjustable) mechanism for insect-like flapping wing micro air vehicles in hover, inspired by two-winged flies (Diptera). This spatial (as opposed to planar) mechanism is based on the novel idea of a double spherical Scotch yoke. The mechanism was constructed for two main purposes: (i) as a test bed for aeromechanical research on hover in flapping flight, and (ii) as a precursor design for a future flapping wing micro air vehicle. Insects fly by oscillating (plunging) and rotating (pitching) their wings through large angles, while sweeping them forwards and backwards. During this motion the wing tip approximately traces a ‘figure-of-eight’ or a ‘banana’ and the wing changes the angle of attack (pitching) significantly. The kinematic and aerodynamic data from free-flying insects are sparse and uncertain, and it is not clear what aerodynamic consequences different wing motions have. Since acquiring the necessary kinematic and dynamic data from biological experiments remains a challenge, a synthetic, controlled study of insect-like flapping is not only of engineering value, but also of biological relevance. Micro air vehicles are defined as flying vehicles approximately 150 mm in size (hand-held), weighing 50–100 g, and are developed to reconnoitre in confined spaces (inside buildings, tunnels, etc.). For this application, insect-like flapping wings are an attractive solution and hence the need to realize the functionality of insect flight by engineering means. Since the semi-span of the insect wing is constant, the kinematics are spatial; in fact, an approximate figure-of-eight/banana is traced on a sphere. Hence a natural mechanism implementing such kinematics should be (i) spherical and (ii) generate mathematically convenient curves expressing the figure-of-eight/banana shape. The double spherical Scotch yoke design has property (i) by definition and achieves (ii) by tracing spherical Lissajous curves.

Optimal Compliant Flapping Mechanism Topologies With Multiple Load Cases

2012 ◽  
Vol 134 (5) ◽  
Author(s):  
Bret Stanford ◽  
Philip Beran
Keyword(s):  
Aerodynamic Force ◽  
Compliant Mechanism ◽  
Micro Air Vehicles ◽  
Flapping Wing ◽  
Gradual Transition ◽  
Multiple Load Cases ◽  
Thrust Generation ◽  
Force Moment ◽  
Turning Maneuver ◽  
Multiple Load

The conceptual design of effective actuation mechanisms for flapping wing micro air vehicles presents considerable challenges, with competing weight, power, authority, and life cycle requirements. This work utilizes topology optimization to obtain compliant flapping mechanisms; this is a well-known tool, but the method is rarely extended to incorporate unsteady nonlinear aeroelastic physics, which must be accounted for in the design of flapping wing vehicles. Compliant mechanism topologies are specifically desired to perform two tasks: (1) propulsive thrust generation (symmetric motions of a left and a right wing) and (2) lateral roll moment generation (asymmetric motions). From an optimization standpoint, these two tasks are considered multiple load cases, implemented by scheduling the actuation applied to the mechanism’s design domain. Mechanism topologies obtained with various actuation-scheduling assumptions are provided, along with the resulting flapping wing motions and aerodynamic force/moment generation. Furthermore, it is demonstrated that both load cases may be used simultaneously for future vehicle control studies: gradual transition from forward flight into a turning maneuver, for example.

scholarly journals Can Scalable Design of Wings for Flapping Wing Micro Air Vehicle Be Inspired by Natural Flyers?

2018 ◽  
Vol 2018 ◽  
pp. 1-24 ◽  
Author(s):  
Yanghai Nan ◽  
Bei Peng ◽  
Yi Chen ◽  
Zhenyu Feng ◽  
Don McGlinchey
Keyword(s):  
Statistical Analysis ◽  
Aspect Ratio ◽  
Scaling Laws ◽  
Micro Air Vehicles ◽  
Flapping Wing ◽  
Performance Estimation ◽  
Wing Design ◽  
Geometric Similarity ◽  
Lumped Parameter ◽  
Scalable Design

Lift production is constantly a great challenge for flapping wing micro air vehicles (MAVs). Designing a workable wing, therefore, plays an essential role. Dimensional analysis is an effective and valuable tool in studying the biomechanics of flyers. In this paper, geometric similarity study is firstly presented. Then, the pw−AR ratio is defined and employed in wing performance estimation before the lumped parameter is induced and utilized in wing design. Comprehensive scaling laws on relation of wing performances for natural flyers are next investigated and developed via statistical analysis before being utilized to examine the wing design. Through geometric similarity study and statistical analysis, the results show that the aspect ratio and lumped parameter are independent on mass, and the lumped parameter is inversely proportional to the aspect ratio. The lumped parameters and aspect ratio of flapping wing MAVs correspond to the range of wing performances of natural flyers. Also, the wing performances of existing flapping wing MAVs are examined and follow the scaling laws. Last, the manufactured wings of the flapping wing MAVs are summarized. Our results will, therefore, provide a simple but powerful guideline for biologists and engineers who study the morphology of natural flyers and design flapping wing MAVs.

Numerical Investigation of the Response of Active Bend-Twist PZT Actuator

2012 ◽  
Author(s):  
Jaret C. Riddick ◽  
Asha J. Hall ◽  
Oliver J. Myers
Keyword(s):  
Numerical Investigation ◽  
Insect Flight ◽  
Micro Air Vehicles ◽  
Flapping Wing ◽  
Control Surface ◽  
Finite Element Analyses ◽  
Pzt Actuator ◽  
Simultaneous Excitation ◽  
Flexural Response ◽  
Twist Actuation

Army combat operations have placed a high premium on reconnaissance missions for micro air vehicles (MAVs). An analysis of insect flight indicates that in addition to the bending excitation (flapping), simultaneous excitation of the twisting degree-of-freedom is required to manipulate the control surface adequately. By adding a layer of angled piezoelectric segments to a Pb(Zr,Ti)O3 (also referred to as PZT) bimorph actuator, a bend-twist coupling may be introduced to the flexural response of the layered PZT, thereby creating a biaxial actuator capable of driving wing oscillation in flapping wing MAVs. The present study presents numerical investigation of the response of functionally–modified bimorph designs intended for active bend-twist actuation of cm-scale flapping wing devices. The relationships of geometry and orientation of the angled segments with bimorph bend-twist response will be presented using results of finite-element analyses.

Untethered Hovering Flapping Flight of a 3D-Printed Mechanical Insect

2011 ◽  
Vol 17 (2) ◽  
pp. 73-86 ◽  
Author(s):  
Charles Richter ◽  
Hod Lipson
Keyword(s):  
3D Printing ◽  
Insect Flight ◽  
Flapping Wing ◽  
Wing Design ◽  
Mechanical Parts ◽  
Design Cycle ◽  
3D Printed ◽  
Printed Materials ◽  
And Control ◽  
3D Printing Technique

This project focuses on developing a flapping-wing hovering insect using 3D-printed wings and mechanical parts. The use of 3D printing technology has greatly expanded the possibilities for wing design, allowing wing shapes to replicate those of real insects or virtually any other shape. It has also reduced the time of a wing design cycle to a matter of minutes. An ornithopter with a mass of 3.89 g has been constructed using the 3D printing technique and has demonstrated an 85-s passively stable untethered hovering flight. This flight exhibits the functional utility of printed materials for flapping-wing experimentation and ornithopter construction and for understanding the mechanical principles underlying insect flight and control.

scholarly journals Lift and thrust generation by a butterfly-like flapping wing–body model: immersed boundary–lattice Boltzmann simulations

2015 ◽  
Vol 767 ◽  
pp. 659-695 ◽  
Author(s):  
Kosuke Suzuki ◽  
Keisuke Minami ◽  
Takaji Inamuro
Keyword(s):  
Lattice Boltzmann ◽  
Lift Force ◽  
Micro Air Vehicles ◽  
Flapping Wing ◽  
The Body ◽  
Immersed Boundary ◽  
Body Model ◽  
Lattice Boltzmann Simulations ◽  
Thrust Generation ◽  
Boltzmann Method

AbstractThe flapping flight of tiny insects such as flies or larger insects such as butterflies is of fundamental interest not only in biology itself but also in its practical use for the development of micro air vehicles (MAVs). It is known that a butterfly flaps downward for generating the lift force and backward for generating the thrust force. In this study, we consider a simple butterfly-like flapping wing–body model in which the body is a thin rod and the rectangular rigid wings flap in a simple motion. We investigate lift and thrust generation of the model by using the immersed boundary–lattice Boltzmann method. First, we compute the lift and thrust forces when the body of the model is fixed for Reynolds numbers in the range of 50–1000. In addition, we estimate the supportable mass for each Reynolds number from the computed lift force. Second, we simulate free flights when the body can only move translationally. It is found that the expected supportable mass can be supported even in the free flight except when the mass of the body relative to the mass of the fluid is too small, and the wing–body model with the mass of actual insects can go upward against the gravity. Finally, we simulate free flights when the body can move translationally and rotationally. It is found that the body has a large pitch motion and consequently gets off-balance. Then, we discuss a way to control the pitching angle by flexing the body of the wing–body model.

scholarly journals FLAPPING WING DEVICES FOR MARS EXPLORATION

2011 ◽  
Author(s):  
Asier Ania ◽  
Dominique Poirel ◽  
Marie-Josée Potvin ◽  
Steeve Montminy
Keyword(s):  
Reynolds Number ◽  
Insect Flight ◽  
Low Reynolds Number ◽  
Flapping Wing ◽  
Low Density ◽  
Mars Exploration ◽  
Unsteady Aerodynamic ◽  
Aerial Vehicle ◽  
Low Reynolds

The use of an aerial vehicle would greatly enhance the domain of exploration on Mars. The main constraint in such a design would be the extreme Martian environment. The low-density atmosphere suggests the use of a low Reynolds number flight regime modeled after flapping wing insect flight. This flapping wing flight employs several unsteady aerodynamic mechanisms; delayed stall, wake capture, and rotational mechanisms. Two prototypes, a flapping wing and a rotary-flapping wing hybrid, have been built and will be tested in order to quantify the 'overall lift' generated and allow us to evaluate the efficacy of flapping wing flight on Mars.

Longitudinal Flight Dynamics of Flapping-Wing Micro Air Vehicles

2012 ◽  
Vol 35 (4) ◽  
pp. 1115-1131 ◽  
Author(s):  
Christopher T. Orlowski ◽  
Anouck R. Girard
Keyword(s):  
Flight Dynamics ◽  
Micro Air Vehicles ◽  
Flapping Wing ◽  
Air Vehicles
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