Dynamical systems analysis of electrostatic and aerodynamic forced vibrations of a thin flexible electrode

Transverse vibrations of an electrostatically actuated thin flexible cantilever perturbed by low-speed air flow is studied using both experiments and numerical modeling. In the experiments the dynamic characteristics of the cantilever are studied by supplying a DC voltage with an AC component for electrostatic forcing and a constant uniform air flow around the cantilever system for aerodynamic forcing. The maximum voltage applied varies from 1 - 9 kV and air flow speeds range from 0.224 - 3.58 m/s (0.5 - 8 mile/hr). The Reynolds numbers for these speeds lie in the range of 1000 - 20000. A range of control parameters leading to stable vibrations are established using the Strouhal number as the operating parameter whose inverse values change from 100 - 2500. The Numerical results are validated with experimental results. Assuming the amplitude of vibrations are small, then a non-linear dynamic Euler-Bernoulli beam equation with viscous damping and gravitational effects is used to model the vibrations of the dynamical system. Aerodynamic forcing is modeled as a temporally sinusoidal and uniform force acting perpendicular to the beam length. The forcing amplitude is found to be proportional to square of air flow velocity by obtaining relationship between the experimental amplitude of vibrations and air flow velocity. Numerical results strongly agree with those of experiments predicting accurate vibration amplitudes, displacement frequency and quasi-periodic displacements of the cantilever tip

Flapping Wing Micro Air Vehicle Wing Manufacture and Force Testing

Numerous wing manufacturing techniques have been developed by various universities for research on Flapping Wing Micro Air Vehicles. Minimal attention though is given to repeatability of wing aerodynamics and dynamic response, which is crucial to avoid asymmetric flapping. Thus the focus of this research becomes twofold. First, repeatable wing manufacturing techniques are developed to ensure flapping wings have similar aerodynamic and dynamic characteristics. For this purpose, four wing designs were selected to not only test the aerodynamics of the different designs, but to also validate manufacturing techniques. The various wing designs are assessed using two methods: dynamic and aerodynamic data. Dynamic data, specifically the wing\u27s structural dynamic response, is measured using a 3D laser vibrometer. From this vibration data, the wings natural frequency modes can be determined which should correlate strongly within the various wing designs if the manufacturing techniques are repeatable. Next, using a piezoelectric flapping actuator, the four wing designs are flapped with force data collected. This data is then used to determine the aerodynamic characteristics of each wing. From the two methods of wing evaluation, it was found that the wings manufactured using a three-layer carbon layup showed greater structural dynamic modal repeatability as compared to one-layer carbon wings. Additionally, Wing Design 3 flapped with the most efficiency with a significantly higher lift to drag ratio as compared to the other wing designs. From this research, the wing manufacturing techniques are quantitatively shown to be repeatable while an optimal wing design based on the maximum lift-to-drag ratio is found which can be used for future research

The effects of wing inertial forces and mean stroke angle on the pitch stability of hovering insects

This paper discusses the wing inertial effects on stability of pitch motion of hovering insects. The paper also presents a dynamic model appropriate for using averaging techniques and discusses the pitch stability results derived from the model. The model is used to predict the body angle of five insect species during hover, which are in good agreement with the available experimental results from different literature. The results suggest that the wing inertia forces have a considerable effect on pitch dynamics of insect flight and should not be ignored in dynamic analysis of hovering insects. The results also suggest that, though the pitch stability of hovering insects is open-loop stable, it may not be vibrationally stabilized. Instead, the pitch stability is a balance of the moment of insect's weight and the aerodynamic moment due to flapping kinematics with a nonzero mean stroke angle. Experiments with a flapping wing device confirm this results. To clearly explain the used model and clarify the difference between vibrational and non-vibrational stabilization, first this paper discusses the vibrational control of a three-degree-of-freedom force-input pendulum with its pivot moving in a vertical plane.Comment: 21 pages, 9 figures, 4 table

Thrust Enhancement and Degradation Mechanisms due to Self-Induced Vibrations in Bio-inspired Flying Robots

Whenever a flapping robot moves along a trajectory it experiences some vibration about its mean path. Even for a hovering case, a flier experiences such vibration due to the oscillatory nature of the aerodynamic forces. In this paper we have studied the effect of such vibration on hovering. We used two setups to measure thrust force generated by flapping robots. One involving loadcell, which does not allow any kind of vibration. The other one involves a pendulum which allows vibration at a particular direction. We used two different flapping robots; one is a traditional flapping robot with two wings and the other one is a four wings robot which exploits clap and peel mechanism to generate thrust. We observed that the loadcell setup measures more thrust for the two wings model than the pendulum setup. The opposite trend was observed for the four wings model. We measured the vibration induced velocity using motion capture system. We used well known aerodynamic models to observe the effect of the vibration during the flapping cycle. To gain physical insight into the vibration affected flow field, we used smoke flow visualization at different instances during the flapping cycle. It revealed that the perturbation ebbs a jet effect in case of the two wings which leads to its adverse effect for thrust generation. On the contrary the perturbation enhances the clapping effect for the four wings robot, resulting favorable for thrust generation

유격을 고려한 무미익 초소형 날갯짓 비행체 통합 설계: 기하분석 및 수치 해석을 통한 접근

학위논문 (석사) -- 서울대학교 대학원 : 공과대학 협동과정 우주시스템 전공, 2021. 2. 신상준.Unlike birds, an insect type tailless flapping wing does not possess tail wings. Therefore, insect type flapping wing may be fabricated in small size and of decreased weight. Because of the taillessness, however, stable flight of an insect type flapping wing depends only on main wings. Thus, a number of researches were conducted regarding its control mechanisms. In this thesis, the trailing edge control, one of the methods developed to produce control moments, is adopted. Such method requires additional shafts that connect the root of the main wing and control mechanism, and the shafts are rotated to deform the wing shape. In this manner, asymmetric aerodynamic forces are produced. The control mechanism uses micro actuators for compact design. However, small size of the micro actuator gearbox causes relatively large backlash and the resulting free play of the main wings that generates undesirable aerodynamic forces. Under such circumstance, design improvement of the control mechanism is conducted to minimize the effects of the free play. First, geometry analysis is performed to investigate the factors that cause the free play. Control mechanism design for the minimized free play is obtained. Then, three-dimensional computer aided design (CAD) of modified configuration is drawn, and kinematic simulations are conducted by RecurDyn to determine the prevention of interference. Finally, the feasibility of modified design is examined by the numerical simulation. The main wings are modeled by the displacement-based geometrically exact beam model combined with cross-sectional analysis. To mimic the free play appropriately, the spring elements are attached to the joints. At the same time, two-dimensional unsteady aerodynamic model is used for aerodynamic forces. Consequently, the reasonable control moments are gathered in terms of the maneuverability.곤충 모방형 날갯짓 비행체는 꼬리날개가 없기 때문에 새 모방형 날갯짓 비행체와 비교하여 가볍고 작게 설계될 수 있다. 그러나, 곤충 모방형 날갯짓 비행체는 꼬리날개가 없다는 특징으로 인하여, 오직 두 날개만을 이용하여 조종력을 발생시킨다. 따라서, 이에 대한 많은 연구가 수행되었고 개발된 여러 자세 제어 방법 중 본 학위 논문에선 날개 끝단 비틀림을 이용한 자세 제어 장치를 다룬다. 해당 방법은 주날개의 뿌리 부분을 자세 제어 장치와 연결하고 이를 회전시켜 날개 끝단에 변형을 발생시킨다. 자세 제어 장치에는 경량화를 위하여 가볍고 작은 장비들이 사용된다. 그러나, 자세 제어 장치 제작에 사용되는 초소형 구동기는 작은 크기로 인하여 내부 기어에 백래시를 갖고 있다. 따라서, 이는 주날개의 불필요한 유격을 발생시킬 수 있다. 이러한 유격은 주날개의 진동으로 이어져, 불필요한 비대칭적 공력을 발생시킬 수 있다. 이러한 상황 때문에 유격이 최소화된 자세 제어 장치 설계를 수행하였다. 첫째로, 기하학적 해석을 통하여 유격에 영향을 주는 요인을 파악하였다. 이를 통하여 유격을 최소화한 설계를 도출하였으며, 3차원 computer aided design (CAD) 형상과 RecurDyn을 이용하여 동역학적 해석을 수행하였다. 이를 통하여 자세 제어 장치의 구동 중 발생하는 간섭을 확인하였다. 최종적으로, 수치적 시뮬레이션을 이용하여 개선된 자세 제어 장치의 타당성을 확인하였다. 이때, 주날개는 변위 기반 기하학적 정밀 보로 모델링 되었으며, 2차원 단면 해석 결과를 사용하여 해석을 수행하였고 공력 모델은 2차원 비정상 모델을 사용하였다. 또한, 유격을 모사하기 위하여 스프링 요소를 관절에 삽입하여 해석을 수행하였다. 결과적으로, 본 연구에서 설계한 자세 제어 장치가 유효한 조종력을 발생시키는 것을 확인하였다.Abstract i Contents iii List of Tables vi List of Figures vii List of Symbols x Preface xi Chpater 1 Introduction 1 1.1 Background 1 1.2 Previous Researches 3 1.2.1 Review of Control Mechanism Design Regarding the Insect-Type Flapping Wing 3 1.2.2 Review of Numerical Simulation Studies Regarding the Insect-type Flapping Wing 6 1.3 Research Objectives and Thesis Outline 8 Chpater 2 Control Mechanism Design with Free play 9 2.1 Overview of Control Mechanism Design with Free play 9 2.2 Control Mechanism: Trailing Edge Control 11 2.3 Components of the Control Mechanism 14 2.4 Control Mechanism Design with Minimize free play effect 17 Chpater 3 Numerical Simulations of FWMAV 25 3.1 Overview of Numerical Simulation based on Flexible Multibody Dynamics 25 3.2 Simulation Setup 26 3.2.1 Simulation Methodology 31 3.2.2 Aerodynamics 34 3.3 Numerical Simulation 37 Chpater 4 Conclusions 47 4.1 Contirbutions 47 4.2 Future Works 48 Acknowledgments 50 References 50 국문초록 55Maste

Design, Manufacture, and Structural Dynamic Analysis of a Biomimetic Insect-Sized Wing for Micro Air Vehicles

The exceptional flying characteristics of airborne insects motivates the design of biomimetic wing structures that can exhibit a similar structural dynamic behavior. For this purpose, this investigation describes a method for both manufacturing a biomimetic insect-sized wing using the photolithography technique and analyzing its structural dynamic response. The geometry of a crane fly forewing (family Tipulidae) is acquired using a micro-computed tomography scanner. A computer-aided design model is generated from the measurements of the reconstructed scanned model of the insect wing to design the photomasks of the membrane and the venation network required for the photolithography procedure. A composite material wing is manufactured by patterning the venation network using photoresist SU-8 on a Kapton film for the assembling of the wing. A single material artificial wing is fabricated using the photoresist SU-8 for both the membrane and the network of veins. Experiments are conducted using a modal shaker and a digital image correlation (DIC) system to determine the natural frequencies and the mode shapes of the artificial wing from the fast Fourier transform of the displacement response of the wing. The experimental results are compared with those from a finite element (FE) model of the wing. A numerical simulation of the fluid-structure interaction is conducted by coupling the FE model of the artificial wing with a computational fluid dynamics model of the surrounding airflow. From these simulations, the deformation response and the coefficients of drag and lift of the artificial wing are predicted for different freestream velocities and angles of attack. Wind-tunnel experiments are conducted using the DIC system to determine the structural deformation response of the artificial wing under different freestream velocities and angles of attack. The vibration modes are dominated by a bending and torsional deformation response. The deformation along the span of the wing increases nonlinearly from the root of the wing to the tip of the wing with Reynolds number. The aerodynamic performance, defined as the ratio of the coefficient of lift to the coefficient of drag, of the artificial wing increases with Reynolds number and angle of attack up to the critical angle of attack

Attitude and Position Control of a Flapping Micro Aerial Vehicle

International audienc

Design, Manufacture, and Structural Dynamic Analysis of a Biomimetic Insect-Sized Wing for Micro Air Vehicles

The exceptional flying characteristics of airborne insects motivates the design of biomimetic wing structures that can exhibit a similar structural dynamic behavior. For this purpose, this investigation describes a method for both manufacturing a biomimetic insect-sized wing using the photolithography technique and analyzing its structural dynamic response. The geometry of a crane fly forewing (family Tipulidae) is acquired using a micro-computed tomography scanner. A computer-aided design model is generated from the measurements of the reconstructed scanned model of the insect wing to design the photomasks of the membrane and the venation network required for the photolithography procedure. A composite material wing is manufactured by patterning the venation network using photoresist SU-8 on a Kapton film for the assembling of the wing. A single material artificial wing is fabricated using the photoresist SU-8 for both the membrane and the network of veins. Experiments are conducted using a modal shaker and a digital image correlation (DIC) system to determine the natural frequencies and the mode shapes of the artificial wing from the fast Fourier transform of the displacement response of the wing. The experimental results are compared with those from a finite element (FE) model of the wing. A numerical simulation of the fluid-structure interaction is conducted by coupling the FE model of the artificial wing with a computational fluid dynamics model of the surrounding airflow. From these simulations, the deformation response and the coefficients of drag and lift of the artificial wing are predicted for different freestream velocities and angles of attack. Wind-tunnel experiments are conducted using the DIC system to determine the structural deformation response of the artificial wing under different freestream velocities and angles of attack. The vibration modes are dominated by a bending and torsional deformation response. The deformation along the span of the wing increases nonlinearly from the root of the wing to the tip of the wing with Reynolds number. The aerodynamic performance, defined as the ratio of the coefficient of lift to the coefficient of drag, of the artificial wing increases with Reynolds number and angle of attack up to the critical angle of attack

Hovering Flight in Flapping Insects and Hummingbirds: A Natural Real-Time and Stable Extremum Seeking Feedback System

In this paper, we show that the physical phenomenon of hovering flight is comprehensively characterized and captured if considered and treated as an extremum-seeking (ES) feedback system. Said novel characterization solves all the puzzle pieces of hovering flight that existed for decades in previous literature: it provides a simple model-free, real-time, stable feedback system. Consistent with natural observations and biological experiments, hovering via ES is simply achievable by the natural oscillations of the wing angles and measuring (sensing) altitude and/or power. We provide simulation trials to demonstrate the effectiveness of our results on dronefly, hawkmoth, bumblebee, fruitfly insects, and hummingbird

The Evaluation of a Biologically Inspired Engineered MAV Wing compared to the Manduca Sexta Wing under Simulated Flapping Conditions

In recent years, researchers have expressed a vested interest in the concepts surrounding flapping wing micro air vehicles (FWMAVs) that are capable of both range and complex maneuvering. Most research in this arena has found itself concentrated on topics such as flapping dynamics and the associated fluid-structure interactions inherent in the motion; however there still remain a myriad of questions concerning the structural qualities intrinsic to the wings themselves. Using nature as the template for design, FWMAV wings were constructed using carbon fiber and Kapton and tested under simplified flapping conditions by analyzing ‘frozen’ digital images of the deformed wing by methods of photogrammetry. This flapping motion was achieved via the design and construction of a flapper that emulates several of the kinematic features that can be seen in naturally occurring flyers. The response to this motion was then compared to the inspiring specimen\u27s wings, the North American Hawkmoth (Manduca Sexta), under the same flapping conditions in order to identify some of the key features that nature has deemed necessary for successful flight. Results showed that though the engineered wing emulated several of the structural characteristics of the biological wing; it still required some design modifications to compare more closely to the biological wing in the flapping motion. Additionally, this research also speaks to the effects of air on the biological wing