Heat is often lost unused in industry, commerce and households and is considered a waste product — while there is a lot of energy potential in waste heat. As part of the project “Theasmart”, scientists and companies are exploring just these potentials to find out how the waste product heat can be used for further purposes through the use of an innovative smart materials technology. The goal of the project is the further qualification of shape memory alloys with special focus on thin hysteresis applications for energy harvesting. In certain applications, these metals can be used as a thermal drive, for example for thermal valves or as thermal air flow regulators. Energy efficiency in processes in industrial companies or households could be improved by their use of waste heat. By 2020, the development of thermally driven generators, so-called “energy harvesters”, and the identification of other areas of application is planned. This publication focuses on first steps towards a process tool which can be actuated by waste heat of a thermal annealing sub-process directly, or used as mechanical energy charging device combined with a releasing mechanism.

In this work the aeroelastic behavior of locally resonating periodic structures is investigated. The plate-like wing behavior will be obtained from the Love-Kirchhoff plate model with a finite number of mechanical resonators periodically distributed along its surface and using assumed-modes expansion. The unsteady aerodynamic loads are obtained from the doublet lattice model. By combining the structural and aerodynamic models, the aeroelastic behavior of the wing over a range of airflow speeds is discussed. Frequency response functions due to simultaneous base and flow excitations are calculated from the absence of flow speed to the linear flutter speed of the system without resonators. The effects of bandgap presence on the flutter boundary of the wing are also discussed.

The literature of aeroelasticity includes the use of smart materials to modify the aeroelastic behavior of fixed or rotary wings. In some cases, they are employed as actuators in active control systems while in others the use of smart materials in passive control schemes is investigated. In this work a different approach is investigated. The aeroelastic behavior of a locally resonant electromechanical metastructure made from flexible substrates with piezoelectric layers connected to resonant shunt circuits is investigated. An electromechanically coupled finite element plate model is employed for predicting the electroelasatic behavior of the wing. The unsteady aerodynamic loads are obtained from the doublet lattice model. By combining the structural and aerodynamic models, the aeroelastic behavior of the metastructure over a range of airflow speeds is studied.

Exploiting mechanical instabilities and elastic nonlinearities is an emerging means for designing deployable structures. This methodology is applied here to investigate and tailor a morphing component used to reduce airframe noise, known as a slat-cove filler (SCF). The vortices in the cove between the leading edge slat and the main wing are among the important sources of airframe noise. The concept of an SCF was proposed in previous works as an effective means of mitigating slat noise by directing the airflow along an acoustically favorable path. A desirable SCF configuration is one that minimizes: (i) the energy required for deployment through a snap-through event; (ii) the severity of the snap-through event, as measured by kinetic energy, and (iii) mass. Additionally, the SCF must withstand cyclical fatigue stresses and displacement constraints. Both composite and shape memory alloy (SMA)-based SCFs are considered during approach and landing maneuvers because the deformation incurred in some regions may not demand the high strain recoverable capabilities of SMA materials. Nonlinear structural analyses of the dynamic behavior of a composite SCF are compared with analyses of similarly tailored SMA-based SCF and a reference, uniformly thick superelastic SMA-based SCF. Results show that by exploiting elastic nonlinearities, both the tailored composite and SMA designs decrease the required actuation energy compared to the uniformly thick SMA. Additionally, the choice of composite material facilitates a considerable weight reduction where the deformation requirement permits its use. Finally, the structural behavior of the SCF designs in flow are investigated by means of preliminary fluid-structure interaction analysis.

This paper presents the modeling, simulation and wind tunnel experimental verification of the aeroelastic behavior of a two-degree-of-freedom (pitch and plunge) typical airfoil section with superelastic shape memory alloy helical springs in the pitch degree-of-freedom. A linearly elastic spring is considered in the plunge degree-of-freedom. Although viscous damping is considered in both degrees-of-freedom, hysteretic damping simultaneously takes place in the pitch degree-of-freedom due to the (stress-induced) pseudoelastic behavior of the shape memory alloy springs. The shape memory alloy phase transformation kinetics and constitutive modeling are based on Brinsons model and the shape memory alloy helical spring behavior is based on classical spring design. The nonlinear effects of shape memory alloy phase transformation are included in the shape memory alloy spring modeling for the representation of hysteretic force-displacement behavior. A two-state linear aerodynamic model is employed to determine the unsteady pitching moment and lift. The aeroelastic behavior of the typical section is numerically and experimentally investigated for different preload levels applied to the shape memory alloys. Numerical predictions and experimental results show that for large enough preload levels (such that shape memory alloy phase transformations take place at small pitch angles) unstable post-flutter regime is replaced by stable limit-cycle oscillations. Moreover, the amplitudes of aeroelastic oscillations decrease with increasing preload levels since more expressive phase transformations are achieved at small pitch angles. Although the amplitudes of the post-flutter limit-cycle oscillations increase with increasing airflow speed (since aerodynamic loads increase with the square of the airflow speed), they remain bounded within acceptable levels over a range of airflow speeds due to hysteretic damping. Moreover, the cutoff airflow speed increases with increasing preload. The experimentally verified results show that the pseudoelastic behavior of shape memory alloy elements can passively enhance the aeroelastic behavior of a typical section.

High performance airfoils with laminar airflow exhibit minimum drag and maximum lift, but tend to sudden stall due to flow separation at low air speed. This requires an increased approach speed of the aircraft, resulting in less steep approaches and a higher noise exposure of the surroundings. New active vortex generators, deployed only on demand at low speed, energizing the boundary layer of air flow and reducing flow separation, can help to overcome this critical situation. Active hybrid composites, combining the actuation capability of shape memory alloys (SMA) with the possibility of tailoring the compliance of fiber reinforced polymers (FRP) on the materials level, provide an active aerodynamic system with high lightweight potential and small space requirements. Being one of the first applications of active hybrid structures from SMA and FRP we will demonstrate the potential of this new technology with an integrated system of active vortex generators for a glider. In this contribution we present - the design process, based on a FE-model and careful characterization of the actuating SMA and the composite material - manufacturing relevant aspects for reliable series production - the testing of single vortex generators in lab scale under aerodynamic load - and an overview of the whole system.

The hair cell is a biological sensor that uses microscopic hair-like structures to detect delicate motions of surrounding fluid. Inspired by this principle, we have created an artificial hair cell (AHC) sensory method based on biomolecular transduction for sensing spatial variations in air flow. The key feature of this method is the use of one-dimensional arrays built from modular AHC units which measure local velocity at different points in a flow profile. Each of the AHC units uses thinly extruded glass fibers as mechanical receptors of air velocity. Hair vibrations are converted to current via hydrogel-supported lipid bilayer membranes through their mechanocapacitive properties. Preliminary tests with linear arrays of three AHC units attempt to measure the air source profile with varying position and intensity. Each unit was fabricated with a hair of different length, giving it a unique vibrational response. This technique was inspired by how organisms use hair cells with tuned responses to mechanically process flow stimuli. A significant challenge in processing the sensors’ output was the limitation of one input channel on the current measurement unit, thus each sensor output had to be sent over the same channel. When several AHC units are excited simultaneously by an airflow, the resulting signal is a superposition of each sensor’s individual response. To separate the signals back into their individual measurements, the Hair Frequency Response Decomposition method is developed, which maps the spectral content of a combined output to the location of excitation in the array. This method takes advantage of the AHC’s high signal-to-noise ratio (compared to other membrane-based AHCs) and linear output response to flow velocity. Results show that the bilayers’ consistent spectral responses allow for an accurate localization of sensor excitation within the array. However, temporal variations in bilayer size affect sensitivity properties and make accurate flow velocity estimation difficult. Nevertheless, under stable bilayer conditions the measured velocity profiles matched closely with theoretical predictions. The implementation of the array sensing method demonstrates the sensory capability of bilayer-based AHC arrays, but highlights the difficulties of achieving consistent performance with bio-molecular materials.

Synchronization opens further ways to improve cantilever-based energy harvesting arrays in view of power output, easier rectification and scaling. Objective of this study is to investigate the synchronization behavior of a cantilever-array based energy harvesting systems. Thereby, synchronization is achieved by mechanical coupling through a so-called “overhang”. Nakajima et al. [1] and Wang et al. [2] already verified this principle for the synchronization of two and three cantilevers, but at constant vibrational excitation. Regarding energy harvesting, no application of this method is presently available. In this paper, we investigate the synchronization behavior of a piezoelectric cantilever-line energy harvester in airflow. The design of the energy harvester bases upon a piezoelectric cantilever-line and a common bluff body, arranged upstream. To investigate synchronization of the cantilevers, three commonly available piezoelectric bimorphs were employed to study synchronization. Mounted on a common bluff body, the effect of overhang material and position was studied. Therefore, different constellations were examined by impulse excitation as well as vortex-induced vibration in a wind channel. In several measurements, we found arrangements and parameters allowing for an in-phase synchronization of neighborly cantilevers of the line. The knowledge gained allows for a direct electrical connection of piezoelectric cantilevers with just one single rectifier unit. Cantilevers coupled with overhangs arranged in the right order oscillate with the same frequency and phase, i.e. without any charge cancellations. This knowledge opens ways to develop basic design rules for the synchronization of cantilevers.

In this work, a recently developed method for forming copolymer-stabilized interfaces (CSI) between aqueous droplets is pursued to as a means to construct smart materials and systems. The ABA type copolymer employed consists of two hydrophilic (PEO) groups sandwiching a hydrophobic PDMS core. Aqueous droplets submerged in triblock copolymer (PEO-PDMS-PEO)-oil mixtures are rapidly coated in copolymer monolayers, however, unlike phospholipid-stabilized droplet interface bilayers (DIBs), electrical measurements reveal that there is no spontaneous formation of a “thinned” interface with droplet contact alone. The capacitance of the interface begins increasing significantly only upon application of sufficient voltage (>100mV), and capacitance then stabilizes within minutes. Further, the interfacial capacitance and area decreases when applied voltage is reduced back to 0mV, and droplets eventually return to their initial separated state. The fact that droplet adhesion and formation of the interface is voltage dependent and completely reversible clearly distinguishes a CSI from a DIB, and the novel polymer based interface is significantly more robust with average rupture potential of ≥ 800mV compared to 200–300mV with DIBs. Durable and stable CSIs could feasibly be used in applications ranging from sensing and energy harvesting to mechanical actuation. To demonstrate, this work introduces a new version of the DIB based hair cell sensor, now replacing lipids with block copolymers to provide greater durability, stability, and resistance to rupture when subjected to airflow. We calculate the current generated by the vibrating membranes in DIBs and CSIs to study the influence of surfactant selection on the hair cell durability and the related airflow operation range. We conclude that the hair cell constructed using triblock copolymer, as opposed to a DIB, withstands higher nominal airflow speeds (45m/s) and higher applied bias voltages (i.e. 0.1–1V) without rupturing. The ability to apply higher voltages provides a means of tuning the hair-cell sensitivity. Separately, the results of initial trials demonstrate the possibility for voltage-controlled shape change using networks of droplets and CSIs. The ability to apply large voltages and induce change in interfacial area leads to rearrangement of the droplet networks due to conservation of volume. Several embodiments of possible actuators based on this mechanism are discussed. In concert, the various aspects of this work highlight the potential use of CSIs in developing novel, reliable smart materials for sensing and actuation.

The long-term vision of our work is to create a new class of smart material that utilizes networks of active, synthetic cell membranes for sensing, actuation, and energy harvesting. Having multiple membrane structures is specifically targeted because a higher density of functional membranes is expected to enable amplification and collective utility, similar to how living tissues and organisms utilize networks of highly connected cells to accomplish large tasks. While there are several known methods for assembling droplet-based networks of synthetic lipid bilayers, there has been much less effort to develop methods for electrically characterizing each interface in a multi-bilayer-droplet network. This paper specifically focuses on a strategy for using electrical measurements to independently record transmembrane currents occurring at each bilayer in multi-bilayer networks where the number of bilayers present is equal to or greater than the number of droplets in the system. Using a multichannel patch clamp amplifier, we develop a measurement technique for sequentially assigning sensing electrodes to apply a non-zero voltage or function as virtual ground ( V =0). Experimental studies on a three-droplet cluster containing three bilayers confirm the validity of the proposed approach for independently interrogating each membrane, and the results allow extension of the method to networks with 4–7 droplets. Furthermore, alamethicin peptide gating is monitored using the measurement cycle in order to interrogate all interfaces. Due to high total membrane area, highly packed systems can provide an increase in the magnitude of sensing current generated by a stimulus. Such amplification could feasibly be employed in droplet-based hair cell sensing applications in which airflow or vibration acts as the perturbation source, and the proposed approach and challenges for interrogating the transduction response in a multi-membrane hair cell sensor are discussed herein.

Charge motion in internal combustion engines is controlled by valves located near the engine ports in the intake path. The valve bodies are obstructions in the air-flow path and are a source of inefficiencies in the engine over its entire operating load. In order to achieve charge motion control without the use of valves, this research investigates the use of synthetic jet actuators to perform swirl and tumble of the air mass entering the cylinder. The purpose of this research is to design, test, and characterize a synthetic jet actuator, and determine the feasibility of using synthetic jet actuators in automotive air-intake systems. The accomplished work to date has led to geometrical optimization, fabrication of a prototype, and experimental investigation for determining jet velocities. The geometrical optimization of synthetic jets has led to a device with a thinner profile that allows it to be embedded in structures with thin (< 5mm) cross-sections and hence we refer to our synthetic jets as surface synthetic jets. It is shown here that air exiting the surface synthetic jets achieves sustained peak velocities well above 125 m/s. A variational principles-based approach is used to model the frequency response of the piezoelectric diaphragm, coupled with the lumped-parameter model for the surface synthetic jets and simulated using MATLAB Simulink ® . The results of this model are validated with experimental results and extended to design charge motion control devices. From these results, it is anticipated that these surface synthetic jet actuators can achieve charge motion control using a radial array of surface synthetic jet actuators distributed around the intake runner.

Shape Memory Alloys (SMAs) are one of the most widely used smart materials. Their attractive characteristics make them interesting for the development of novel devices. Most of these devices make use of their shape memory effect or superelasticity; these effects are based on diffusionless phase transitions. SMAs can be used in different forms. In particular, wires are often used for actuation purposes because they exert linear forces and large strokes, up to the 8% of their original (memorized) length. However, they work at very low frequencies. SMAs are thermally activated. The limitation on their actuation bandwidth is a consequence of their capability to increase and decrease their temperature. The most common way of heating SMA wires is by Joule heating. Afterwards, they normally cool down by releasing thermal energy to their surroundings by conduction or convection. The heating and the cooling come from different physic’s principles and the cooling is a slower process than the heating one. Therefore, the cooling of SMAs is the main concern regarding to the SMA wire’s maximum attainable working frequency. In this paper, the effect of different applied heating and cooling rates on the resulting SMA wire’s working frequency is studied. Different heating rates have been applied to an SMA wire by applying different levels of electrical power. In a similar manner, different cooling rates have been applied to the wire by applying different forced airflows around the SMA wire. The use of a forced airflow has shown to increase the convective heat transfer coefficient between the wire and the surrounding air up to eight-fold. SMA wires’ working frequency depends on the amplitude of strains at which it performs. The higher the amplitude, the lower the maximum attainable frequency. Moreover, the relationship between the temperature and the strain is highly non-linear. For that reason, the range of strains in which the wire works has also an effect on the resulting attainable frequency for a given working amplitude. This is of great interest for SMA actuators since a similar working amplitude can result in very different attainable frequencies, depending on the range of temperatures within which the wire performs. Experimental results show that the SMA wire’s working frequency can be increased up to threefold by making it work within the appropriate temperature range. Afterwards, this improvement is reflected on the overall performance of the actuator in which the SMA wire is embedded.

Early embodiments of droplet interface bilayer (DIB)-based hair cell sensors demonstrated the capability of sensing discrete and continuous perturbations, including single flicks and constant airflow, respectively, of a hair structure that is held in close proximity to a single lipid membrane. In those studies, the use of a single bilayer formed between a pair of droplets provided the necessary environment for studying the physical mechanism of mechanotransduction of a membrane-based sensor as well as the sensitivity and directionality of the assembly. More recently, we showed that additional lipid-coated droplets could be connected in series to form multi-bilayer arrays. Measurements of bilayer current through each interface demonstrated that perturbation of the hair creates a vibration that propagates across several droplets, allowing for the additional interfaces to also sense the perturbation. Depending on the location of the hair in the droplet array, these sensing currents can occur in-phase with one another, allowing for a total sensing current to be easily summed. Two important remaining questions about multi-bilayer arrays include: 1) How is signal propagation affected by the configuration of droplets in the array? 2) How does perturbation of multiple hair structures affect signal propagation and sensing currents in a droplet-array? To study these questions, we form linear series and L-shaped arrays of DIBs where each droplet is instrumented with a sensing electrode. Our experiments show that the motion of the perturbed hair can be transduced by up to three membranes away from the hair and that a change in the orientation of successive interfaces does not significantly affect the propagation of vibrational energy. Separately, experiments on serial arrays with multiple hairs indicate that a second, unperturbed hair does not affect bilayer currents generated by the perturbed hair and that hairs of varying length can add frequency selectivity and stimulus localization capability to multi-bilayer sensors.

Performance demands of future unmanned air vehicles will require rapid autonomous responses to changes in environment. Towards this goal, we expect that the next generation flight control systems will include advanced sensors beyond the contemporary array. One promising scenario correlates measurements of flow footprints over aircraft surfaces with aerodynamic data to aid navigation and feedback control algorithms. As a sensor for this concept, we construct artificial hair sensors (AHSs) based on glass microfibers enveloped in an annular, radially-aligned piezoresistive carbon nanotube (CNT) forest to measure air flow in boundary layers. This study includes an analysis of the sensitivity based on laboratory scale electromechanical testing. The sensors in this work utilize nine micron diameter S2 glass fibers as the sensing mechanism for coupling to boundary layer air flows. The annular CNT forest resides in a fused silica microcapillary with electrodes at the entrance. The sensor electrical transduction mechanism relies on the resistance change of the CNT forest due to changes in both the bulk and contact resistance as a function of mechanical loading on the fiber. For the electromechanical analysis, the sensors are controllably loaded to measure both the force and moment acting at the base of the hair and the resulting deflection of the CNT forest inside of the microcapillary is measured to estimate the stress on the forest and the pressure between the forest and the electrode. The electrical responses of the sensors are compared to the mechanical state of the CNT forest. This work represents the development of a characterization tool to better understand and control the response of CNT based AHSs.

A fully hydrogel-supported, artificial hair cell (AHC) sensor based on bilayer membrane mechanotransduction is designed with sensitivity and versatility in mind. Thanks to fabrication improvements from previous generations, the sensor demonstrates peak current outputs in the nanoamp range and can clearly measure inputs as high as 2k Hz. Characterization of the AHC response to base excitation and air pulses show that membrane current oscillates with the first three bending modes of the hair. Output magnitudes reflect of vibrations near the base of the hair. A 2 DOF Rayleigh-Ritz approximation of the system dynamics yields estimates of 19 N/m and 0.0011 Nm/rad for the equivalent linear and torsional stiffness of the hair’s hydrogel base, although double modes suggest non-symmetry in the gel’s linear stiffness. The sensor output scales linearly with applied voltage (1.79 pA/V), avoiding a higher-order dependence on electrowetting effects. The free vibration amplitude of the sensor also increases in a linear fashion with applied airflow pressure (18.4 pA/psi). Based on these sensitivity characteristics, an array sensing strategy for these sensors is proposed.

Bio-inspiration has introduced new and innovative flow control methods in gust alleviation, maneuverability and stability improvement for morphing aircraft wings. The bio-inspired wing model under consideration imitates the techniques used by birds to manipulate localized air flow through the installation of feather-like panels across the airfoil’s upper and lower surface, replacing the traditional wing’s surface and trailing edge flap. Each flap is designed to rotate into both the airfoil profile and inbound air flow, using a single degree of freedom about their individual hinge points located at 20%, 40%, 60% and 80% of the chord. This wing morphing technique offers flap configurations typically unattainable by traditional aircraft and enables some advantageous maneuvers, including reduced turning radii and aero-braking. Due to the number of potential configurations, a generalized adaptive panel method (APM) has been developed to model the pressure distribution using a series of constant-strength doublets along the airfoil surface. To accommodate for the wake regions generated by the unconventional wing profiles, viscous Computational Fluid Dynamics (CFD) simulations are performed to characterize these regions and identify their outer boundaries. The wake profile geometries are integrated into the APM, and are used to accurately model the aerodynamic influence of the wake. To calculate the drag generated by each configuration, Thwaites’ laminar and Head’s turbulent boundary layer methods are implemented to enable identification of flow transition and separation along the airfoil surface. The integration of these aerodynamic techniques allows the flight characteristics, including the pressure, friction, lift, drag, and moment coefficients, of each morphing airfoil configuration to be calculated. The computed aerodynamic coefficients are validated using experimental data from a 4′×1′×1′ test section in a low speed suction wind tunnel operating over a Reynolds Number range of 150,000–450,000.

In this paper, the modeling and analysis of a nonlinear rectangular plate-like wing with embedded piezoceramics is presented for aeroelastic energy harvesting. The nonlinear electromechanical finite-element plate model is based on the von Karman plate assumptions while the unsteady aerodynamic model uses the doublet-lattice method (originally in frequency domain). The aerodynamic model is converted to the time domain by using Roger’s approximation. A load resistance is considered in the electrical domain of the problem. The set of nonlinear equations is solved with the iterative Newton-Raphson method and the generalized alpha method is used to numerically integrate the equations. Five different wing configurations with aspect ratios varying from one to five are investigated. The effect of the aspect ratio on the linear aeroelastic behavior is first investigated for the short circuit condition. Later, the nonlinear electroaeroelastic behavior is investigated for a range of load resistances and the different aspect ratios of the linear case. The effects of aspect ratio and load resistance on the cut-in speed of limit cycle oscillations (LCOs), on the range of airflow speeds of LCOs of acceptable amplitudes and also on the mechanical and electrical outputs of the generator are investigated.

Airflow over/under/around a vehicle can affect many important aspects of vehicle performance including vehicle drag (and through this vehicle fuel economy), vehicle lift and downforce, and cooling/heat exchange for the vehicle powertrain and A/C systems. While active devices are present on all aircraft, the majority of known airflow control devices in current use in ground transportation are of fixed geometry, location, orientation, and stiffness. The project, conducted during the 2004–2006 timeframe, whose performance requirements, design, and bench-top prototype build phases, are described in this paper was successful in developing an SMA actuator based approach for opening and closing a vertically-oriented-blade louver system to be used for on-demand control of the airflow into the engine compartment, i.e. for on-demand control of both cooling airflow as well as aerodynamic drag. Beyond feasibility, the initial full scale bench top working models demonstrated an active materials based approach which would have decreased weight and a smaller packaging envelop than a comparable motor driven unit. This demonstration showed that actuation speed, force, and cyclic stability all could meet the application requirements. The specific design that was selected, a set of parallel vertically oriented blades each linked through a gear to a common rack that is translated by a linear SMA actuator, uses straight linear actuation to produce a reversible synchronous 90 degree rotation of the blades, i.e. a full opening and closing capability for the louver system. Key technical issues that remained to be demonstrated and resolved through design modifications if necessary in Part 2 — on-vehicle performance testing — of this study were related in most part to robustness in the harsh vehicle front-end environment, a prime example being mechanism stalling due to ice or mud buildup.

Pneumatic artificial muscles (PAMs) are lightweight, flexible actuators capable of higher specific work than comparably-sized hydraulic actuators at the same pressure and electric motors. PAMs are composed of an elastomeric bladder surrounded by a helically braided sleeve. Lightweight, compliant actuators are particularly desirable in portable, heavy-lift robotic systems intended for interaction with humans, such as those envisioned for patient assistance in hospitals and battlefield casualty extraction. However, smooth and precise control remains difficult because of nonlinearities in the dynamic response. The objective of this paper is to develop a control algorithm that satisfies accuracy and smooth motion requirements for a two degree-of-freedom manipulator actuated by pneumatic artificial muscles and intended for interaction with humans, such as lifting a human. This control strategy must be capable of responding to large, abrupt variations in payload weight over a high range of motion. In previous work, the authors detailed the design and construction of a proof-of-concept PAM-based manipulator. The present work investigates the feasibility of combining output feedback using proportional-integral-derivative control or fuzzy logic control with model-based feedforward compensation to achieve improved closed-loop performance. The model upon which the controller is based incorporates the internal airflow dynamics, the geometric parameters of the pneumatic actuators, and the arm dynamics. Simulations were performed in order to validate the control algorithm, guide controller design, and predict optimal gains. Using real-time interface software and hardware, the controller was implemented and experimentally tested on the manipulator. Performance was evaluated for several trajectories, and different payload weights. The effect of varying the feedforward gain was also analyzed. Model refinement further improved performance.

Piezoelectric energy harvesters have recently captured a lot of attention in research and technology. They employ the piezoelectric effect, which is the separation of charge within a material as a result of an applied strain, to turn what would otherwise be wasted energy into usable energy. This energy can then be used to support remote sensing systems, batteries, and other types of wireless MEMS devices. Such self powered systems are particularly attractive where hardwiring may not be feasible or numerous battery sources unreasonable. The source of excitation for these systems can include direct actuation, natural or mechanical vibrations, or fluid energy (aerodynamic or hydrodynamic). Fluid based energy harvesting is increasingly pursued due to the ubiquitous nature of the excitation source as well as the strong correlation with other types of excitation. Vortex-induced vibrations as well as vibrations induced by bluff bodies have been investigated to determine potential gains. The shape and size of these bluff bodies has been modeled in order to achieve the maxim power potential of the system. Other studies have focused on aeroelastic fluttering which relies on the natural frequency of two structural modes being achieved through aerodynamic forces. Rather than a single degree of freedom, as seen in the VIV approach, aeroelastic flutter requires two degrees of freedom to induce its vibrational state. This has been modeled through a wing section attached to a cantilevered beam via a revolute joint. To accurately model the behavior of these systems several types of dampening must be considered. Fluid flow excitation introduces the component of dampening via fluid dynamics in addition to structural dampening and electrical dampening from the piezoelectrics themselves. Air flow speed modifies the aerodynamic dampening and it has been shown that at the flutterer boundary the aerodynamic dampening dissipates while the oscillations remain. However, such a system state exhibits a decaying power output due to the shunt dampening effect of the power generation itself. Research in energy harvesting is quickly progressing but much has yet to be discovered. The focus of this paper will be fluid as a source of excitation and the development that has followed thus far. Configurations and applications of previous works will be examined followed by suggestions of new research works to move forward in the field.