Hydrogen production and delivery is critical to successful fuel cell operation. One of the most common methods to produce hydrogen is via electrolysis of water. However over-potential losses at the electrodes results in poor efficiency and an increase in power consumption. In this study we carried out experiments of water electrolysis with novel single crystal Ruthenium nano-rod arrays as the device cathode. We show that the increased active area of the nanostructured electrode serves to reduce the operating current density of the electrolyzer causing the over-potential to show a corresponding decrease. In addition to the decreased over-potential, the power needed to produce one mole of hydrogen was also reduced for the nanostructured electrolyzer compared to an electrolyzer with planar electrodes.
Several recent studies have shown that interfacial slip at the nanotube-matrix interfaces in carbon
nanotube polymer composites can give rise to significant dissipation of energy causing the material
structural damping to increase. This effect can be used to efficiently inject damping into composite and
heterogeneous structures. However if the interfacial slip of nanotube additives can be prevented, then
significant enhancement in stiffness and strength is possible. To inhibit interfacial slippage of nanotubes
we established covalent bonds at the nanotube-matrix interfaces by using an epoxidation procedure. The
resultant nano-composites are shown to be resistant to interfacial slip and exhibited a higher storage
modulus and a lower loss modulus compared to the baseline composite (without nanotube epoxidation).
These results indicate that functionalizing nanotubes to establish direct covalent linkages is an effective
way to engineer structural components with enhanced mechanical properties.
Multiwalled carbon nanotubes are dispersed in polycarbonate matrices using a novel solution mixing technique and dynamic load tests are performed to characterize the storage and loss modulus. Tests are also performed with pristine polycarbonate (no carbon fillers), to compare the response of the two materials. The test results indicate that as the strain amplitude is increased, the storage modulus decreases in conjunction with an increase in the loss modulus. This suggests that at large strain levels the adhesion between the nanotubes and polymer is not strong enough to prevent interfacial slip, resulting in frictional sliding at the tube-polymer interfaces. This debonding at the filler-matrix interface is responsible for the observed decrease in storage modulus and increase in loss modulus. The nanotube-polymer sliding energy dissipation mechanism shows potential to reliably and efficiently deliver high levels of structural damping to polymer structures.
We investigate Tungsten (W) nanorod electrodes as gas ionizers. These W nanorods having square-base pyramidal apexes are grown using a glancing angle sputter deposition technique with substrate rotation. We show that few tens of volts of anode voltage applied to the W nanorods are sufficient to ionize a range of different gas species including Ar, CO2, N2 and O2. A distinct ionization onset voltage is observed for each individual gas specie, which suggests that these nanostructured ionization devices may be useful for gas sensing applications. In addition, the low anode voltage and high ion currents observed in this study indicates that the gas ionization devices could be operated using commercially available off-the-shelf batteries.
Recent studies at the Rensselaer Polytechnic Institute have shown that electric field can have a profound effect on individual carbon nanotube ensembles. We have shown that nanotubes can be aligned along the electric field lines, and can also be made to move along the field lines above a critical or threshold electric field. Experiments were repeated with nano-particles such as C-60 (fullerenes) and these effects were not observed, which indicates that the aspect ratio and one-dimensionality of the nanotubes plays a critical role. These observations can foreshadow novel electro-mechanical applications for nanotube elements.
This paper investigates the potential of exploiting interfacial sliding interactions in carbon nanotube
thin films for structural damping applications. Carbon nanotubes, due to their huge effective interfacial
area, may provide an unprecedented opportunity to dramatically improve damping properties with minimal
weight penalty. Three different mechanisms for interfacial friction damping in nanotube films were
identified in this paper. These include: 1) Energy dissipation due to inter-tube interactions, 2) Energy
dissipation due to nanotube-polymer interactions and 3) Energy dissipation due to nanotube and
encapsulated nanowire interactions. These damping mechanisms are investigated using computational
techniques (such as molecular dynamics) as well as experimentation (viscoelastic shear, bending tests). The
results indicate that over 15-fold increase in the material loss factor for an epoxy thin film can be achieved
by the use of carbon nanotube fillers.
Multiwalled carbon nanotube thin films were fabricated using catalytic chemical vapor deposition of xylene-ferrocene mixture precursor. The nanotube films were employed as inter-layers within composite systems to reinforce the interfaces between composite plies, enhancing laminate stiffness as well as structural damping. Experiments conducted using a piezo-silica composite beam with an embedded nano-film sub-layer indicated up to 200% increase in the inherent damping level and 30% increase in the baseline bending stiffness with minimal increase in structural weight. Scanning Electron Microscopy (SEM) characterization of the nano-film was also conducted to investigate the mechanics of stiffness and damping augmentation. The study revealed a fascinating network of densely packed, highly interlinked multiwalled nanotubes (MWNTs). This inter-tube connectivity resulted in strong interactions between adjacent nanotube clusters as they shear relative to each other causing energy dissipation within the nano-film. Molecular Dynamics (MD) simulations confirmed that inter-tube interaction was the dominant mechanism for damping within the nano-film layer. The cross-links between nanotubes also served to improve load transfer within the network resulting in improved stiffness properties.
This paper investigates the impact of non-intrusive carbon nanotube coatings on the power consumption of piezoceramic sheet actuators. Due to their nano-scale cylindrical structure, carbon nanotubes provide an order of magnitude increase in the exposed surface area compared to the uncoated piezoceramic sheet. This along with their excellent thermal conductivity allows the nanotube coating to act as a heat sink, drawing energy away from the bulk piezoceramic material and dissipating it to the atmosphere. To demonstrate the proof-of-concept multiwalled carbon nanotube thin films were deposited on the surfaces of 10 mil thick, commercially available PZT-5H sheets. The piezoelectric sheets were actuated at several different excitation frequencies and voltage settings, both before and after application of the nano-film coating. Strain, perpendicular to the poling direction, and current measurements made on these samples indicated that while the piezoelectric samples with nano-film coating exhibited strain behavior similar to the baseline uncoated samples, they required upu to 15% less peak power for high frequency actuation.
This paper presents on-going research directed towards the development of MEMS actuators for improved aerodynamic efficiency of micro-rotorcraft. A 6 inches diameter micro-rotor system was developed and tested in hover. Results indicated that profile power losses associated with low Reynolds number viscous flows and flow separation and stall at high angles of attack limit the rotor performance at micro-scale. It is envisaged that tripping the flow from laminar to turbulent at the leading edge of the rotor blade can prevent formation of the laminar separation bubble and improve lifting efficiency of the micro-rotor. This study will present the design of a prototype MEMS actuator (piezoelectric thin film). It is envisaged that multiple arrays of such MEMS devices can be assembled on the surface of the airfoil section to create a smart skin. The smart skin when actuated provides controllable surface roughness that can be used to enable premature boundary layer transition.
Shape Memory Alloy (SMA) wires, were integrated within E-glass composite beams. The fiber volume fraction of the SMA material was 10 percent. Several baseline beams were also fabricated. Both the baseline and SMA reinforced composite beams were tested to failure in tension. The SMA reinforced beams were tested in both the martensite phase (room temperature) as well as the austenite phase (75 deg C). The test results indicated that SMA reinforced composites can offer significant increase in the strain-energy absorption prior to failure thereby improving the fracture toughness and crashworthiness for such systems. Significant increase in damping was also observed for the SMA reinforced composite when the wires were transformed from the martensite to the austenite phase by resistive heating.
This paper presents the open-loop hover testing of a Mach- scaled (1/7-scale) rotor with piezoelectric bender actuated trailing-edge flaps. The flap motion generates new unsteady aerodynamic loads, which if correctly phased can be used to achieve active vibration suppression. The objective of the present tests is to demonstrate the open-loop control authority of the actuator-flap system. The model rotor was tested in hover condition on the University of Maryland rotor test rig. These tests were conducted using a Bell-412 Mach- scaled rotor hub. Trailing-edge flap deflections of ±5 to ±10 degrees were achieved in the 1 - 4/rev frequency range at 1800 RPM. The associated oscillatory rotor thrust per blade for 3/rev flap excitation was ±6.9 lbs (40% of steady rotor thrust per blade at 8 degrees collective). These results demonstrate the open-loop effectiveness of the actuator-flap system. Future work will include closed-loop control tests conducted in forward flight in the Glen L. Martin wind tunnel.
This paper presents an analytic model and validation tests of Froude and Mach scaled rotors featuring piezoelectric bender actuated trailing-edge flaps for active vibration suppression. A finite element structural formulation in conjunction with time domain unsteady aerodynamics is used to develop the rotor blade and bender-flap coupled response in hover. The analysis accounts for the aerodynamic, centrifugal, inertial and frictional loads acting on the coupled bender-flap-rotor system in hover. To investigate the feasibility of piezo-bender actuation and validate the analytic model, a 6 foot diameter, two-bladed Froude scaled rotor with piezo-bender actuation is tested on the hover stand. Flap deflections of +/- 4 to +/- 8 degrees, for 1 to 5 /rev bender excitation were achieved at the Froude scaled operating speed of 900 RPM. The trailing-edge flap activation resulted in a 10% variation in the rotor thrust levels at 6 degrees collective pitch. The analytic model shows good correlation with experimental flap deflections and oscillatory hubloads for different rotor speeds and collective settings. Based on the analytic model, two Mach scaled rotor blades with piezo-bender actuation are designed and fabricated. To achieve the desired flap performance at Mach scale, an 8-layered, tapered bender is fabricated. The bender performance is further improved by selectively applying large electric fields in the direction of polarization for individual piezoceramic elements. A radial bearing is incorporated to reduce frictional loads at the blade-flap interface. Preliminary testing of the Mach scaled blades at 900 RPM in a vacuum chamber revealed negligible degradation in flap performance because of centrifugal and frictional loading. The analysis predicts that flap deflections of +/- 5 to +/- 10 degrees for 1 to 4 /rev bender excitation can be achieved at the Mach scaled operating speed of 2100 RPM. Future work will involve hover and wind tunnel testing at Mach scaled operating speeds.
This paper presents the testing of a Froude scaled rotor featuring piezoceramic bimorph actuated trailing-edge flaps for active vibration suppression. An analytical model for the coupled bimorph actuator trailing-edge flap dynamic response in the rotating environment was developed. The analysis takes into account the aerodynamic, centrifugal, inertial and frictional loads acting on the actuator-flap system. The linkage arm length associated with the mechanical amplification mechanism was selected in order to maximize flap performance in the rotating environment. The bimorph clamping was improved to prevent actuator slippage under high centrifugal loads. The analytical model was validated by carrying out a series of bench tests, vacuum chamber tests and hover tests. In hover, flap deflections of plus or minus 6 degrees at 4/rev flap excitation were achieved at 900 rpm, thus demonstrating the potential of the piezoceramic bender as a lightweight and compact actuation system for individual blade control purposes. This paper also includes a feasibility study for piezo-bimorph actuation of a trailing-edge flap for a Mach scaled rotor model.
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