| The Characterization of Material Properties and Structural Dynamics of the Manduca Sexta Forewing for Application to Flapping Wing Micro Air Vehicle Design |
13 Sep 2012 |
206 pages |
| Authors:
Ryan P O'Hara; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
 | The Manduca Sexta species of moth serves as a source of biological inspiration for the future of micro air vehicle flapping flight. The ability of this species to hover in flapping flight has warranted investigation into the critical material, structural, and geometric properties of the forewing of this biological specimen. A rigorous morphological study of the Manduca Sexta forewing was conducted to characterize the physical and material properties of the ... |
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| An Analysis of Undersea Glider Architectures and an Assessment of Undersea Glider Integration into Undersea Applications |
Sep 2012 |
91 pages |
| Authors:
William P Barker; NAVAL POSTGRADUATE SCHOOL MONTEREY CA DEPT OF SYSTEMS ENGINEERING
|
| Currently, buoyancy driven underwater gliders are deployed globally to gather oceanographic data from across the world's oceans. This thesis examines the utility of underwater gliders within the context of providing additional U.S. Navy capabilities. An extensive survey of available underwater gliders was undertaken and the resultant survey pool of ten gliders was down selected to five gliders of fixed wing configuration. A comprehensive architectural analysis was then conducted of seven ... |
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| Detection of Non-hazardous, Fluorescent Ricin-B Via an Immunoassay on Simulated Plastic Wings |
Sep 2012 |
18 pages |
| Authors:
Glenn Beatty; Asha Hall; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD VEHICLE TECHNOLOGY DIRECTORATE
|
| As a schedule 1 controlled substance, ricin is one of the deadliest plant toxins in existence, and also one of the most easily weaponizable. This combination has resulted in a recent surge of studies proposing new and improved methods of detecting ricin, primarily involving aqueous phase immunoassays. Successive methods report higher binding affinities and correspondingly lower detection limits, but little research has addressed the potential for new modes of implementation, ... |
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| High Performance Piezoelectric Actuators and Wings for Nano Air Vehicles |
26 Aug 2012 |
144 pages |
| Authors:
Christopher D Rahn; Srinivas A Tadigadapa; PENNSYLVANIA STATE UNIV STATE COLLEGE
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| Swarms of flying robotic insects could revolutionize hazardous environment exploration, search and rescue missions, and military applications. Reducing size to insect scale enables entrance into extremely narrow spaces with inherent stealth advantages. For mass production, these vehicles must have reliable and repeatable fabrication processes that define flapping wing mechanisms with microscale features and produce large flapping amplitudes at frequencies in the range of many insects. This report focuses on the ... |
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| Experimental Characterization and Validation of Simultaneous Gust Alleviation and Energy Harvesting for Multifunctional Wing Spars |
Aug 2012 |
30 pages |
| Authors:
Ya Wang; Daniel J Inman; MICHIGAN UNIV ANN ARBOR DEPT OF AEROSPACE ENGINEERING
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| Principles for Designing Compliant Multifunctional Wing Structures with Integrated Solar Cells for MAVs |
15 Apr 2012 |
26 pages |
| Authors:
Hugh A Bruck; Sayandra K Gupta; MARYLAND UNIV COLLEGE PARK DEPT OF MECHANICAL ENGINEERING
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| Conceptual Layout of Wing Structure Using Topology Optimization for Morphing Micro Air Vehicles in a Perching Maneuver |
22 Mar 2012 |
189 pages |
| Authors:
James R Elgersma; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
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| A topology optimization model for conceptual wing structure layouts of morphing micro air vehicles (MAVs) has been developed and implemented in MATLAB. Specifically, a six degree-of-freedom finite element (FE) model with a general quadrilateral discretization scheme was created by superposition of a known simple linear plane membrane element and a Kirchhoff plate bending element derived herein. The purpose of the six degree-offreedom model was to accommodate in-plane and out-of-plane aerodynamic ... |
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| Evaluation of the Thorax of Manduca sexta for Flapping Wing Micro Air Vehicle Applications |
Mar 2012 |
182 pages |
| Authors:
Alex C Hollenbeck; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT
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| The tobacco hornworm hawkmoth (Manduca sexta) provides an excellent model from which to garner knowledge pertaining to the development of a Flapping Wing Micro Air Vehicle (FWMAV). Insect-sized FWMAVs will be used by the future warfighter for reconnaissance, nuclear/chemical/biological hazard sensing, and targeting. One of the major challenges facing FWMAV developers is the energetically demanding nature of low Reynolds flapping flight. Investigating the Manduca sexta thorax/wing flapping mechanism as a ... |
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| Bio-Inspired Integrated Sensing and Control Flapping Flight for Micro Aerial Vehicles |
28 Feb 2012 |
58 pages |
| Authors:
Soon-Jo Chung; ILLINOIS UNIV AT URBANA-CHAMPAIGN
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| This AFOSR YIP project provides a comprehensive understanding of the unique dynamics and control characteristics of tailless micro aerial vehicle equipped with flexible, articulated wings. This project has successfully demonstrated the ability to stabilize and control the robotic flapping testbed by using the phase synchronized nonlinear oscillators inspired by the central pattern generators in spinal cord. Furthermore, it is shown that the dihedral angle of the wing can be varied ... |
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| The Morphological Characterization of the Forewing of the Manduca sexta Species for the Application of Biomimetic Flapping Wing Micro Air Vehicles |
Jan 2012 |
15 pages |
| Authors:
R P O'Hara; A N Palazotto; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH DEPT OF AERONAUTICS AND ASTRONAUTICS
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| To properly model the structural dynamics of the forewing of the Manduca sexta species, it is critical that the material and structural properties of the biological specimen be understood. This paper presents the results of a morphological study that has been conducted to identify the material and structural properties of a sample of male and female Manduca sexta specimens. The average mass, area, shape, size and camber of the wing ... |
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| Development of Photographic Dynamic Measurements Applicable to Evaluation of Flapping Wing Micro Air Vehicles |
Dec 2011 |
86 pages |
| Authors:
Jeremy C Murray; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH DEPT OF AERONAUTICS AND ASTRONAUTICS
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| Developments in the area of flapping wing micro air vehicles (FWMAVs) of a small size and with limited range. This has lead to a great deal of interest in biomimetric designs based on flapping wing flyers, including the North American Hawkmoth (Manduca Sexta). By utilizing high speed photography and photogrammetry the dynamic flapping of the wing can be characterized for comparison with mathematical models, namely computational fluid dynamics (CFD) and ... |
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| Design of a Five-Axis Load Cell for Submerged Wing Testing in an Oil Tank |
Dec 2011 |
30 pages |
| Authors:
John Gerdes; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
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| The design of a load cell utilizing the bending beam principle is presented. The load cell measures the forces and moments created by a flapping wing submerged in an oil tank. The design process is described starting with an overview of the design methodology and the conceptual design. The functional and geometric constraints are then identified. Performance requirements are used to optimize the load cell geometry and detail the conceptual ... |
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| Sensory Coordination of Insect Flight |
30 Sep 2011 |
12 pages |
| Authors:
Sanjay Sane; TATA INST OF FUNDAMENTAL RESEARCH BANGALORE (INDIA) NATIONAL CENTRE FOR BIOLOGICAL SCIENCES
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| This is the final report of a project that studied antennal positioning in moths and freely flying bees, location of odor sources in the fruit fly, coordination of wings and halters in the soldier fly, and landing behavior in the housefly. |
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| Modeling Interactions Between Flexible Flapping Wing Spars, Mechanisms, and Drive Motors |
Sep 2011 |
29 pages |
| Authors:
David B Doman; Chin P Tang; Sean Regisford; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIR/CONTROL SCIENCES DIV/CONTROL DESIGN AND ANALYSIS BRANCH
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| A system of dynamical equations is presented that allow micro air vehicle (MAV) or- nithopter designers to match drive motors to loads produced by exible apping wing spars. The model can be used to examine the coupled system-level behavior of brushed DC motors, gear trains, and any number of linkages and exible wing spars. A Lagrangian approach is used to derive the governing di erential equations of motion for a ... |
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| Flapping Wing Flight Dynamic Modeling |
22 Aug 2011 |
109 pages |
| Authors:
Benjamin Y Leonard; VIRGINIA POLYTECHNIC INST AND STATE UNIV BLACKSBURG
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| Highly agile, hover capable flapping wing flight is a relatively new area of study in engineering. Researchers are looking to flapping flight as a potential source for the next generation of reconnaissance and surveillance vehicles. These systems involve highly complicated physics surrounding the flapping wing motion and unusual characteristics due to a hover requirement not normally associated with conventional aircraft. To that end this study focuses on examining the various ... |
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| Limited Evaluation of AIM-9 Control Surface Effects on F-16 LCO Characteristics |
AUG 2011 |
13 pages |
| Authors:
Anthony P. Massett; Reinald G. Groult; Robert T. Ungerman; Jason B. Honabarger; Jared E. Salk; Pierluigi De Paolis; Timothy R. Jorris; AIR FORCE FLIGHT TEST CENTER EDWARDS AFB CA
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| Limit Cycle Oscillation (LCO) is a self-sustained airframe structural response due to interaction between airframe aeroelastic properties and flight condition aerodynamic effects. F-16 LCO has typically resulted in lateral motions of the fuselage and crew that could have operational impacts on such things as pilot fatigue, weapons tracking or structural integrity. Historic flight test data could not isolate the effect that aerodynamic differences had on LCO over mass and inertia ... |
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| Study for Air Vehicles at High Speeds, Identifying the Potential Benefits to Transport Aircraft of a Continuously Variable Geometry Trailing-Edge Structure that can be Utilized for Aircraft Control, Trim, Load-Alleviation, and High Lift |
Aug 2011 |
133 pages |
| Authors:
Raj K Nangia; NANGIA AERO RESEARCH ASSOCIATES BRISTOL (UNITED KINGDOM)
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| One of the technologies emerging in recent years concerns variable aerofoil shaping (or morphing), using clever internal mechanisms. Previous studies have noted potential aerodynamic efficiency gains, gust loads alleviation, stagnation point control for laminar flow onset or Shock position / strength control. Previous work along some of these lines has also been in TACT & MAW programs. Although such mechanisms may provide a lower sectional Clmax, compared with a point ... |
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| Digital Image Correlation of Flapping Wings for Micro-Technologies |
Aug 2011 |
18 pages |
| Authors:
Leslie Hall; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD VEHICLE TECHNOLOGY DIRECTORATE
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| The unpredictable, and therefore inherently dangerous, situations warfighters experience have created a demand for advanced environmental knowledge of impending threats. Small, stealthy, and versatile micro-technologies have great potential in this area and can provide autonomous reconnaissance and nonlethal protection while either crawling or flying. One particular challenge with flying systems is designing a lightweight vehicle while maintaining critical function performance. This project focuses on using digital image correlation software and ... |
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| Light UAV Support Ship (ASW) (LUSSA) |
Aug 2011 |
43 pages |
| Authors:
Cayle Bradley; David Coar; Daniel Nowakowski; James Riley; NAVAL SURFACE WARFARE CENTER CARDEROCK DIV BETHESDA MD
|
| With the success of unmanned aerial vehicles (UAVs) in intelligence, surveillance, and reconnaissance (ISR) missions around the globe, the US Navy continues to re-evaluate its approach to other mission areas such as search and rescue and anti-submarine warfare (ASW). Recent tests onboard Navy aircraft carriers have proven the ability to successfully launch and recover large, fixed-wing aircraft autonomously from their flight decks. With these advancing technologies, a strong interest has ... |
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| Three-Dimensional Bending Analysis of Functionally-Modified Bimorph PZT Actuator for cm-Scale Flapping Wing |
JUL 2011 |
20 pages |
| Authors:
Jaret C. Riddick; Asha Hall; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| 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 ... |
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| Can Wing Tip Vortices Be Accurately Simulated? |
JUL 2011 |
14 pages |
| Authors:
Ryan Termath; Jason Lechniak; Keerti Bhamidipati; AIR FORCE FLIGHT TEST CENTER EDWARDS AFB CA
|
| Modeling and Simulation (M&S) computational fluid dynamics (CFD) techniques were used to better understand wing tip vortices about a wing section. The CFD results were compared to experimental wind tunnel data derived from the University of Iowa (Ref. 2). The experiment used Stereoscopic Particle Image Velocimetry (SPIV) to measure the flow field. The SPIV data from the experiment illustrates the vortex core development and behavior downstream of the trailing edge ... |
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| Helicopter Maritime Environment Trainer: Software Product Specification |
Jun 2011 |
108 pages |
| Authors:
Leo Boutette; Ken Ueno; Jason Dielschneider; DEFENCE RESEARCH AND DEVELOPMENT TORONTO (CANADA)
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| The Helicopter Maritime Environment Trainer (HelMET) was developed by Defence R&D Canada - Toronto (DRDC Toronto) for training helicopter pilots to land on the flight deck of a Canadian Patrol Frigate (CPF) in a virtual environment. The HelMET was installed at 12 Wing, Canadian Forces Base (CFB) Shearwater, Nova Scotia, Canada [reference: Summary per document cited in next paragraph]. DRDC Toronto Document: CR2002-030 Atlantis Document: AP905-03128 titled Helicopter Maritime Environment ... |
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| Helicopter Maritime Environment Trainer: Maintenance Manual (Simulateur D'Entrainement Virtuel pour Helicoptere Maritime: Manual D'Entretien) |
Jun 2011 |
118 pages |
| Authors:
Leo Boutette; Ken Ueno; Jason Dielschneider; DEFENCE RESEARCH AND DEVELOPMENT TORONTO (CANADA)
|
| The Helicopter Maritime Environment Trainer (HelMET) was developed by Defence R&D Canada - Toronto (DRDC Toronto) for training helicopter pilots to land on the flight deck of a Canadian Patrol Frigate (CPF) in a virtual environment. The HelMET was installed at 12 Wing, Canadian Forces Base (CFB) Shearwater, Nova Scotia, Canada [reference: Summary per document cited in next paragraph]. DRDC Toronto Document: CR2002-028 Atlantis Document: ED997-0000369 titled Helicopter Maritime Environment ... |
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| Helicopter Maritime Environment Trainer: Operator Manual (Simulateur D'Entrainement Virtuel Maritime: Manuel de L'Operateur) |
Jun 2011 |
244 pages |
| Authors:
Leo Boutette; Ken Ueno; Jason Dielschneider; DEFENCE RESEARCH AND DEVELOPMENT TORONTO (CANADA)
|
| The Helicopter Maritime Environment Trainer (HelMET) was developed by Defence R&D Canada - Toronto (DRDC Toronto) for training helicopter pilots to land on the flight deck of a Canadian Patrol Frigate (CPF) in a virtual environment. The HelMET was installed at 12 Wing, Canadian Forces Base (CFB) Shearwater, Nova Scotia, Canada. [reference: Summary per document cited in next paragraph]. DRDC Toronto Document: CR2002-022 Atlantis Document: ED997-00368 titled Helicopter Maritime Environment ... |
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| Helicopter Maritime Environment Trainer: Software Test Document |
Jun 2011 |
132 pages |
| Authors:
Leo Boutette; Ken Ueno; Jason Dielschneider; DEFENCE RESEARCH AND DEVELOPMENT TORONTO (CANADA)
|
| The Helicopter Maritime Environment Trainer (HelMET) was developed by Defence R&D Canada - Toronto (DRDC Toronto) for training helicopter pilots to land on the flight deck of a Canadian Patrol Frigate (CPF) in a virtual environment. The HelMET was installed at 12 Wing, Canadian Forces Base (CFB) Shearwater, Nova Scotia, Canada [reference: Summary per document cited in next paragraph]. DRDC Toronto Document: CR2002-027 Atlantis Document: ED990-01155 titled Helicopter Maritime Environment ... |
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| Helicopter Maritime Environment Trainer: Operational Software CSCI Version Description Document (Simulateur D'Entrainement Virtuel pour Helicoptere Maritime: Logiciel Operationnel CSCI, Document de Description de la Version) |
Jun 2011 |
42 pages |
| Authors:
Leo Boutette; Ken Ueno; Jason Dielschneider; DEFENCE RESEARCH AND DEVELOPMENT TORONTO (CANADA)
|
| The Helicopter Maritime Environment Trainer (HelMET) was developed by Defence R&D Canada - Toronto (DRDC Toronto) for training helicopter pilots to land on the flight deck of a Canadian Patrol Frigate (CPF) in a virtual environment. The HelMET was installed at 12 Wing, Canadian Forces Base (CFB) Shearwater, Nova Scotia, Canada [reference: Summary per document cited in next paragraph]. DRDC Toronto Document: CR2002&-031 Atlantis Document: VD905-03128 titled Helicopter Maritime Environment ... |
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| Numerical Investigation of a Low Aspect Ratio Flat Plate |
19 May 2011 |
18 pages |
| Authors:
Yongsheng Lian; LOUISVILLE UNIV KY
|
| This report presents the key findings resulting from an AFOSR grant. In this reseasrch we extended our previous results on the linear pitch-ramp-return of a two-dimensional (2D) flat plate to that of a three-dimensional (3D) flat plate of various aspect ratios, in an attempt to quantify 3D effects and the boundary effects on flapping wing aerodynamics. Specifically we compared the leading edge vortex (LEV) between the two-2D and the corresponding ... |
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| Vertical Unmanned Aircraft System Alternative for the F-35B JSF |
07 MAR 2011 |
34 pages |
| Authors:
James Frey; ARMY WAR COLL CARLISLE BARRACKS PA
|
| The U.S. Marine Corps has much at stake with the F-35B Short Takeoff and Landing (STOVL) version of the Joint Strike Fighter. In a strategic gamble, the Corps has shaped an amphibious force around the technology and capabilities promised by this program. To support the nation's expeditionary force in readiness, the conceptual capabilities of this platform will continue to provide a unique and powerful piece of the Marine Air Ground ... |
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| Acquisition of a Scanning Laser Vibrometer System for Experimental Studies on Nonparametric Nonlinear System Identification and Aeroelastic Instability Suppression |
06 Mar 2011 |
5 pages |
| Authors:
Lawrence A Bergman; Alexander F Vakakis; D M McFarland; ILLINOIS UNIV URBANA DEPT OF AEROSPACE ENGINEERING
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| The PIs current research and development, funded by AFOSR, aims to develop novel means of vibration control for aerospace systems, system identification procedures for strongly nonlinear dynamical systems, and a fully passive limit cycle oscillation (LCO) suppression system for a model generic transport wing (GTW) previously designed, built and tested in the TDT at NASA Langley. Initial efforts by the PIs led to the development of the Nonlinear Energy Sink ... |
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| Unsteady Flow Structure on Low Aspect Ratio Wings |
06 Jan 2011 |
106 pages |
| Authors:
Donald Rockwell; LEHIGH UNIV BETHLEHEM PA DEPT OF MECHANICAL ENGINEERING AND MECHANICS
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| The overall objective of this investigation was to determine the quantitative flow structure on low aspect ratio wings subjected to basic classes of maneuvers, in order to provide a basis for interpretation of induced forces. Techniques of particle image velocimetry were employed for critical planes of the flow field, and a technique of stereo particle image velocimetry was developed for water-based systems. Post-processing of the acquired images allowed determination of ... |
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| AHPCRC (Army High Performance Computing Research Center) Bulletin. Volume 3, Issue 1 |
Jan 2011 |
33 pages |
| Authors:
HIGH PERFORMANCE TECHNOLOGIES INC RESTON VA
|
| AHPCRC research efforts are evolving in response to the Army's top priorities for supporting and protecting soldiers and the stated needs of our colleagues at the Army laboratories. At this stage of the program, several projects are delivering new technologies and capabilities to their Army counterparts, for use in warfighter-directed applications. AHPCRC researchers are integrating computational fluid dynamics, structural design, algorithm development, and mechanical modeling to develop a flapping-wing micro-aerial ... |
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| Perching Experiment at Low Reynolds Number: Force and PIV Measurements of Rectangular Flat Wing Models in Perching Motion |
10 NOV 2010 |
73 pages |
| Authors:
Rolf E. Radespiel; TECHNICAL UNIV BRAUNSCHWEIG (GERMANY) INST OF FLUID MECHANICS
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| This report comprises aerodynamic measurements of a wing in perching motion carried out with the MAVlab facility at the Institute of Fluid Mechanics of Braunschweig University. In this context, the perching motion is modeled according to the wing motions of birds to rapidly reduce velocity when landing on a small spot i.e. a perch. The here discussed perching motion is defined as a discontinuous pitching of a wing from low ... |
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| Wingbeat Shape Modulation for Flapping-Wing Micro-Air-Vehicle Control During Hover (Postprint) |
Jun 2010 |
18 pages |
| Authors:
David B Doman; Michael W Oppenheimer; David O Sigthorsson; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIR/CONTROL SCIENCES DIV/CONTROL DESIGN AND ANALYSIS BRANCH
|
| A new method of controlling a flapping-wing micro air vehicle by varying the velocity profiles of the wing strokes is presented in this manuscript. An exhaustive theoretical analysis along with simulation results show that this new method, called split-cycle constantperiod frequency modulation, is capable of providing independent control over vertical and horizontal body forces as well as rolling and yawing moments using only two physical actuators, whose oscillatory motion is ... |
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| X-HALE: A Very Flexible UAV for Nonlinear Aeroelastic Tests |
Apr 2010 |
24 pages |
| Authors:
Carlos E Cesnik; Patrick J Senatore; Weihua Su; Ella M Atkins; Christopher M Shearer; Nathan A Pitcher; MICHIGAN UNIV ANN ARBOR DEPT OF AEROSPACE ENGINEERING
|
| The University of Michigan has designed and is currently building an unmanned aerial vehicle, denoted X-HALE, which is aeroelastically representative of very flexible aircraft. The objective of this test bed is to collect unique data of the geometrically nonlinear aeroelastic response coupled with the flight dynamics to be used for future code validation. The aircraft will present specific aeroelastic features (e.g., coupled rigid/elastic body instability, large wing deflection during gust, ... |
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| Dynamics and Control of a Biomimetic Vehicle Using Biased Wingbeat Forcing Functions: Part 2 - Controller (Postprint) |
Jan 2010 |
38 pages |
| Authors:
David B Doman; Michael W Oppenheimer; David O Sigthorsson; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIRECTORATE
|
| A control strategy is proposed for a minimally-actuated flapping-wing micro air-vehicle (FWMAV). The proposed vehicle is similar to the Harvard RoboFly that accomplished the first takeoff of an insect scale flapping wing aircraft, except that it is equipped with independently actuated wings. Using the derivation of the aerodynamic forces and moments from Part I, a control allocation strategy and a feedback control law are designed that enable the vehicle to ... |
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| Dynamics and Control of a Biomimetic Vehicle Using Biased Wingbeat Forcing Functions: Part 1 - Aerodynamic Model (Postprint) |
Jan 2010 |
36 pages |
| Authors:
David B Doman; Michael W Oppenheimer; David O Sigthorsson; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIRECTORATE
|
| An aerodynamic model, for a minimally actuated flapping wing micro air vehicle (FWMAV), is derived from blade element theory. The vehicle considered in this work is similar to the Harvard RoboFly, except that it is equipped with independently actuated wings. A blade element-based approach is used to compute both instantaneous and cycle-averaged forces and moments for a specific type of wingbeat motion that enables nearly decoupled, multi-degree-of-freedom control of the ... |
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| Aerodynamics Characteristics of Butterfly Flight Through Measurement of Three-Dimensional Unsteady Velocity Field Using TR-PIV System |
19-Nov-2009 |
43 pages |
| Authors:
Debopam Das; INDIAN INST OF TECH KANPUR
|
| This report investigates understanding insect flight (having flapping and feathering motion) in view of lift & thrust generation, essential for flight control, with simultaneous measurement of velocity and forces. The present work is divided into two major portions. One being the flow visualization and PIV measurements, the other is force measurement. |
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| Dynamics and Control of a Minimally Actuated Biomimetic Vehicle: Part 1 - Aerodynamic Model (Postprint) |
Aug 2009 |
27 pages |
| Authors:
David B Doman; Michael W Oppenheimer; David O Sigthorsson; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIRECTORATE
|
| An aerodynamic model for the forces and moments acting on a minimally actuated flapping wing micro air vehicle (FWMAV) are derived from blade element theory. The proposed vehicle is similar to the Harvard RoboFly that accomplished the first takeoff of an insect scale flapping wing aircraft, except that it is equipped with independently actuated wings and the vehicle center-of-gravity can be manipulated for control purposes. Using a blade element-based approach, ... |
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| Dynamics and Control of a Minimally Actuated Biomimetic Vehicle: Part 2 - Control (Postprint) |
Aug 2009 |
25 pages |
| Authors:
David B Doman; Michael W Oppenheimer; David O Sigthorsson; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIRECTORATE
|
| vA control strategy is proposed for a minimally-actuated flapping-wing micro air-vehicle (FWMAV). The proposed vehicle is similar to the Harvard RoboFly that accomplished the first takeoff of an insect scale flapping wing aircraft, except that it is equipped with independently actuated wings and the vehicle center-of-gravity can be manipulated for control purposes. Using the results from the derivation of the aerodynamic forces and moments from Part I, a control allocation ... |
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| Altitude Control of a Single Degree of Freedom Flapping Wing Micro Air Vehicle (Postprint) |
Aug 2009 |
21 pages |
| Authors:
David B Doman; Michael W Oppenheimer; Michael A Bolender; David O Sigthorsson; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIRECTORATE
|
| A control strategy is proposed for a minimally actuated flapping wing micro air vehicle. The Harvard RoboFly vehicle accomplished the first takeoff of an insect scale flapping wing aircraft. This flight demonstrated the capability of the aircraft to accelerate vertically while being constrained by guide-wires to avoid translation and rotation in the other five degrees of freedom. The present work proposes an altitude control scheme that would enable a similar ... |
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| Structural Optimization of Joined-Wing Beam Model with Bend-Twist Coupling Using Equivalent Static Loads |
Jun-2009 |
80 pages |
| Authors:
Nicholas S Green; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT
|
| This study is based on the merger of two separate theories to further the efficiency with which joined-wing structural models are designed. The first theory is Geometrically Exact Beam Theory (GEBT). GEBT is a small strain beam theory which is capable of accurately capturing the geometric bend-twist coupling in beam elements that are experiencing large global deformations. This is crucial to the joined-wing problem as it is geometrically nonlinear. The ... |
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| Micro-Scale Flapping Wings for the Advancement of Flying MEMS |
Mar-2009 |
139 pages |
| Authors:
Nicholas R Coleman; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
| This research presents conceptual micro air vehicles (MAV) with total dimensions less than one millimeter. The effort sought to advance understanding of MAV at sub-millimeter dimensions by fabricating and testing micro scale flapping wings. The biomimetic wings derived from three different insects; the dragonfly, house fly, and butterfly, were selected based off of their natural attributes. The fabricated wings utilize a thermal bimorph structure consisting of polysilicon and gold which ... |
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| Bio-Mimetic Millimeter-Scale Flapping Wings for Micro Air Vehicles |
Mar-2009 |
22 pages |
| Authors:
Eric Wetzel; Ronald G Polcawich; Christopher Kroninger; Jeffrey Pulskamp; Jessica Bronson; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| In this report, we present designs of Micro-Electro-Mechanical System (MEMS) fabricated millimeter-scale flapping wings with some characterization of their structural properties and flapping performance. Wings of varied bio-mimetic design, including membrane and ribs-like structures, are flapped at resonance from lead zirconate titanate (PZT) bending actuators at their base. Laser Doppler vibrometer (LDV) measurements and finite element (FE) analysis predictions of the flapping frequencies and mode shapes and the flapping amplitude ... |
|
| Enabling Technologies for Nano Air Vehicles |
10-Feb-2009 |
86 pages |
| Authors:
Jamey D Jacob; OKLAHOMA STATE UNIV STILLWATER
|
| This project investigated several areas with the aim of improving performance and operational use of nano air vehicles (NAVs) by understanding fundamental operating principles and developing key technologies. The project developed plasma actuators for thrust and maneuvering control and examined flapping flight through the development of a high speed videogrammetry system and a gust/shear tunnel to replicate flow fields seen as the NAY scale. In the first portion of the ... |
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| Nonlinear Dynamic Response Optimization Using the Equivalent Static Loads for a Joined-Wing |
01-Sep-2008 |
49 pages |
| Authors:
Gyung-Jin Park; HANYANG UNIV GYEONGGI-DO (SOUTH KOREA) DEPT OF MECHANICAL ENGINEERING
|
| The joined-wing airplane proposed by Wolkovich in 1986 is defined as an airplane that incorporates tandem wings arranged to form diamond shapes in both top and front views. The joined-wing can lead to increased aerodynamic performances as well as reduction of the structural weight. However, the joined-wing has high geometric nonlinearity under the gust load. The gust load acts as a dynamic load. In previous researches, linear dynamic response optimization ... |
|
| Performance Piezoelectric Airframes for Nano Air Vehicles |
30-Jun-2008 |
17 pages |
| Authors:
H Kommepalli; A Hirsh; C Rahn; S Tadigadapa; PENNSYLVANIA STATE UNIV UNIVERSITY PARK
|
| Currently, Unmanned Air Vehicles (UAVs) are too large to penetrate buildings for situational awareness and reconnaissance, emplace important sensors, and sample and return material. While a variety of Micro Air Vehicles have been built and flown that use propellers and flapping wings for lift generation, Nano Air Vehicles (NAVs), defined as weighing less than 10 grams with wingspans less than 7.5 cm, have yet to be flown. NAV-scale actuators and ... |
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| Biomimetic Micro Air Vehicle Testing Development and Small Scale Flapping-Wing Analysis |
MAR 2008 |
114 pages |
| Authors:
Craig E. Svanberg; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH DEPT OF AERONAUTICS AND ASTRONAUTICS
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| The purpose of this research was to develop testing methods capable of analyzing the performance of a miniature flapping-wing mechanism that can later be adapted for the development a biomimetic flapping-wing micro air vehicle (MAV). Three small scale flapping mechanisms capable of single plane flapping, flapping with active pitch control, and flapping/pitch with out-of-plane movement were designed using SolidWorks. The flapping-only model was fabricated on an Objet 3-dimensional printer and ... |
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| Nonlinear Stochastic Flutter of a Cantilever Wing with Joint Relaxation and Random Loading |
21 FEB 2008 |
152 pages |
| Authors:
Raouf A. Ibrahim; Ronald F. Gibson; WAYNE STATE UNIV DETROIT MI DEPT OF MECHANICAL ENGINEERING SCIENCES
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| The research project has generated a number of problems addressing the uncertainties and relaxation problems in aeroelastic structures. Specifically, three main problems that are of important concern to the aerospace industry and the Air Force technology have been addressed. These are: (1) The influence of structure uncertainties of the flutter of an aircraft wing. (2) Stabilization of wing flutter via parametric excitation. (3) Influence ofjoint relaxation on the flutter of ... |
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| Initial Investigation on the Aerodynamic Performance of Flapping Wings for Nano Air Vehicles |
FEB 2008 |
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| Authors:
F. Lesage; N. Hamel; X. Huang; W. YUAN; M. Khalid; P. Zdunich; DEFENCE RESEARCH AND DEVELOPMENT CANADA VALCARTIER (QUEBEC)
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 | A four year project was approved with the purpose of increasing our understanding of the issues concerning the flight of very small air vehicles using flapping wings. This technical memorandum presents the progress made during the first year of the project. The potential impact of this technology on military operations and R&D is first described. The project plan, as revised during the first year, is presented. It combines the development ... |
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| Nonequilibrium Hypersonic Aerothermodynamics Using the Direct Simulation Monte Carlo And Navier-Stokes Models |
17-Jan-2008 |
262 pages |
| Authors:
Andrew J Lofthouse; MICHIGAN UNIV ANN ARBOR
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| Hypersonic flight vehicles are a current topic of interest in both civilian and military research. NASA is currently designing a Crew Transport Vehicle (CTV) [44, 69] and Crew Exploration Vehicle (CEV) [32] to replace the space shuttle; reentry vehicles are, by definition, hypersonic vehicles. Military requirements for reconnaissance and surveillance, as well as the mission of the United States Air Force to rapidly project power globally makes the design of ... |
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Reports by Keyword(s)
WINGS
