Flapping Wing Propulsion For A Micro Air Vehicle
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Flapping Wing Propulsion For A Micro Air Vehicle
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Author : K. D. Jones
language : en
Publisher:
Release Date : 2000
Flapping Wing Propulsion For A Micro Air Vehicle written by K. D. Jones and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2000 with categories.
Computational Investigation Of Flapping Wing Propulsion For A Micro Air Vehicle
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Author : Seng Chuan Lim
language : en
Publisher:
Release Date : 2006
Computational Investigation Of Flapping Wing Propulsion For A Micro Air Vehicle written by Seng Chuan Lim and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2006 with Aerodynamics categories.
The low Reynolds number aerodynamics of the flapping wing Micro-Air Vehicle (MAV) developed at NPS by Max Platzer and Kevin Jones was studied numerically. The dynamic mesh simulation model of the full multi-wing configuration, which consists of a fixed wing and a pair of aft position, opposed pitch/ plunge flapping wings was developed using an advanced CFD code that is available commercially. The unsteady flow fields, wake structures and forces were determined by solving the incompressible Navier-Stokes equations, and the results were compared to past experimental observations. The results were encouraging and provided impetus for future computational optimization studies on the NPS flapping wing MAV.
Fixed And Flapping Wing Aerodynamics For Micro Air Vehicle Applications
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Author : Thomas J. Mueller
language : en
Publisher: AIAA
Release Date : 2001
Fixed And Flapping Wing Aerodynamics For Micro Air Vehicle Applications written by Thomas J. Mueller and has been published by AIAA this book supported file pdf, txt, epub, kindle and other format this book has been release on 2001 with Aerodynamics categories.
This title reports on the latest research in the area of aerodynamic efficency of various fixed-wing, flapping wing, and rotary wing concepts. It presents the progress made by over fifty active researchers in the field.
An Experimental Investigation Of The Geometric Characteristics Of Flapping Wing Propulsion For A Micro Air Vehicle
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Author : Jason Papadopoulos
language : en
Publisher:
Release Date : 2003-06-01
An Experimental Investigation Of The Geometric Characteristics Of Flapping Wing Propulsion For A Micro Air Vehicle written by Jason Papadopoulos and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2003-06-01 with categories.
The geometric characteristics of flapping-wing propulsion are studied experimentally through the use of a force balance and a Micro Air Vehicle (MAV) system. The system used is built to duplicate the propulsion system currently on the flying model at the Naval Postgraduate School (NPS) MAV model. Experiments are carried out in a low speed wind tunnel to determine the effects of mean separation and plunge amplitude on the flapping wing propulsion system. Additionally, the effects on flapping wing shape, frequency, and MAV angle on attack (AoA) are also investigated. Some flow visualization is also performed. The intent is to optimize the system so that payload and controllability improvements can be made to the NPS MAV.
An Experimental Investigation Of Flapping Wing Propulsion For Micro Air Vehicles
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Author : Sean J. Duggan
language : en
Publisher:
Release Date : 2000-06-01
An Experimental Investigation Of Flapping Wing Propulsion For Micro Air Vehicles written by Sean J. Duggan and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2000-06-01 with categories.
Flapping-wing propulsion is studied experimentally through thrust measurements and flow visualization. The objective of the research is to provide further insight into the aerodynamics of flapping-wing micro air vehicles (MAVs) . Experimental work is conducted in the NPS 1.5 m x 1.5 m in-draft wind tunnel. A previously constructed model is suspended by thin wires and is used to measure the thrust performance of the flapping-wing MAV. For this experiment, the model is tested in four configurations; three with varying wing mount stiffness and the fourth with an articulated pitch mechanism. Thrust is indirectly determined using a laser range-finder to measure stream-wise displacement of the model. Three methods of flow visualization are attempted to gain further insight into the flow-field around the MAV. First tufts are placed on and around the model to identify the flow-field Second, a smoke rake placed outside the tunnel is used to route smoke into the test section. Thirdly, a smoke wire system is used to produce smoke in the test section. Experimental results are compared with flow visualization results and previous experimental and numerical work.
An Experimental Investigation Of Flapping Wing Aerodynamics In Micro Air Vehicles
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Author : Christopher J. Bradshaw
language : en
Publisher:
Release Date : 2003-06-01
An Experimental Investigation Of Flapping Wing Aerodynamics In Micro Air Vehicles written by Christopher J. Bradshaw and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2003-06-01 with categories.
Flapping-wing propulsion was studied experimentally through Laser Doppler Velocimetry. Measurements were both time-averaged and unsteady, and were conducted on a Micro- Air Vehicle (MAV) model developed at NPS by Professors Max Platzer and Kevin Jones. The objective of this work was to further understanding of the aerodynamics of flapping-wing propulsion. In specific, this study examined separation control on the leading fixed wing due to entrainment by the trailing flapping wings. Further, a study of wake topology examined differences between the optimal and off-optimal cases. Experimental studies took place in the NPS 5' x 5' low speed wind tunnel. The model was supported on a test stand and LDV measurements of the flow field were taken. Studies were made at varying freestream velocities, angles of attack, and flapping frequencies. The test stand was instrumented with force balances to show forces in both the streamwise and vertical directions.
Experimental Investigation Of Pitch Control Enhancement To The Flapping Wing Micro Air Vehicle
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Author : Chee Kian Chin
language : en
Publisher:
Release Date : 2006
Experimental Investigation Of Pitch Control Enhancement To The Flapping Wing Micro Air Vehicle written by Chee Kian Chin and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2006 with Laminar flow categories.
The mechanical pitching characteristic of the NPS flapping-wing Micro Air Vehicle (MAV) developed by Professor Kevin D. Jones are studied experimentally through the use of constant temperature anemometry and force balance techniques. The MAV without the main fixed-wing is placed in a laminar flow field within a low speed wind tunnel with the wake after the flapping wings characterized with a constant temperature anemometer and thrust generation measured by a load cell at various neutral angles, flapping frequencies and free stream velocities. The experiments seek to determine the effects on the MAV propulsion when the neutral angle of attack of the flapping wings is varied. Flow visualization is also performed to better enhance understanding of the flow field across the pitched flapping wings.
On The Use Of Vortex Flows For The Propulsion Of Micro Air And Sea Vehicles
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Author :
language : en
Publisher:
Release Date : 2003
On The Use Of Vortex Flows For The Propulsion Of Micro Air And Sea Vehicles written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2003 with categories.
Recent interest in flapping-wing propulsion, in particular for hovering or low-speed flight of micro air vehicles, has led to a renewed interest in the measurement and prediction of unsteady, vortex-dominated flows. The proposed vehicles typically operate at Reynolds numbers below 20,000, and operate with mildly to fully separated flow throughout the flapping cycle. This paper provides a brief history on the topic, and summarizes research efforts at the Naval Post-graduate School over the last decade, demonstrating the current numerical and experimental capabilities, and indicating areas where further work is required. Specifically, several wind and water tunnel experiments are described where the vortex structures generated by single flapping foils and by two foils arranged in a biplane configuration were visualized and thrust was measured as a function of flapping amplitude and frequency. Additional experiments are reported which show the potential of flapping foils to energize flat-plate boundary layers and to suppress or reduce regions of flow separation. Two and three-dimensional panel code and two-dimensional Navier-Stokes computations are also described to analyze these flapping-foil experiments.
The Development Of Flapping Wings For A Hovering Micro Air Vehicle
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Author : Derek John Bilyk
language : en
Publisher:
Release Date : 2000
The Development Of Flapping Wings For A Hovering Micro Air Vehicle written by Derek John Bilyk and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2000 with categories.
This document presents the methods and results of early experiments, conducted at the University of Toronto's Institute for Aerospace Studies, toward the development of wings for a hovering, flapping-wing micro air vehicle. The vehicle envisioned symmetrically actuates four wings within a 15 cm diameter, horizontal disc, thrusting the air downward, using the 'clap-fling' aerodynamic effect. The entire vehicle will fit within a 15 cm cube. Following an elementary, quasi-steady analysis to estimate the required flapping-frequency, test equipment was designed to evaluate various wing concepts. An empirical test process allowed many wing designs to be evaluated through a wide flapping-frequency range and at several flapping amplitudes. One year of experimentation led to a design capable of generating more than 50 grams of thrust while consuming less than 6 W of power. This performance is comparable to the best that an unducted propeller or rotor of the same diameter would achieve.
Progress In Astronautics And Aeronautics
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Author :
language : en
Publisher:
Release Date : 2001
Progress In Astronautics And Aeronautics written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2001 with Aerodynamics categories.