project presentation day program april 15, 2008 for wpi’s formula sae team while adhering to the...
TRANSCRIPT
Phone: 508-831-5221
Fax: 508-831-5680
E-mail: [email protected]
Aerospace Engineering Program
Room 250 Higgins Laboratory
100 Institute Road
Worcester, MA 01609
Worcester Polytechnic Institute
Project Presentation Day Program
April 15, 2008
Aerospace Engineering Program
Guest Review Panel
José A. Miletti
Supervisory Mechanical Engineer
U.S. Army Natick Soldier Center
Justin Urban
Fellow - Test Engineering
Fluid Components Integration
Pratt & Whitney Aircraft
Bruce Pote
Director of Hall Thruster Propulsion Programs
Busek Co. Inc.
Page 13
Aerodynamic Analysis and Fabrication of Formula Style Race Car
Chassis
Doug Cimon, Derek Duval, Klementina Gerova
Advisors: Professors Eben Cobb, David Olinger, Gretar Tryggvason
The purpose of the this project is to design and fabricate a full aerodynamic
package for WPI’s Formula SAE team while adhering to the rules set forth by
Society of Automotive Engineers International. The front and rear multi-
element wings along with the underbody diffuser were designed to generate a
maximum low-speed down-force while maintaining minimum drag. The com-
plementing body design utilizes aerodynamic loading for quality race perform-
ance by reducing wake vortex generation. Three different types of analysis
were used in the completion this project: wind tunnel testing, computational
fluid dynamics, and track testing.
Worcester Polytechnic Institute Page 12
Design Optimization of a 4-Propeller Autonomous 3DOF Hover
Mark Dupuis, Jonathon Gibbons, Maximillian Hobson-Dupont, Alex Knight,
Artem Lepilov, Michael Monfreda, George Mungai
Advisors: Professors Michael Demetriou, David Olinger
An autonomous quad-rotor is an aerial helicopter with four horizontal rotors
designed in a square configuration capable of locating lost or jeopardized
victims, gathering military intelligence, or surveillance. The project team de-
signed a miniaturized quad-rotor able to determine its own attitude through
an onboard sensor system. A computer program using formulated control
equations and an onboard processing system enables the quad-rotor to fly to
a pre-determined position while correcting its attitude, which results in steady
level autonomous flight.
8:30—8:35 Opening Remarks, Professor Nikolaos Gatsonis, Director,
Aerospace Engineering Program
8:35—8:55 Thermal and Structural Analysis of a Rocketborne Experiment
T. Huynh, K. Parker
Advisor: Professor Nikolaos Gatsonis
Sponsor: MIT Lincoln Labs
8:55—9:15 Experimental Study of Parachute Suspension Line Drag
S. Black, B. Mandadzhiev, A. Thompson
Advisor: Professor David Olinger
Sponsor: Natick Army Soldier Center
9:15—9:35 Integration of a Small Vacuum Facility
V. Herrera, M. Macri, V. Tourgee
Advisor: Professor Nikolaos Gatsonis
9:35—9:55 Thermal Energy Scavenging to Power Aircraft Engine Test Sensors
D. Bradway, D. Bryand, G. Bukowski, C. Scanio
Advisor: Professor David Olinger
In collaboration with Pratt & Whitney Aircraft
9:55—10:15 W.A.R.R.I.O.R.S. III (WPI AIAA Research Rocket)
J. Buhler, T. Coverstone, N. Cummings, S. Fleming, T. Huleatt, T. McDonald, P. Renaud,
M. Yocum
Advisor: Professor John Blandino
10:15—10:35 Wind Power from Kites
R. Buckley, C. Colschen, M. DeCuir, M. Hurgin, E. Lovejoy, N. Simone
Advisor: Professor David Olinger
10:35—10:55 Multiple Satellite Imaging Systems
R. Cormier, K. Elliott, J. Frey, I. Janzen,
Advisor: Professor Islam Hussein
10:55—11:15 Design and Control of an Autonomous Helicopter
Y. Alperin, R. Graves, C. Jerry, J. McClintock, R. Sobel
Advisors: Professors Michael Demetriou, David Olinger
11:15—11:35 Attitude Control Systems
R. Leverence, M. Rivera, R. Staunch
Advisor: Professor Islam Hussein
11:35—11:55 Development of a Plasma Source with Integrated Particulate Injector
J. Basile, M. Dickson, W. Flaherty, B. Kolk
Advisor: Professor John Blandino
11:55-12:15 Design Optimization of a 4-Propeller Autonomous 3DOF Hover
M. Dupuis, J. Gibbons, M. Hobson-Dupont, A. Knight, A. Lepilov, M. Monfreda, G. Mungai
Advisors: Professors Michael Demetriou, David Olinger
12:15-12:35 Aerodynamic Analysis and Fabrication of Formula Style Race Car Chassis
D. Cimon, D. Duval, K. Gerova
Advisors: Professors Eben Cobb, David Olinger, Gretar Tryggvason
12:35 Judges caucus; Students complete EBI Exit Survey; Lunch outside HL116
4:00 Award Presentation Ceremony HL116
Program
Worcester Polytechnic Institute Page 2
Thermal and Structural Analysis of a Rocketborne Experiment
Thomas Huynh, Krystal Parker
Advisor: Professor Nikolaos Gatsonis
Sponsor: MIT Lincoln Labs
The MIT Lincoln Laboratory High Powered–Missile Alternative Range Target
Instrument (HP-MARTI) program will design and operate an optical-sensor
module (OSM) onboard an expendable rocket. The HP-MARTI program will
test and characterize the effects of a megawatt airborne laser on a missile
during its boost-phase. This project provides a survivability analysis of the HP-
MARTI OSM and considers the effects of aerodynamic heating, laser heating,
and aerodynamic loading on the rocket and OSM structure, through a coupled
thermal and structural numerical analysis. Results show that at 40,000 feet
the structure of the rocket and the OSM withstands the increased thermal
and structural stresses, allowing enough time for the optical sensors to col-
lect data before failure.
Page 11
Development of a Plasma Source with Integrated Particulate Injector
Joseph Basile, McConnell Dickson, William Flaherty, Brian Kolk
Advisor: Professor John Blandino
A plasma discharge chamber was designed and built to investigate the charg-
ing of dust in a plasma. The design was based on an ion thruster discharge
chamber using a filament cathode. The discharge chamber consists of an
aluminum cylinder with gas and electrical feedthroughs. A filament cathode
is used to ionize this gas and create the plasma. Magnets are used to in-
crease the electron residence time in the gas and hence the number of colli-
sions. Dust is introduced using a rate-controllable dispenser and then falls
through the chamber where it is charged through collisions with ions and
electrons. Some of these dust particles fall into an induction charge detector
that measures their charge. A Langmuir probe is also used to collect data on
the plasma to investigate its properties.
Dust Reservoir
Vibrator Motor
CDMS
Plasma Discharge Chamber
Dust Dispenser
Magnets
Probe Access Hole
Retarding Screen Induction Sensor Tube
Amplifier Electronics
Anode Support Posts Magnets
Worcester Polytechnic Institute Page 10
Attitude Control Systems
Rick Leverence, Marcos Rivera, Ryan Staunch
Advisor: Professor Islam Hussein
Attitude control systems play an integral role in many modern technologies.
This project develops an autonomous attitude control system for an underwa-
ter vehicle. Throughout the project, an understanding of the fundamentals of
attitude control and an appreciation for the complexity involved in a relatively
simple, yet comprehensive, operational system were achieved. More specifi-
cally, the mathematical expressions, computer programs, and physical vari-
ables and components, along with the interactions between elements of the
system, were extensively studied.
Page 3
Experimental Study of Parachute Suspension Line Drag
Steve Black, Boris Mandadzhiev, Amanda Thompson
Advisor: Professor David Olinger
Sponsor: Natick Army Soldier Center
The drag force created by suspension lines on a parachute system can often
be a large part of the total aerodynamic drag of the system. For parafoils,
parachute systems with a high glide ratio, the suspension line drag can result
in a reduction of the glide ratio and overall degradation in the parachute sys-
tem performance.
This project was completed on-campus at WPI, with collaboration from engi-
neers from the project sponsor, the U.S. Army Natick Soldier Center. In this
work, wind tunnel testing of parachute suspension line drag was undertaken.
An experimental apparatus to measure suspension line drag was designed
and constructed. Wind tunnel tests were carried out for a variety of suspen-
sion lines, different line orientations, line tensions, and wind tunnel speeds.
Dimensional analysis was completed to determine the important non-
dimensional parameters for the problem. Instantaneous drag data was ana-
lyzed using Fast Fourier Transfer to determine the frequency response of the
suspension lines. Mean drag data was also measured and analyzed.
Worcester Polytechnic Institute Page 4
Integration of a Small Vacuum Facility
Victor Herrera, Michael Macri, Von Tourgee
Advisor: Professor Nikolaos Gatsonis
This project involves the integration of a bell-jar vacuum chamber with a mi-
cro-flow delivery system. A structure to support the bell-jar and associated
equipment is designed for a 405 kg maximum load. A hoist mechanism is
designed to allow lifting of the 114 kg bell-jar cover. The design and struc-
tural analysis of these systems are performed using software. This project
provides also analysis and estimates of the mass flow that will be delivered
into the bell-jar using a pressure-decay microflow system.
Page 9
Design and Control of an Autonomous Helicopter
Yan Alperin, Ryan Graves, Curtis Jerry, James McClintock, Evan Sobel
Advisors: Professors Michael Demetriou, David Olinger
Through mathematical modeling, control scheme development, and extensive
testing, this project has taken the first steps in rendering a miniature helicop-
ter autonomous. This report contains the relevant equations of motion, the
associated control schemes, as well as the steps taken to create a sensor-
driven flight computer allowing autonomous operation. Further development
and testing of the control board is necessary to apply the completed control
scheme which allows autonomous flight of a remote control helicopter to a
preselected position.
Worcester Polytechnic Institute Page 8
Multiple Satellite Imaging Systems
Roland Cormier, Katie Elliott, Jason Frey, Isaiah Janzen
Advisor: Professor Islam Hussein
This Major Qualifying Project explores the theory of multiple satellite imaging
with consideration given to aperture movement, field of view of each aper-
ture, number of apertures, aperture spacing, frequency of interest, and time;
simulates the concept through a MATLAB® simulation in both one and two
dimensions; provides the groundwork for a physical experiment to demon-
strate the concept through three different wave types: infrared, radio, and
acoustic.
Page 5
Thermal Energy Scavenging to Power Engine Test Sensors
Dustin Bradway, Daniel Bryand, Gregory Bukowski, Corina Scanio
Advisor: Professor David Olinger
In collaboration with Pratt & Whitney Aircraft
In order to validate the performance of their aircraft engines, Pratt & Whitney
needs to measure pressures at various engine stations. Currently, the pres-
sure transducers are powered by external power sources in a test stand. This
setup requires the use of a great deal of wiring leading to long installation
time and instrumentation system failures. The goal of this project was to
power the pressure transducers wirelessly with a required 10 volt excitation
at 10 milliamps. This was done by scavenging thermal energy from the engine
with a thermoelectric generator package. This device uses the temperature
difference between the engine exterior at station 12.5 and the surrounding
ambient air to generate power. The generator was packaged between two
metal plates with an attached heat sink to maximize the temperature differ-
ence and power output. Temperature differences of approximately 60 de-
grees Celsius and voltages of 2.5 volts were achieved for extended periods of
time. A power converter was used to step up the voltage to the required 10V.
In addition, rechargeable batteries were used to supplement the power during
engine startup. This package will provide enough voltage to power most wire-
less devices and eliminate the problems associated with current instrumenta-
tion during engine tests at Pratt & Whitney.
Worcester Polytechnic Institute Page 6
W.A.R.R.I.O.R.S. III (WPI AIAA Research Rocket)
Jared Buhler, Troy Coverstone, Nicholas Cummings, Siobhan Fleming, Tho-
mas Huleatt, Theodore McDonald, Patrick Renaud, Megan Yocum
Advisor: Professor John Blandino
This project investigated two areas related to high powered model rocketry;
aerodynamics and hybrid rocket motors. In the aerodynamics area, the team
investigated the phenomenon of fin flutter. Models for fin flutter in the litera-
ture were reviewed and results measured using scaled fins in a low speed
wind tunnel. A flight compatible data acquisition system was designed and
built to measure and record flutter data during flight. In the hybrid propulsion
area, motors were designed, built and tested which used either PVC or paraf-
fin with nitrous oxide. Thrust data was collected using a thrust stand and data
collection system built as part of the project. CFD modeling was used to inves-
tigate the flow of air over fins of different geometry and the flow oxidizer
through different injectors.
Page 7
Wind Power from Kites
Ryan Buckley, Chris Colschen, Michael DeCuir, Max Hurgin, Erik Lovejoy, Nick
Simone
Advisor: Professor David Olinger
The goal of this project was to design and build a one-kilowatt scale system
for generating power using a kite. Kite power has the potential to be more
economical than using wind turbines because kites can fly higher than tur-
bines can operate. At higher altitudes, wind speeds and available power are
increased. In the developed system, a large windboarding kite pulls the end
of a long rocking arm which turns a generator and creates electricity. This
motion is repeated using a mechanism that changes the angle of attack of
the kite during each cycle, thus varying its lift force and allowing a rocking
motion of the arm. The end of the arm turns a shaft with a flywheel attached
and spins a mounted generator, whose output then gets stored in batteries
for later use. A MATLAB simulation was used to predict a power output for the
system of approximately one kilowatt. All sub-components of the system
(power conversion mechanism, angle of attack mechanism, and kite control
mechanism) have been lab tested. The complete kite power system has been
field tested with the kite attached to a fixed rocking arm. These tests showed
that the system structure can withstand the structural loads imposed by the
kite. A future application for this system will be in a developing nation without
access to a power grid.