Project Presentation Day Program April 15, 2008

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


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,


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


9:35—9:55 Thermal Energy Scavenging to Power Aircraft Engine Test Sensors

D. Bradway, D. Bryand, G. Bukowski, C. Scanio


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


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


11:15—11:35 Attitude Control Systems

R. Leverence, M. Rivera, R. Staunch


11:35—11:55 Development of a Plasma Source with Integrated Particulate Injector

J. Basile, M. Dickson, W. Flaherty, B. Kolk


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


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


Thermal and Structural Analysis of a Rocketborne Experiment

Thomas Huynh, Krystal Parker


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


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


Attitude Control Systems

Rick Leverence, Marcos Rivera, Ryan Staunch


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


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.


Integration of a Small Vacuum Facility

Victor Herrera, Michael Macri, Von Tourgee


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


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.


Multiple Satellite Imaging Systems

Roland Cormier, Katie Elliott, Jason Frey, Isaiah Janzen


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


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.


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


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


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.

Documents

Project Presentation Day Program April 15, 2008