F09-26-REIGNITE
Proposal
CONTROLLABLE IGNITION
Proposed For: Boeing
F09-26-REIGNITE
Saluki Engineering Company
11/19/2009
F09-26-REIGNITE
SALUKI ENGINEERING COMPANY
F09-26-REIGNITE
PROPOSAL
Prepared For: Boeing
19 November 2009
Prepared By:
Ryan Vojtech, ME (Project Manager)
Ryan Affara, ME
Dustin Mennenga, ME
Jeremy Moyer, ME
Jack Palmieri, ME
Joshua Snead, ME
F09-26-REIGNITE
Saluki Engineering Company (SEC)
Mailcode 6603
Southern Illinois University
Carbondale, IL 62901
773-550-7926
vojtech@siu.edu
Dr. Suri Rajan
Professor - Mechanical Engineering and Energy Processes
Southern Illinois University Carbondale
Mailcode 6603
Carbondale, IL 62901
To whom it may concern:
This letter is in response to your request for a design proposal regarding a rocket ignition
system able to reignite midflight. The following proposal has been created for the purpose of
designing a small scale prototype rocket to create a hybrid reignition system. The entire team as
a whole would like to thank the Boeing Company for the concept, as well as the opportunity to
develop a product for them.
Today, studying the concept of rocket reignition is important to many companies because
of the potential energy savings on the rockets. Saving energy, or fuel, equates to saving money
and running the rockets much more efficiently. Our design for the system is one that will be
relatively simple, but will still be able to adequately achieve all of the Boeing Company’s
requirements for this project.
Again, our entire team is thrilled to be working on an innovative project for a company as
successful and established as Boeing. Any questions, comments, or concerns you have regarding
the proposal please feel free to contact me by my listed phone number or email address.
Sincerely,
Ryan Vojtech
F09-26-REIGNITE
EXECUTIVE SUMMARY
Saluki Engineering Company (SEC) group F09-26 proposes to design a small hybrid
rocket motor with the ability to turn the combustion process on and off while in-flight. The main
objective is to be able to control thrust. Some benefits of this design include minimal impact to
the environment during operation, low cost in small scale production, regulation of thrust, and
reignition.
Ignition in the combustion chamber will occur initially by igniting the flow of propane
with a spark plug. Using nitrous oxide as an oxidizer and paraffin wax as a solid fuel grain,
thrust can be controlled by varying the flow of gas and oxidizer into the combustion chamber.
Manually controlled valves will be used in order to vary these flows. Testing will be conducted
in order to achieve different thrust conditions.
Subsystems involved with the project include combustion, heat transfer, gas flow, and
safety. This proposal includes descriptions of each system and how they relate to our project.
Information on pricing and other resources obtained, along with a timeline and action item list
(AIL) will be included as well.
Work began August 25th 2009 and will reach completion May 6th 2010. The initial cost
of design is estimated to be less than $500.00.
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RESTRICTION ON DISCLOSURE OF INFORMATION
The information provided in or for this proposal is the confidential, proprietary property
of the Saluki Engineering Company of Carbondale, Illinois, USA. Such information may be
used solely by the party to whom this proposal has been submitted by Saluki Engineering
Company and solely for the purpose of evaluating this proposal. The submittal of this proposal
confers no right in, or license to use, or right to disclose to others for any purpose, the subject
matter, or such information and data, nor confers the right to reproduce, or offer such
information for sale. All drawings, specifications, and other writings supplied with this proposal
are to be returned to Saluki Engineering Company promptly upon request. The use of this
information, other than for the purpose of evaluating this proposal, is subject to the terms of an
agreement under which services are to be performed pursuant to this proposal.
F09-26-REIGNITE
TABLE OF CONTENTS
1. Introduction
1
2. Literature Review
2
2.1. Existing Hybrid Rocket Systems
2
2.2. Combustion
5
2.3. Heat Transfer: Combustion Chamber
7
2.4. Gas Systems
10
2.5. Safety
12
2.6. Tests and Measurements
14
2.7. Summary
16
3. Basis of Design
16
4. Project Description
17
5. Engineer’s Scope of Work
18
5.1. Deliverables
18
5.2. Design and Testing Activities
18
5.3. Specifications
19
6. Subsystem Descriptions
19
6.1. Combustion
19
6.2. Heat Transfer
20
6.3. Fluids/Gas Systems
20
6.4. Thermodynamics
20
6.5. Safety
21
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6.6. Testing
21
7. Pricing
22
8. Validity Statement
24
9. Project Organization Chart
24
10. Project Timeline
25
11. Action Item List (AIL)
26
12. Conclusion
27
13. Appendix A: Personal Resumes
28
14. Appendix B: Preliminary Drawings
36
15. Appendix C: References
38
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LIST OF TABLES, EQUATIONS, AND FIGURES
FIGURES
Figure 1: Hyperion Rocket Test
3
Figure 2: Hypertek Rocket System
4
Figure 3: Boundary Layer of Solid Fuel
8
Figure 4: Temperature and Concentration Profiles
10
Figure 5: Gas Flow System
10
Figure 6: Max Flux vs. Regression Rate
11
Figure 7: FBD of Thrust Stand
15
Figure 8: Moments and Thrust Matrix
15
Figure 9: Test Measurements Setup
16
Figure 10: Organization Chart
24
Figure 11: Test Stand with Rocket and Fuel Tanks
36
Figure 12: Hybrid Rocket
36
Figure 13: Rocket/Nozzle View
37
Figure 14: Fuel Lines Entering Rocket
37
EQUATIONS
Equation 1
5
Equation 2
8
Equation 3
8
Equation 4
11
Equation 5
11
Equation 6
21
TABLES
Table 1: Important Thermal Properties of Fuels/Fuel Components
7
Table 2: Temperature Distribution
9
Table 3: Properties of Propane and Nitrous Oxide
12
Table 4: Design Basis
16
Table 5: Project Costs
23
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1. INTRODUCTION
Hybrid propulsion is becoming a more and more common application in rocket design today.
The reason for this is because hybrid rockets are cheaper to make, but also safer as well because
of the fuel types used. Another reason hybrid powered rockets have been becoming more popular
is the fact that there is a lot more information on them because of the recent research and
development by various companies. With the numerous benefits of hybrid propulsion already
discovered, and possibly more benefits still to be uncovered, there has been an increase in the
number of companies looking into this and trying to be leaders in hybrid technologies.
The approach Team 26 REIGNITE is taking to complete Boeing’s request is to build a small
scale hybrid rocket plumbed with the necessary equipment needed for reignition. There are many
reasons for making the rocket on a smaller scale; the overall cost for the materials is less, ease of
working on the rocket, it allows the team to be able to test it in more areas, and it is also safer in
case of something going wrong. The rocket itself will be a relatively simple design; this is
because most of the team’s research is involved with the reignition system of the rocket, rather
than the rocket itself.
This project was chosen by the design team because we felt that we could successfully
deliver on Boeing’s requests, and provide new and valuable data on rocket reigntion. The team
has many of the school’s equipment and labs at our disposal, as well as a faculty advisor who has
an extensive background in combustion and thermodynamics.
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2. LITERATURE REVIEW
Hybrid rockets incorporate the use of a solid fuel and a liquid or gaseous oxidizer. There
are many benefits of the use of hybrid rockets. They are fairly inexpensive to fabricate and
exhibit minimal impact to the environment during operation. Also, regulations of thrust and
reignition capabilities are very important aspects of these rockets. This technology has been
used in the past and is continually looked at as an option for rockets today. Some of the major
components of study for hybrid rockets include the storage and flow of oxidizer, combustion of
the solid fuel and oxidizer, testing, measuring pressures, temperatures, and thrust, and the safety
measures that need to be taken during fabrication and testing. This literature outlines a basic
understanding of the workings of hybrid rockets and their past use.
2.1 EXISTING HYBRID ROCKET SYSTEMS
While hybrid rocket reignition has not been around for a long time, there have still been a
few companies who have been experimenting in this field for a while. And those companies
have made enough progress for other companies and groups to compare and contrast their
designs with already proven ones. Many of the companies use similar designs and change the
fuel and oxidizers, if anything. So for this section, the different designs will be looked at rather
than the fuel combinations.
The Environmental Aeroscience Corporation (eAc) [1] is a company that has been
designing and building hybrid rockets for over 20 years. They were responsible for the first
hybrid/ nitrous oxide rocket to be fired, the first hybrid rocket used by NASA, as well as
performing research for DARPA and the US Air Force [1]. The eAc has developed many rocket
designs but the Hyperion I and II rockets really utilized hybrid rockets and reignition more than
the others. The propulsion systems for these rockets were molded polymer fuel grain, and
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nitrous oxide was used as the oxidizer [2]. Once the eAc had learned how to successfully use
nitrous oxide in their rockets they focused on reignition for the Hyperion II. The Hyperion II
uses slightly different fuels than its older brother, the Hyperion I; it has metalized solid fuel, and
self-pressurizing nitrous oxide. In preliminary testing, the eAc was able to fire the rocket for 10
seconds, turn it off for 15 seconds, and reignite it for 5 more seconds. All this was done without
any external reignition system, and the rocket utilized 98% of its fuel showing that reignition is
not necessarily a waste of fuel [3]. Figure 1 is a picture of the eAc company testing one of their
Hyperion rockets [4].
Figure 1: Hyperion Rocket Test [4]
The company Hypertek probably has one of the most user friendly hybrid rocket systems
that is commercially available now. This is because it is a smaller design, bringing the cost
down, that is primarily made for testing at universities or other rocket enthusiasts [5]. They sell
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various different versions of the rocket and also have all the drawings and dimensions of the
rocket on their website. The propulsion system for these rockets uses thermoplastic fuel grains
and nitrous oxide [6]. The Hypertek rockets use a Kline valve which helps distribute the
oxidizer uniformly and safely. Another aspect which makes the Hypertek rocket great for
universities and students is its safety features. For one, the ignition system is completely
pyrotechnic free, and the fuel and the oxidizer are completely separated until ignition making the
rocket much less volatile. Also, the only thing a user has to do to the rocket to re-launch it, is
simply unscrew the spent fuel grain and put a new one on [7]. Shown below is Figure 2, which
is a 3-D rendering of a complete Hypertek rocket system [8].
Figure 2: Hypertek Rocket System [8]
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2.2 COMBUSTION
The combustion mechanism occurring in traditional hybrid rocket systems is that of a
diffusion flame which occurs due to the arrangement of the combustion chamber. A diffusion
flame is an artifact of the mixing process between the fuel and oxidizer which occurs due to a
diffusion process in the solid fuel. This diffusion flame is supported by the gaseous oxidizer
flowing over the solid fuel, which produces a velocity boundary layer whose magnitude varies in
relation the local Reynolds number [9]. Diffusion flames are typically characterized by high soot
production (due to the unmixed nature of the air-fuel mixture), and a burn rate limited to the
diffusion rate of the solid.
Diffusion in a solid [10] can be characterized by the following equation:
Equation 1:
∂φ/∂t = D (∂2φ/∂x2)
Where; φ: concentration of solid (mol/m3)
t: time (s)
D: diffusion coefficient
x: length (m)
The characteristic flame can be characterized by the Reynolds number, which describes
the combustion flow as either laminar or turbulent, and accordingly evaluates the mixing
process. Laminar flow is initiated by molecular mixing, whereas in turbulent flow mixing is
enhanced by eddy currents [9]. The combustion flow process achieved in a hybrid rocket motor
is a function of many factors which include: combustion chamber geometry, nozzle geometry,
air-fuel flow rates, and the properties of the respective fuel and oxidizers chosen. These methods,
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developed in conjunction with the Zeldovich-Novozhilov solid-phase energy conservation
method, provide a calculation strategy for transient solid-propellant burning [11].
The diffusion rate of the solid fuel is a rate limiting function of the heat transfer rate
occurring at the interacting surface between the solid and gaseous components. In dealing with
hybrid combustion, methods have been devised which increase the heat release rate by the
addition of energetic ingredients such as aluminum (Al, Li , etc.) could lead to an increase in the
heat release at the fuel surface. This phenomenon occurs when the aluminum particles are
oxidized to aluminum oxide which stabilize the velocity boundary layer and provide a more
energetic interaction surface [12].
Common fuels utilized in hybrid rocket combustion include: Hydroxyl-terminated
polybutadiene (HTPB), butyl rubber, polyethylene, and paraffin [13] [14]. The regression rate,
and consequently the performance of the rocket is also a characteristic of the specific fuel chosen
to be used and must be considered in conjunction with the relevant thermal properties.
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Table 1: Important Thermal Properties of Fuels/Fuel Components [15]
Thermal Properties
Specific
Melting
Density
Point (K)
(kg/m3)
Thermal
α 106
Heat (cp),
conductivity (k),
(m2/s)
(J/kg K)
(W/mK)
Aluminum oxide
2323
3970
765
36
11.9
Paraffin
300
900
2890
0.24
-
Butyl Rubber (hard)
300
1190
-
0.16
-
Polyethylene
403
1400
1000
0.24
0.7
2.3 HEAT TRANSFER: COMBUSTION CHAMBER
Heat generated by the solid fuel and oxidizer (N2O) is an important process of the hybrid
rocket. Inside the combustion chamber the reaction rate is so low at low temperatures that the
heat generated is lost to the surroundings but if the temperature of the gas is raised high enough,
the reaction rate becomes high enough that the heat generated exceeds losses to the surroundings
and the reaction takes off. If enough nitrous oxide is used, the fuel gases liberated from the solid
fuel grain will be completely oxidized and the product gases will generally have temperatures
over 5000º F [16].
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Figure 3: Boundary Layer of Solid Fuel
Decomposition of nitrous oxide can be ignited at temperatures as low as 1202º F. The
thermal conductivity of N2O is 14.57 mW/(m.K) [17]. The thermal conductivity of C3H8 is
15.198 mW/(m.K) [18]. Figure 3 is an image of the solid fuel inside the combustion chamber
and shows the heat transfer from the solid fuel to the oxidizer/fuel mixture [19]. Cylindrical
systems often experience temperature gradients in the radial direction only and may therefore be
treated as one dimensional [15]. To estimate the amount of heat transferred through the cylinder
Fourier’s Law is applied. It is given by,
Equation 2:
q= -k2πrLdT/dr
where k is the thermal conductivity, r is the radius, L is the length of the cylinder, and T is
temperature.
This will not be a completely accurate assumption because it does not take into affect
heat generated inside the combustion chamber and other factors. The dimensions of the
cylindrical steel tube and temperatures at the surface determine other values such as temperature
distribution and thermal resistance. Thermal resistance can be used to help find the heat transfer
through the wall of the cylinder for safety reasons. The equation is given by,
Equation 3:
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Rt=[ln(r2/r1)]/2πLk
F09-26-REIGNITE
where r1 and r2 are the inner and outer radii of the cylinder, L is the length of the cylinder, and k
is the thermal conductivity. Temperature distribution is useful in finding temperatures at certain
points inside the cylinder. Table 2 below gives the equations to determine the temperature
distribution in the cylinder with or without energy generation.
Table 2: Temperature Distribution [15]
Temperature Distribution without Energy
Temperature Distribution with Energy
Generation
Generation
T(r)=
(Ts,1 - Ts,2)
ln(r/r2)+Ts,2
ln(r1/r2)
T(r)= Ts+( q r22/2k) ln(r/r1)-( q /4k)(r2-r12)
r1=inner radius
k=thermal conductivity
r2=outer radius
r1=inner radius
Ts=surface temperature
r2=outer radius
q =energy generation
Ts=surface temperature
Figure 4 shows the temperature profiles when the fuel and oxidizer are near the solid fuel grain
[20].
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Figure 4: Temperature and Concentration Profiles [20]
2.4 GAS SYSTEMS
Figure 5: Gas Flow System
In the gas flow system, shown in Figure 5, two gases are used to help ignite and oxidize the
combustion in the hybrid motor, propane (C3H8) and nitrous oxide (N2O). The characteristics of
these gases, such as pressure and rate at which these gases are being added, are used when
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designing and making calculations. Pressure can be measured but to calculate a mass flow rate
first the velocity must be calculated by using the Bernoulli equation:
Equation 4:
Where p = pressure, γ = specific weight of fluid, z = change in elevation, V = velocity, and g =
acceleration due to gravity [21]. Then the velocity can be used to find the mass flow rate by the
equation
Equation 5:
𝑚̇ = 𝜌𝐴𝑉 = 𝜌𝑄
Where 𝑚̇ = mass flow rate, ρ = density of fluid, A = cross-sectional area of the pipe, and Q =
volumetric flow rate [21]. Then the thrust of the engine can be compared to the mass flow rate
of the gases, or like in one previous experiment, the mass flux was calculated and compared to
the regression of the solid fuel [22], as shown in Figure 6 below
Figure 6: Max Flux vs. Regression Rate [22]
Properties of these gases are used for both calculations and safety reasons, and some properties
are listed in Table 3 below
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Table 3: Properties of Propane and Nitrous Oxide [17] [18]
Propane (C3H8)
Nitrous Oxide (N2O)
Molecular weight : 44.096 g/mol [15]
Molecular weight : 44.013 g/mol [16]
Gas density (1.013 bar and 15 °C) : 1.91 kg/m3
[15]
Gas density (1.013 bar and 15 °C) : 1.872
kg/m3 [16]
Specific gravity (air= 1)(1.013 bar and 21 °C):
1.55 [15]
Specific gravity (air = 1) (1.013 bar and 21 °C
(70 °F)) : 1.53 [16]
Ratio of specific heats (Gamma:Cp/Cv) (1 bar
and 25 °C (77 °F)) : 1.134441 [15]
Thermal conductivity (1.013 bar and 0 °C (32
°F)) :15.198 mW/(m.K) [15]
Ratio of specific heats (Gamma:Cp/Cv) (1.013
bar and 15 °C (59 °F)) : 1.302256 [16]
Thermal conductivity (1.013 bar and 0 °C (32
°F)) : 14.57 mW/(m.K) [16]
2.5 SAFETY
Hybrid rockets are known to be the safest rocket motors to construct. These rockets are
not as complex as liquid propellant engines, they are less expensive, and are classified as having
no TNT equivalent explosive power. However, there are safety concerns that need to be
discussed. The largest hazard for a hybrid rocket would be if a flame or even hot gasses were to
flow back through the injector, making the nitrous oxide ignite and causing a tank explosion.
This is called a “blow back” and can be caused during unstable combustion where the pressure
drop is not sufficient. Other hazards from a hybrid rocket include vessel ruptures from the hot
combustion gases due to an insulation failure or when too much nitrous oxide enters the
combustion chamber prior to ignition it can result in a temporary over pressure once ignited [23].
The implementation of a miniature propane ignition system is possible for a hybrid
rocket. Propane is an extremely flammable liquefied gas. All known extinguishers can be used in
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case of a fire. In high concentrations, if propane is inhaled, it can cause loss of mobility and
consciousness, but even in low concentrations, propane can cause dizziness, headache, nausea
and loss of co-ordination [24]. A victim exhibiting these symptoms should be removed from the
contaminated area while wearing a breathing apparatus and keeping the victim warm and rested.
Flush eyes with water for at least 15 minutes if the propane is spilled. Propane should be kept in
a suitable container away from oxidant gases below 50°C in a well ventilated place. Propane is
conventionally stored in standard pressure vessels at 140 psi [25].
Nitrous oxide is a possible oxidizer for the hybrid rocket. Nitrous oxide is labeled as a
non flammable, non toxic gas, but can be used as an oxidizing substance like in a hybrid rocket.
This liquefied gas strongly supports combustion and is able to react violently with combustible
materials [17]. Nitrous oxide can cause the same effects as propane from inhalation and the same
first aid measures should be taken. All known fire extinguishers can be used on this oxidant. The
boiling point of nitrous oxide is -88.5°C at 1 atm, and is normally maintained as a liquid at a
pressure of 54 bar [23]. The main hazard is when exposure to a fire could cause this container to
explode. Combustion products from a fire could produce hazardous fumes of nitric
oxide/nitrogen dioxide while the propane can produce the undetectable carbon monoxide.
Noise is a factor that may be overlooked when considering a hybrid rocket. According to
OSHA standards, in a general industry atmosphere the maximum impulse noise allowed is 140
dB [26]. This is the decibel level when permanent hearing damage begins and is equivalent to a
gun muzzle blast or a jet engine from 100 feet away. Eardrum rupture begins at 150 dB when the
sound of a handgun shot at 1 foot away is 155 dB. A hybrid rocket is known to make hissing
sounds but may be able to produce hearing damage so proper ear protection should be worn
when operating the rocket.
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With all the hazards to a hybrid rocket, the hybrid rocket is still known as being much
safer than a liquid or solid fuel rocket since the fuel in a hybrid does not contain an oxidizer
making an explosion far less likely. The safety of a hybrid rocket is enhanced by the control of
the independently controlled oxidizer, which initiates the combustion process. Stainless steel will
be able to withstand any effects of corrosion and will be thick enough to withstand the high
temperature and high pressure of combustion. As long as the rocket is well designed and
carefully constructed, the hybrid will be very safe.
2.6 TESTS AND MEASUREMENTS
Static testing of the designed hybrid rocket will need to be done in order to collect data.
Data acquisition during testing would include the measurements of thrust, gas and fluid flow,
temperatures and pressures [27].
In other hybrid rocket tests, the thrust of the rocket was measured using a “strain gauge
load cell” mounted in front of the motor on the “test sled” [28]. Thrust power can also be
measured through the use of beam deflection. The rocket can be mounted on vertical beams with
known, uniform dimensions and material properties. When the rocket is fired strain gauges on
the beams could “convert strain to a voltage proportional to the thrust force” [29]. The
University of Arkansas at Little Rock used a bit more sophisticated program to test the thrust of
their hybrid rocket motors. The stand they use is composed of “six uniaxial force elements”
[30]. Uniaxial forces are measured and using known distances between elements, moments can
be calculated. A matrix can be constructed relating distances between elements, resultant forces
in the elements, forces in the XYZ directions, and the moments around each axis. From this
matrix, the thrust value can be calculated [30].
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Figure 7: FBD of Thrust Stand [30]
Figure 8: Moments and Thrust Matrix [30]
Another proposed method for measuring thrust is using a horizontal track and a spring. A spring
with known spring constant will be used. The length that the spring stretches could be measured
and used to measure the force applied to the spring (i.e. thrust). This relationship can be
expressed as F = -ks, where k is the spring constant and s is the length of stretch [31]. Thrust can
be plotted against oxidizer flow rate [29].
Pressure in the fuel chamber can be measured with a gauge mounted at the front of the
motor and the pressure of the oxidizer was measured between the oxidizer tank and the oxidizer
valve. Using thermocouples, the temperature of the rocket’s external casing and the temperature
of the flame exiting the nozzle can be measured for analysis. In other cases, temperature
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measurements were also taken within the solid fuel to help determine regression over the course
of the testing [28]. The figure below shows the possible placement of measurement devices [28]
Figure 9: Test Measurements Setup [28]
2.7 SUMMARY
Hybrid rockets are very interesting ideas that have been studied and used for years. Their
capability to be safer and more efficient rockets makes them more desirable than either solid or
liquid propellant rockets. Concepts that have been explored and discussed here include
combustion and reignition, heat transfer within the combustion chamber, gas flow of the oxidizer
through the system, safety measures that need to be taken, and methods for accurately testing the
rocket. Past ideas will be intertwined with new ideas in order to further explore the potential of
hybrid rockets.
3. BASIS OF DESIGN
Table 4: Design Basis
SEC F09-26-REIGNITE STANDARDS
Request for Proposal
SEC RFP Project Description
SEC RFP Design Report Deliverables Checklist
SEC Policies and Procedure Manual
Proposal for Project #F09-26REIGNITE
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22-Sep-09
22-Sep-09
22-Sep-09
22-Sep-09
19-Nov-09
F09-26-REIGNITE
4. PROJECT DESCRIPTION
Hybrid rockets have become increasingly popular due to their safety, regulation of thrust
capabilities, and the ability to stop and start ignition during flight. However, exploration into
these rockets still needs to be done to completely harness these capabilities. This project seeks to
design and test a small, static, hybrid rocket motor. The rocket system will require the use of
nitrous oxide as the fuel oxidizer and a propane ignition system in order for the fuel to be ignited
and then reignited after a period of time. The rocket’s thrust must also be controlled. Testing of
a rocket system is very important to the design process.
The diagram below shows the five main components involved in hybrid rocket system
design. Each of these components is very general and can be broken down further. The gas
system will deal with the flow of liquid or gaseous fuels and oxidizers from their respective
storage tanks into the combustion chamber. Combustion will involve the thermodynamic and
heat transfer properties of the fuels as they interact and burn. The rocket motor body design will
also incorporate heat transfer properties to ensure that the casing will not fail. Testing and
measurements can be broken up into heat and thrust measurements.
GAS SYSTEM
FUELS &
OXIDIZERS
SAFETY
HEAT
TRANSFER
HYBRID ROCKET
SYSTEM
COMBUSTION
ROCKET CASING
TESTING &
MEASUREMENTS
THERMODYNAMICS &
HEAT TRANSFER
HEAT
MEASUREMENTS
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THRUST
MEASUREMENTS
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5. SCOPE OF WORK
5.1 DELIVERABLES

Literature Review

Technical description of entire system including subsystems

Engineering drawings of subsystems

List of materials

System Specifications

Data acquired during testing of rocket system

Technical analysis and corresponding solutions

Cost analysis

Work schedule (planned and actual)
5.2 DESIGN AND TESTING ACTIVITIES

Select materials, design, and fabricate rocket motor casing

Select an appropriate solid fuel grain to use with nitrous oxide oxidizer

Design and assemble nitrous oxide and propane storage and distribution subsystem

Assemble components and test apparatus

Acquire temperature and thrust measurement data from testing
o Thermocouples will be used to find temperature readings of the rocket casing
and the gases exiting the rocket. These will be analyzed to ensure that the
casing is not in danger of melting or deforming and flame temperatures can be
used to calculate thrust.
o Thrust will be measured by mounting the rocket on track so the engine will
move horizontally. A spring will be attached to the rocket. The force to
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stretch the spring (thrust) can be calculated by measuring the spring’s
deflection.
5.3 SPECIFICATIONS

Casing Dimensions
o Outer Diameter – 4”
o Inner Diameter – 3”
o Length – 9”

Casing Materials: Stainless steel with a graphite inner liner

Possible Solid Fuels: Polyvinyl Chloride, Paraffin Wax, or an equivalent

Oxidizer: Nitrous Oxide

Liquid Fuel for Ignition: Propane

Thrust Capabilities: Engine will be operated at a constant, measureable thrust.
The thrust will then be increased by 10%. This will exhibit our goal to control
thrust.
6. SUBSYSTEM S DESCRIPTION
6.1 COMBUSTION
The combustion subsystem will interface thermochemistry, combustion kinetics,
combustion flame characteristics, and solid state diffusion principles to effectively control the
combustion process occurring in the hybrid rocket motor. The REIGNITE project entails a
controllable ignition system which must shut off and on as desired, while still possessing the
ability to control thrust. Select fuels and oxidizers must be chosen in accord with acceptable fuel
regression rates such that a robust combustion flame can be achieved. Important considerations
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to evaluate would be achievable air-fuel ratios, flame travel in the combustion chamber, exhaust
velocities, and system temperatures experienced as a result of the combustion process.
6.2 HEAT TRANSFER
The heat transfer system will account for the heat transfer effects induced on the
operating components as a result of the combustion process. Calculating the energy generated by
the combustion of the propane (C3H8) and nitrous oxide (N2O) will allow important heat rate
calculations to be made such that the heat flux experienced through the cylinder can be
established, as well as the calculated temperature at desired locations throughout the cylinder to
ensure that material limits are not exceeded. Also, using thermocouples at various points along
the rocket motor will allow temperatures to be directly measured so that state points can be
established in accord with the necessary parameters to calculate rocket motor thrust.
6.3 FLUIDS/GAS SYSTEMS
The fluid subsystem aims to accurately and satisfactorily calculate and predict the
miscibility of the incoming propane (C3H8) and nitrous oxide (N2O) mixture at various operating
pressures and flow rates. Using continuity and momentum principles, orifice flow opening
dimensions can be determined to allow volumetric and mass flow rate calculations to be made in
order to provide appropriate mass balances for combustion and thermodynamic calculations
which need to be made to determine the thrust produced by the rocket motor.
6.4 Thermodynamics
The thermodynamic subsystem will incorporate combustion, heat transfer, and fluid
subsystems to incorporate enthalpy, entropy, internal energy, pressure, and temperature at
Page | 20
F09-26-REIGNITE
measured point into the prescribed calculation methodology such that exhaust velocities can be
established. Determining these parameters will also allow a complete thermodynamic analysis of
the operating system to be formulated which will enable state points, and system characteristics
to be evaluated in accord with the fundamental laws of thermodynamics.
6.5 SAFETY
The safety subsystem will insure that the pressures experienced in the combustion
chamber do not exceed the pressure limits of the pressure vessel. Also, a barrier system which
surrounds the test stand is to be designed in order to contain the components of the rocket in case
of failure. Calculations must also be devised to ensure that operating conditions are within
acceptable levels with respect to the operating temperatures and pressures of the components to
insure that the integrity of the rocket motor is maintained. The safety subsystem also has the
responsibility to oversee that all operations are in accord with prescribed safety standards.
6.6 TESTING
The measurement subsystem will integrate a measurement apparatus composed of a
sliding rack and spring to measure the thrust produced by the hybrid rocket motor. The motor
will be attached to the sliding rack, and will exert a force on the spring in doing so. Knowing the
spring constant of the chosen spring will allow thrust to be measured according to the following
relation:
Equation 6:
Where; F=the force exerted on the spring
k=spring constant
x=displacement of the spring
Page | 21
F=-kx
F09-26-REIGNITE
It will be important to seamlessly include the thrust measurement rack with the test stand and
rocket motor, so that system functionality and capability are not compromised in doing so.
Temperature data will also be acquired during testing. Air and exhaust temperatures will
be measured at both the inlet and outlet of the rocket engine in order to determine thermal
properties. After finding the state points, calculations can be done to determine the thrust
produced by the rocket. The outside temperature of the rocket engine casing will also be
monitored throughout testing to ensure that the casing does not melt or deform. Thermocouples
will be used to measure temperature.
Nitrous
Oxide Tank
Propane
Tank
Combustion Chamber
Temperature
Measurements
With Solid Fuel Grain
Thrust
Measurements
The diagram above shows the flow of nitrous oxide and propane from their respective tanks into
the combustion chamber where they combine with solid fuel and burns. From these processes
we will measure the temperatures of the gases exiting the rocket and the thrust resulting from
combustion.
7. PRICING
Team 26 working on the REIGNITE Project, as part of the Saluki Engineering Company,
hereby offers to perform the work, as defined in this proposal, for a cost-plus-fixed-fee price of
four hundred sixty seven dollars and seventy-five cents ($467.75).
Page | 22
F09-26-REIGNITE
Table 5: Project Costs
Source
Comments
1
1
1
1
4
Price
($)
186.43
12.99
176.73
150
8.18
www.mcmaster.com
www.mcmaster.com
www.mcmaster.com
www.mcmaster.com
www.mcmaster.com
Donated
Sourced
Donated
Sourced
2
107.38
www.mcmaster.com
1
32.16
www.mcmaster.com
1
2
11.3
90.89
www.mcmaster.com
www.mcmaster.com
Braided Stainless Line
10ft
24.95
11
Nitrous Oxide Tank
1
200
12
AN Fittings
15
15
13
Propane Tank
1
50
14
Paraffin Wax
1lb.
3.65
15
Universal
Thermocouple
4
5.59
Item
Description
Quantity
1
2
3
4
5
8
9
Stainless Steel Cylinder
Stainless Steel Disc
Graphite round
Test Stand - Steel table
Ball Valve
Gas Pressure
Regulators
Stainless Stock for
Nozzle
Test Spring
Ball Bearing Slider
10
6
7
Total
Total with Donations
www.summitracing.com
Sourced
Sourced
www.summitracing.com
www.summitracing.com
www.idealtruevalue.com
Sourced
Sourced
www.amazon.com
1043.09
467.75
As an addendum to the total cost with donations, resources such as gas pressure
regulators and thermocouple measurement devices can be sourced from the available Southern
Illinois University – Carbondale facilities which utilize this standard equipment.
In addition the REIGNITE team would like to thank Dr. Dale Wittmer for donating the
graphite to be used in the combustion chamber, and Tim Attig for providing the stainless steel
housing to be used as the combustion chamber. These donations help to greatly keep the cost of
this project to a minimum so that the completion of this project can come to fruition.
Page | 23
F09-26-REIGNITE
8. VALIDITY STATEMENT
Saluki Engineering Company will keep certain people available solely for this project who
are well-qualified to do the work while this offer is pending. Saluki Engineering Company
reserves the right to review the content of this proposal thirty (30) days from the date of
submittal if no work has been awarded. After this time, modifications may be made to the
proposal in order keep the proposal valid and up to date. If Boeing is unable to make a decision
within thirty (30) days of the proposal submittal, Saluki Engineering Company will be willing to
discuss any actions needed to be taken for a successful contract closing.
9. PROJECT ORGANIZATION CHART
Figure 10: Organization Chart
Page | 24
F09-26-REIGNITE
10. PROJECT TIMELINE
18Jan
Activity
25Jan
1Feb
8-Feb
15-Feb
Verify Specs
Design
Subsystems
Calculations
Order Parts
Build
Subsystems
Final Assembly
Testing
Written
Report/Docs
Finalize
Reports
Design
Reviews Orals
Progress Report
Design Report
Poster
As
bid:
Activity:
Milestone:
Page | 25
As
worked:
Activity:
Milestone:
22Feb
1Mar
15Mar
22Mar
29Mar
5Apr
12Apr
19Apr
26Apr
3May
10May
F09-26-REIGNITE
11. ACTION ITEM LIST (AIL)
Activity
Responsibility
of:
Assigned
Due
Extended
Date
Status
1
Verify Specifications
RV, JM
1/18/2010
1/27/2010
-
0%
2
ALL
1/18/2010
2/24/2010
-
0%
RV
1/21/2010
1/27/2010
-
0%
4
Perform Calculations
Finalize meeting arrangements with
FTA
Update Norms and Expectations
JP
1/21/2010
1/27/2010
-
0%
5
Design Subsystems
ALL
1/21/2010
2/24/2010
-
0%
6
Complete Team Memo
RV
1/25/2010
2/1/2010
-
0%
7
Order Parts
RV, JM
1/25/2010
2/10/2010
-
0%
8
Design Reviews
DM, RA
1/25/2010
2/8/2010
-
0%
#
3
9
Build Subsystems
ALL
2/8/2010
2/29/2010
-
0%
10
Written Progress Reports
ALL
2/22/2010
3/1/2010
-
0%
11
Final Assembly
ALL
2/22/2010
3/6/2010
-
0%
Page | 26
Comments
F09-26-REIGNITE
12. CONCLUSION
Team # 26: REIGNITE would like to thank Boeing for the opportunity to bid on their project
requesting for the design and testing of a small hybrid rocket. The team will design and build a
static hybrid rocket engine capable of thrust control and reignition. The rocket’s means of
combustion will consist of a solid fuel grain, nitrous oxide as an oxidizer, and propane as fuel
source for ignition and reignition. All design, testing, and analysis will be completed in 16
weeks and will cost less than $500.00. For any questions please contact:
Ryan Vojtech, Project Manager
773-550-7926
vojtech@siu.edu
Page | 27
F09-26-REIGNITE
13. APPENDIX A: PERSONAL RESUMES
Ryan Vojtech
vojtech@siu.edu
Permanent Address:
Address:
5205 S. Nottingham
308
Chicago, IL 60638
62901
(773) 550-7926
College
355 Neely Drive, Allen 1
Carbondale, IL
(773) 550-7926
OBJECTIVE: To attend a graduate program in the Mechanical Engineering field during Fall of 2010.
SUMMARY:
● Conducted research and development work with biodiesel, optical diagnostics, and cold combustion
techniques at Argonne National Laboratory.
● Worked at International Truck and Engine to develop solutions to problems in production vehicles
through research and development.
● Collaborated with the Kawasaki Motorcycle Company to have two brand new ZX600 motorcycles
donated for use in our Formula SAE program.
EDUCATION:
Bachelor of Science in Mechanical Engineering, May 2010
Minor in Mathematics, May 2010
G.P.A : 3.848/4.0
Relevant Coursework
● Thermodynamics
● Heat Transfer
● Fluid Mechanics
● Differential Equations
● Calculus
● Numerical Methods
● Mechanics of Materials ● Chemistry
● Machine Design
EXPERIENCE:
Navistar Engine Group
2008
● Worked as an intern in the cooling system department for International Truck & Engine
SIU College of Engineering
2009
● Provide supplemental instruction for various levels college of mathematics
Argonne National Laboratory
2009
● Research and development with biodiesel, optical diagnostics, and cold combustion
techniques
SKILLS:
● Microsoft Office (Excel, PowerPoint, & Word)
● LabView
● Mechanically inclined (aptitude with tools, lathe and mill machining, and welding)
HONORS:
● College of Engineering Dean’s List
● AISIN Engineering Scholarship
ACTIVITIES:
● Society of Automotive Engineers
Page | 28
F09-26-REIGNITE
● Formula SAE Race Team
● American Society of Mechanical Engineers – Internal Combustion Engines Division
RESEARCH WORK:
Determining Specific NOx Engine Emissions When Using Oxygenated Fuels and Exhaust Gas
Recirculation in Compression Ignition Engines. RYAN C. VOJTECH (Southern Illinois University,
Carbondale, IL, 62901) STEPHEN A. CIATTI, SWAMINATHAN SUBRAMANIAN (Argonne National
Laboratory, Argonne, IL, 60439).
Page | 29
F09-26-REIGNITE
Ryan E. Affara
Cell: (630) 639-7262
Email: ryaffara@siu.edu
Local Address:
713 West College Street
Carbondale, IL 62901
Permanent Address:
840 Cleburne Rd.
Bartlett, IL 60103
OBJECTIVE
An entry level position in an engineering industry which would allow me to develop my skills
and contribute to organizational goals.
EDUCATION
Bachelor of Science in Mechanical Engineering (Dec., 2010)
Southern Illinois University-Carbondale, IL
Major GPA: 3.3 / 4.0
Overall GPA: 3.2 / 4.0
Relevant Coursework: Machine Design, Thermodynamics, Fluid Mechanics, Mechanical
Analysis.
SKILLS
Well experienced with AutoCAD, Interpreting constructional blueprints,
Microsoft Office: Word, Power Point, Excel
EXPERIENCE
2004-2009 Structural Technologies Inc.
Bloomingdale, IL
■ Drew detailed elevation, plan view, and construction detail drawings of buildings and roofs.
■ Measured and evaluated construction elements for various structures.
■ Inspected masonry, balconies, and areas of reconstruction.
■ Organized project summary sheets, this includes work details, bill of materials
and contractor construction and installation notes.
Honors / Awards
SIU Engineering and Technology Scholarship
Fall 2006 - Spring 2007
Dean’s List
Spring 2009
ACTIVITIES
American Society of Mechanical Engineers (ASME) Fall 2007 - Present
P.R. Officer
Fall 2007 - Spring 2008
Responsibilities: publicizing events and meetings, design and post flyers
Senior Design Project-Controllable Ignition
Fall 2009
Page | 30
F09-26-REIGNITE
Dustin Mennenga
dm32@siu.edu
Permanent Address:
2370 CR 1800 E
Urbana, IL 61802
217-643-6287
College Address:
1101 E Grand Ave
Apartment P3
Carbondale, IL 62901
217-979-7714
OBJECTIVE: Entry-level Mechanical Engineering position.
SUMMARY of QUALIFICATIONS
Outgoing, dedicated worker able to communicate well with others
 Experienced team leader ready for a new and challenging opportunity
 Achieved Dean’s List status
EDUCATION
 Bachelor of Science degree in Mechanical Engineering, projected May 2010
 Attending Southern Illinois University, Carbondale, IL
 Current Cumulative G. P. A.: 3.6/4.0
Relevant Coursework (Completed)
- AutoCAD, Autodesk Inventor - Dynamics
- C++
Thermodynamics
- Mechanical Analysis & Design
- Heat Transfer - Fluid Mechanics
Mechanics of Materials
EXPERIENCE
Engineering Intern (Project Management)
June 2009 – August
2009
Kraft Foods Global, Inc., Springfield, MO
 Learned process of executing a project in a large manufacturing setting
 Engineered 2D designs, performed cost estimates, scheduled meetings, requested and
reviewed quotes, purchased equipment, planned installation schedules, worked with
contractors to fulfill project scope, updated cash flow, performed checkout procedure, and
executed startup
 Was project manager for $100M project, researched machinery, selected vendor, scheduled
meetings with vendor, maintenance, production, and project engineers for Q&A, created
requisition, updated cash flow/forecasted, and set up installation plan
Engineering Intern
June 2008 – August
2008
Kraft Foods Global, Inc., Springfield, MO
 Learned a great deal about the food processing industry and how it functions
 Was presented a problem, observed functions of machinery and operators, collected a large
data set, performed a statistical analysis over the data collected and put together a
presentation for upper management including why problem is there and possible solutions
Waiter
July 2008 – August
2008
Steak n’ Shake, Springfield, MO
 Improved communication skills while working in a fast paced environment
 Prioritized multiple tasks immediately in order to satisfy both the customers and co-workers
Construction Worker
May 2006 – May 2008
Wendell Wolken Construction, Urbana, IL
Page | 31
F09-26-REIGNITE

Demonstrated ability to work cooperatively (roofing or doing carpentry in a group of 2-6
efficiently)
 Gained experience working with various equipment (levelers, T-squares, nail guns, boom lift)
Field Worker
May 2005 – August
2005
Monsanto (DeKalb Genetics Corporation), Thomasboro, IL
 Revealed work ethic and dedication to company (worked overtime when needed and worked
through harsh weather conditions outdoors)
 Performed tasks such as pollinating, detasseling, taking samples, and counting corn for
research
 Worked cooperatively in groups of 5-20 people
HONORS / AWARDS
 Freese Scholarship, Aisin Manufacturing Scholarship
 Dean’s List and SJO High School Honor Roll (all 4 years)
 Defensive Leadership Award (St. Joseph-Ogden, Illinois, High School Football) -- State
Playoffs
 Spanish Club (all 4 years); Varsity Letters in Wrestling and Track
ACTIVITIES
 Industry Representative for the American Society of Mechanical Engineers in charge of
corporate recruitment
 Attended Leadership Conference in Madison, WI, representing SIUC ASME, Fall 2007
 Intramural flag football; kickboxing; Intramural basketball; Katrina Relief Volunteer Biloxi,
Dec. 2005
 Volunteered at Living Word Fellowship Church as sound man for youth band (4 years)
Page | 32
F09-26-REIGNITE
JEREMY W. MOYER
Home:
108 E. Locust St.
Watseka, Illinois 60970
(815) 432-3706
School:
Bldg. 5 Apt. 303C
900 E. Park St.
Carbondale, IL 62901
Cell: (815)383-2113
jeremywm@siu.edu
OBJECTIVE
To pursue an internship that incorporates mechanical engineering in a field that allows me to work in
teams and gain further knowledge through hands on experiences.
EDUCATION
Southern Illinois University-Carbondale
Carbondale, Illinois
Senior
August 2006 – Present
GPA- (through Spring 2009) 3.928/4.0
Relevant Course Work- (Electives and Design Classes Taken) Energy in Society, Introduction to
Nanotechnology, Applied Fluid Mechanics for Mechanical Engineers, Machine Design I, Mechanical
Analysis and Design (Courses planned to be completed Spring 2010) Senior Design
EXPERIENCE
Pence Oil Company
Watseka, Illinois
Attendant, Cashier, Office Assistant
July 2001 – August 2008
SIUC College of Engineering
Peer Mentor, Supplemental Instructor
August 2007 – Present
 Help freshman and sophomore students adjust to college life
 Help Pre-Calculus students complete in-class assignments
United States Public Health Service
Engineering Junior Co-Step Bemidji Area IHS
May 2009-August 2009
 Worked for Office of Environmental Health and Engineering
 Reviewed and edited Energy Audits for hospitals and clinics
 Arranged NEPA checklists and an Environmental Assessment for ARRA projects
 Viewed and learned to read HVAC and building schematics.
 Developed Project Summary, Scopes of Services, and Requests for Proposal Documents for
future construction projects.
EXTRA-CURRICULARS
College-American Society of Mechanical Engineers, Tau Beta Pi
Awards and Honors
Dean’s List for six semesters, Alpha Lambda Delta Honor Society, Tau Beta Pi
SKILLS
Computer experience with Microsoft Word, Excel, Power Point, and some use of Inventor, money
management, creative, problem solving, working in groups or teams
REFERENCES
Dr. John W. Nicklow
Todd M. Scofield, P.E.
Associate Dean
Director, DFM, OEHE
College of Engineering
Bemidji Area HIS
(618)453-4321
(218)444-0531
Page | 33
Mike Anderson
Facility Manager
White Earth Health Cntr.
(218)983-6318
F09-26-REIGNITE
Jack Palmieri
JackP35@siu.edu
Permanent Address:
162 East Schick Road
55
Bloomingdale, IL 60108
630-893-4152
College Address:
905 East Park Street, Apt.
Carbondale, IL 62901
630-346-5282
OBJECTIVE: To obtain an internship with your company for the summer (May-Aug) of 2010.
SUMMARY
 Achieved Dean’s List status every semester while being active on the SAE Formula 1 Team
 Member of Golden Key and Alpha Lambda Delta honor societies
 Maintained a 3.6/4.0 G.P.A. while working 15 hours a week
EDUCATION
Bachelor of Science in Mechanical Engineering, minor in Mathematics December 2010
Southern Illinois University, Carbondale, IL 62901
G.P.A. 3.6/4.0
Relevant Completed Coursework
 Heat Transfer
● C++
● Dynamics ● Thermodynamics I and II
 Intro to CAD
● Statics
● Fluids
● Mechanics of Materials
EXPERIENCE
Student Worker, Southern Illinois University- Carbondale, IL
January 2008Present
 Calculus I and II supplemental instructor
 Grader for the Department of Mathematics
Painter’s Apprentice, Village Auto Body- Schiller Park, IL
June 2004-August 2007
 Prepped, dry sanded, and wet sanded various body panels
 Detailed, changed fluids, and installed parts on customer’s vehicles
SKILLS
 Microsoft Office (Word, Powerpoint, Excel)
 AutoCAD
 Autodesk Inventor
 Knowledge of engines and drivetrains
HONORS / ACHIEVEMENTS
 Dean’s List: Fall 2006, Spring 2007, Fall 2007, Spring 2008, Fall 2008, Spring 2009
 Roffmann Engineering Scholarship award winner
 Member Golden Key- international honor society
 Member Alpha Lambda Delta- national freshman honor society
ACTIVITIES
 SAE Formula One Team: Fall 2006-Present
 American Society of Mechanical Engineers: Fall 2006-Present
 Private tutor for local high school and middle school students: Spring 2008-Present
 Improving performance/appearance on family and friends cars in spare time
Page | 34
F09-26-REIGNITE
Joshua D. Snead
jsnead@siu.edu
1114 West St. Louis St.
Nashville, IL 62263
618-781-8947
609 East Campus Drive, Apt. 802
Carbondale, IL 62091
618-327-6674
OBJECTIVE: To obtain a job after graduation in the summer of 2010.
SUMMARY
 Obtained the Provost Scholarship by scoring 31 on the ACT and ranking 1st in my class
 Achieved Deans List Status Every Semester while involved in extracurricular activities
EDUCATION
Bachelor of Science in Mechanical Engineering, May 2010
Southern Illinois University, Carbondale, IL 62901
G.P.A.: 3.91 / 4.00
Relevant Coursework
* Thermodynamics
* Physics
* Dynamics
* Material Science
* C++
* CAD
EXPERIENCE
Externship with Advanced Technology Services, Inc. March 9, 2009 – March 13, 2009
 Learn what a mechanical engineer does at the Caterpillar Tech Center in Peoria
 Learn about diesel engines and how to run tests to improve them.
Intramural Sports Referee and Supervisor
September 2008– Present
 Enforce the rules and help students to enjoy their experience playing intramurals
 Oversee the overall running of sporting events and help teach new referees
SKILLS




AutoCAD
Inventor
C++
Microsoft Office
HONORS / AWARDS
 Provost Scholarship, 2007, 2008
 Alpha Lambda Delta, National Honor Society 2008
 Tau Beta Pi, Engineering Honor Society 2009
ACTIVITIES
 Member ASME, Southern Illinois University Carbondale, 2007, 2008, 2009
 Intramural Sports: Flag Football, Basketball, Softball, Volleyball, 2007, 2008, 2009
REFERENCES
 Available upon request
Page | 35
F09-26-REIGNITE
14.APPENDIX B: PRELIMINARY DRAWINGS
Figure 9: Test Stand with Rocket and Fuel Tanks
Figure 10: Hybrid Rocket
Page | 36
F09-26-REIGNITE
Figure 13: Rocket/Nozzle View
Figure 14: Fuel Lines Entering Rocket
Page | 37
F09-26-REIGNITE
15.APPENDIX C: REFERENCES
[1] "EAc." Hybrid Rockets - eAc. Web. 17 Oct. 2009.
<http://www.hybrids.com/about.html>.
[2] "EAc." Hybrid Rockets - eAc. Web. 17 Oct. 2009.
<http://www.hybrids.com/hyperionI.html>.
[3] "EAc." Hybrid Rockets - eAc. Web. 17 Oct. 2009.
<http://www.hybrids.com/hyperion.html>.
[4] "Hyperion II Testing Picture." Hybrid Rockets - eAc. Web. 17 Oct. 2009.
<http://www.hybrids.com/hyperion.html>.
[5] HyperTEK - The Easiest Access of Them All. Web. 17 Oct. 2009.
<http://www.hypertekhybrids.com>.
[6] "!" HyperTEK - The Easiest Access of Them All. Web. 17 Oct. 2009.
<http://www.hypertekhybrids.com/products.html>.
[7] "EAc." Hybrid Rockets - eAc. Web. 17 Oct. 2009.
<http://www.hybrids.com/hypertek.html>.
[8] "Hypertek Rocket Rendering" Web. 17 Oct. 2009.
<http://www.hypertekhybrids.com/gallery/compgsea01.jpg>.
[9] Heywood, John B. Internal combustion engine fundamentals. New York: McGraw-Hill,
1988. Print.
[10] Callister, William D. Materials science and engineering an introduction. Hoboken, NJ:
John Wiley & Sons, 2006. Print.
[11] Geatrix, David R. "Transient Solid-Propellant Burning Rate Model." Proc. Of
AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Sacramento, CA.
2006. Print.
[12] Bradford, Michael D., Roy J. Kniffen Jr., and Bevin C. McKinney. Hybrid rocket
combustion enhancement. Patent 5582001. Print.
[13] Rajan, Suri. "Solid Fuels." Telephone interview. 16 Oct. 2009.
[14] Strand, H.D., and R. Ray. "Hybrid Rocket Combustion Study." California Institute of
Technology. Web.
[15] Incropera, Frank P., David P. DeWitt, Theodore L. Bergman, and Adrienne S. Lavine.
Introduction to Heat Transfer. 5th ed. New York: Wiley, 2006. Print.
Page | 38
F09-26-REIGNITE
[16] Jacobson, Michael D. Multi-ignition controllable solid-propellant gas generator.
Patent 6250072. 26 June 2001. Print.
[17] "Nitrous oxide, N2O, Physical properties, safety, MSDS, enthalpy, material compatibility,
gas liquid equilibrium, density, viscosity, flammability, transport properties." Physical
properties of gases, safety, MSDS, enthalpy, material compatibility, gas liquid
equilibrium, density, viscosity, flammability, transport properties. Web. 17 Oct. 2009.
<http://encyclopedia.airliquide.com/encyclopedia.asp?GasID=55>.
[18] "Propane, C3H8, Physical properties, safety, MSDS, enthalpy, material compatibility, gas
liquid equilibrium, density, viscosity, flammability, transport properties." Physical
properties of gases, safety, MSDS, enthalpy, material compatibility, gas liquid
equilibrium, density, viscosity, flammability, transport properties. Web. 17 Oct. 2009.
<http://encyclopedia.airliquide.com/encyclopedia.asp?GasID=53>.
[19] "Hybrid Rocket Motor." Oct. 2006. Web. 13 Oct. 2009.
<http://www.tsinghua.edu.cn/docsn/lxx/mainpage/a/Web/index_files/Page349.htm>.
[20] "Hybrid Rocket Propulsion for Space Launch." Stanford Aero/Astro Department. 9 May
2008. Web. 20 Oct. 2009.
<http://aa.stanford.edu/aeroastro/50th/presentations/Karabeyoglu.pdf>.
[21] Crowe, Clayton T., Donald F. Elger, and John A. Roberson. Engineering Fluid Mechanics.
8th ed. John Wiley & Sons, Inc., 2005. Print.
[22] Shanks, Robert, and M. Keith Hudson. "A Labscale Hybrid Rocket Motor for
Instrumentation Studies." Journal of Pyrotechnics 11 (2000). Web. 15 Oct. 2009.
<http://users.rowan.edu/~marchese/rockets05/paper1.pdf>.
[23] "Hybrid Rocket Science - www.ukrocketman.com." Ukrocketman.com - home. Web. 17
Oct. 2009. <http://www.ukrocketman.com/rocketry/hybridscience.shtml>.
[24] Physical properties of gases, safety, MSDS, enthalpy, material compatibility, gas liquid
equilibrium, density, viscosity, flammability, transport properties. Web. 17 Oct. 2009.
<http://encyclopedia.airliquide.com/encyclopedia.asp>.
[25] "Propane@Everything2.com." Welcome to Everything@Everything2.com. Web. 17 Oct.
2009. <http://everything2.com/title/propane>.
[26] "Noise Levels." Quiet Solution. Web. 17 Oct. 2009.
<www.quietsolution.com/Noise_levels.pdf>.
[27] Sutton, George Paul. Rocket propulsion elements an introduction to the engineering of
rockets. New York: Wiley, 1986. Print.
[28] Eilers, Shannon D., and Stephen A. Whitmore. "Correlation of Hybrid Rocket Propellant
Regression Measurements with Enthalpy-Balance Model Predictions." Journal of
Spacecraft and Rockets 45.5 (2008): 1010-020. Print.
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