NASA RFP

i
Tarleton Aeronautical Team
Tarleton State University
2012 – 2013 NASA University Student Launch Initiative Proposal
Science Mission Directorate Payload Option
August 31, 2012

Executive Summary
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The Tarleton Aeronautical Team is pleased to submit this proposal in response to the
2012-2013 University Student Launch Initiative (USLI).
University Background
Tarleton State University is a public university located near Dallas-Fort Worth. The
university was founded in 1899 and became a part of the Texas A&M System in 1917.
Tarleton is one of the state’s fastest growing institutions and currently has the second
largest enrollment in the Texas A&M System. Tarleton State University has a diverse
student population, representing 49 states and 34 countries. Students have the
opportunity to choose from 85 undergraduate and graduate degree programs.
Our Proposal
To facilitate review of our proposal, we have mirrored the National Aeronautics and Space
Administration (NASA) Student Launch Project Statement of Work (SOW) so that our
numbering system corresponds to those in the SOW. We believe that we have been
responsive to each requirement and have documented our analyses in the appropriate
sections. Through the advisement of NASA engineers at the Advance Rocketry
Workshop on July 18-21, we have included as much detail as possible. We present a
baseline design that we plan to refine over the next several months through additional
testing, evaluation and analysis.
Our Team
We are an interdisciplinary team comprised
from six different disciplines.
The majority of the team competed in the
2012 Texas CanSat competition in
preparation for USLI. CanSat is an
international design-build-launch
competition sponsored by The American
Astronautical Society (AAS), American
Institute of Aeronautics and Astronautics
(AIAA), NASA, and Naval Research
Laboratory (NRL). The Tarleton Aeronautical Team was the only Texas team participating
in the 2012 International CanSat competition, placing 6th
of 41 teams. Our competition
included institutions such as Virginia Tech, the University of Minnesota, the University of
Michigan, Embry Riddle Aeronautical University, as well as teams from Canada, Turkey,
Columbia, and India.
Figure 1 – 2012 CanSat Payload

Executive Summary
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We believe this competition prepared us well
for the NASA USLI Project. It involved the
end-to-end life cycle of a complex
engineering project including Preliminary
Design Review (PDR), Critical Design
Review (CDR), post-mission summary, and
debrief. Building on the experience from the
2012 CanSat competition, we have
assembled a team whom we are confident
will perform well at the NASA USLI
competition.
Our Funding
We have secured a significant portion of the funding required for this project through a
wide range of University organizations and other community support functions. We have
$11,500 committed from the Tarleton President’s Circle, the Provost’s Office, the Dean of
the College of Science, and the Tarleton Foundation. The Office of Student Research
has also committed $8,000-$12,000. Additional sources necessary to fund the project
have been identified. We are pursuing USLI Science Mission Directorate (SMD) funding.
Figure 3 – Initial USLI Funding
Our Facilities
The Team will have unlimited access to a 5,000 square-foot fabrication and test launch
facility off-campus. The team will also have scheduled access to a 600 acre high-altitude
test launch and building facility owned by Team Mentor Pat Gordzelik; he is Level three
Figure 2 – Sixth Place CANSAT
Team

Executive Summary
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TRA certified and Vice President of the Tripoli Rocketry Association. His facility features
5,280-foot Federal Aviation Administration (FAA) flight waivers and access to static motor
test stands. On campus, all team members will have access to the 900-square-foot
rocketry lab in the Mathematics building, as well as facilities in the Science and
Engineering buildings.
The on-campus facilities offer unlimited access to computers, printers, projectors,
workspace, conference tables, soldering station and circuit fabrication, oscilloscopes,
logic analyzers, regulated power supplies, electronics prototyping equipment, circuit
testing equipment, circuit simulators, teleconference room equipped with a portable
projector, and wireless Internet access.
Safety Plan
We have an experienced team; five members are level 1 NAR certified. These members
will be seeking level 2 National Association of Rocketry (NAR) certification under Pat
Gordzelik, VP of TRA. In addition, you will find a comprehensive safety plan presented in
the Safety Section.
Our Baseline Design
The flight vehicle will total 103 inches in length with a 4-inch body diameter. This is
composed of a nosecone, upper body structure, payload housing structure, and lower
body structure. All sections of the flight vehicle will be made of fiberglass with the
exception of the clear acrylic payload housing where the SMD payload will be stored.
(Reference section: Technical Design 1.a)
The upper body structure will house the main parachute. The lower body structure will
house the drogue parachute and the motor. The nosecone and lower body structure are
designed to separate and deploy the appropriate descent control systems. (Reference
section: Technical Design 1.b)
From the four motors we reviewed, we selected the Cesaroni K1440. We concluded that
the total calculated mass would likely increase, thus decreasing the calculated apogee of
5,515 feet. Additionally, its high thrust to weight ratio will allow the rocket to easily depart
from the launch rail. Trade studies will be conducted to reaffirm this selection throughout
the design process. (Reference section: Technical Design 1.c)
The SMD payload will be mounted to a payload framework within the acrylic payload
housing. This design is intended to allow the UV sensor, Solar Irradiance sensor, and
cameras to function without being externally exposed. (Reference section: Technical
Design 1.d)

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Table of Contents
General Information.…………………….…………………..………………………………… 1
1. Organization…………..…………………………….................................................. 1
2. Adult Educators………………………………………………………………………… 1
3. Safety Officer…………………………………...………………………………………. 1
4. Team Leader…………………………………………………………………………..... 1
5. Team Infrastructure………………..……………………........................................... 2
6. TRA Section…………………………………………….………………………………. 6
Facilities / Equipment……………………………..……………………………………………. 6
1. Facilities……………………………….………….….................................................. 6
2. Computers Equipment……………………………………………............................. 8
3. EIT Accessibility Standards ………………………………………...……….............. 9
Safety…………………………………………………………................................................ 9
1. Safety Plan………………………………………………………….…………………… 9
2. Procedures for NAR/TRA Adherence………………………………………...……… 11
3. Plan for Briefing Students………………………………………………..................... 11
4. Incorporation of All Caution Statements…………………………………………..…. 12
5. Acknowledgement of Regulations…………………………………………….……… 12
6. Rocket Motors ………………………………………………………………………….. 13
7. Safety Statement ……………………………………………………………………… 13
Technical Design …………………………………………..………………………………….. 13
a. General Vehicle Description…………………………….…………………………… 14
b. Recovery System………………………………………..…………………………….. 15
c. Motor……………………..…………………………………………………………....... 24

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Table of Contents Continued:
d. Payload Description ……………………………………..…………………………… 28
e. Requirements……………………………………...………………………………….. 37
f. Challenges and Solutions……………………………………………………………. 43
Educational Engagement ……………………………………………………………………. 43
Project Plan………………………………….………………………………………………… 48
1. Timeline …………………………………………………..…………………………… 48
2. Budget Plan ………………………………………………....................................... 51
3. Funding – Tarleton State University (TSU) and others………………….……….. 53
4. Community Support Plan ……………………………………………...……………. 54
5. Challenges and Solutions …………………………………………………...…….... 54
6. Project Sustainability Plan………………………………..………………………….. 55
Appendix A: Resumes ………………………………………………………....................... 56
Appendix B: EIT Accessibility Standards………………………………………………….. 65
Appendix C: Pre-Launch Checklist ………………………………..….…………….……… 70
Appendix D: Launch Pad Checklist ………………………………………………………… 71
Appendix E: Material Safety Data Sheets …………………………………………………. 72
Appendix F: Risks, Failures, and Hazards……………………………….……………….. 117
Appendix G: NAR High Power Rocket Safety Code…………………..…………………. 122
Appendix H: Federal Aviation Regulations 14 CFR………………………………………. 125
Appendix I:
Bureau of Alcohol, Tobacco, Firearms, and Explosives Rules and Procedures….… 128
Appendix J: Lab Safety…………….………………………………………………………… 137
Appendix K: Hazard Waste Management………….………………………………………. 157

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Table of Contents Continued:
Appendix L: Fire Safety……………………….………………………………….………….. 171
Appendix M: Safety Statement……………………………………………………………… 177
List of Graphics
Figure 1: 2012 CanSat Payload……..…………………………………………………….…… ii
Figure 2: Sixth-Place CanSat Team…………………………………………………………… iii
Figure 3: Initial USLI Funding……………………………………..…………………………… iii
Figure 4: Team Hierarchy…………………………………………………………………….… 2
Figures 5: Team Members…………………...........................……………………………..… 5
Figure 6: Rocket Lab……………………………………………………..……………………… 6
Figure 7: Low-Altitude Test Launch Facility…………………………………………………… 8
Figure 8: Internal Vehicle Presentation ………………………………………………..……. 13
Figure 9: External Vehicle Presentation…………………………….……………………….. 13
Figure 10: Fin Design………………….………………………………….…………………… 15
Figure 11: E-Match Diagram …………………………………..…………………………...… 17
Figure 12: Ejection Staging…………………………………………….……………………… 20
Figure 13: Cesaroni K1440 Thrust Curve…………………………………..……………….. 25
Figure 14: Cesaroni K1850 Thrust Curve………………………..………………………….. 26
Figure 15: Aero-Tech K700 Thrust Curve …………………………………………………... 27
Figure 16: Cesaroni K820 Thrust Curve………………..……………………………….…... 28
Figure 17: Payload Layout…………………………………………………………………….. 29
Figure 18: CAD Rendering of Payload Layout………………….…………………………… 30

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List of Graphics (Cont’d)
Figure 19: Conceptual Wiring Diagram………………………………………………………. 35
Figure 20: Payload Software Flow Chart…………….….…………………………………... 36
Figure 21: Travelling Estimate…………..……………………………………………….…… 47
Figure 22: USLI Dates….................................................................................................. 49
Figure 23: Team Dates…………………………..…….…………………………………….... 50
Figure 24: Launch Day Rocket and Payload……………..…………….…………………… 52
Figure 25: Research and Development……………………………..……………………….. 53
Figure 26: Total Project Budget……………………….……………………………………… 53

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List of Tables
Table 1: Facilities and Equipment………………….……………………………….………. 7
Table 2: Material Safety Summary………………………….………………………………. 9
Table 3: Fin Specifications…………………………………………………….……………. 15
Table 4: Recovery Systems Budget Summary……………………………………………. 22
Table 5: Motor Trade and Selection………………………………………………………… 24
Table 6: Electronic Trade and Selection……………………..…………………………….. 31
Table 7: Technical Design Cost Summary……………………….………………………… 38
Table 8: Lessons and Group Activities……………………………………………………… 45
Table 9: Field Trips and Rocket Day ……………………………………..………………… 45
Table 10: Educational Budget…………………………………..……………………………. 46
Table 11: Educational Engagement Travel Budget………………………………………… 47
Table 12: Tarleton Rocket Day Budget…………………….…………………………….…. 47
Table 13: Tentative Meeting Schedule …………………………..……………………….… 48
Table 14: Propulsion Budget……………………………………………………………….… 51
Table 15: Payload Electronic Components Budget………………………………………... 51

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General Information
1. Organization
Tarleton Aeronautical Team
Tarleton State University
Box T-0470
Stephenville, Texas 76402
DUNS: 801781865
Cage Code: 5RTD4
2. Adult Educators
Dr. Bowen Brawner, Professor
Mathematics Department
brawner@tarleton.edu
Dr. Bryant Wyatt, Department Head
Mathematics Department
wyatt@tarleton.edu
3. Safety Officer
Blake Lohn-Wiley
Graduate Mathematics Student
blake.lohnwiley@gmail.com
4. Team Leader
Dustin Neighbors
Undergraduate Engineering Physics Student
dustywithsparks@gmail.com

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5. Team Infrastructure
The team currently consists of nine team members representing six different majors
from the STEM fields. The complete team will consist of between nine and fifteen
members. The key participants and duties are listed below as well as a team hierarchy.
All resumes can be found in appendix A.
Team Member Duties
Name: Duties:
Dustin Project Manager, Lead Engineer
Jake Lead Engineer, Technical Editor
Billy Electronics Engineer, Chief Draftsman
John Chief Programmer, Simulation Data Analyst
Amber Recovery Systems Engineer, Research
Bert Structural Engineer, Electrical Engineer
Blake Safety Officer, Research
Chelsea Web Design, Draftsman
Lou Educational Outreach Coordinator
Figure 4 – Team Hierarchy

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Team Member Bios
Dustin N. – Team Manager/Chief Engineer
Dustin is currently a sophomore Engineering Physics student at Tarleton State
University. He is soon to be a new father. He formed and led the Tarleton
Aeronautical Team through the 2012 International CanSat Competition in
Abilene, TX, in which the team placed sixth overall. His reason for starting and
continuing in the Tarleton Aeronautical Team is to apply what he is learning in
the classroom to a real world engineering project. Dustin aspires to be a
successful entrepreneur and start his own engineering firm.
Lou F.– Educational Outreach
Lou is a junior biology major working towards his teacher’s certification. He wants
to teach secondary school after graduation with the ability to teach physics,
chemistry, earth science, and biology. He joined the team because he has
always had a great passion for science and mathematics. He hopes to create
new experiences, meet new people, and incorporate real world experiences into
his education while working on this project. He loves small animals and enjoys
participating in outdoor activities.
Jake R. – Lead Engineer
Jake is a graduate Mathematics student with a B.S. in Engineering Physics. He
enjoys playing music, particularly guitar, and is interested in rebuilding and
tinkering with vintage tube amplifiers. He joined the team in hopes to gain
knowledge and experience in aerospace engineering and high powered rocketry.
Jake worked for the Tarleton State University Observatory for 3 years, where he
was involved in photometric analysis of eclipsing binary star systems and
asteroid detection. He is now a graduate assistant for the Mathematics
department while working on his Masters in Mathematics.
Blake L. – Safety Officer,
Blake is a graduate Mathematics student with a B.S. in Mathematics. He enjoys
playing guitar and wakeboarding with friends. He joined the team to further his
pursuit of knowledge and to gain expertise in areas outside of mathematics. The
subject of aerospace engineering and high powered rocketry has always
fascinated him. Blake worked for the Math Department as a tutor in the Math
Clinic for 4 years. Blake plans to complete his M.S. in Mathematics, followed by a
Master’s in aerospace engineering.

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Chelsea K. – Web Design
Chelsea is a junior in Manufacturing Engineering Technology. She recently found
a love for storm chasing. Joining the Tarleton Aeronautical Team this year, she
hopes to gain experience in applying drafting, web managing, mathematics, and
physics to the real world. Chelsea’s background includes experience in website
managing using Cascade for Tarleton’s Keeping It R.E.A.L. program and tutoring
students in mathematics and English. Her future plans are to complete her B.S.
in Manufacturing Engineering Technology, followed by a continued education for
a M.S. in Manufacturing and Quality and Leadership.
Bert H. – Electrical Engineer
Bert is a graduate Mathematics student with a B.S. in Electrical Engineering. He
enjoys playing drums and classical guitar. He joined the team in order to expand
his experience with real-world electronic circuits, particularly with real-time data
acquisition and long-distance data transmission. Bert is a member of IEEE
Robotics and Automation Society and IEEE Computer Society, where he
attended lectures and participates in projects aimed at building his understanding
of robotic kinematics and software development. He is now a graduate assistant
for the Mathematics department while working on his Master’s degree in Applied
Mathematics. Bert plans to complete his M.S. in Mathematics, followed by joining
the Robotics Institute at Carnegie Mellon for a PhD in Robotics Engineering.
Amber D. – Recovery Systems
Amber is a senior double major in physics and mathematics. She is multilingual
and plays the flute. She joined the Tarleton State Aeronautical Team this year
on the USLI project as a way to get hands on experience in rocket design and as
an opportunity to use her education in a real world application. Her experience
includes working as an undergraduate research assistant on two disease
population model optimization projects, as well as research in conducting a
nonparametric regression analysis of CMB angular power spectra. She plans on
getting a PhD in solid state physics and working in industry.

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John P. – Propulsion and Software
John is a senior computer science major. He loves his mother. He joined the
Tarleton Aeronautical Team for an opportunity to apply skills learned in the
classroom to a real world project. His experience includes participating in the
CanSat competition and working as a computer science tutor. He plans on
getting a PhD in computer science and working for NASA.
Billy F. – Electronics Engineer
Billy is a senior in Mathematics with support in Computer Science. He is
sometimes known to eat a Raw Vegetation and Animal Food diet. He joined the
team to apply his education towards gaining real world experience in aeronautics
and to watch rockets disappear into the sky. He participated in the 2012
International CanSat competition in Abilene, TX. Billy hopes to become an
inventor and change the world.
Five team members, pictured below, attended the 2012 NASA Advanced Rocketry
Workshop in Huntsville, Alabama where they received their level 1 NAR certification.
The workshop was a phenomenal learning experience and provided an excellent
introduction to the USLI Competition.
Figure 5 – Team members at the workshop listed from left to right: Blake L., Jake R.,
Dustin N., John P., Lou F.

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6. TRA Section
The TRA section we will be associating with for launches will be West Texas Rocketry
Prefecture number 121, as well as Cloud Busters Prefecture number 34.
Facilities / Equipment
1. Facilities
Throughout the course of this project, the Tarleton Aeronautical Team will have 24/7
access to various saws, routers, hand tools, welders, and an acetylene torch at a 5,000
square-foot test launch facility in Glen Rose, TX owned and supervised by Dr. Bryant
Wyatt. Also off campus, the team will have scheduled access to a 600 acre high-
altitude test launch and building facility owned and supervised by team mentor, Pat
Gordzelik, featuring 5,280-foot FAA flight waivers and access to static motor test
stands. On campus, all team members will have 24/7 access to the 900-square-foot
rocketry lab in the Mathematics building, as well as facilities in the Science building and
Engineering building.
The Mathematics Building offers unlimited access to computers, printers, projectors,
white boards and tables, with the additional availability of a conference table, soldering
station and circuit fabrication tools offered by the team conference room in Room 337.
The Science Building offers access to oscilloscopes, logic analyzers, and regulated
power supplies. The Engineering building offers access to electronics prototyping
equipment, circuit testing equipment, and circuit simulators. The Administration building
offers access to a twenty-person teleconference room equipped with a portable
projector, and wireless Internet access.
Figure 6 – Rocketry Lab

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Table 1 – Facilities and Equipment
Facility
Hours of
Accessibility
Access
Type
Necessary
Individuals
Work Area Equipment
Low-Altitude
Test-Launch
and
Fabrication
Facility
24/7
Off-
Campu
s
Dr. Bryant
Wyatt
800 acres
+ 5,000 ft²
Fabrication
Building
Saws, Routers,
Machining tools,
Welders,
Acetylene torch,
Safety equipment
High-Altitude
Test-Launch
Facility
Scheduled
Off-
Campu
s
Pat
Gordzelik
600 acres
+ 6,000 ft²
Fabrication
Building
5,280-foot FAA
flight waivers,
Static motor test
stands, Safety
equipment
Mathematics
Building-
Rocketry Lab
24/7
On-
Campu
s
Any Team
Member
900 ft²
Computers,
Software,
Printers,
Projectors, Circuit
fabrication tools
Conference table,
Soldering station
Science
Building-
Physics Lab
24/7
On-
Campu
s
Any Team
Member
1,500 ft²
Oscilloscopes,
Logic analyzers,
Regulated power
supplies, Vacuum
chamber
Engineering
Building-
Circuitry Lab
24/7
On-
Campu
s
Any Team
Member
1,800 ft²
Electronics
prototyping
equipment and
software, Circuit
testing
equipment, Circuit
simulators

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Figure 7 – Low-Altitude Test Launch and Fabrication Facility
2. Computer Equipment
The Tarleton Aeronautical Team has access to a wide range of computing equipment.
University desktops, which are available in every campus building, operate on Windows
7 and Linux systems, offer broadband Internet and e-mail access, and provide
AutoDesk Inventor used for CAD design, Conifer Systems Cascade used for Web
development, and Microsoft Word used for document development.
Additional software available to the team includes:
 MATLAB  Maple  AutoCAD Electrical
 Arduino IDE  PCB Express  Solid Works 2010
 RASAero  RockSim  CadSoft Eagle
 NI Multisim  Wolfram Mathematica  AutoDesk Inventor
Professional

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3. EIT Accessibility Standards
The Tarleton Aeronautical Team shall implement the technical standards posed by
Subpart B of the Architectural and Transportation Barriers Compliance Board Electronic
and Information Technology (EIT) Accessibility Standards (36 CFR Part 1194)
(http://ecfr.gpoaccess.gov/cgi/t/text/text-idx?c=ecfr&tpl=/ecfrbrowse/Title36/36cfr
1194_main_02.tpl). Regulations (a) through (l) of §1194.21 (refer to Appendix B.1) on
software applications and operating systems will be met.
The team shall adhere to regulations (a) through (p) of §1194.22 (refer to Appendix B.2)
concerning web-based intranet and internet information and applications.
Regulations (a) through (d) of §1194.26 (refer to Appendix B.3) regarding desktop and
portable computers shall be satisfied.
Safety
1. Safety Plan
Material Safety
The appropriate Materials Safety Data Sheet (MSDS) (Located in Appendix E) shall be
referenced in each instance involving the handling of potentially hazardous materials.
The MSDS will be available at locations where the hazardous materials are used or
stored. All team members shall be knowledgeable of the Material Safety Data Sheet
associated with each hazardous material.
Table 2 – Material Safety Datasheet Summary
Material Prevalence Risks Mitigation
Ammonium
Perchlorate
Found in rocket
motors
Risk of fire,
burns
Keep away from heat,
treat burns normally
Black Powder Found in injection
charges
Risk of fire,
burns
Keep away from heat,
treat burns normally
Epoxy 3M DP420 Found in bonding
parts of fiberglass
together
Skin Irritation,
Risk of Fire
Flush area with water,
Keep away from heat
Paint Used to coat
outside layer of
rocket
Risk of Fire,
Skin Irritation
Flush area with water
Keep away from heat

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Facilities
a. Rocket construction will take place at the Team Test Launch Facility, which provides
access to all the necessary fabrication equipment. The construction of the payload
will take place at the Math Building located on the Tarleton State University Campus.
The team shall conduct their low altitude test launches at the Team Test Launch
Facility. The team shall conduct high altitude test launches at the launch facilities of
Pat Gordzelik, the team mentor.
b. For a team member to enter the above mentioned facilities, they must adhere to the
following guidelines:
 Always ask a well-informed member of the team or the Safety Officer if unsure
about equipment, tools, procedures, or materials.
 Always follow the safety regulations associated with hazardous materials and
federal, local, and state laws.
 Always adhere to the following safety equipment rules:
1 Protective clothing must be worn.
2 Use goggles where appropriate.
3 Use face mask where appropriate.
4 Wear gloves where appropriate.
 Always be aware of your surroundings.
Risk Assessment
Risk assessment includes consideration of relevant risks to the completion of the
project, how likely they are to happen, and their consequences. A risk assessment was
completed for the possible loss of access to facilities. Each area has several risks and
each risk is associated with a number of possible impacts. Techniques for mitigation
have been established. In the event that a problem arises possible actions are
addressed. The Facility Risks to the Completion of the Project Table can be found in
Appendix F.1 on page 117.

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Failure mode analysis was done for the following systems: vehicle, payload, and
recovery. This is structured around three main categories: possible failures, failure
consequences, and mitigations. The Failure Modes Table can be found in Appendix F.2
on page 118.
Hazard analysis was done for use of facilities. This analysis has six elements: risk,
sources, likelihood, consequences, mitigation, and actions. The Hazard Analysis Table
can be found in Appendix F.3 on page 120.
2. Procedures for NAR/TRA adherence
The Tarleton Aeronautical Team will be advised by NAR Level 3 certified Pat Gordzelik.
Mr. Gordzelik will help ensure that all NAR high-powered safety code requirements
(Located in Appendix G) are met. He will be responsible for the purchase, safe storage,
transport, and handling of the rocket motors. He will also be present whenever the
rocket is being launched. Tripoli # 121 West Texas Rocketry will help in assisting with
our launches as well.
3. Plan for briefing students
Prior to the construction of the rocket, a risk assessment and safety meeting will be
conducted to describe proper procedures. The information will be displayed in
PowerPoint format and will contain the following subjects: Federal Aviation Regulations,
NAR/TRA High Power Rocket Safety Code, NFPA 1127 Code for High Power Rocketry,
Risk Assessment, Chemical Safety, Fire Safety, and Lab Safety. A week after the safety
presentation, the Team will be given a test, which they must pass in order to take part in
any aspect related to the rocket.
Prior to every launch, meetings will be conducted that reinforce the material covered in
the risk assessment and safety meeting. Before any rocket can be launched the rocket
must go through a pre-launch and launch pad safety checklist.

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4. Incorporation of all caution statements
A safety binder shall be kept throughout the entirety of the design, construction, and
launch process. Also, a safety checklist shall be maintained at each launch. Caution
statements will be included in all necessary proceedings.
5. Acknowledgement of Regulations
All team members shall be thoroughly briefed on the project risks, NAR high-power
safety code, and the FAA's laws and regulations regarding the use of airspace. Each
team member shall be required to read NAR's Safety Presentation slides. The team
shall have a safety briefing conducted by NAR/TRA personnel before any launch takes
place.
5.1 The team shall be cognizant and abide by all federal, state, and local laws
regarding unmanned rocket launches and motor handling, including the
following regulations and checklists:
5.2 14 CFR 101, Subchapter F, Subpart C: Amateur Rockets (Located in
Appendix H)
5.3 27 CFR Part 55: Commerce in Explosives (Located Appendix I)
5.4 The handling and use of low-explosives (Ammonium Perchlorate Rocket
Motors, APCP) (Located in Appendix E)
5.5 NAR Model Rocket Safety Code (Located in Appendix G)
5.6 Hazardous Waste Management (Located in Appendix K)
5.7 Fire Safety (Located in Appendix L)
5.8 Lab Safety (Located in Appendix J)
5.9 Pre-Launch Checklist (Located in Appendix C)
5.10 Launch Pad Checklist (Located in Appendix D)
6. Rocket Motors
Team mentor, Pat Gordzelik, will be responsible for the purchase, safe storage,
transport, and handling of the rocket motors. He will also supervise all test launches. Mr.
Gordzelik is level three certified with TRA and NAR and is also the vice president of
TRA.

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7. Safety Statement
All team members have participated in a safety presentation and signed the Safety
Statement, Appendix M. The Safety Statement acknowledges that each member will
adhere to the rules and regulations of all relevant governing bodies.
Technical Design
A proposed and detailed approach to our rocket and payload design is shown in figures
8 and 9, which display an internal and external presentation of the proposed vehicle.
The center of pressure is marked accordingly at 83.8 inches from the tip of the
nosecone, while the center of gravity is at 66.5 inches. These measurements,
calculated by Open Rocket software, show that the center of gravity is 4.31 caliber
ahead of the center of pressure; this assures adequate flight stability.
Figure 8 – Internal Presentation of Vehicle
Figure 9 – External Presentation of Vehicle

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a. General Vehicle Description
The rocket body will be 4 inches in diameter. This size was chosen to allow adequate
room for our payload and recovery system electronics. The rocket body will be 8 feet
and 7 inches long, consisting of four main sections: the nosecone (fiberglass), upper
body structure (fiberglass), payload housing structure (acrylic), and the lower body
structure and fins (fiberglass). Fiberglass was chosen for the majority of the vehicle
body due to its high durability, high melting temperature, low cost, and availability. All
fiberglass will be 0.125 inches thick, unless otherwise specified. All sections will be
attached via couplers.
Our nosecone will be a short, blunt, smooth, elliptical shape, and approximately 11
inches in length. This includes a 4-inch shoulder length based on the 4-inch body
diameter, as the nosecone shoulder should be no less than one body diameter in
length. This shape was chosen because the contest requires our rocket to remain
subsonic throughout flight. At less than 0.8 Mach this choice is best. (Page 9 of 2012
Advanced Rocketry Workshop NASA SLP Manual)
The upper body structure is 2 feet in length. This is to ensure adequate room for all
components (Including altimeters, black powder ejection charges, arming switches,
main parachute with accessories, and e-match).
The payload housing structure will be constructed of a clear acrylic cylinder; 4 inches in
diameter and 0.25 inch thick. Both ends will have 4.5 inches of the clear acrylic cylinder
milled down to 0.125 inch thickness; making a shoulder at each end of 3.75 inches
diameter. These shoulders will be used to couple the payload housing structure to both
the upper body structure and the lower body structure. Clear acrylic was chosen for the
payload housing structure due to its strength, light weight, and transparency;
transparent payload housing allows external observation of electronics once installed.
The transparent payload housing structure will allow ultraviolet radiation and solar
irradiance measurements to be taken internally. This will also allow the cameras to
function within the payload housing structure.
The lower body structure is 3 feet in length. This section will be comprised of two
compartments: drogue parachute compartment and motor housing. The drogue
parachute compartment will be one foot in length and sealed apart from the motor
housing by a solid fiberglass disk (0.25 inches) using epoxy. The length was chosen to
provide adequate room for the altimeters, e-match, parachute, and parachute

15
accessories without compromising accessibility. The motor housing will be two feet in
length which was determined by the motor selection.
There will be four fins equally spaced and mounted with epoxy. The fin specifications
and appearance are displayed in Table 3 and Figure 10, respectively.
Table 3 – Fin Specifications
b. Recovery System
In order to increase the chances of a successful recovery by minimization of drift
distance, a dual-stage deployment recovery system will be employed (requirement 2.1).
This recovery system is composed of a drogue parachute and a main parachute. The
main parachute will be located and eject from the top of the upper body structure, just
below the nosecone. In order to minimize both landing radius and terminal velocity, the
main parachute will be released approximately 500 feet from the ground. The drogue
parachute will be located and ejected from the drogue parachute compartment at the
front of the lower body structure, rather than the motor housing compartment at the rear
of the lower body structure (requirement 2.14.2). It will be released when the vehicle is
at apogee. This will ideally occur at 5,280 feet, but no higher than 5,600 feet
(requirements 1.1 and 1.2.3.3). It is imperative that the drogue parachute be deployed
at apogee and no later in order to avoid damage to the rocket body caused by the
jarring that would ensue should the vehicle be in descent upon release.
S Sweep length 4.5 inches
Sweep angle 45 degrees
Height 4.5 inches
Tip chord 1.5 inches
Root chord 7.5 inches
Fin cant Zero degrees
Fin rotation Zero degrees
Figure 10 – Fin Design

16
Many high-powered rocket designs ignite the ejection charges via time-delay elements
in the motor, appropriate timing and redundancy are difficult to achieve by such
methods. In order to eliminate the burden of choosing the right delay and to improve
redundancy, each deployment will be controlled by two altimeters (requirement 2.5).
Two altimeter systems shall be employed, composed of a main altimeter, backup
altimeter, and e-match wiring. The main altimeter will be a Featherweight Raven3 and
the backup will be a PerfectFlite StratoLogger, programmed independently of the
payload and monitored remotely (requirement 2.4). Each altimeter will be housed in a
sealed 4.5-inch compartment below each parachute compartment in the vehicle body
(requirements 2.12, 2.12.1, 2.12.3, and 2.12.4). Each altimeter will have its own
dedicated power supply, a standard 9-volt battery(requirement 2.7). Each altimeter
system shall be mounted vertically on a 0.25-inch-thick, 3.75-inch-wide, 4-inch-tall
fiberglass board. Each board will then be epoxied on either end to a 0.25-inch-thick,
3.75-inch-diameter fiberglass disk. The entire setup will then be bolted to the bulkhead,
in the sealed compartments, below each parachute compartment. One additional
PerfectFlite altimeter will be mounted with the system below the drogue parachute
compartment. This will serve as the scoring altimeter since it has a beeper.
The Featherweight altimeter has been chosen as the main altimeter for its remarkable
versatility. It has full functionality regardless of positioning, has visible and audible
readout of individual channel continuity and battery voltage, allows for user calibration of
the accelerometer rather than presets, can record up to eight minutes of high-rate data
plus an additional 45 minutes per flight, and has a downloadable interface program
which is easy to read.
The PerfectFlite altimeter has been chosen as a backup altimeter for its high level of
reliability. False triggering has been eliminated for up to 100 miles per hour wind gusts,
the precision sensor and 24-bit analog-to-digital converter (ADC) allow for 99.9 percent
accurate altitude readings, and the selectable apogee delay for dual setups such as the
one we are using prevents overpressure from simultaneous charge firing. Additionally,
each altimeter will be equipped with an externally-accessible magnetic arming switch
capable of being locked in the “on” position for launch (requirements 2.6, 2.8). The
arming switches dedicated to the dual altimeters which control main parachute
deployment will be located at least 6 feet above the base of the launch vehicle
(requirement 2.9). Those dedicated to the dual altimeters which control drogue
parachute deployment will be located 2 feet above the base of the launch vehicle
(requirement 2.9).

17
Each altimeter will be programmed to light a 1-foot low-current Daveyfire N28BR electric
match (requirements 2.13, 2.14, and 2.14.1). The basic construction of an electric
match, or e-match, is shown in Figure 11. Each match will ignite two separate black
powder charges, one main and one backup.
This will ensure separation and
ejection of the proper parachute at the
proper time. At 5,000 feet on ascent
the electric matches for the drogue
parachute black powder charges will
be ignited to ensure full release at
apogee. The e-matches for the main
parachute will be ignited at 700 feet
on descent to ensure a slowed impact and minimal drift.
With the assumption that the entire mass of each charge will be burned and converted
into a gas, the basic Ideal Gas Law is used, PV = NRT. P = design pressure (pounds
per square inch), V = volume of cylindrical compartment in the rocket body which
houses the two charges and the parachute (inches cubed), N = mass of powder
(pounds) to be evenly distributed between and packed into two plastic tubes, R =
universal gas constant (inches-pound force per pound mass), and T = initial combustion
temperature of the powder (Rankine). Using commercially available FFFFg black
powder, P = 15 pounds per square inch since the inside body diameter (D = 3.5 inches)
is less than 7.5 inches, V = 0.25πD²L from the volume of a cylinder where L is the
compartment length (inch), N = PV/RT is the mass to be found in ounces by accounting
for the conversion 1 pound = 16 ounces = 454 grams, R = 266, and T = 3307 Rankine.
From this the mass equation reduces to N = 0.0735*L (in grams). For ejection of the
drogue parachute L = (12 – 4.5 inches) = 7.5 inches, to give N = 0.539 grams = 0.019
ounces for each the main and backup charges. For ejection of the main parachute L =
(24 – 4.5 inches) = 19.5 inches, to give N = 1.434 grams = 0.0506 ounces for each the
main and backup charges.
Assuming use of a Cesaroni K1440 motor, the total vehicle launch weight is estimated
to be 326 ounces = 20.375 pounds. We considered the addition of up to 10 percent
ballast, as well as the fuel compartment being empty by deployment of the drogue
parachute, and estimated the vehicle weight at 20 pounds. These values may change
throughout the design process, but the process will not. Note that the drag coefficient
for domed parachutes is approximately 1.5, atmospheric density at sea level and 70
degrees Fahrenheit is approximately 0.0024 slugs per cubic foot, and descent rate
Figure 11 – E-match Diagram

18
should be no more than 15 feet per second in order to minimize damage to the launch
vehicle.
The size of the drogue parachute can then be estimated from D = 24√ , where D is
the ideal diameter of the drogue parachute and is the weight of the launch vehicle.
This gives D = 28.397 inches = 2.366 feet. Since commercial availability limits
parachute size to 0.5 foot increments, the diameter of the drogue is chosen to be 2.5
feet. By similar analysis, the size of the main parachute is estimated from D =
39.6√ . This gives D = 84.377 inches = 7.031 feet. The diameter of the main
parachute is chosen to be 8 feet. This is a conservative estimate with regard to terminal
velocity but slightly immoderate with regard to landing radius if wind speeds are in
excess of 15 miles per hour. However, programming full deployment to occur no later
than 500 feet from the ground on descent should allow for minimal drift. These
equations are derived from Newton’s Second Law of Motion s = 2w/ρv²c, where s =
reference area, w = vehicle weight, ρ = density of air, v = terminal velocity, and c = drag
coefficient as provided by the parachute manufacturer.
The chosen sizes of the main and drogue parachutes should be such that the kinetic
energy of each independent (tethered) section of the launch vehicle upon landing is no
greater than 75 foot-pounds. Based on Newton’s Second Law of Motion, with the
assumptions of constant descent rate between ejections and simple downward motion,
the maximum descent rate upon ejection of each parachute is given by
v =√ .
In the above equation, note that w = vehicle weight in pound-mass, ρ = sea-level air
density at 70 degrees Fahrenheit = 0.075 pound-force per cubic foot, c = drag
coefficient, and s = surface area of each parachute dome = π(height)²[3*(radius) –
(height)] where height is assumed to be *(radius). With a total vehicle weight of
20 pounds = 320 ounces = 9.24 kilograms, the maximum descent rate for the first 4,780
feet upon drogue release at apogee is 73.47 feet per second = 22.39 meters per
second. Upon release of the main this drops to a maximum 12.83 feet per second =
3.91 meters per second descent rate for the remaining 500 feet.
Descent time after each event can be calculated from t = d/v, where d = distance
travelled in feet and v = maximum descent velocity. The first 4,780 feet of descent thus
takes no less than 65.06 seconds. Similarly the final 500 feet of descent takes no less

19
than 38.97 seconds. In a constant 15 mile per hour wind, the concept of relative
velocity enables the calculation of a landing radius of 1,430.46 feet for the first half of
the descent with an additional 857.44 feet for the second half. The maximum landing
radius is thus found to be (1,430.46 + 857.44) feet = 2287.9 feet from the launch pad
which is within the required 2,500 feet maximum landing radius (requirement 2.3).
The top component contains tethered together the nosecone, main parachute, main
parachute altimeter housing, and payload sections. The bottom component contains
tethered together the drogue parachute, drogue parachute altimeter housing, and motor
sections. The proposed total weight of the top component is then = 4.60 kilograms,
while that of the bottom component is = 4.64 kilograms. By the maximum final
descent rate of = 3.91 meters per second, the maximum terminal kinetic energy of
the top component is found to be = 35.16 Joules = 25.93 foot-pounds. Similarly,
the maximum terminal kinetic energy of the bottom component is found to be 35.47
Joules = 26.16 feet pound force. These are each less than the maximum allowable 75
foot-pound-force terminal kinetic energy (requirement 2.2).
The selected parachutes are made of silicone-coated low-porosity ripstop nylon with all
seams reinforced with nylon webbing and 0.5 inches mil spec nylon sewn around the
canopy to ensure both strength and light weight. The hexagonal 2.5 foot drogue weighs
1.45 ounces, while the dual-cross-form 8 foot main weighs 26.3 ounces. These
parachutes have also been selected for their low probability of entanglement. There are
only four suspension lines on the main parachute but which have a tested tensile
strength of 200 pounds per square inch. There are only six suspension lines for the
drogue parachute but which have a tested tensile strength of 160 pounds per square
inch. Additionally standard high-power model rocketry 900 pound-working-strength
swivels will be implemented on each shock harness. Further, each parachute will be
quick-linked to the bridle of a 2,000 degrees Fahrenheit-plus-heat-resistant Nomex
deployment bag and neatly folding each parachute along with all shroud lines and shock
cord into the bag. This keeps each parachute contained long enough to get it away from
the fins and to eject in an orderly fashion. This also keeps the material away from the
heat of the ejection charge firing. Figure 12 demonstrates the ejection staging.

20
Figure 12 – Ejection Staging
In order to enable deceleration of the two separated components on descent, 0.5-inch
tubular Kevlar shock harnesses will be put in place. These have been chosen for
strength and flame-proof construction. Additionally, these shock harnesses include pre-
sewn Nomex loops for safe and secure connection to the chutes by quick links. The
body length is approximated to be 8 feet, 7 inches including the nosecone. The main
harness is chosen to be approximately two body lengths to keep the main parachute
away from the body plus 15 percent (calculated 18.45 feet) to account for knotting. The
drogue harness is chosen to be approximately three body lengths to pull the drogue
parachute up and away from the vehicle while minimizing the risk of denting or zippering
plus 15 percent (calculated 27.04 feet) to account for knotting. Thus, based on
commercial availability, the length of the main shock harness is chosen to be 20 feet,
while that for the drogue is chosen to be 25 feet.

21
In order to ensure that separation in the rocket body only occurs upon ejection,
removable threaded nylon shear pins will be used. These will be inserted through holes
drilled on either side of the couplings between the nosecone shoulder and main
parachute compartment, as well as between the payload and drogue parachute
compartments (requirement 2.10). When the ejection charge fires, the force of the
coupler sliding past will snap the shear pins. However, other stresses under 25 pound
force such as those caused by shifting mass, drag, or ejection from another
compartment should not be strong enough to cause separation. Stainless steel delta-
shaped quick links, with a working load of 1,000 pounds, will be used. These will
secure each parachute to its shock harness, and each shock harness to a u-bolt at the
bulkhead of each altimeter compartment to ensure secure tethering throughout the
flight.
A 1.25-inch BeeLine GPS will be used to recover each component upon landing, in the
event that tethering separation on descent occurs or visual contact is lost. The first will
be mounted inside the nosecone and the second will be mounted under the bulkhead of
the drogue compartment. These placements should shield the devices from parachute,
black powder charge, and fuel ejection (requirements 2.11.1 and 2.12.2). A
corresponding ground receiver will be located on the launch site (requirements 2.4 and
2.11). A fully integrated RF transmitter, GPS and RF antennas, GPS Module, and
battery will all be contained in one package (requirement 2.11.3).
Altogether, these devices simultaneously transmit latitude, longitude, altitude, course,
and speed. The BeeLine GPS has been chosen for its small size, reasonable cost,
transmission range at up to 20 miles line of sight, frequent usage in high-powered
model rocketry, use of standard decoding hardware (automatic packet reporting system,
or APRS), and operation frequency on any frequency in the 70-centimeter amateur
radio band. The additional features of course and speed will allow for real-time
calculation of landing distance and terminal kinetic energy, as well as serve as a check
of the altimeters. The mounting precautions taken along with the 8 hour battery life of
the included Lithium-Poly battery, the non-volatile flight-data memory storage (3 hours
at 1 Hertz), and the user-programmable transmission rates and output power will
together ensure that the devices remain fully functional during the course of the flight
(requirement 2.11.2).
The components of the recovery section are itemized in Table 4. This includes the total
cost and mass (where available) of each item. The total cost reflected in this table is for
one fully assembled rocket.

22
Table 4 – Recovery Systems Budget
Item Distributor Item
Number
Unit
Dimensions
Unit
Cost
Qty. Total
Cost
Main
Altimeters
Featherweight
Altimeters
Raven3 1.8” x 0.8” x
0.55”, 0.34oz
$155.00 2 $310.00
Backup
Altimeters
PerfectFlite StratoLogger
SL100
2.75” x 0.9” x
0.55”, 0.45oz
$79.95 3 $239.85
Electric
Matches
Coast Rocketry Daveyfire
N28BR
1’ long $2.95 4 $11.80
FFFFg
Black
Powder
Goex Goex 4F
Black
Powder
1lb $15.75 1 $15.75
Black
Powder
Ejection
Charge
Holders
Aerocon
Systems
BPSmall 15, 0.0676oz $3.00 1 $3.00
Swivels Commonwealth
Rocketry
SWLDK80 1.5” $1.99 2 $3.98
Main
Shock
Cord
Giant Leap
Rocketry
Tubular
Kevlar
0.5” x 25’ $37.79 1 $37.79
Drogue
Shock
Cord
Giant Leap
Rocketry
Tubular
Kevlar
0.5” x 20’ $31.49 1 $31.49
Main
Parachute
Rocketman
Enterprises
8 ft.
Standard
Low-Porosity
1.1oz
Ripstop
8’ round $65.00 1 $65.00
Flame-
proof Main
Rocketman
Enterprises
DB8 3.25” x 3.25”
x 6.5”
$40.00 1 $40.00

23
Parachute
Deployme
nt Bag
(custom)
Drogue
Parachute
Rocketry
Warehouse
TopFlight
30” 1.7oz
Ripstop
30” round $12.95 1 $12.95
Flame-
proof
Drogue
Parachute
Deployme
nt Bag
Rocketman
Enterprises
DB2 3.25” x 3.25”
x 18.5”
(custom)
$25.00 1 $25.00
U-Bolts Sunward
Aerospace
U-Bolt
Assembly –
¼”
(Compact)
0.212” x 1.5”
x 2.125”,
1.77oz
$4.29 2 $8.58
Quick
Links
Commonwealth
Rocketry
¼” Stainless
Steel Delta
Quick Link
2.375” x
0.375” x
1.25”
$2.99 4 $11.96
Main
Shock
Cord
Giant Leap
Rocketry
Tubular
Kevlar
0.5” x 25’ $37.79 1 $37.79
Shear
Pins
Missile Works 2-56 Nylon
Shear-Pin
(10 pack)
10 at 0.08” x
0.5” each,
0.002oz
$1.00 1 $1.00
Arming
Switches
Featherweight
Altimeters
Featherweig
ht Magnetic
Switch
0.55” x 0.75” $25.00 4 $100.00
GPS Big Red Bee BeeLine
GPS-
Package
Deal
2 oz, 1.25” x
3”
$289.00 2 $578.00
Total Estimated Cost of Recovery Section Components $1496.15
Table 4 – Recovery Systems Budget (Cont’d)

24
c. Motor
Four motors were considered for this project. Each use a solid ammonium
perchlorate composite propellant that has been approved by NAR and TRA. The main
characteristics considered for motor selection are diameter, length, thrust to weight
ratio, total impulse, average thrust, maximum thrust, burn time, launch mass, empty
mass and projected apogee height. The burn profile of each motor selection will also be
taken into account. Each motor has a diameter of 2.125 inches (54mm). The following
table lists the four motor selections and their main characteristics. All data from the table
was calculated or obtained by using the Open Rocket simulation software. The motors
were compared as shown in Table 5.
Table 5 – Motor Trade and Selection
Length
Thrust
to
Weight
Total
Impulse
Average
Thrust
Maximum
Thrust
Burn
Time
Launch
Mass
Empty
Mass
Apogee Price
Cesaroni K1440
22.52”
(57.2cm)
15.9 : 1
532.4lbfs
(2368Ns)
324.6lbf
(1444N)
487.4lbf
(2168N)
1.64s 66.8oz 25.8oz 5515ft $157.94
Cesaroni K815
25.55”
(64.9cm)
8.82 : 1
518.0lbfs
(2304Ns)
185.7lbf
(826N)
269.8lbf
(1200N)
2.79s 77.5oz 29.1oz 5243ft $170.71
AeroTech K700
22.36”
(56.8cm)
7.49 : 1
513.5lbfs
(2284Ns)
154.9lbf
(689N)
231.3lbf
(1029N)
3.3s 71.8oz 26.2oz 5288ft $152.99
Cesaroni K820
22.52”
(57.2cm)
9.16 : 1
535.9lbfs
(2384Ns)
188.2lbf
(837N)
386.7lbf
(1720N)
2.84s 69.9oz 26.5oz 5552ft $148.36

25
Cesaroni K1440
The Cesaroni K1440 has a total impulse of 2368 Newton-seconds, which does not
exceed the total impulse maximum of 5120 Newton-seconds. The motor’s
corresponding thrust curve as calculated by the open rocket software is represented in
Figure 13. As shown in the thrust curve, the motor has a regressive motor burn. Thus,
as the motor burns thrust decreases. As shown in the above table and marked in Figure
13, average thrust for this motor is 324.6lbf = 1444N. In the following calculation, the
mass of the rocket at launch is used because it represents the maximum mass that the
motor would have to be able to lift during the flight. In order that the motor be able to lift
the rocket, it must produce enough thrust to overcome the force of gravity, or enough
mechanical energy to achieve a thrust to weight ratio of at least 1.0. In general for a
high-powered rocket, the thrust to weight ratio is given by
.
With this motor, the launch mass of the rocket is 326oz = 9.24kg. Noting that the
acceleration of gravity is approximately 9.8m/s², for this motor the thrust to weight ratio
is given by = 15.9 : 1, which exceeds the suggested ratio of 5 : 1.
Figure 13 – Cesaroni K1440 Thrust Curve

26
Cesaroni K815
The Cesaroni K815 has a total impulse is 2304 Newton-seconds, which does not
Figure 14. As shown in the thrust curve, the motor quickly reaches the maximum thrust,
steeply drops, and then starts a progressive motor burn followed by a regressive motor
burn. As shown in Table 5 and marked in Figure 14, average thrust for this motor is
185.7lbf = 826N. With this motor, the launch mass of the rocket is 337oz = 9.55kg.
Noting that the acceleration of gravity is approximately 9.8m/s², for this motor the thrust
to weight ratio is given by = 8.82 : 1, which exceeds the suggested ratio
of 5 : 1. One downside to the Cesaroni K815 is the length of 25.55 inches. The current
design allows for only two feet in the motor mount section of the rocket. If this were to
be the final motor selection the motor mount section of the rocket would have to be
extended.
Aero-Tech K700
The Aero-Tech K700 has a total impulse of 2284 Newton-seconds, which does not

27
Figure 15. As shown in the thrust curve, the motor has a regressive motor burn. Thus,
as the motor burns thrust decreases. As shown in the above table and marked in Figure
15, average thrust for this motor is 154.9lbf = 689N. With this motor, the launch mass of
the rocket is 331oz = 9.38kg. Noting that the acceleration of gravity is approximately
9.8m/s², for this motor the thrust to weight ratio is given by T/W =
689N/9.38kg*9.8m/s² = 7.49 : 1, which exceeds the suggested ratio of 5 : 1. One
downside to the Aero-Tech K700 is that many high powered rocket enthusiasts have
discouraged the use of Aero-Tech motors due to their high level of variability in
comparison to Cesaroni motors.
Figure 15 – Aero-Tech K700 Thrust Curve
Cesaroni K820
The Cesaroni K820 has a total impulse of 2384 Newton-seconds, which does not
Figure 16. As shown in the thrust curve, the motor has a somewhat neutral but overall
regressive motor burn. Thus, as the motor burns thrust decreases slowly. As shown in
Table 5 and marked in Figure 16, average thrust for this motor is 188.2lbf = 837N. With

28
this motor, the launch mass of the rocket is 329oz = 9.32kg. Noting that the acceleration
of gravity is approximately 9.8m/s², for this motor the thrust to weight ratio is given by
= 9.16 : 1, which exceeds the suggested ratio of 5 : 1.
After evaluating the four motors, the Cesaroni K1440 is the proposed selection. This
selection is based upon the apogee height achieved. Considering total mass will most
likely increase and not decrease, the calculated apogee of 5515 feet will inevitably
decrease. The motor also has a high thrust to weight ratio, allowing it to easily depart
from the launch rail.
d. Payload Description
The payload section of the flight vehicle will be enclosed in the acrylic payload housing
structure. The payload housing structure is designed to remain attached to the upper
body tube throughout the flight. The payload is proposed to consist of a fiberglass cap
at the upper portion of payload housing structure, a threaded lower portion of the
payload housing structure, and a payload framework on which the payload circuits are
mounted. The payload framework is composed of two aluminum rails attached to a
threaded cap. Modular circuit boards, with a width of no more than 3.5 inches and
stacked in a vertically orientation, will be mounted to the aluminum rails. The threaded
cap will be screwed into the threaded lower end of the acrylic payload housing structure.

29
The intent of this is to provide a modular design for the payload framework and provide
a pressure seal from the drogue parachute compartment. This modular design allows
easy access to the each circuit board and its corresponding components. Figure 17
represents the conceptual layout of the payload.
3.5 in
34.5 in
Figure 17 – Payload Layout: Front view (left), rear view (right)

30
The payload will be equipped with the
appropriate electronic hardware for meeting the
SMD payload requirements (requirement 3.1.3).
The main flight computer will be an Arduino
Mega 2560-R3. We will also use 2 Arduino Pro
Mini 328s to control specific processes of video
and image capture. The payload circuitry will be
divided into sections as shown in Figure 18. This
allows an organized layout of components based
upon the required power supply and
microcontroller for that section. We will have
redundant sensors for measuring temperature,
pressure, relative humidity, solar irradiance, and
ultraviolet radiation.
The microcontrollers and sensors will be
calibrated to sample at no less than 0.2 Hz
during descent, followed by 0.017 Hz after
landing (requirements 3.1.3.2 and 3.1.3.3). Two
cameras, each controlled by a dedicated Arduino
Pro Mini, will be mounted to face 180 degrees away from each other to better capture
the surrounding environment. The cameras will take a minimum of 5 pictures of proper
orientation (requirement 3.1.3.6); two during descent and three post landing
(requirement 3.1.3.5). We will have a total of five 9 volt batteries in the payload section.
This is to ensure adequate capacity for operating all sensors and components, and
furthermore allows independent voltage leveling of each battery to the corresponding
payload section. Each section of the electronics layout will have a dedicated 9-volt
power supply from an Ultralife U9VLBP battery. This voltage will be leveled by an
appropriate buck converter to either 3.3V or 5V, depending on the sensors of that
section. The payload will have a GPS tracking unit that will be controlled by the Arduino
Mega (requirement 3.1.3.9). Each camera will have its data stored on a dedicated
microSD card under the control of an Arduino Pro Mini. All other sensor data will be
stored onboard to a microSD card, under control of the Arduino Mega (requirement
3.1.3.7). A Sparkfun LCD will be used to display relevant data that can be viewed
through the transparent acrylic body tube.
All data stored onboard will also be transmitted to the team ground station (requirement
3.1.3.7). This will be achieved by an XBee Pro 900MHz Radio Transmitter located in the
Figure 18 – CAD Rendering of
Payload Layout

31
payload section under control of the Arduino Mega. Signal will be received by a high
gain, directional patch antenna located at the ground station, and will be displayed in
real-time through MATLAB on the ground station computer. The orientation of the
ground station antenna will be controlled by an automated tracking system. The GPS
will relay the coordinates of the rocket vehicle to the ground station computer, where a
program will predict rocket trajectory. This information will be used to actuate the
directional antenna, in both azimuth and elevation, to achieve tracking; minimizing loss
in reception during flight and descent.
Table 6 shows dimensions and costs of electronic components being considered for use
in the payload.
Table 6 – Electronics Trade and Selection
Rating
Breakout
Board
Distributor
Part
Number
Interface
Dimensions
(L x W x H)
Mass
Input
Voltage
Current
Draw
Cost
Flight Computer
1. Sparkfun
Arduino
2560-R3
N/A
2.125 x
4.3125”
2.3oz
(65g)
7 – 12V
20 -
200mA
$58.95
2. Sparkfun
Arduino
Pro Mini
328
N/A 0.7 x 1.3”
.07oz
(2g)
5 – 12V 150mA $18.95
Altimeter
1.
DSS
Circuits
BMP180 I2
C 0.625 x 0.5”
.04oz
(1.1g)
1.8 -
3.6V
3 –
32μA
$15.00
2. Sparkfun BMP085 I2
C 0.65 x 0.65”
.04oz
(1.1g)
1.8 -
3.6V
3 –
12μA
$19.95
3. Pololu MPL115A1 SPI 0.5 x 0.75”
.04oz
(1.1g)
2.4 –
5.5V
10μA $24.95
Hygrometer
1. Sparkfun HIH4030 Analog 0.75 x 0.30”
.04oz
(1.1g)
4 – 5.8V 200μA $16.95
2. Adafruit SHT11 Serial 0.43 x 0.49”
.004oz
(0.1g)
2.4 –
5.5V
10μA $35.00
Table 6 – Electronics Trade and Selection (Cont’d)

32
3. Robotshop RB-Dfr-68 I2
C 0.67 x 1.26”
.18oz
(5g)
2.4 –
5.5V
10μA $24.00
Thermometer
1.
DSS
Circuits
BMP180 I2
C 0.625 x 0.5”
0.04oz
(1.1g)
1.8 -
3.6V
3 –
32μA
$15.00
C 0.65 x 0.65”
0.04oz
(1.1g)
1.8 -
3.6V
3 –
12μA
$19.95
3. Adafruit SHT11 Serial 0.43 x 0.49”
0.004o
z
(0.1g)
2.4 –
5.5V
10μA $35.00
Pressure Sensor
1.
DSS
Circuits
BMP180 I2
C 0.625 x 0.5”
0.04oz
(1.1g)
1.8 -
3.6V
3 –
32μA
$15.00
C 0.65 x 0.65”
0.04oz
(1.1g)
1.8 -
3.6V
3 –
12μA
$19.95
3. Pololu MPL115A1 SPI 0.5 x 0.75”
.05oz
(1.4g)
2.4 –
5.5V
10μA $24.95
UV Sensor
1. sglux
TOCON_A
BC3
Analog
0.4 x 0.4 x
0.3”
0.02oz
(0.5g)
2.5 –
15V
0.8mA
$148.0
0
2. Apogee SU-100 Analog
0.925 x
0.925 x 1.08”
2.65oz
(75g)
0V 0A
$159.0
0
3.
Solar Light
Inc.
PMA1107 Analog
1.6 x 1.6 x
1.8”
7.05oz
(200g)
0V 0A
$525.0
0
Pyranometer
1. Adafruit TSL2561 I2
C 0.75 x 0.75”
0.053o
z(1.5g)
2.7 –
3.6V
0.5mA $12.50
2. Apogee SP-110 Analog
0.925 x
0.925 x 1.11”
2.47oz
(70g)
0V 0A
$169.0
0
3. Sparkfun TEMT6000 Analog 0.39 x 0.39”
0.04oz
(1g)
5V 20mA $8.99

33
Wireless Transmitter / Receiver
1. Digi
XBee-PRO
XSC S3B
Serial
0.31oz
(8.7g)
2.4 –
3.6V
215mA $42.00
XBee Circuit Board Spacing Adapter
1. Parallax 32403 N/A
1.16 x 1.0 x
0.58”
- 0V 0A $2.99
2. Sparkfun 08276 N/A 1 x 1” - 0V 0A $2.95
GPS
1. Locosys LS20031 Serial 1.18 x 1.18”
0.49oz
(14g)
3 – 4.2V 29mA $60.00
Camera
1. Adafruit VC0706 Serial 1.26 x 1.26”
1.76oz
(50g)
5V 75mA $42.00
2. Sparkfun
SEN-
10061
Serial 1.26 x 1.26”
1.76oz
(50g)
5V
80-
100mA
$49.95
3. Adafruit 613 Serial 2 x 2 x 2.5”
5.29oz
(150g)
5V 75mA $59.95
16GB SDHC Micro-SD Card
1. Wal-Mart
3FMUSD1
6FB-R
N/A
2.2 x 0.3 x
3.4”
0.11oz
(3g)
N/A N/A $9.99
Micro-SD Adapter
1. Adafruit 254 SPI
1.25 x 1 x
0.15”
0.12oz
(3.43g)
3 – 5V 150mA $15.00
2. Parallax 32312 SPI
1.11 x 1 x
0.47”
0.11oz
(3g)
3.3V 0.5 mA $14.99
3. Sparkfun 00544 SPI 0.94 x 0.94”
0.09oz
(2.5g)
5V 0.5mA $9.95
LCD
1. Sparkfun 10168 SPI 1.75 x 1.75”
2.47oz
(70g)
3.3 – 6V
240 -
320μA
$9.95

34
2. Sparkfun 11062 SPI 1.5 x 2.5”
2.47oz
(70g)
3.3 – 6V
108 –
324mA
$34.95
Voltage Leveler
1.
Self
Manufacture
Buck
Converter
N/A - - N/A - -
Power Supply
1. Ultralife U9VLBP N/A
1.81x1.04x0.
69”
1.28oz
(36.4g)
5.4 –
9.9V
Max 120
mA
$6.65

35
Figure 19 shows a conceptual wiring layout for the microcontroller and electronic
components. This does not reflect the final wiring schematic, but displays the general
scheme for electrical connections.
Figure 19 – Conceptual Wiring Diagram

36
Figure 20 illustrates the software logic proposed for the payload section. Until the
project begins, the software will not be finalized.
Figure 20 – Payload Software Flow Chart

37
e. Requirements
Vehicle Requirements
This section discusses the vehicle, recovery system, payload, and general requirements
as given in the 2012-2013 NASA SLP Manual.
The motor selection will be based on the appropriate thrust need to lift the mass of the
rocket vehicle to 1 mile AGL. All motors being considered adhere to the requirements of
APCP fuel source and NAR and TRA regulations. Of the motors considered, the largest
total impulse is 2384 Newton-seconds. Our proposed choice of motor is a Cesaroni
K1440. The impulse of the motor will not allow the rocket vehicle to reach a supersonic
velocity. The rocket motor to be used will be a standard, commercially available motor
that can be ignited by a standard 12 volt DC firing system. No other circuitry or
equipment will be required to initiate launch (Vehicle Requirements 1.1, 1.3, 1.9 – 1.12).
The Perfect-flight altimeter will be used. This device reports altitude as a series of beeps
as required. The payload section will have 2 BMP180 pressure/temperature sensors
that will be used to calculate altitude and 2 redundant sensors in case of device failure.
Additional altimeters will be used in conjunction with black powder ejection charges to
allow separation of various sections at prescribed altitudes. The altimeter to be used for
official scoring will be pre-determined and implemented into the rocket design
accordingly. The perfect flight altimeter is capable of producing these beeps to indicate
the maximum altitude achieved during flight. Our design incorporates no other audible
electronics other than the altimeter required for official scoring. The official, marked
altimeter shall be incorporated into the rocket vehicle such that it will suffer no damage
or loss of functionality throughout the flight. A team member will be delegated to ensure
that the NASA official will receive a report of the achieved altitude from the flight. The
aerodynamic characteristics of the vehicle, along with the selection of the motor, will be
made such that the rocket will not achieve an altitude greater than 5,600 feet AGL
(Vehicle Requirements 1.2).
The proposed recovery system will allow the entirety of the rocket vehicle to safely drift
back to ground level such that the vehicle will experience no structural damage. The
vehicle is proposed to have 4 sections, all tethered together during the entire flight such
that they are attached after any separation events (Vehicle Requirements 1.4, 1.5).
A pre-flight configuration procedure will be developed and implemented that is
achievable in the specified 2 hour time frame. A power budget will be used to justify

38
required system runtime of all critical on-board components to maintain at least one
hour of functionality while on the launch pad (Vehicle Requirements 1.6, 1.7).
Rail buttons to be mounted on the vehicle body will be compatible with the 1010 rail.
The ballast system to control altitude will not consist of any more than 10% of the total
mass of the unballasted rocket vehicle (Vehicle Requirements 1.8, 1.14).
A full-scale demonstration flight with full-scale motor (Cesaroni K1440) and payload
onboard will be performed and reviewed to ensure functionality and integrity of all
systems. In the event that the payload is not included, mass simulators will be utilized
aboard the rocket. If we use mass simulators, their position in the vehicle will accurately
reflect the mass location of the full scale system. Our demonstration flight will include
the complete ballast system to be used in the official flight. Our mentor, Pat Gordzelik
(TRA Vice President), will be present at the full-scale demonstration launch and
certifying our flight form. After successfully completing the full-scale demonstration
flight, the launch vehicle or any of its components shall not be modified without the
concurrence of the NASA Range Safety Officer (RSO); however, a successful full scale
demonstration will warrant no needed changes to our rocket design
(Vehicle Requirements 1.15).
Our projected budget will allow the total cost of the rocket and payload to be
approximately $3,200, less than the $5,000 limit (Vehicle Requirements 1.16). The
breakdown of each subsystem cost is shown in Table 7.
Table 7 – Technical Design Cost Summary
Subsystem Cost
Payload $877.16
Recovery System $1,496.15
Motor $297.87
Vehicle Housing $400.06
Pursuant to the listed prohibitions, the design of vehicle will have no forward canards,
one rearward firing motor, and will not expel titanium sponges. Furthermore, our design
includes only one solid-propellant motor (Vehicle Requirements 1.17).

39
Recovery System Requirements
A dual-stage deployment recovery system will be employed. The upper section consists
of the nosecone, main parachute, main deployment altimeter housing, and payload
sections tethered together. The booster section contains the drogue parachute, drogue
deployment altimeter housing, and motor sections tethered together. The proposed
total weight of the upper section is = 4.60 kilograms, while that of the booster section
is = 4.64 kilograms. By the maximum final descent rate of = 3.91 meters per
second, the maximum terminal kinetic energy of the upper section is then =
35.16 Joules = 25.93 feet pound force, while that of the booster section is 35.47 Joules
= 26.16 feet pound force, each less than the required maximum 75 feet pound force
terminal kinetic energy. Calculating descent time after each event to be t = d/v where d
= distance travelled in feet and v = maximum descent velocity upon each event, the first
part of descent takes no less than 65.06 seconds while the second half of the descent
takes no less than 38.97 seconds. In a constant 15 mile per hour wind, the concept of
relative velocity enables the calculation of a landing radius of 1,430.46 feet for the first
half of the descent with an additional 857.44 feet for the second half. The maximum
landing radius is thus found to be (1,430.46 + 857.44) feet = 2,287.9 feet from the
launch pad which is within the required 2,500 feet maximum landing radius (Recovery
Systems Requirements 2.1 – 2.3).
The main Featherweight Raven3 and the backup PerfectFlite StratoLogger altimeters as
well as the BeeLine GPS will be programmed independently of the payload and
monitored remotely using the manufacturer software. Each deployment will be
controlled by two altimeters, the main a Featherweight Raven3 and the backup a
PerfectFlite StratoLogger. They will be equipped with an externally accessible magnetic
arming switch capable of being locked in the “on” position for launch. The magnetic
arming switches will not generate magnetic waves because current is not run through
the magnets when locked. The arming switches dedicated to the dual altimeters
controlling main parachute deployment will be located at 5 feet above the base of the
launch vehicle, while those dedicated to the dual altimeters controlling drogue
parachute deployment will be located at 2 feet above the base of the launch vehicle.
The altimeters shall have their own dedicated power supplies; the chosen altimeters are
each capable of running independently for weeks on a standard 9V battery. Each
altimeter will be programmed to light a one-foot-long low-current Daveyfire N28BR
electric match to ignite two separate black powder charges, one main and one backup,
to ensure separation and ejection (Recovery Systems Requirements 2.4 – 2.9, 2.12.1,
2.12.3, 2.13).

40
Removable threaded nylon shear pins will be inserted through holes drilled on either
side of the couplings between the nosecone shoulder and main parachute compartment
and between the payload and drogue parachute compartments (Recovery Systems
Requirements 2.10).
A 1.25-inch BeeLine GPS will be mounted inside of each the nosecone and upper
internal outer motor compartment with a corresponding ground receiver located on the
launch site. The upper section contains tethered together the nosecone, main
parachute, main parachute altimeter housing, and payload sections, while the bottom
component contains tethered together the drogue parachute, drogue parachute
altimeter housing, and motor sections. In order to locate each of the two tethered
vehicle sections, a 1.25-inch BeeLine GPS will be mounted inside of each the nosecone
and under the bulkhead of the drogue compartment. The mounting precautions taken
along with the eight-hour battery life of the included Lithium-Poly battery, the non-
volatile flight-data memory storage (three hours at 1-Hz), and the user-programmable
transmission rates and output power will together ensure that the devices remain fully
functional during flight. The BeeLine GPS contains a fully integrated RF transmitter,
GPS and RF antennas, GPS Module, and battery all in one package, so while beeping
can be programmed to occur in conjunction with transmission, it does not replace the
transmitting tracking device (Recovery Systems Requirement 2.11).
Each set of altimeters are to be housed in a sealed 4.5-inch compartment below each
parachute compartment in the vehicle body. The transmitting tracking devices are to be
located in the nosecone and motor housings. There are several compartments between
the altimeters and the transmitting tracking devices in one case and at least a bulkhead
in between in the other case. There is also a full parachute compartment and a
bulkhead in between the main parachute altimeters and the payload, so no other
transmitting electronics on board should be able to interfere with any of the four
altimeters (Recovery Systems Requirement 2.12).
Pursuant to the listed prohibitions, our design will not include flashbulbs or a rear
ejection parachute design (Recovery Systems Requirement 2.14).
Payload Requirements
Option 3.1.3 (The Science Mission Directorate) shall be chosen for our payload design.
We hope to gain sponsorship for this selection. To ensure the SMD requirement of data
acquisition is met the team has done a trade and selection for pressure, temperature,
relative humidity, solar irradiance and ultraviolet radiation sensors. We have yet to

41
finalize our choice of sensor models. The proposed flight computer, Arduino Mega
2560-R3, is capable of operating at one iteration every 5 seconds or faster. After it has
detected a successful landing it will reduce the clock cycles to once every minute. After
10 minutes on the ground it shall stop collecting data. The onboard camera shall take
pictures at two predetermined heights during the descent phase of the rocket. After
landing, pictures will be taken in 3 minute intervals until the payload has terminated
processing data. Methods of controlling camera orientation will be investigated. All
images will be stored to an onboard micro-SD memory device, while all telemetry shall
be transmitted via XBee radios to our ground station. A Locosys LS20031 GPS unit will
be used to track the location of our payload. During the flight, the payload will not
separate from the upper section of the rocket. The rocket is being designed with the
intention of being launched more than once; our payload will be recovered and reused
without any modifications (Payload Requirements 3.1.3, 3.5).
Upon retrieving the flight and sensor data from the onboard SD card it will be analyzed
following the scientific method (Payload Requirements 3.2).
Our proposed rocket will not include any UAV components and will not require any
jettison events (Payload Requirements 3.3, 3.4).
General Requirements
The Team Safety Officer has prepared and will enforce the use of the launch and safety
checklist as presented in the safety section. It will be included in the PDR, CDR, FRR,
and launch day operations. No part of the project has been done by anyone other than
the team members of the Tarleton Aeronautical Team. Our project plan is included
within our proposal and will be overseen by our project manager Dustin. All current
members are at least 18 years of age and US citizens. These members are identified in
the school information section of our proposal (General Requirements 4.1 – 4.3, 4.5,
4.6).
Our TRA mentor, Pat Gordzelik, is level 3 certified with NAR and TRA. He is currently
the vice president of the TRA. His TRA membership number is 5746. The Team Safety
Officer will ensure that the team abides by the rules and guidance of Mr. Gordzelik. Our
faculty mentors are Dr. Bryant Wyatt and Dr. Bowen Brawner. Dr. Brawner is level 1
certified with NAR (General Requirements 4.4, 4.5, 4.7).
The Team Educational Outreach Coordinator is in charge of the educational
engagement portion of the project. He has planned multiple events to involve at least

42
100 middle-school students and educators. The Team Web Designer will be in charge
of developing and maintaining the team Web site where all required deliverables will be
posted (General Requirements 4.8, 4.9).
f. Challenges and Solutions
Reaching an Apogee of One Mile
Several energy management ideas have been researched. The proposed design
approximates the total mass and uses the Open Rocket simulation software to calculate
apogee. If the apogee height is above one mile, a ballast mass of less than ten percent
of the total mass would be added to the nosecone.
Camera Orientation
To force the camera to stay oriented such that the pictures display the sky at the top
and the ground at the bottom, a multi-servo mechanism controlled by a gyroscope and a
microprocessor has been considered.
Maintaining Telemetry
Through past experience with wireless transmission at high acceleration, the team
realizes that maintaining telemetry throughout the flight will be a challenge. One
consideration to solve this challenge is an automated tracking system based on GPS,
acceleration, and altitude data transmitted from the payload.
Protecting Sensors from Atmospheric Damage
The initial rocket design allowed the pyranometer, UV sensor, and camera to be
exposed to the outer atmosphere. To protect these sensors and to simplify the design
the proposed solution is the use of a clear acrylic payload structure. Through testing the
team will calculate the effects of clear acrylic on the accuracy of these sensors and the
clarity of the camera pictures.
Structural Integrity of Acrylic
One perceived challenge is the strength of acrylic. The strength of acrylic will be
measured through testing. If the measured strength does not meet the standards of a
high powered rocket, supplementary payload designs will be implemented

43
Educational Engagement
Outreach Goals
The education outreach goal is to promote student interest and attitudes toward studies
in science, technology, engineering, and mathematics (STEM). The target population is
area middle school science and mathematics students. Many of the classrooms in the
region serve high numbers of Hispanic and low socio-economic students, who have
historically been underrepresented in the STEM fields. The Department of Labor report
The STEM Workforce Challenge (2007) emphasized that the low engagement of
students from these demographics, who comprise a growing proportion of the college
population, is a major concern to U.S. competitiveness and growth.
The project design is made up of four interrelated initiatives that are increasing in scope
and size. The first three specifically target students in grades 6th
through 8th
(middle
school) while the fourth initiative reaches out to the community at large. The initiatives
specific to middle school students include single class lessons, large group activities,
and field trips to the University. The fourth initiative is our community outreach event.
The team will construct and use math and science lesson plans encouraging students to
pursue STEM fields. All lessons and activities will use best practices, complying with
state and national standards for STEM education for the appropriate grade levels
(http://www.education.ne.gov/science/Documents/National_Science_Standardspdf.pdf,
http://www.education.com/reference/article/Ref_National_Grade_8_Math/). Research
has shown that using hands-on activities and investigations leads to greater student
engagement and deeper understanding of STEM concepts. Lou F., a biology major
pursing teacher certification, is the lead on all educational initiatives.
Implementation of the first three initiatives will require two to four team members to visit
local school STEM classrooms. Lessons will focus on the three laws of Newtonian
motion, incorporating interactive activities to help the students learn the material.
Students will also be given worksheets involving measurements of an actual rocket to
assist with visual learning.
Rockets from the Advanced Rocketry Workshop in Huntsville, Alabama will be used for
demonstrations. The use of real rockets will help maintain student attention and assist
the students in the learning process. Students will compare the motor tube size to the
airframe and measure the size of the fins. They will also learn how to calculate the
thrust-to-weight ratio of a rocket and the proper ratio that should be used when
launching a rocket. In addition the team plans to survey established and effective

44
lessons that are available through the Web and other resources. Other STEM topics
within the school curriculum pertaining to rocketry may also be discussed.
The middle school campus visits will include bottle rocket launches. These
presentations will allow students to launch their own two liter water rockets into the air.
Stations will be set up with a mount such that every student will get a chance to launch
his or her own water rocket.
The community outreach portion, Tarleton Rocket Day, is designed as a follow-up event
to the educational initiatives. Tarleton Rocket Day will bring out the larger community
and the families of these middle school students to experience the science of rocketry in
a fun, engaging environment. The event should improve parental understanding of
science and change their attitudes about STEM careers. This will increase the likelihood
that they will encourage their child’s future pursuits in STEM fields.
Tarleton Rocket Day is tentatively scheduled to take place on the Tarleton State
University campus on March 23, 2013. Tarleton University President Dr. Dottavio has
already expressed his support of this event. Families from nearby surrounding towns
will be invited to come enjoy a day with our rocket team and learn about the principles of
rocketry. While the first three of our four educational initiatives are aimed at middle
school students, there will be no age limit for Tarleton Rocket Day.
Different stations set up all over campus will include water rocket stations for younger
students and a higher powered rocket station for high school students. There will also
be poster stations all over campus to teach students about specific rockets and how
they work, including how to successfully launch a rocket. Students will get to hear
about some of the failures from our past rocket launches and how to prevent them.
There will also be a station to show students how to specifically calculate the
displacement of a rocket. This aids in finding a landed rocket in case sight of it is lost
during descent.
Students will also learn about the NASA Student Launch Initiative (SLI), a project which
would prepare them for university student competitions such as the NASA University
Student Launch Initiative (USLI). This will further stimulate the amount of students
heading towards STEM fields.
Since students will need to be monitored to ensure safe launches, many of the team
members will be present for these activities. A dedicated team member will show the
students how to properly place their rockets on the mount. Each mount will then be
inspected by a team member prior to launch. Under the supervision of a designated

45
team member each student will have the design freedom to paint his or her own rocket
and choose a basic fin shape.
Area schools that have already committed to participation in our educational initiatives
are listed below. Those in the first table are expected to be reached by the first two
initiatives, while those in the second table will likely participate in the second two
initiatives. We expect to reach approximately 2,500 area middle school students.
Comprehensive feedback will be gathered through evaluation surveys given to
participants at each event. All surveys will be compiled and reviewed by the team. An
action plan will be implemented to ameliorate any problems.
Table 8 – Lessons and Group Activities
Middle School Location Expected Number of
Students Reached
Cross Plains Cross Plains, TX 76443 46
Hamilton Junior High Hamilton, TX 76531 38
Henderson Junior High Stephenville, TX 76401 63
Glen Rose Junior High Glen Rose, TX 76403 27
Table 9 – Field Trips and Rocket Day
Middle School Location Expected Number of
Students Reached
St. Stephen’s Episcopal
School
Austin, TX 78746 205
Harmony Science Academy San Antonio, TX 78245 192
Harmony Science Academy Waco, TX 76710 120
Greenhill School Addison, TX 75001 266
Harmony Science Academy Fort Worth, TX 76133 143
Carrollton Christian Academy Carrollton, TX 75010 105
Santo Forte Junior High
School
Azle, TX 76020 418
Westview Middle School Austin, TX 78727 859
Briscoe Junior High School Richmond, TX 77406 1146
Harmony School of Ingenuity Houston, TX 77025 103

46
Table 10 – Educational Engagement Budget
Material Quantity Company Price
5” corner irons 20 Stanley $ 91.80
¾” wood screws 200 Bolt Depot $ 12.56
5” mounting plate 1 none Created
6” spikes 10 Jamar $ 5.00
10” spikes
50 pound
bag
Daybag Outlet $ 64.00
5x¼” carriage bolts 10 Drillspot $ 5.80
¼” nuts 200
Wholesale
Bolts
$ 2.78
3” eyebolt 50 Grainger $ 25.05
¾” washers 20 Grainger $ 5.47
¼” nuts (for eyebolt) 200
Wholesale
Bolts
$ 2.78
¼” washers (for eyebolt) 50 Amazon $ 5.20
#3 rubber stopper – 1
hole
1 WidgetCo $ 0.59
snap-in tubeless tire
valve
50 Grainger $ 67.28
12”x18”x¾” wood board 1 none Created
2 liter plastic bottle 1 Wal-Mart $ 2.67
electric drill & bits 1 none Have
Screwdriver 1 none Have
pliers or open-end
wrench
1 none Have
Vice 1 Wal-Mart $ 19.00
12’ of ¼” cord 1 none Have
Pencil 1 none Have
Total per unit $ 309.98
Total for 10 mounts $ 3,099.80
*Used for bottle rocket launch pad for students in 2 liter water rocket launching activity.

47
Figure 21 – Traveling Estimate
Table 11 – Educational Engagement Travel Budget
Miles Gas (gallons) Cost
282 18.8 $62.04
*Estimate for gasoline priced on 8/1/12 subject to change, fuel based on 15 passenger
van: estimated 15 miles per gallon highway.
Figure 21 shows distance of travel to different schools for educational engagement.
Mileage is calculated from round-trips. Table 12 gives a projected budget for the
planned Tarleton Rocket Day.
Table 12 – Tarleton Rocket Day Budget
Material Quantity Company Price
Poster 10 Office Depot $ 147.90
1/2A6-2 Motor 10 Estes $ 110.10
Blue Streak
Rocket 10 Apogee $ 105.10
Total $ 363.10
0
20
40
60
80
100
120
140
Cross Plains Glen Rose Hamilton Stephenville
M
i
l
e
s
Town
Traveling
Traveling

48
Project Plan
1. Timeline
The Tarleton Aeronautical Team understands that a project of this magnitude requires a
lot of time and dedication. We have organized the following schedule to meet the
requirements of the project, as shown below in Table 13. Gantt Charts detailing the
project timeline follow.
Table 13 - Tentative Meeting Schedule
Sunday Monday Tuesday Wednesday Thursday Friday Saturday
8:00am Sub-
Team
Meetings
and
Flight
Testing
Sub-
Team
Meetings
and
Flight
Testing
9:00am
10:00am
11:00am
12:00pm Team
Meeting
Team
Meeting1:00pm Sub-
Team
Meetings
and
Flight
Testing
2:00pm
3:00pm
4:00pm Sub-Team
Meetings5:00pm Team
Meeting6:00pm
7:00pm
8:00pm

51
2. Budget Plan
A summary of the costs for various aspects of the project has been assembled into
chart format for efficiency and ease of use. Table 14 refers to pertinent information
about the rocket motor, motor casing, as well as motor retainer.
Table 14 – Propulsion Budget
Manufacturer Item Distributor Price
Cesaroni K1440 Apogee $157.94
Aeropack
54mm Motor
Retainer
Apogee $34.00
Cesaroni
54mm 6-Grain
Case
Apogee $105.93
Total Cost of Propulsion System $297.87
Table 15 is a list of all currently proposed payload components and their prices as well
as other pertinent data.
Table 15 – Payload Electronic Components Budget
Purpose Component Price Quantity Total
Flight
Computer
Arduino 2560-R3 $58.95 1 $58.95
Arduino Pro Mini $18.95 2 $37.90
Pressure,
Temperature
BMP180 $15.00 4 $60.00
Humidity HIH4030 $16.95 2 $33.90
Ultraviolent
Radiation
TOCON_ABC3 $148.00 2 $296.00
Solar
Irradiance
TSL2561 $12.50 2 $25.00
Wireless
Transmitter
XBee-PRO XSC
S3B
$42.00 1 $42.00
XBee
Adapter
Parallax 32403 $2.99 1 $2.99
GPS LS20031 $60.00 1 $60.00
Camera VC0706 $42.00 2 $84.00
On Board
Storage
16GB Micro-SD $9.99 3 $29.97

52
Table 15 – Payload Electronics Components Budget (Cont’d)
Micro-SD
Adapter
Adafruit 254 $15.00 3 $45.00
LCD Sparkfun 11062 $34.95 1 $34.95
Power
Supply
U9VLBP $6.65 10 $66.50
Total Price Spent on the Payload Electronic Components $877.16
Approximate cost for proposed ground station design amounts to $2500.
The following budgets have been estimated from the trade selection contained in each
of the above sections and rounded for clarity. The launch day rocket and payload
budget is $3,415 (Figure 24). In accordance with competition guidelines, this amount
does not exceed $5,000. This portion of the budget includes the cost of materials for
the recovery system, payload, vehicle, and motor to be used on launch day. For
research and development (R&D) the proposed budget is $13,800 (Figure 25). This
includes an estimated SMD Payload (R&D) cost of $5,000. The total budget (Figure 26)
includes educational outreach ($3,500) and team travel to competition ($9,200), giving a
total project budget of $29,915.
Figure 24 – Launch Day Rocket and Payload
$1,500.00
44%
$980.00
29%
$600.00
17%
$335.00
10%
Launch Day Rocket and Payload
Recovery
Payload
Vehicle
Motor

53
Figure 25 - Research and Development
Figure 26 - Total Project Budget
$5,000.00
36%
$4,000.00
29%
$3,000.00
22%
$1,800.00
13%
Research and Development
Payload
Motor
Recovery
Vehicle
$13,800.00
46%
$9,200.00
31%
$3,500.00
12%
$3,415.00
11%
Total Project Budget
Research and
Development
Travel
Education
Launch Day Rocket and
Payload

54
3. Funding – Tarleton State University (TSU) and others
 TSU President’s Circle, the Provost’s Office, the Dean of the College of
Science and the Tarleton Foundation: $11,500 (Received 8/29/2012)
 NASA SMD Payload: $2780 (Pending Approval)
 DUNS: 801781865 Cage Code: 5RTD4
 TSU REAL Grants: $1500- $3000 Committed.
 TSU Student Research Grant: $8000-$12000 Committed.
 Local Businesses: $250 Received 7/8/2012.
 Texas Space Grant Consortium: Proposal Submitted to director on
8/27/2012; Awaiting Response
 SpaceX: We are in correspondence with the educational outreach officer
at Space X in McGregor, Texas
4. Community Support Plan
 Parallelus Incorporated
Local electronic company that will review the circuitry and
programming aspects of our design reviews.
 Community Volunteer Engineering Review Board
A panel of expert engineers from local industry will review and
critique our design and documentation.
 Marsha Decker – Technical Editor
English Adjunct Instructor who will review the grammatical aspects
and format of our design reviews.
 Various Small Businesses
Due to the team’s effort, local businesses have expressed interest
in supporting the Tarleton Aeronautical Team.
5. Challenges and Solutions
 Time Management
The project requires a time intensive schedule to complete tasks.
We will organize our time thoroughly. Time also must be delegated
appropriately to ensure completion of the project.
 Budget Management
All cost will be carefully documented and maintained such that we
can monitor budget standing throughout the course of the project.
 Documentation Management

55
On top of community supported reviews we have scheduled team
reviews of all documentation prior to specified deadlines. We will
utilize DropBox, an online storage means, so that all members have
access to documents. Each team member is responsible for the
upkeep of documentation to their specified sub-system.
6. Project Sustainability Plan
By sponsoring a rocket day, the rocket team plans to begin an annual event that will
make a lasting impact on Tarleton’s campus. This should draw interest and
sustainability to the project. We also plan to present at student research symposiums on
campus as well as at affiliated universities. Our success at the CanSat competition last
semester has already sparked interest in the program. Interest in aeronautics at
Tarleton has grown incredibly since the team’s inception.
Deliverables as stated in the SOW
1. A reusable rocket and science or engineering payload ready for the official launch.
2. A scale model of the rocket design with a payload prototype. This model should be
flown prior to the CDR. A report of the data from the flight and the model should be
brought to the CDR.
3. Reports, PowerPoint presentations, and Milestone Review Flysheets due according
to the provided timeline, and shall be posted on the team Web site by the due date.
(Dates are tentative at this point. Final dates will be announced at the time of award.)
4. The team(s) shall have a Web presence no later than the date specified. The Web
site shall be maintained/updated throughout the period of performance.
5. Electronic copies of the Educational Engagement form(s) and comprehensive
feedback pertaining to the implemented educational engagement activities shall be
submitted prior to the FRR.
The team shall participate in a PDR, CDR, FRR, LRR, and PLAR. (Dates are tentative
and subject to change.)
The PDR, CDR, FRR, and LRR will be presented to NASA at a time and/or location to
be determined by NASA MSFC Academic Affairs Office.

56
Appendix A – Resumes
Dustin Neighbors
(806) 319-3723 1073 West Long Street
dustin.neighbors@go.tarleton.edu Stephenville, TX 76401
OBJECTIVE: Obtain a lead position on the Tarleton Aeronautical Team for which I may use my
knowledge, skills, and experience in Engineering and Physics in order to help solve group problems.
PROFESSIONAL QUALIFICATIONS
 Superior management skills, thriving in a professional environment.
 Outstanding conflict resolution skills, dealing with a broad range of personality types and
situations.
 Strong computer skills, experience with various software packages.
 Excellent problem solver and team player with natural leadership abilities
EDUCATION
Bachelor of Science in Engineering Physics—Expected Dec. 2015
Tarleton State University, Stephenville, TX
Minor in Mathematics
GPA—3.25 institutional, 3.25 cumulative
EDUCATIONAL PROJECTS
Project manager / Lead Engineer
International CanSat Competition, Aug 2011 – July 2012
WORK EXPERIENCE
Harvest Foreman
Neighbors Harvesting Inc. May 2007 – May 2010
Duties include but not limited to daily operations management, transportation logistics management,
as well as personnel management.
Maintenance Engineer
Susan Scheafer CPA
Cross Plains, TX July 2010 – present
Duties include building and grounds assessment, performing general maintenance, as well as managing
exterior remodel.
PROFESSIONAL AFFILIATIONS
Sigma Alpha Phi (The National Society of Leadership and Success)

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