University of Evansville Student Launch Team, Project ACE, Will Design, Develop, and Launch a Reusable Rocket

Home , Drogue parachute

University of Evansville

Student Launch

Enclosed: Proposal

Submitted by: 2016 – 2017 Rocket Team Project Lead: David Eilken

Submission Date: September 30, 2016

Payload: Fragile Material Protection

Submitted to: NASA Student Launch Initiative Program Officials Faculty of the UE Mechanical Engineering Program

University of Evansville College of Engineering and Computer Science 1800 Lincoln Avenue; Evansville, Indiana 47722

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Abstract

The following proposal is for the NASA University Student Launch Initiative (USLI). This project is a research based competition that promotes teamwork, academic development, and community outreach [1]. Throughout this project the University of Evansville Student Launch team, Project ACE, will design, develop, and launch a reusable rocket.

Project ACE’s rocket is split into 4 subsections: airframe, propulsion, recovery, and payload.

The airframe will consist of two carbon fiber body tubes, a fiberglass nosecone, and 3 fiberglass fins. The total length of the rocket is projected to be 104”. Drag acting on the airframe will be calculated using OpenRocket and Computational Fluid Dynamics (CFD) and will be validated with wind tunnel testing. The rocket is expected to weigh approximately 25.3 pounds (without the motor) and will be propelled by an Aerotech L850W motor.

Project ACE will use a dual-deployment recovery system with redundant electrical systems to ensure proper execution of the recovery process. Black powder charges will be used to separate the rocket first at apogee, then again at around 1000 feet to deploy the drogue and main parachute, respectively. The team has chosen to design a fragile materials protection system that will be housed in the bow section of the rocket. The payload is designed to have concentric cylinders attached with wire rope isolators and traditional springs in order to absorb and dampen the vibrations of the rocket’s flight.

Major project deliverables and deadlines include the Preliminary Design Review (PDR) on

October 31st, the Critical Design Review (CDR) on January 13th, and the Flight Readiness

Review (FRR) on March 6th. Launch Day for the NASA Student Launch Initiative will be on

April 8th. The anticipated budget for this project is $10,970.00.

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Table of Contents

Abstract ...... ii

List of Figures ...... v

List of Tables ...... vi

Introduction ...... 1

Team Structure ...... 1

Background ...... 2

Project Objectives ...... 3

Facilities & Equipment ...... 4

Safety ...... 6

Safety Plan...... 6

Procedures for NAR/TRA to Perform ...... 8

Pre-Launch Briefing ...... 9

Caution Statements ...... 9

Legal Compliance ...... 10

Purchase, Storage, Transport, and Use of Rocket Motors/Energetic Devices ...... 10

Statement of Understanding and Compliance with Safety Regulations ...... 11

Technical Approach ...... 12

General Vehicle Specifications ...... 12

Projected Altitude ...... 19

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Recovery...... 20

Propulsion...... 22

Ignition System ...... 24

Electronic Payload...... 24

Main Payload...... 25

Areas of Risk ...... 27

Technical Requirements / Countermeasures ...... 29

Project Deliverables ...... 34

Project Schedule...... 35

Project Budget ...... 38

Funding Plan ...... 39

Educational Engagement ...... 40

Sustainability...... 42

Summary ...... 42

References ...... 43

Appendix A - High Powered Rocketry Safety Code ...... 44

Appendix B – OpenRocket Inputs & Data ...... 46

Appendix C – Detailed Task Breakdown ...... 53

Appendix D – Detailed Parts List / Cost Tracking ...... 58

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List of Figures

Figure 1 - Team Structure ...... 2

Figure 2 - Rocket Isometric View ...... 3

Figure 3 - Primary Workspace ...... 4

Figure 4 - Wind Tunnel for testing ...... 5

Figure 5- Annotated Overview of Rocket ...... 12

Figure 6 - Isometric View of 3D Model ...... 13

Figure 7 - Annotated Side View ...... 14

Figure 8 - Fin Drawing ...... 15

Figure 9 - Mass Breakdown of Rocket ...... 16

Figure 10 - Full Body with Dimensions ...... 18

Figure 11 - Cross Section with Dimensions ...... 18

Figure 12 - Simulation Results of Altitude, Vertical Velocity, and Vertical Acceleration .... 19

Figure 13 - Projected dynamics during main parachute deployment ...... 21

Figure 14 - Propulsion Schematic ...... 23

Figure 15 - Cylinder 1, Outer Cylinder ...... 26

Figure 16 - Cylinder 2, Inner Cylinder ...... 26

Figure 17 - Gantt Chart ...... 37

Figure 18 - Budget Breakdown ...... 39

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List of Tables

Table 1 - Important Contacts ...... 1

Table 2 - Risk Assessment ...... 7

Table 3 - Table of Parts Associated with Annontated Side View...... 14

Table 4 - Motor Details ...... 23

Table 5 - Fragile Housing Support Material Matrix ...... 27

Table 6 - Areas of Risk ...... 27

Table 7 - Launch Vehicle Requirements & Countermeasures ...... 30

Table 8 - Recovery Requirements & Countermeasures ...... 33

Table 9 - Payload Requirements & Countermeasures ...... 34

Table 10 - Project Deliverables...... 34

Table 11 - Critical Dates ...... 36

Table 12 - Budget...... 38

Table 13 - Funding Sources ...... 40

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Introduction

Team Structure

Information on the team structure is broken down into main components: important contacts and team members. The important contacts are displayed in Table 1.

Table 1 - Important Contacts

Category Name Contact Information Location

(314)-740-2052 Safety Officer Bryan Bauer - [email protected] (630)-287-1775 Team Lead David Eilken - [email protected] (812)-488-2899 University of Evansville Adult Educator A Dr. David Unger [email protected] Evansville, IN (812)-488-2211 University of Evansville Adult Educator B Dr. Jessie Lofton [email protected] Evansville, IN Laünch Crüe 8991 West, County Road NAR Section (NAR Section - 900 S. Holland, Indiana 519) [2]

Project ACE consists of 8 fourth-year students, 2 third-year students, and 6 second-year students. It is anticipated 6 first year students will join the team in January. Currently, Project

ACE classifies these first-year students as unofficial members. This leads to a team of 22 students. It should be noted that one fourth-year student is working on a volunteer basis. The team is broken down into six subsections – Propulsion, Aerodynamics, Main Payload,

Electronics Payload, Recovery, and Safety/Education. There is a fourth-year student in charge of each subsection. Payloads A & B have an additional fourth-year student to assist in the electronics portion of the design. Each fourth-year student has either a second-year student, third-year student, or both, assisting in the design, building, and testing of the respective

1 | P a g e components. Each of these team members ultimately report to the team lead who works with the adult educators to ensure that the project is progressing adequately. A flow chart of the team breakdown can be seen in Figure 1.

Figure 1 - Team Structure

Background

NASA’s Student Launch Initiative (USLI) is a research based, nationally recognized competition. Project ACE, fielded by the University of Evansville, aims to compete and succeed in this competition. In short, the team proposes to launch a high powered rocket exactly 5,280 feet above ground level with a scientific payload onboard. The path to this competition will involve substantial engineering design, predictive modeling, wind tunnel testing, sub-scale

2 | P a g e testing, and full-scale testing. In addition to this, Project ACE aims to communicate regularly with NASA officials to ensure compliance with competition guidelines, and to expand upon the team’s knowledge of high power rocket design.

The purpose for taking part in this competition is three fold. First, the team wants to bring national recognition to the University of Evansville by competing in such a prominent competition. Secondly, the proposed project will greatly enhance team member’s technical & teaming skills through the myriad of challenges offered by USLI. Finally, the team wants to use this project to provide meaningful scientific data to NASA from payload findings.

Project Objectives

This proposal contains the framework for how Project ACE plans to meet objectives. Both quantitative and qualitative objectives have been set forth for this project. The team’s primary goal is to successfully launch and recover a high power rocket that meets all specified criteria (an isometric view of this rocket is shown in Figure 2.) This includes that the team participates in all

Figure 2 - Rocket Isometric View

3 | P a g e necessary design reviews and report submissions. Project ACE intends to fly between 5,125 feet

& 5,375 feet. The team anticipates being able to shrink this altitude window as more is learned about predicative capabilities. It is also an objective to field a payload that is successful (cargo does not break) and has meaningful scientific data backing it. The data collected should clearly indicate the optimal setup to provide for a successful payload, along with considerations for alternatives.

Qualitative goals involve local community outreach activities & learning. For community outreach, Project ACE intends to provide meaningful interactions with youth in the community that ultimately increases their interest in STEM. Lastly, team members will strive to gain substantial insight on rocketry and the science behind it.

Facilities & Equipment

The primary workspace available is the Energy Systems lab at the University of Evansville.

Figure 3 - Primary Workspace

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The specific area where the rocket will be constructed is shown in Figure 3.

The team has access to the room 24 hours a day, 7 days a week. This lab has room for construction of the rocket, and houses the wind tunnel needed to run the scale model testing. The wind tunnel that will be used for testing is shown in Figure 4.

Figure 4 - Wind Tunnel for testing

The lab is located in the same building as the machine shop, which allows the team access to all of the tools and machines needed to build and assemble the rocket. These machines include, but are not limited to, a CNC Mill, CNC Lathe, band saw and drill press.

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Safety

Safety Plan

The materials used by the team for the creation of the rocket are subject to change depending upon the results obtained from subscale and pre-launch tests, which will focus on the reliability, durability, and functionality of various pieces of the rocket. The major structural materials that will be used for the launch vehicle include Blue Tube, aluminum, carbon fiber, and G10 fiberglass. These materials will be used for components including the motor mount, fins, body, and nosecone. When fabricating these materials, masks will be worn to avoid inhaling the fine dust produced by sanding and cutting operations. Furthermore, nylon will be used for the parachute and shock cords, and epoxy will be used to adhere each section together. To ensure safe handling of these materials, materials safety data sheets (MSDS) will be kept on file in the

Energy Systems Lab so that each team member has access to them at all. For further detail on the hazards associated with each material, a risk assessment can be found in Table 2. In this assessment the probability of each risk occurring is estimated on a low-medium-high scale, and the severity of the risk is measured on a 1-to-4 scale, with 4 being a low risk, and 1 having a severe impact. Lastly, proposed mitigations are also given for each risk to help thwart potential hazards and accidents.

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Table 2 - Risk Assessment

Risk Assessment Risk/Hazard Description Likelihood Severity Proposed Mitigation Inhalation of toxic fumes, or Work in well ventilated accidental ingestion or contact Epoxy High 4 spaces, and wear gloves with skin leading to irritation or when handling the epoxy rash Work in well ventilated Inhalation of dust particles from spaces, and wear a mask Dust Particles sanding or machining operations High 4 when sanding to avoid resulting in breathing problems inhaling dust particles Improper handling of shop tools Ensure proper training for Tools and Machinery or machining operations leading Medium 3 all team members working in Lab to personal injury or destruction with any tool or machinery of equipment Properly transport motor Exposure to rocket fuel in from offsite location to Rocket Propellant contact with skin leading to Medium 2 launch site using proper irritation and burns PPE Gases may be toxic if exposed in areas with inadequate Store in fireproof cabinet to Black Powder ventilation. Also keep away Medium 2 keep away from fire and from open flame, sparks, and high temperatures heat Properly transport motor Motor Improper handling or storage of from offsite location to Handling/Accidental motor resulting in accidental or Low 1 launch site. Ensure proper Ignition unexpected ignition connections before launch Maintain safe distance from launch pad. Have team Failure of motor to ignite and Launch Failure Low 1 mentor/safety officer launch rocket properly inspect rocket on launch pad Failure of the parachute to Parachute Maintain safe distance from deploy leading to freefall of Low 1 Deployment Failure launch pad rocket back to ground

The main facility that the team will utilize when fabricating the rocket is a laboratory space

in the Bowen Labs at the University of Evansville. This room was chosen because of its close

7 | P a g e proximity to the machine shop, which will be used when machining and fabricating various pieces of the rocket. In addition to this, an added benefit of this area is that it houses a ventilation hood. This added safety benefit which will be very helpful when team members are handling epoxy or exposed to debris during the painting and sanding of the rocket.

Bryan Bauer, the team safety officer, will be responsible for overseeing the safety of

University of Evansville students/faculty and all the members of the team throughout the entirety of the project. His responsibilities will include, but are not limited to, working with team members in the selection of materials to ensure the safest components that allow full functionality are being used, assisting and educating team members on the risks and hazards associated with the fabrication or implementation of materials to the rocket, and ensuring all

NAR and FAA safety guidelines, rules, and requirements are observed during subscale and full scale testing at the local rocketry club as well as the competition in Huntsville, Alabama.

Furthermore, before all launches, all team members will be educated on the risks associated with each part of the rocket, and each person will briefed on the risk assessment, detailing the proper procedures to follow in order to mitigate and control these hazards.

Procedures for NAR/TRA to Perform

The University of Evansville Rocketry Team agrees to abide by all rules and regulations set forth by the NAR and TRA for high powered rocketry. Before launch, each team member will be briefed on the high powered rocketry safety regulations, which can be found in their entirety in

Appendix A. Additionally, each team member will be given a copy of the rules to review to ensure safe flight.

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Pre-Launch Briefing

As previously mentioned, all team members will go through a pre-launch briefing to discuss the various risks associated with launch, and how each of these potential hazards can be mitigated to avoid accidents. This meeting will be run by the safety officer, Bryan Bauer, and will be mandatory for all team members to attend who are working on the project due to the breadth of safety information that will be covered beyond the launch day application. In addition to launch-day safety, the presentation will also cover proper lab safety operation procedures, for things such as painting, sanding, or machining, as well as the proper personal protection equipment that goes along with each of these operations. After proper briefing and full understanding by all team members, the registered safety office (RSO) will give his approval to launch.

Overall, the purpose of this safety meeting is to ensure the safety of the team members as well as bystanders, along with the university and all of its equipment. These briefings will take place before each launch and also when deemed necessary by the safety officer. As different phases of the project begin, in particular the building phase, the team will meet to be reminded of the risks associated with the tasks they are about to complete, thus helping avoid any neglectful behavior and accidents. Any team member who does not adhere to the safety plan and rules set forth by the NAR and TRA will not be allowed to participate in any hands-on activity with the rocket.

Caution Statements

The importance of personal protection equipment (PPE) and proper use of all tools will be heavily emphasized in a meeting that will take place before the build phase of the project. In addition to this meeting, a chart will be constructed that will display the proper PPE for each 9 | P a g e operation during the building and fabrication phase. Furthermore, material safety data sheets

(MSDS) will be stored in an accessible place in the workshop so that all team members can access them and review the potential risks of the substance that will be handled before construction.

Legal Compliance

The UE Rocket Team and all members agree to fully comply with all federal, state, and local laws regarding unmanned rocket launches and motor handling. The safety officer will brief all team members on these rules and regulations prior to each launch of the rocket. Throughout the project, the team will attend monthly launches of the NAR Section 519 rocketry club, the Laünch

Crüe, which is located in Holland, Indiana. The team’s relationship with this established NAR chapter will allow for interaction with other experienced individuals in the area of high powered rocketry and will allow for mentoring, guidance, and support. In addition to this, the team plans to run all tests at this facility, which is in compliance with all FAA rules and has the ability to receive a waiver allowing rockets to be launched to 10,000 feet.

Purchase, Storage, Transport, and Use of Rocket Motors/Energetic Devices

The team plans to purchase the rocket motors and all reloads form AeroTech, a licensed rocketry motor vendor. All motors will be purchased by Dr. David Unger, a team mentor who has Level 2 certification with the NAR, and will shipped directly to the University of Evansville in his name. Upon arrival, the motors will be stored in a fireproof case. When testing the rocket, following the pre-launch safety meeting, the safety officer will transport all the motors necessary along with other energetic devices to the launch site in the fireproof case.

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Statement of Understanding and Compliance with Safety Regulations

All team members of the UE Rocket Team will be briefed of the safety rules and regulations and agree to comply with said rules. The team understands that the range safety officer will inspect each rocket before it is flown, and has the final decision as to whether or not the rocket is safe to fly. If the rocket is deemed unsafe to fly by the safety inspector, the team will not fly the rocket until all issues are addressed, and the rocket is re-inspected by the safety officer. The team also recognizes that failure to abide by these rules will result in disqualification and removal from the program.

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Technical Approach

General Vehicle Specifications

The airframe for the rocket is split into 4 main systems: electronic

payload, main payload, recovery, and propulsion. These systems are

depicted on Figure 5. The electronic payload will be housed in the

nosecone. Ballast will be mounted to the bow side of the electronic

payload’s mount. The main payload section will house the fragile

materials payload and will be held in place by a bulkhead on the aft

end and by the nosecone shoulder on the bow end. The recovery

section will house the main parachute, the drogue parachute, and the

recovery electronics bay. The propulsion section will house the thrust

plate, centering rings, inner tube, and fins.

Material considerations for the airframe included fiberglass, carbon

fiber, and Blue Tube. The team intends to use carbon fiber for the body

tubes because it has a higher tensile strength, lower density, and a

lower ductility compared to that of fiberglass or Blue Tube. Flexibility

in a rocket airframe is an unwanted characteristic so a lower ductility is

beneficial. In addition, the higher tensile strength of carbon fiber will

ensure a higher allowable stress than that of fiber glass.

The bulkheads will be made of 0.25” aluminum. They will be

milled on a 3-axis CNC mill. Aluminum will be used to ensure the

Figure 5- Annotated recovery and propulsion sections have strong attachment points. Overview of Rocket 12 | P a g e

Fiberglass and plywood are common choices for bulkheads because they are sturdy, lightweight materials. However, since the design of the rocket is for an L-class motor, weight is not a constraint for material selection. This allows the team to choose a stronger material (aluminum) over fiberglass or plywood.

An isometric exploded view of the 3D model for the rocket can be seen in Figure 6.

Figure 6 - Isometric View of 3D Model

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The material for the fins and nosecone will be G-10 fiberglass because it can be commercially purchased at a low cost. The nosecone will have an ogive profile with a 4:1 length ratio, bought commercially. Additionally, fiberglass fins offer more strength than that of balsa wood. A G-10 fiberglass sheet will be purchased and milled to the proper shape again using the

3-axis CNC mill. Carbon fiber and ULTEM plastic are also materials used for fin design; however, these choices provide little benefit while carrying a significantly higher cost. An overview of the main components housed in the body is shown in Figure 7 and in Table 3.

Figure 7 - Annotated Side View

Table 3 - Table of Parts Associated with Annontated Side View

Part Name Material Part Name Material 1 Ogive Nosecone Fiberglass 9 Engine Block Aluminum 2 Main Payload - 10 Inner Tube Blue Tube 3 Payload Bulkhead Aluminum 11 Bow Centering Ring Aluminum 4 Bow Recovery Bulkhead Aluminum 12 Aft Centering Ring Aluminum 5 Drogue Nylon 13 Thrust Plate Aluminum 6 Recovery Electronics Bay - 14 Fin Fiberglass 7 Main Parachute Nylon 15 Bow Body Tube Carbon Fiber 8 Aft Recovery Bulkhead Aluminum 16 Aft Body Tube Carbon Fiber

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The clipped delta design will be used for the fins with the dimensions provided in Figure 8.

This design offers a large surface area to stabilize the rockets while creating little drag. The fins will have a thickness of 0.25”. As shown, the fins will have a height of 7.5”, a root chord of

11.5”, and a tip chord of 5.8”. This equates to a total surface area of approximately 63 in2.

Figure 8 - Fin Drawing

Values for mass have been estimated for each section of the rocket. The mass breakdown is presented in Figure 9. The total projected rocket weight is 33.5 lbf including motor.

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Mass Breakdown

*All weights lbf

Motor, 8.1, 24% Aerodynamics, 10.1, 30%

Electronic Payload, 1.0, 3%

Recovery, 7.9, 24% Main Payload, 4.1, 12% Propulsion, 2.3, 7%

Figure 9 - Mass Breakdown of Rocket The total length of the rocket is expected to be 104”, using 5.5” diameter body tubes. The lengths of the body tubes and nosecone can be seen in Figure 10.

The lengths of the individual subsections can are included on Figure 11. The nosecone, including shoulder, is 27.25”. The main payload section is 12” long. The recovery section is 34” long. The propulsion section is 22” long. The bow body tube is designed with 2” of open space in order to accommodate unforseen changes in the lengths of the sections housed in the bow body tube.

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The aft body tube is designed to use the full length of the tube (48”) in order to move the center of gravity towards the bow. This will increase the calipers (cal) between the center of pressure (CP) and the center of gravity (CG), thus increasing stability.

The CP is currently located 83.6” aft of the tip of the nosecone. The CG is currently located 68.8” aft of the tip of the nosecone. These are shown on Figure 2. The CG and CP are represented by the blue dot and red dot respectively. This configuration produces a stability of

2.67 cal, which is 0.67 cal higher than required by the NASA USLI 2017 Student Handbook.

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22”

33”

104”

1”

48”

Figure 10 - Full Body with Dimensions Figure 11 - Cross Section with Dimensions

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Projected Altitude

The projected altitude was calculated using OpenRocket, an open source software. This open source software has similarities between commercially available software such as Rocksim.

OpenRocket originated at Helsinki University of Technology as a Master’s Thesis by Sampo

Niskanen [3]. OpenRocket is also used regularly by other SLI teams. The estimated altitude for the rocket is 5,384ft, prior to adding ballast to the simulation. The team will maintain an up-to- date OpenRocket simulation because of the uncertainty in rocket weight. These weights will become more precise during the design phase and exact during the build phase. Currently, the uncertainty only alters the projected altitude by 75 feet in either direction. A plan is to add around 50% of the allowable ballast to lower the projected altitude to exactly 5,280 feet. This will give more flexibility in either direction for fine tuning. See Figure 12 for the simulation

Figure 12 - Simulation Results of Altitude, Vertical Velocity, and Vertical Acceleration

19 | P a g e results for the expected altitude, velocity, and acceleration of the rocket. Inputs for OpenRocket can be found in Appendix B.

Recovery

The launch vehicle will utilize a dual-deployment recovery system with redundant altimeters to ensure that the vehicle lands safely and at a reasonable distance from the launch site. A 12” long coupling tube will house the recovery electronic systems, and will serve to unite the two carbon-fiber body tubes. At apogee, a black powder ejection charge will pressurize the volume above the coupling tube, separating the rocket into two sections and deploying a small, ripstop nylon drogue parachute. When the rocket has descended to an altitude of 1000 feet, a second black powder ejection charge will pressurize the volume below the coupling tube, separating the rocket again and deploying the main parachute, also made of ripstop nylon. All three sections of the rocket will be tethered together using lengths of tubular nylon cord, protected from the ejection charges by flameproof fabric and attached to the bulkheads using eyebolts.

The coupling tube containing the electronics will be sealed on both ends using plywood bulkheads. The electronics will be mounted to a plywood sled secured to the bulkheads by threaded rods. Two independently-powered PerfectFlite StratoLogger CF altimeters will be used as the main and backup recovery altimeters. Each altimeter will be armed independently using a rotary locking switch. Additionally, two igniters will be inserted into each black powder ejection charge (one wired to the main altimeter and one to the backup) to ensure that both parachutes are deployed. Nomex flameproof fabric shields will be used to protect the parachutes from the high- temperature black powder explosions.

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Using the average atmospheric and weather conditions for an April day in Huntsville,

Alabama, a number of OpenRocket simulations were conducted to choose the best combination of parachutes; a 24” drogue parachute and a 72” main parachute will be utilized. This size drogue parachute provides a safe initial descent rate of 75 ft/s, which is suitable for keeping the landing site within 600 ft of the launch site, while also ensuring that the main parachute does not open under excessive speed. The main parachute generates a maximum acceleration of 425 ft/s2 upon deployment, and causes the rocket to impact the ground with a speed of 18.9 ft/s, as shown in Figure 13. It should be noted that Figure 13 presents the same data as Figure 14, but focuses on the parachute deployment portion of the flight. The nose cone of the rocket will have the maximum kinetic energy of any section, impacting the ground with 71 ft-lbf of energy.

Figure 13 - Projected dynamics during main parachute deployment

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Propulsion

With the rocket weighting 25.3 pounds at burnout, a large level 2 motor was needed to reach the projected altitude. After studying the L & K class motors, the K class motors were determined to be insufficient as they consistently projected an altitude well below 5,280ft. The team opted for the L class motor, which OpenRocket predicts to reach just above the mile marker. The L class motor ensures that Project ACE has the flexibility to reach the mile marker even with moderate wind conditions. This motor also gives more design flexibility considering current uncertainty in weight. As seen in Figure 12, the maximum velocity and acceleration are

631 ft/s and 229 ft/s2, respectively; resulting in a Mach number of 0.57.

The motor will have three centering rings and one bulkhead. The centering rings will be made out of either aluminum or G10 fiberglass and the bulk head will be made out of aluminum.

The centering rings along the inner tube will be positioned to allow a tab for the fins to be attached to both the centering rings and the inner tube. The centering ring on the aft end of the motor mount will be 0.75” thick to allow a retaining ring to be attached to secure the motor in place. The inner tube will be a 2.95” (75mm) diameter Blue Tube to hold the motor casing in place. This tube will be 21” long to have enough room for the motor casing. Figure 14 is a diagram of the motor mount and components needed for the propulsion section.

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Bulkhead Centering Rings

Inner Tube and Motor

Figure 14 - Propulsion Schematic

The motor that will be used is an AeroTech L850W. This is the preliminary selection for the rocket. Motor specifications can be found in Table 4.

Table 4 - Motor Details

Manufacturer AeroTech

Make L850W Total Impulse 3695 Ns Weight 8.1 lbs Weight Empty 3.54 lbs Length 20.9 in Diameter 2.95 in Type Reloadable Burn Time 4.24 s Average Thrust 868 N Max Thrust 1185 N

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With the motor selected, analysis will begin using FEA to ensure that the centering rings will not shear from the body and inner tube. The FEA results will later be validated by strain gauges.

Ignition System

According to the 2017 NASA Student Launch Handbook, the High Power Rocket Safety

Code states that the rocket will have an electrical launch system with electrical motor igniters.

These requirements, provided by the NAR, state that the igniters are only to be installed once the rocket is at the launch pad or at an area designated for launch preparations. Other conditions that need to be met include a safety interlock within the launch system that is in series with the launch switch that is only installed once the rocket is ready to launch. The launch switch then must return to the "off" position once the system has been ignited.

The ignition system being used for this project will be a ground-based system that has the ability to ignite an L-Class motor so that the target distance of one mile may be achieved. As mentioned in the Propulsion section of this proposal, the rocket's motor will be an Aerotech

L850W. Based upon the L-Class motor specification, the ignition system will only require 300 feet of cord between the controller and the igniter switch. Launch Crüe local club has agreed to let Project ACE use their standard 12V firing system, which adheres to all requirements.

Electronic Payload

The official scoring altimeter will be an Altus Metrum TeleMega. This altimeter gives the team the ability to track the altimeter live while the rocket is in flight. It has an advanced accelerometer that will allow for detailed flight data which will be used to validate the team’s models of the rocket during testing. The TeleMega also contains the GPS tracking device that is required by NASA.

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The altimeter will be mounted inside the nose cone. It will bolt to a plate so that it can be removed for servicing if necessary. The plate will be attached to mounting brackets inside the nose cone so that the altimeter is in an airtight chamber. This chamber needs to be waterproof to protect the altimeter during test flights in case the rocket happens to land in a pond at the testing site.

To receive the data sent by the TeleMega, an antenna will be used on the ground. An

Arrow 440-3 Yagi Antenna will be connected to a laptop and which will record all data through open source software.

Main Payload

The design for the housing of the fragile material is comprised of two concentric cylinders connected via a spring system. This system can be seen in Figure 15 and Figure 16. Cylinder 1, the outer cylinder, which will have an OD matching the ID of the rocket’s body tube is shown in

Figure 15. This outer cylinder will also be relatively thin to maximize horizontal travel of the inner cylinder. Cylinder 1 will also serve as the mounting portion of the payload by resting between the drogue parachute and the nose cone. Cylinder 2, the inner cylinder, as well as one possible spring system can be found in Figure 16. The spring system mounts both to the outer surface of cylinder 1 (pictured) and inner surface of cylinder 2. Cylinder 1 and the spring system fit within the outer cylinder, thus creating the concentric cylinders. The “springs” labeled (a) are wire rope isolators and springs labeled (b) are traditional linear springs.

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Figure 15 - Cylinder 1, Outer Cylinder Figure 16 - Cylinder 2, Inner Cylinder

Once the mathematical model is complete the number of traditional springs and wire rope isolators will be known. This model will determine the maximum spring constant needed to secure cylinder 2 within cylinder 1 while minimizing the force seen by the fragile material. By using springs, cylinder 2 receives forces gradually, thus reducing the maximum experienced force.

The unknown object(s) will be placed within cylinder 1 which will be filled with a support material that will be determined experimentally. The material will be firm enough to hold the object in place within cylinder 2 so that it cannot bounce and hit the walls of the cylinder, leaving the spring system to reduce the majority of the forces. A matrix of possible support materials has been created and will be tested individually to select the best option. The material matrix can be seen in Table 5.

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Table 5 - Fragile Housing Support Material Matrix

Testing Materials Weight # To Be Tested Egg 1.75 oz 2 Glass Stir Rod .2 oz Glass Sheet N/A N/A Light Bulb 1.1 oz 3 Small Ceramic/Porceline China N/A N/A Contact Support Materials (inside cylinder) Weight per cubic ft. Density Grain Size Liquid or Solid? Vescocity Aerogel N/A N/A N/A N/A Packing Peanuts .2 lb N/A Varies Solid N/A Non-newtonion Fluid N/A N/A N/A Both Varies High Density Foam (Cubes) Varies .93 g/cm^3 As needed Solid N/A Spray in High Density Foam Varies 3 lb /ft^3 N/A Solid N/A

To test the different materials performance, a drop test will be performed at different heights to mimic the different impact forces caused by the main parachute ejection, impact with the ground, and drogue parachute release. The spring system will be designed and built after the mathematical model is finished and the number of springs is selected. Both components of the payload will be first tested separately and then together to isolate any potential issues.

Areas of Risk

In all projects there is inherent risk. Project ACE has prepared a list of areas of risk and proposed countermeasures or mitigations to them.

Table 6 - Areas of Risk

Number Area of Risk Proposed Countermeasure(s) Recovery electronics suffer battery Each altimeter will be powered by a separate 1 failure. 9-Volt battery. Fully charged batteries will be used for each launch. Recovery altimeter suffers an Two PerfectFlite Stratologger CF altimeters 2 electrical failure or pressure will be used to ensure parachute deployment malfunction. at the proper altitudes. Recovery electronics are not armed Rotary locking on-off switches will activate 3 for takeoff. each recovery circuit. LED indicators will be used to show when the system is hot. Igniter fails to trigger ejection Redundant igniters on separate circuits will be 4 charge. used for each ejection charge

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Number Area of Risk Proposed Countermeasure(s) Ejection charge causes damage to Nomex flameproof fabric will be used to 5 parachute or shock cord upon shield the parachutes and shock cords. ignition. Body sections collide after Long lengths of shock cord will tether the 6 parachute deployment. sections together, staggering the sections so that they hang at different lengths. Shock cord tears through body Shock cord will be of sufficient length that the 7 tube upon parachute deployment. nylon will absorb the sudden acceleration.

Ejection charge fails to separate The amount of black powder will be carefully rocket sections. calculated to ensure that the parachute 8 compartment is properly pressurized.

Rocket separates before ejection Threaded nylon shear pins will be used to 9 charge ignition. hold the rocket sections together. Parachute deployment supplies Parachute size will be optimized to minimize extreme acceleration to fragile ground impact speed as well as maximum 10 payload. acceleration. Tubular nylon shock cord will stretch upon deployment to absorb extreme forces.

Drogue ejection force causes main Careful calculations will be used to determine parachute compartment to the number of shear pins required to keep the 11 separate. main parachute compartment attached until desired ejection time. Parachutes/shock cord become Parachutes and shock cord will be carefully 12 tangled during packed to ensure smooth release. deployment/descent. Fragile Material breaks inside Soft insulator material will be on all surfaces 13 Cylinder 1. of inner cylinder with support material holding fragile material in place. Inner cylinder bounces around Concentric cylinder design with spring and 14 within rocket tube. damper system will hold both cylinders in place. Motor being angled in the Motor Centering Rings will be used to ensure that 15 Mount the motor is concentric with the center of the rocket Motor falls out of the rocket after A retention system will be attached to the aft 16 fuel is used centering ring to ensure the motor stays in the motor mount

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Number Area of Risk Proposed Countermeasure(s) Motor’s impulse causes it to shoot An aluminum engine block will be placed in 17 through the bow side of the inner front of the motor mount to ensure the motor tube does not shoot through Centering Ring shears from the The centering rings will be made from 18 impulse of the motor during flight aluminum to withstand the shearing forces Centering rings fails due to fatigue Because of aluminum does not have an 19 infinite fatigue life, a redundant centering ring is used in the motor mount to keep the motor centered in the rocket Centering is either too small in the G5000 Rocketpoxy will be used to close any outer diameter dimension or comes gap between the centering ring and the body 20 loose from motor impulse and tube and to secure the centering ring from vibration coming loose Deflection in the airframe due to Carbon fiber will be used for the airframe as it 21 stress from the recovery process on has the largest tensile strength and the lowest the bulkheads ductility of all materials considered Damage to the fins or nosecone A spare fin will be machined and further spare 22 upon landing fins and a spare nosecone will be accounted for in the budget Rail button fails during launch Proper installation and alignment of rail 23 buttons to avoid binding in the launch rails Cracks in the airframe due to A pre-launch inspection of the rocket will be 24 storage and transportation of performed to check for cracks in the airframe rocket Gaps between airframe and All components will be purchased from recovery coupler or nosecone rocketry suppliers to ensure minimal 25 tolerances and a precision fit; a pre-launch inspection of the rocket will be performed to check for gaps Collision with a bird Carbon fiber will be used for the airframe as it 26 has the largest tensile strength in order to withstand impact forces and in-flight stresses Official Altimeter fails The altimeter will be tested extensively prior 27 to launch to ensure it can survive the flight.

Technical Requirements / Countermeasures

NASA declares all requirements for the launch vehicle, recovery system, and payload in their

2017 USLI Student Handbook. All requirements have been summarized in Table 7, Table 8, and

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Table 9. The requirements for the launch vehicle, along with the countermeasures associated are located in Table 7. Requirements for the recovery system and its respective countermeasures are shown in Table 8. A description of payload requirements and the proposed design features to satisfy its requirements are presented in Table 9.

Table 7 - Launch Vehicle Requirements & Countermeasures

Aerodynamics Handbook Summarized Requirement Proposed Feature to Satisfy Requirement Number 1.1 The vehicle shall deliver the The rocket team will utilize OpenRocket, science or engineering payload to RockSim, CFD, & test flight data to achieve an apogee altitude of 5,280 feet an accurate prediction of altitude. above ground level (AGL). 1.2 The vehicle shall carry one commercially available, The rocket will house a Atlus Metrum barometric altimeter for recording TeleMega altimeter in the nosecone to the official altitude used in record the official altitude used in determining the altitude award determining the altitude award winner. winner. 1.3 All recovery electronics shall be Batteries & altimeter will be purchased powered by commercially from online rocketry sources. available batteries. 1.4 The launch vehicle shall be designed to be recoverable and The rocket is reusable in design because we reusable. Reusable is defined as are using a motor that has refuels that can being able to launch again on the be reloaded into the motor under same day without repairs or supervision. modifications. 1.5 The launch vehicle shall have a maximum of four (4) independent sections. An independent section is The launch vehicle will have 3 independent defined as a section that is either sections: the aft body tube, the bow body tethered to the main vehicle or is tube and nosecone, and the coupler. recovered separately from the main vehicle using its own parachute.

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Aerodynamics Handbook Summarized Requirement Proposed Feature to Satisfy Requirement Number 1.6 The launch vehicle shall be limited The launch vehicle shall be a single stage. to a single stage. 1.7 The launch vehicle shall be capable of being prepared for The launch vehicle will be designed with an flight at the launch site within 4 efficient and quick to construct design that hours, from the time the Federal requires fewer than 4 hours to prepare. Aviation Administration flight waiver opens. 1.8 The launch vehicle shall be capable of remaining in launch- The launch vehicle design will ensure all ready configuration at the pad for components have a life of greater than 1 a minimum of 1 hour without hour without loss of functionality. losing the functionality of any critical on-board component. 1.9 The launch vehicle shall be capable of being launched by a The ignition system will be using a 12 volt standard 12-volt direct current direct current firing system. firing system. 1.10 There will be no external circuity for the The launch vehicle shall require no ignition system because it will be a ground external circuitry or special ground based ignition system being placed support equipment to initiate underneath the rocket before launch with launch (other than what is 300 ft of cord between the igniter and the provided by Range Services). controller. 1.11 The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant (APCP) which is The motor being used is a solid fuel motor approved and certified by the from AeroTech. The motor is the L850W. National Association of Rocketry (NAR), Tripoli Rocketry Association (TRA), and/or the Canadian Association of Rocketry (CAR).

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Aerodynamics Handbook Summarized Requirement Proposed Feature to Satisfy Requirement Number 1.12 Pressure vessels on the vehicle No pressure vessels will be used. shall be approved by the RSO. 1.13 The total impulse provided by a The motor will produce an impulse of 3695 Middle and/or High School launch N-s which is below the specified total vehicle shall not exceed 5,120 impulse that is allowed. Newton-seconds (L-class). 1.14 The launch vehicle shall have a The launch vehicle will have a static minimum static stability margin of stability margin of 2.67. 2.0 at the point of rail exit. 1.15 The rocket team will utilize OpenRocket, The launch vehicle shall accelerate RockSim, CFD, & test flight data to achieve to a minimum velocity of 52 fps at an accurate prediction of minimum velocity rail exit. at rail exit. 1.16 All teams shall successfully launch A subscale model with comparable weights, and recover a subscale model of lengths, and masses will be launched prior their rocket prior to CDR. to the CDR. 1.17 All teams shall successfully launch and recover their full-scale rocket The project schedule will ensure a full-scale prior to FRR in its final flight con- rocket launch occurs before the FRR. figuration. 1.18 The rocket will have 3 bolts holding the nosecone to the bow body tube and shear Any structural protuberance on the pins holding the coupler to the bow and aft rocket shall be located aft of the body tubes. These structural protuberances burnout center of gravity. are all located aft of the burnout center of gravity 1.19 The launch vehicle will follow all Vehicle Prohibitions prohibitions laid out in section 1.19 of the 2017 SL NASA Student Handbook.

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Table 8 - Recovery Requirements & Countermeasures

Recovery Handbook Summarized Requirement Proposed Feature to Satisfy Requirement Number 2.1 Vehicle must deploy a drogue Dual-deployment altimeters will be parachute at apogee, followed by a programmed to fire ejection charges at main parachute at a much lower apogee and at ~1000 feet. altitude. 2.2 A successful ground ejection test Multiple ejection tests will be conducted for both parachutes must be prior to sub- and full-scale launches. conducted prior to sub- and full- scale launches. 2.3 No part of the launch vehicle may Parachute sizes will be optimized to have a kinetic energy of greater minimize kinetic energy at ground impact. than 75 ft-lbf at landing. 2.4 Recovery electrical circuits must Recovery electronics will be located in a be independent of payload circuits. separate, shielded coupler. 2.5 Recovery system must include Two PerfectFlite Stratologger CF altimeters redundant, commercial altimeters. will be used. 2.6 Motor ejection cannot be used for Black powder ejection charges will be used primary or secondary deployment. to eject parachutes. 2.7 Each altimeter must be armed by a Locking rotary switches and LED indicators dedicated switch accessible from will be used to confirm the state of the the rocket exterior. recovery electronics. 2.8 Each altimeter must have a Separate 9-Volt batteries will be used to dedicated power supply. power the altimeters. 2.9 Each arming switch must be Locking rotary switches will be used to arm lockable to the “ON” position. each altimeter. 2.10 Removable shear pins must be Threaded nylon shear pins will be used to used to seal the parachute seal the parachute compartments. compartments. 2.11 Tracking device(s) must transmit All parts of the launch vehicle will be the position of any parts of the tethered together; position will be launch vehicle to a ground transmitted via a flight computer in the nosecone. receiver. 2.12 Recovery system electronics must Recovery electronics will be located in a not be adversely affected by any separate, shielded coupler. other on-board electronics.

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Table 9 - Payload Requirements & Countermeasures Payload Handbook Summarized Requirement Proposed Feature to Satisfy Requirement Number 3.4.1 Design container capable of Concentric cylinders with spring system and protecting an unknown object of support material unknown size and shape. 3.4.1.2 Object must survive duration of Concentric cylinders with spring system and flight support material 3.4.1.4 Once the object is obtained, it Support material within cylinder 1 that must be sealed in its housing until allows object to be inserted and not spill after the launch and no excess any material such as a high viscosity fluid material may be added after or malleable solid. receiving the object.

Project Deliverables

All intermediate and final deliverables are listed in Table 10, along with due dates. These deliverables include all tangible prototypes/models, all activities such as participation in the educational engagement requirement, and all reports. Reports and presentations, such as the

Preliminary Design Review, are listed as one combined deliverable in Table 10.

Table 10 - Project Deliverables

Number Description Due Date 1 A reusable rocket with the required payload system ready for official Apr. 5, 2017 launch shall be provided. 2 A scale model of the rocket design with a payload prototype shall be Jan. 13, 2017 flown before the CDR & flight data shall be brought to the CDR. 3 The team website must be maintained & updated throughout the period - of performance.

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4 Reports, PDF slideshows, & Milestone Review Flysheets will be completed & posted to the team website by specified due dates (see - below). 5 Electronic copies of the Educational Engagement forms & any lessons Mar. 6, 2017 learned will be submitted prior to FRR & within two weeks of the event. 6 Submitted Proposal Oct. 3, 2016 7 Participation in PDR (Preliminary Design Review) Oct. 31, 2016 8 Submitted Design Report Dec. 2, 2016 9 Participation in CDR (Critical Design Review) Jan. 13, 2017 10 Participation in FRR (Flight Readiness Review) Mar. 6, 2017 11 Participation in LRR (Launch Readiness Review) Apr. 6, 2017 12 Participation in PLAR (Post Launch Assessment Review) Apr. 24, 2017

Project Schedule

Both NASA and the University of Evansville set numerous deadlines throughout the year.

These deadlines include submission dates for reports and presentations. Other major dates such as the final competition and when scale models must be launched are also defined. The team classified these as “Critical Dates”. Each of the critical dates can be seen in Table 11. In addition to University of Evansville due dates and NASA due dates, Project Ace has included a

“Team Due Date” column. These are the dates that the team holds themselves to in an effort to mitigate any risk of late submissions. The scale launch dates listed in Table 11 will likely prove to be the most important, as they are dependent on availability of the launch site. This site only has launches once a month, so it is crucial that the team is prepared when such dates come around.

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Table 11 - Critical Dates

Due Date Activity NASA U.E. Team Project Kickoff Aug. 15, 2016 - - General Motor Selection/Data Sept. 30, 2016 - Sept. 16, 2016 Informal Design Sketches - Sept. 21, 2016 Sept. 19, 2016 Proposal Sept. 30, 2016 Oct. 3, 2016 Sept. 27, 2016 Motor Selection/ Data Oct. 31, 2016 Oct. 7, 2016 Proposal Presentation - Oct. 24, 2016 Oct. 22, 2016 PDR Report Oct. 31, 2016 - Oct. 26, 2016 PDR Flysheet Oct. 31, 2016 - Oct. 26, 2016 PDR Presentation Oct. 31, 2016 - Oct. 28, 2016 Sub-Scale Launch Motor Selection - - Nov. 30, 2016 Sub-Scale Launch - - Dec. 11, 2016 Design Report - Dec. 2, 2016 Nov. 29, 2016 Motor Mount Design/ FEA Jan. 13, 2017 - Nov. 30, 2016 All Structural elements FEA Jan. 13, 2017 - Nov. 30, 2016 CDR Report Jan. 13, 2017 - Dec. 9, 2016 CDR Flysheet Jan. 13, 2017 - Dec. 9, 2016 CDR Presentation Jan. 13, 2017 - Jan. 11, 2017 Full Scale Launch - - Feb. 12, 2017 FRR Report Mar. 6, 2017 - Mar. 1, 2017 FRR Flysheet Mar. 6, 2017 - Mar. 1, 2017 FRR Presentation Mar. 6, 2017 - Mar. 3, 2017 Competition Apr. 5, 2017 - Apr. 5, 2017 LRR Report Apr. 6, 2017 - Apr. 3, 2017 PLAR Report Apr. 24, 2017 - Apr. 21, 2017

From the critical dates the team was able to create a Gantt chart – shown in Figure 17. The

Gantt chart helps visualize the schedule of the project and enabled the team to adjust the scope accordingly. It was known that deadlines could not be adjusted, so certain aspects of the project had to be adjusted to ensure overall completion. This, for example, included changing from a variable-drag to a projected altitude targeting system. An extensive list of team and individual tasks is displayed in Appendix C.

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Period: 4 Plan Project ACE

PLAN PLAN ACTIVITY T/M Responsible START DURATION WEEK (Week 1 ends September 4th, 2016) 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 Proposal David 1 4 Preliminary Design Report David 6 4 PDR Presentation David 8 2 Interim Design Report David Critical Design Report David 11 5 CDR Presentation David 15 5 Flight Readiness Report David 23 4

Reporting FRR Presentation David 26 2 Project Final Report David Launch Readiness Review David 29 4 Post Launch Assesment David 33 2 Budget Creation David 1 1 Website Creation Bryan 1 3 Motor Type Selection Andrew G 1 3 Motor Mount Design Andrew G 1 5 Rocksim Model Andrew G 3 18 Body Component Selection Torsten 1 6 3D Rocket Model Torsten 4 11 CFD Model Torsten 15 6 Payload A Design Justin 1 9

Design Payload B Design Braden 1 11 Data Acquisition Design David 3 6 Data Transmission Design David 3 6 Design of Recovery System Andrew S 1 9 Design Tracking System Andrew S 9 4 Scale Model Design Torsten 10 3 Design Education Activity Bryan 1 8 Propulsion Construction Andrew G 10 6 Body Construction Torsten 11 11 Payload A Construction Justin 9 14

Build Payload B Construction Braden 12 11 Recovery System Construction Andrew S 9 12 Data Systems Construction David 8 13 Scale Model Construction Torsten 12 3 Scale Model Test Bryan 14 2 Motor Testing Bryan 11 10 Parachute Testing Bryan 23 6

Testing Wind Tunnel Testing Bryan 23 9 Recovery Testing Andrew S 21 7 Educational Engagement Bryan Preparation for Competition David 31 1 Competition David 32 1

Figure 17 - Gantt Chart

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Project Budget

Project ACE was able to create an accurate budget by requiring each sub-section lead to maintain a detailed component list. This list, located in Appendix , contains a description, quantity, and cost of each item on the rocket. Also included in the table are projected costs for the sub-scale rocket, educational engagement activities, travel, and administrative expenses.

From the projected costs in the components list, a variable contingency percentage was implemented to each sub-section. These contingencies ensure that the team has funds for unforeseen costs. Contingency percentages are higher for risk filled sub-sections than for low- risk sub-sections. For example, the aerodynamics sub-section has a 33% contingency for purchase of unforeseen components & risk of damage; while the recovery section has a 7% contingency due to the low chance of costly components being damaged. The official budget with these contingencies built in can be found in Table 12. A quick visual to the impact each sub-section has on the entire budget is provided in Figure 18.

Table 12 - Budget

Item Forecasted Amount Percent of Total Operating $ 150.00 1% Travel / Lodging $ 3,930.00 36%

Launch Pad $ 220.00 2% Aerodynamics (Body) $ 1,400.00 13% Propulsion $ 1,550.00 14% Main Payload $ 500.00 5% Electronic Payload $ 670.00 6%

Recovery $ 1,050.00 10% Scale Model $ 1,200.00 11% Educational Engagement $ 300.00 3% Total $ 10,970.00

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3% 1%

11%

10% 36%

14% 2% 13%

Operating Travel / Lodging Launch Pad Aerodynamics (Body) Propulsion Main Payload Electronic Payload Recovery Scale Model Educational Engagement

Figure 18 - Budget Breakdown

Funding Plan

The $10,970 necessary to fund the 2016-2017 University of Evansville Student Launch

Project ACE team will be acquired through the three following University connections, Dr.

David Unger (Indiana Space Grant Award), University of Evansville Student Government

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Association (SGA), and the University of Evansville’s College of Engineering and Computer

Science. The team will be using a grant of $5,000 to help fund the project, thanks to the Indiana

Space Grant Consortium & Dr. David Unger. Project ACE will also be approaching the

University of Evansville’s SGA to request a donation of $3,930 to fund projected costs of lodging and travel when attending competition this spring. Lastly the team will be striving for a donation of $2,040 from the University of Evansville College of Engineering and Computer

Science to help reach the predicted budget. These funding sources can be seen in Table 13. The

University of Evansville College of Engineering and Computer Science will also be dedicating a room in the Bowen Engineering Labs for the team to construct and store the Rocket.

Table 13 - Funding Sources

Funding Amount Remaining NASA Grant $ 5,000.00 $ 5,970.00 SGA $ 3,930.00 $ 2,040.00 U.E. ENGR $ 2,040.00 $ - Total $ 10,970.00 $ -

Educational Engagement

One of the requirements of this project is that the team will be required to engage at least 200 participants in science, technology, engineering, and mathematics (STEM) activities. These activities should be hands-on, educational, and geared towards children in grades K-12. In each of these activities, only those individuals that the group has direct interaction with will be counted to the 200-person quota. After the completion of every event, a report will be completed and submitted to NASA detailing the STEM-related activities preformed, and the number of members that participated in the event. These documents will be used to monitor the team’s

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For the first educational engagement activity, the team plans on running a booth at an event promoting STEM-related topics, which will take place at a local high school. The plan is to have two experiments set up that will allow the students who visit the booth to explore various facets of engineering through hands-on interaction. One of the experiments will allow students to build and experiment with snap circuits, and the other section will allow visitors to interact with hydraulic robot arms. In each of these stations, students will gain hands-on experience while the basic engineering operations for each mechanism/experiment is explained, thus allowing kids to understand how each experiment worked and related to engineering. Through these activities, the team estimates it will be able to directly reach roughly 50 high school students interested in

STEM.

In addition to this, for future educational activities, the team plans to host various STEM- related events at the university. These events, such as Engineering Explorers, allow kids of various ages to explore engineering principles through hands on experiments such as building tennis ball launchers to throw a ball a certain distance, creating small-scale rockets out of household items, and constructing a bridge from toothpicks and marshmallows to hold a certain amount of weight. Overall, from all of these activities, the team hopes to reach many students of various ages in order to promote STEM-related topics, with the hope that these interactions will encourage students to pursue careers in science, technology, engineering, and mathematics fields.

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Sustainability

The team plans to reach out to the University of Evansville and other local partners to acquire grant money and expertise. The team greatly values these partnerships and it intends to maintain the relationships that they’ve already built for many years to come. This will increase the likelihood that the team’s funding stream will be renewable each year. Since members of the team will change from year to year, the team would like to utilize the previous success of past members and the newfound interest of first time members to increase the performance of the project.

Through promotion and interaction with students in the community, the team hopes that the reach of this project will ultimately increase interest in space programs and other STEM related topics, leading to more new members. High schools and elementary schools will continue to be the main areas of educational emphasis in order to stir the motivations of young and old students. The current team, as well as future teams, plan to join with the University of

Evansville’s Engineering Department to run various educational engagement activities to engage local youth in informative rocketry activities.

Summary

Project ACE’s current design will provide the framework for a successful project. The brainstorming, down selecting, and design hours each sub-section has received, coupled with early integration of sections via CAD & OpenRocket, instills confidence in the projected outcomes. With the payload, the team is confident that meaningful scientific data and a viable option for housing fragile materials can be provided for NASA & future teams. For the

University of Evansville, the national recognition this project receives will be highly beneficial

42 | P a g e as it produces publicity in the community and towards prospective students. The team’s subscale and full-scale rocket will be able to be displayed in the atrium of the engineering building – creating a talking point for anyone who walks through. Lastly, work on this project will create a solid foundation for the students who continue the project in the future.

References

[ G. C. M. S. F. Center, "2017 NASA's Student Launch," 10 08 2016. [Online]. Available:

1] http://www.nasa.gov/sites/default/files/atoms/files/nsl_un_2017_web.pdf. [Accessed 11 08

2016].

[ C. Ring, "Launch Crue," 27 9 2016. [Online]. Available: https://www.launchcrue.org/.

[ S. Niskanen, Development of an Open Source model rocket simulation software,

3] Helsinki: HELSINKI UNIVERSITY OF TECHNOLOGY, 2009.

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Appendix A - High Powered Rocketry Safety Code High Powered Rocketry Safety Code

High Powered Rocket Safety Code National Association of Rocketry (NAR) – Effective August 2012

1. Certification. I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing. 2. Materials. I will use only lightweight materials such as paper, wood, rubber, plastic, fiberglass, or when necessary ductile metal, for the construction of my rocket. 3. Motors. I will use only certified, commercially made rocket motors, and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer. I will not allow smoking, open flames, nor heat sources within 25 feet of these motors. 4. Ignition System. I will launch my rockets with an electrical launch system, and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area. My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch, and will use a launch switch that returns to the “off” position when released. The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position. 5. Misfires. If my rocket does not launch when I press the button of my electrical launch system, I will remove the launcher’s safety interlock or disconnect its battery, and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket. 6. Launch Safety. I will use a 5-second countdown before launch. I will ensure that a means is available to warn participants and spectators in the event of a problem. I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table. When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations. I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable. When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127. 7. Launcher. I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight, and that is pointed to within 20 degrees of vertical. If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher. I will use a blast deflector to prevent the motor’s exhaust from hitting the ground. I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table, and will increase this distance by a factor of 1.5 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant. 8. Size. My rocket will not contain any combination of motors that total more than 40,960 N- sec (9208 pound-seconds) of total impulse. My rocket will not weigh more at liftoff than

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one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch. 9. Flight Safety. I will not launch my rocket at targets, into clouds, near airplanes, nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site, and will not put any flammable or explosive payload in my rocket. I will not launch my rockets if wind speeds exceed 20 miles per hour. I will comply with Federal Aviation Administration airspace regulations when flying, and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site. 10. Launch Site. I will launch my rocket outdoors, in an open area where trees, power lines, occupied buildings, and persons not involved in the launch do not present a hazard, and that is at least as large on its smallest dimension as one-half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet, whichever is greater, or 1000 feet for rockets with a combined total impulse of less than 160 N-sec, a total liftoff weight of less than 1500 grams, and a maximum expected altitude of less than 610 meters (2000 feet). 11. Launcher Location. My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour, not including traffic flow related to the launch. It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site. 12. Recovery System. I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again, and I will use only flame-resistant or fireproof recovery system wadding in my rocket. 13. Recovery Safety. I will not attempt to recover my rocket from power lines, tall trees, or other dangerous places, fly it under conditions where it is likely to recover in spectator areas or outside the launch site, nor attempt to catch it as it approaches the ground.

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Appendix B – OpenRocket Inputs & Data OpenRocket Inputs & Data

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Appendix C – Detailed Task Breakdown Detailed Task Breakdown

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Estimated

Apr. Apr. 3, 2017

Oct. 5, 2016 Oct.

Mar. 1, 2017 Mar.

Jun. Jun. 1, 2016

Mar. 3, 2017 Mar.

Mar. 1, 2017 Mar.

Nov. 2, 2016 Nov.

Jun. Jun. 1, 2016

Sep. 4, 2016 Sep.

Dec. 9, 2016

Sept. 9, 2016 Sept.

Oct. 28, 2016 28, Oct.

Oct. 26, 2016 26, Oct.

Sept. 6, 2016 Sept.

Nov. 30, 2016 30, Nov.

Jan. 11, 2017 Jan. 11,

Apr. 21, 2017 Apr. 21,

Apr. 12, 2017 Apr. 12,

Jan. 18, 2017 Jan. 18,

Aug. 28, 2016 28, Aug.

Aug. 19, 2016 19, Aug.

Sep. 16, 2016 16, Sep.

May. 16, 2016 16, May.

Sept. 21, 2016 21, Sept.

Sept. 15, 2016 15, Sept.

Sept. 14, 2016 14, Sept.

Sept. 16, 2016 16, Sept.

Sept. 27, 2016 27, Sept.

End Date End

1-Jul

Start Date

Oct. 5, 2016 Oct.

Oct. 1, 2016 Oct.

Feb. 1, 2017 Feb.

Mar. 3, 2017 Mar.

Jan. Jan. 1, 2017

Feb. 1, 2017 Feb.

Jan. Jan. 1, 2017

Nov. 2, 2016 Nov.

May. 1, 2016 May.

Sept. 5, 2016 Sept.

Sept. 1, 2016 Sept.

Oct. 28, 2016 28, Oct.

Oct. 20, 2016 20, Oct.

Oct. 28, 2016 28, Oct.

Sept. 1, 2016 Sept.

Jan. 11, 2017 Jan. 11,

Apr. 14, 2017 Apr. 14,

Apr. 10, 2017 Apr. 10,

Aug. 15, 2016 15, Aug.

Aug. 25, 2016 25, Aug.

Feb. 25, 2017 25, Feb.

Mar. 15, 2017 15, Mar.

Feb. 28, 2017 28, Feb.

Aug. 15, 2016 15, Aug.

May. 25, 2016 25, May.

Sept. 15, 2016 15, Sept.

Sept. 14, 2016 14, Sept.

Sept. 12, 2016 12, Sept.

Ayman

Jacob

Derek

Sophomore

Dylan

Kaylee

Total

Cody

Craig

Junior

Total

Estimated Hours Estimated

Bryan

Braden

Torsten

Justin

Senior

Andrew S. Andrew

Andrew G. Andrew

David

Total

Person

Andrew

David

Justin

David

Bryan

David

Responsible

Task*

2.3.4.4 Redesign 2.3.4.4

2.3.4.6 Launch Switch w/ Returning to "off" Position "off" to Returning w/ Switch Launch 2.3.4.6

2.3.4.5 Igniter Installation Hatch Design Hatch Installation Igniter 2.3.4.5

2.3.4.4 Ignition Safety Interlock Design Interlock Safety Ignition 2.3.4.4

2.3.4.3 Ignition Fastening Design Fastening Ignition 2.3.4.3

2.3.4.2 Ignition Placement Ignition 2.3.4.2

2.3.4.1 Ignition Research Ignition 2.3.4.1

2.3.4 Ignition Design Ignition 2.3.4

2.3.2.1 Collaboration with Aerodynamics with Collaboration 2.3.2.1

2.3.2 Rear Aerodynamics Design Aerodynamics Rear 2.3.2

2.3.1.3 Redesign 2.3.1.3

2.3.1.2 Motor Placement Motor 2.3.1.2

2.3.1.1 Motor Fastening Design Fastening Motor 2.3.1.1

2.3.1 Motor Mount Design Mount Motor 2.3.1

2.3 Conceptual Model Creation Model Conceptual 2.3

2.2.2 Simulated Thrust Curve Thrust Simulated 2.2.2

2.2 Mission Performance Predictions Performance Mission 2.2

2.1.5 Select projected motor projected Select 2.1.5

2.1.4 Caclulate projected Altitude projected Caclulate 2.1.4

2.1.3 Motor Elimination Motor 2.1.3

2.1.2 Motor Comparision Motor 2.1.2

2.1.1 Motor Research Motor 2.1.1

2.1 Motor Type Selection (General, Proposal Level) Proposal (General, Selection Type Motor 2.1

2 Propulsion 2

1.22 Recruiting 1.22

1.21.1 Meeting Planning Meeting 1.21.1

1.21 Meetings 1.21

1.20 HAM Radio Liscence Liscence Radio HAM 1.20

1.19.2 Weekly Time Card Compiling Card Time Weekly 1.19.2

1.19.1 Time Card Format Creation Format Card Time 1.19.1

1.19 Time Cards Time 1.19

1.18 Purchasing 1.18

1.17 Meet Course Deliverables Course Meet 1.17

1.16.1 Local Rocket Meetings Rocket Local 1.16.1

1.16 Travel Arrangements for Testing & Competition & for Testing Arrangements Travel 1.16

1.15 Create and Maintain Website Maintain and Create 1.15

1.14 Integration of Subsections Integration 1.14

1.13 Create Detailed Task Breakdown Task Detailed Create 1.13

1.12 Create Schedule Create 1.12

1.11.1 Budget Monitoring Budget 1.11.1

1.11 Create Budget Create 1.11

1.10 Orchestrate Meetings Orchestrate 1.10

1.9.2 Flight Readiness Review Practice Review Readiness Flight 1.9.2

1.9.1 Create Flight Readiness Review Presentation Review Readiness Flight Create 1.9.1

1.9 Flight Readiness Review (Presentation) Review Readiness Flight 1.9

1.8.2 Critical Design Review Practice Review Design Critical 1.8.2

1.8.1 Create Critical Design Review Presentation Review Design Critical Create 1.8.1

1.8 Critical Design Review (Presentation) Review Design Critical 1.8

1.7.2 Preliminary Design Review Practice Review Design Preliminary 1.7.2

1.7.1 Create Preliminary Design Review Presentation Review Design Preliminary Create 1.7.1

1.7 Preliminary Design Review (Presentation) Review Design Preliminary 1.7

1.6.2 Compile Post Launch Assesment Launch Post Compile 1.6.2

1.6.1 Create Standards for Post Launch Assesment Launch Post for Standards Create 1.6.1

1.6 Post - Launch Assesment (Report) Assesment - Launch Post 1.6

1.5.2 Compile Lanch Readiness Review Readiness Lanch Compile 1.5.2

1.5.1 Create Standards for Launch Readiness Review Readiness Launch for Standards Create 1.5.1

1.5 Launch Readiness Review Readiness Launch 1.5

1.4.2 Compile Flight Readiness Review Readiness Flight Compile 1.4.2

1.4.1 Create Standards for Flight Readiness Review Readiness Flight for Standards Create 1.4.1

1.4 Flight Readiness Review (Report) Review Readiness Flight 1.4

1.3.2 Write Critical Design Review Design Write Critical 1.3.2

1.3.1 Create Standards for Critical Design Review Design for Critical Standards Create 1.3.1

1.3 Critical Design Review (Report) Review Design Critical 1.3

1.2.2 Write Preliminary Design Review Design Write Preliminary 1.2.2

1.2.1 Create Standards for Preliminary Design Review Design for Preliminary Standards Create 1.2.1

1.2 Preliminary Design Review (Report) Review Design Preliminary 1.2

Write Proposal 1.1.2

1.1.1 Create Standards for Proposal Standards Create 1.1.1 1.1 Proposal (Report) / Research (Report) Proposal 1.1 1 Project Management Project 1 54 | P a g e

Apr. Apr. 2, 2017

Oct. 9, 2016 Oct.

Oct. 7, 2016 Oct.

Mar. 5, 2017 Mar.

Dec. Dec. 4, 2016

Dec. Dec. 5, 2016

Dec. Dec. 1, 2016

Oct. 26, 2016 26, Oct.

Jan. 22, 2017 Jan. 22,

Nov. 20, 2016 20, Nov.

Nov. 30, 2016 30, Nov.

Jan. 15, 2017 Jan. 15,

Sep. 30, 2016 30, Sep.

Feb. 12, 2017 12, Feb.

Sept. 16, 2016 16, Sept.

Sept. 29, 2016 29, Sept.

Sept. 25, 2016 25, Sept.

Sept. 21, 2016 21, Sept.

Sept. 14, 2016 14, Sept.

Sept. 30, 2016 30, Sept.

Sept. 21, 2016 21, Sept.

Sept. 14, 2016 14, Sept.

1-Nov

1-Feb

1-Nov

1-Aug

1-May

12-Jan

30-Nov

12-Feb

30-Mar

15-Sep

Nov. 1, 2016 Nov.

Sept. 5, 2016 Sept.

Aug. 15, 2016 15, Aug.

Aug. 30, 2016 30, Aug.

Aug. 15, 2016 15, Aug.

Not happening Not

Sept. 15, 2016 15, Sept.

Sept. 21, 2016 21, Sept.

Sept. 15, 2016 15, Sept.

Sept. 29, 2016 29, Sept.

Sept. 21, 2016 21, Sept.

Sept. 15, 2016 15, Sept.

Sept. 17, 2016 17, Sept.

Sept. 14, 2016 14, Sept.

Sept. 29, 2016 29, Sept.

Sept. 25, 2016 25, Sept.

Sept. 21, 2016 21, Sept.

Sept. 15, 2016 15, Sept.

Sept. 14, 2016 14, Sept.

Sept. 21, 2016 21, Sept.

Torsten

Andrew

Junior

Andrew

David

Andrew

David

Andrew

David

Andrew

3.5 Determination of Center of Mass of Center Determination 3.5

3.4.2 Painting 3.4.2

3.4.1 Paint Effect on Drag Drag on Effect Paint 3.4.1

Paint 3.4

3.2.3 Wind Tunnel Scale Construction Scale Tunnel Wind 3.2.3

3.2.2 1/2 Scale Construction Scale 1/2 3.2.2

3.2.1 Full Scale Construction Scale Full 3.2.1

3.3 Fins, Body, Nose Cone Construction Cone Nose Body, Fins, 3.3

3.2.3 Wind Tunnel Scale Selection Scale Tunnel Wind 3.2.3

3.2.2 1/2 Scale Selection Scale 1/2 3.2.2

3.2.1 Full Scale Selection Scale Full 3.2.1

3.2 Fins, Body, Nose Cone Selection Cone Nose Body, Fins, 3.2

3.1.4.Wind Tunnel Scale 3D Model 3D Scale Tunnel 3.1.4.Wind

3.1.3 1/2 Scale 3D Model 3D Scale 1/2 3.1.3

3.1.2 Integration of Subcomponent Models into 3D Model 3D into Models Subcomponent of Integration 3.1.2

3.1.1 General, Proposal-Level Rocket Model & Component Selection Component & Model Rocket Proposal-Level General, 3.1.1

3.1 3D Modeling - Entire Rocket - Entire Modeling 3D 3.1

3 Aerodynamics 3

2.9.2.4 Motor Mount Testing Mount Motor 2.9.2.4

2.9.2.2.2 Data Analysis Data 2.9.2.2.2

2.9.2.2.1 Testing Testing 2.9.2.2.1

2.9.2.4 Pressure Testing Pressure 2.9.2.4

2.9.2.2.2 Data Analysis Data 2.9.2.2.2

2.9.2.2.1 Testing Testing 2.9.2.2.1

2.9.2.2 Thrust Testing Thrust 2.9.2.2

2.9.2.1.2 Data Analysis Data 2.9.2.1.2

2.9.2.1.1 Testing Testing 2.9.2.1.1

2.9.2.1 Impulse Testing Impulse 2.9.2.1

2.9.2 Motor Testing Motor 2.9.2

2.9.1.5 Misfire Testing Misfire 2.9.1.5

2.9.1.4 Ignition Safety Interlock Testing Interlock Safety Ignition 2.9.1.4

2.9.1.3 Ignition Mount Testing Mount Ignition 2.9.1.3

2.9.1.2 Fuel Igition Testing Igition Fuel 2.9.1.2

2.9.1.1 Switch Testing Switch 2.9.1.1

2.9.1 Ignition Testing Ignition 2.9.1

Testing 2.9

2.8.5 Rail Exit Velocity Exit Rail 2.8.5

2.8.4 Launch Thrust-Weight Ratio Thrust-Weight Launch 2.8.4

2.8.3 Rocket Flight Stability Flight Rocket 2.8.3

2.8.2 Key Design Features Design Key 2.8.2

2.8.1 Final Motor Choice/ description Choice/ Motor Final 2.8.1

2.8 Flight Readiness Review Presentation Review Readiness Flight 2.8

2.7.4 Rail Exit Velocity Exit Rail 2.7.4

2.7.3 Thrust-to-Weight ratio Thrust-to-Weight 2.7.3

2.7.2 Rocket Flight Stability in Static Diagram Static in Stability Flight Rocket 2.7.2

2.7.1 Final Motor Choice Motor Final 2.7.1

2.7 Critical Design Review Presentation Review Design Critical 2.7

2.6.7 Show Scale Model Results Model Scale Show 2.6.7

2.6.6 Actual Motor Thrust Curve Thrust Motor Actual 2.6.6

2.6.5 Altitude Predictions with Final Design Final with Predictions Altitude 2.6.5

2.6.4 Motor Mounts Motor 2.6.4

2.6.3 Final Analysis and Model Results Model and Analysis Final 2.6.3

2.6.2 Final Drawings Final 2.6.2

2.6.1 Specify Motor Specify 2.6.1

2.6 Critical Design Review Design Critical 2.6

2.5.3 Rail Exit Veloctiy Exit Rail 2.5.3

2.5.2 Thrust-Weight Ratio Thrust-Weight 2.5.2

2.5.1 Baseline Motor Selection Motor Baseline 2.5.1

2.5 Preliminary Design Review Design Preliminary 2.5

2.4.3.2 Compare to Full Scale Numbers Scale Full to Compare 2.4.3.2

2.4.3.1 Physical Similitude Calculations Similitude Physical 2.4.3.1

2.4.3 Simulate Half Scale Model Scale Half Simulate 2.4.3

2.4.2.7 Final Rocket Simulation Rocket Final 2.4.2.7

2.4.2.6 Redesign 2 Redesign 2.4.2.6

2.4.2.5 Second Weighted Section Simulation Section Weighted Second 2.4.2.5

2.4.2.4 Final Motor Selection Simulation Selection Motor Final 2.4.2.4

2.4.2.3 Redesign 2.4.2.3

2.4.2.2 Preliminary Weighted Sections Simulation Sections Weighted Preliminary 2.4.2.2

2.4.2.1 Preliminary Motor Selection Simulation Selection Motor Preliminary 2.4.2.1

2.4.2 Simulate Full Scale Model Scale Full Simulate 2.4.2

2.4.1.2 Resimulate 2.4.1.2

2.4.1.2 Discussion with Other Sections Other with Discussion 2.4.1.2 2.4.1.1 Simulation 1 Simulation 2.4.1.1 2.4.1 Model Rocket with Motor w/ Different Weights Different w/ Motor with Rocket Model 2.4.1 55 | P a g e

3-Feb

4-Nov

3-Feb

2-Dec

9-Sep

28-Oct

18-Nov

11-Nov

30-Sep

feb. 1, 2017 feb.

Mar. 5, 2017 Mar.

Dec. Dec. 4, 2016

Sep. 5, 2016 Sep.

Jan. 22, 2017 Jan. 22,

Nov. 20, 2016 20, Nov.

Jan. 22, 2017 Jan. 22,

Nov. 20, 2016 20, Nov.

Jan. 15, 2016 Jan. 15,

Jan. 22, 2017 Jan. 22,

Sep. 30, 2016 30, Sep.

Sep. 20, 2016 20, Sep.

Sep. 30, 2016 30, Sep.

Ongoing and changing and Ongoing

3-Oct

7-Nov

1-Nov

5-Dec

Oct. 1 Oct.

1-Aug

1-May

31-Oct

21-Nov

14-Nov

23-Jan

12-Jan

29-Aug

15-Aug

10-Sep

Dec. Dec. 4, 2016

Sep. 5, 2016 Sep.

Aug. 1, 2016 Aug.

Oct. 10, 2016 10, Oct.

Jan. 22, 2017 Jan. 22,

Sep. 10, 2016 10, Sep.

Sept. 15, 2016 15, Sept.

Sept. 10, 2016 10, Sept.

2.5

Stewart

Braden

Justin

Torsten

6.3.1 Parachute testing (multiple wind speeds) wind (multiple testing Parachute 6.3.1

6.3 Recovery System Testing System Recovery 6.3

6.2.5 Scaled model construction model Scaled 6.2.5

6.2.4 Full-system integration Full-system 6.2.4

6.2.3 Ejection system assembly system Ejection 6.2.3

6.2.2 Circuit assembly Circuit 6.2.2

6.2.1 Bulkhead assembly Bulkhead 6.2.1

6.2 Recovery System Construction System Recovery 6.2

6.1.6 Scaled model design model Scaled 6.1.6

6.1.5 Parachute modeling Parachute 6.1.5

6.1.4 Circuit design & programming & design Circuit 6.1.4

6.1.3 Bulkhead design Bulkhead 6.1.3

6.1.2.6 Electronics 6.1.2.6

6.1.2.5 Bulkhead components Bulkhead 6.1.2.5

6.1.2.4 Ejection system Ejection 6.1.2.4

6.1.2.3 Shock cord and hardware and cord Shock 6.1.2.3

6.1.2.2 Altimeters 6.1.2.2

6.1.2.1 Parachutes (Drogue & Main) & (Drogue Parachutes 6.1.2.1

6.1.2 Recovery System Component Selection Component System Recovery 6.1.2

6.1.1 Recovery System Research System Recovery 6.1.1

6.1 Recovery System Design System Recovery 6.1

6 Recovery 6

5.8 Meetings/Group Work Meetings/Group 5.8

5.7 Reports 5.7

5.7 Ensure that all components can be subjected to rocket stresses rocket to subjected be can components all that Ensure 5.7

5.6 Determine if Separation is Necessary is if Separation Determine 5.6

5.5 Collaboration with Payload A over Data Collection Data over A Payload with Collaboration 5.5

5.4 Create Test Plan to Ensure Hardware in Good Working Order Working Good in Hardware Ensure to Plan Test Create 5.4

5.3 Payload B Redesign B Payload 5.3

5.3.3 Data Analysis Data 5.3.3

5.3.2 Carry Out Testing Carry 5.3.2 Out

5.3.1 Design Testing Plan Testing Design 5.3.1

5.3 Payload Testing and Experimentation and Testing Payload 5.3

5.2.2 Construction of Mounting of Construction 5.2.2

5.2.1 Construction of Experiment and housing and Experiment of Construction 5.2.1

5.2 Payload B Construction B Payload 5.2

5.1.3 Design of Mounting of Design 5.1.3

5.1.2 Design of Experimental Apparatus Experimental of Design 5.1.2

5.1.1 Design of Experiment of Design 5.1.1

5.1 Payload B Design (Fragile Material Housing) Material (Fragile Design B Payload 5.1

5 Payload B Payload 5

4.10 Meetings/Reports 4.10

4.9 Ensure that all components can be subjected to rocket stresses rocket to subjected be can components all that Ensure 4.9

4.8 Determine if Separation is Necessary is if Separation Determine 4.8

4.7 Collaboration with Payload B over Motherboard over B Payload with Collaboration 4.7

4.6 Create Test Plan & Test to Ensure Components in working order working in Components Ensure to Test & Plan Test Create 4.6

4.5.1.2 Construct Wireless Transmitter Wireless Construct 4.5.1.2

4.5.1.1 Design Wireless Transmitter Wireless Design 4.5.1.1

4.5.2 Wireless Transmission Wireless 4.5.2

4.5.1.2 Construct Ground Station Wireless Reciever Wireless Station Ground Construct 4.5.1.2

4.5.1.1 Design Ground Station Wireless Receiver Wireless Station Ground Design 4.5.1.1

4.5.1 Wireless Receiver Wireless 4.5.1

4.5 Data Transmission Data 4.5

4.4 Integration with Data Collection System Collection Data with Integration 4.4

4.3 Payload A Redesign A Payload 4.3

4.2.3 Arming and Disarming Electronics Disarming and Arming 4.2.3

4.2.2 Radio Frequency and GPS Tracking GPS and Frequency Radio 4.2.2

4.2.1 Official Altimeter Official 4.2.1

4.2 Payload A Construction A Payload 4.2

4.1.3 Arming and Disarming Electronics Disarming and Arming 4.1.3

4.1.2 Radio Frequency and GPS Tracking GPS and Frequency Radio 4.1.2

4.1.1 Official Altimeter Official 4.1.1

4.1 Payload A Design Design A Payload 4.1

4 Payload A Payload 4

3.11 Redesign of Rocket Body, Nosecone, Fins Nosecone, Body, of Rocket Redesign 3.11

3.10 Study Feasability of Real-Time Drag Changing Drag of Real-Time Feasability Study 3.10

3.9 Collaboration with Launch Pad for Guides Pad Launch with Collaboration 3.9

3.8.3 Wind Tunnel Scale Performance Scale Tunnel Wind 3.8.3

3.8.2 1/2 Scale Rocket Performance Rocket Scale 1/2 3.8.2

3.8.1 Full Scale Rocket Performance Rocket Scale Full 3.8.1

3.8 CFX Modeling CFX 3.8 3.7 Optimization of Center of Mass vs Center of Pressure Center vs of Mass of Center Optimization 3.7 3.6 Determination of Center of Pressure of Center Determination 3.6 56 | P a g e

5-Apr

3-Feb

4-Dec

20-Jan

25-Mar

17-Mar

25-Mar 25-Mar

17-Mar

Feb. 5, 2017 Feb.

Dec. 2, 2016

Dec. 8, 2016

Dec. 9, 2016

Dec. 7, 2016

Dec. 2, 2016

Oct. 28, 2016 28, Oct.

Oct. 25, 2016 25, Oct.

Oct. 10, 2016 10, Oct.

Nov. 18, 2016 18, Nov.

Nov. 11, 2016 11, Nov.

Jan. 14, 2017 Jan. 14,

Feb. 26, 2017 26, Feb.

Sept. 30, 2016 30, Sept.

4-Nov

9-Jan

5-Dec

23-Jan 17-Mar

20-Mar

Nov. 7, 2016 Nov.

Feb. 5, 2017 Feb.

Jan. Jan. 9, 2017

Dec. 2, 2016

Sept. 1, 2016 Sept.

Nov. 28, 2016 28, Nov.

Nov. 14, 2016 14, Nov.

Jan. 31, 2017 Jan. 31,

Aug. 29, 2016 29, Aug.

Feb. 26, 2017 26, Feb.

Dec. 12, 2016 Dec. 12,

Sept. 30, 2016 30, Sept.

101

10 10

93 70

4 71

10 10

187

7.5

131

0 15

7.5

382

20 20

40 379

365 279

303

10 369

253

10 10

Bryan

Stewart

David

Stewart

Stewart Stewart

Total Hours Total

9.4 Create Display for Educational Engagement Activity Engagement for Educational Display Create 9.4

9.3 Create Presentation for Educational Engagement Activity Engagement for Educational Presentation Create 9.3

9.2 Create Report for Educational Engagement Activity Engagement for Educational Report Create 9.2

9.1 Create and Orchestrate Educational Engagement Activity Engagement Educational Orchestrate and Create 9.1

9 Educational Engagement Educational 9

8.6 Manage and Maintain Failure Mode Analyses Mode Failure Maintain and Manage 8.6

8.5 Manage and Maintain Hazard Analysis Documents Analysis Hazard Maintain and Manage 8.5

8.4 Manage and Maintain MSDS Sheets MSDS Maintain and Manage 8.4

8.3 Creation of Safety Checklist Checklist of Safety Creation 8.3

8.2 Designated Head of Safety Head Designated 8.2

8.1.2 Maintain all Safety Activities per NASA per Activities Safety all Maintain 8.1.2

8.1.1 Monitor Team Activities per NASA Handbook sec. 4.3 sec. Handbook NASA per Activities Team Monitor 8.1.1

8.1 Create a Detailed Step-by-Step Launch Procedure Launch Step-by-Step Detailed a Create 8.1

8 Safety 8

7.9 Assess Rocksim with 1/2 Scale Test Scale 1/2 with Rocksim Assess 7.9

7.8 Assess Rocksim with Fullscale Data Fullscale with Rocksim Assess 7.8

7.7 Create Stand for Wind Tunnel Testing for Wind Tunnel Stand Create 7.7

7.6 Modify Wind Tunnel for Scale Testing for Scale Wind Tunnel Modify 7.6

7.5 Work with Subsections to Optomize Sections based on Testing on based Sections Optomize to Subsections Work 7.5 with

7.4.1 Assess CFX with Results with CFX Assess 7.4.1

7.4 Wind Tunnel Testing Testing Wind 7.4 Tunnel

7.3.3 Assess CFX with Results with CFX Assess 7.3.3

7.3.2 Construction and Conduction of 1/2 Scale Testing Experiments Testing Scale 1/2 of Conduction and Construction 7.3.2

7.3.1 Design of 1/2 Scale Testing Experiments Testing Scale 1/2 of Design 7.3.1

7.3 1/2 Scale Testing Scale 1/2 7.3

7.2 Manage Junior Level Testing Level Junior Manage 7.2

7.1 Oversee all Subsection Testing Subsection all Oversee 7.1

7 Testing 7

6.5 Obtain Launch License Launch Obtain 6.5

6.4.3 Launch Pad Fabrication Pad Launch 6.4.3

6.4.2 Launch Pad Material Aquisition Material Pad Launch 6.4.2

6.4.1 Launch Pad Design Pad Launch 6.4.1

6.4 Launch Pad Launch 6.4

6.3.4 Full-system testing Full-system 6.3.4

6.3.3 Circuit and transmitter testing transmitter and Circuit 6.3.3

6.3.2 Ejection system testing system Ejection 6.3.2 6.3.1 Parachute testing (multiple wind speeds) wind (multiple testing Parachute 6.3.1 57 | P a g e

Appendix D – Detailed Parts List / Cost Tracking Detailed Parts List / Cost Tracking

Section Item Description Part Number Manufacturer Lead Time (days) Quantity Price (ea) Price (total) Nose Cone 5.5" FIBERGLASS 4:1 OGIVE NOSE CONE 20540 Apogee 1 $ 84.95 $ 84.95 Body Tube 5.5" x 48" Carbon Fiber Airframe Wildman Rocketry 30 days 2 $ 350.00 $ 700.00 Fins G10 FIBERGLASS SHEET 1/4" X 1 SQ FT 14154 Apogee 4 $ 54.00 $ 216.00 Nose Cone Threads Adhesive Mount Nut 98007A013 McMaster 10 $1.44 $ 14.44 Nose Cone Bolts Stainless Steel Button-Head Socket Cap Screws 98007A013 McMaster 50 $ 0.13 $ 6.28 Rail Buttons LARGE AIRFOILED RAIL BUTTONS (FITS 1.5" RAIL - 1515) 13069 Apogee 3 $ 10.00 $ 30.00

$ - Aerodynamics $ -

$ 1,051.67 Motor AeroTech L850W 7538M AeroTech 1 $ 450.00 $ 450.00 Retaining System Aero Pack 75mm Retainer - L 24054 Apogee 1 $ 47.08 $ 47.08 Epoxy G5000 Rocketpoxy 2-pint package 30511 Apogee 2 $ 38.25 $ 76.50 Motor Mount 75mm Blue Tube 48" 10504 Apogee 1 $ 29.95 $ 29.95 Motor Reloads AeroTech L850W Refuels 12850P AeroTech 3 $ 199.99 $ 599.97

Propulsion Centering Rings and Bulkheads (1/4) thick 6061-T651 Aluminum Plate P314T6 Metal Depot 7 1 $ 144.03 $ 144.03

$ 1,347.53 5.5" Aluminum Bulkplate 25096 MadCow Rocketry 2 $ 25.00 $ 50.00 U-Bolts w/mounting plates for use with aluminum bulkhead (pack of 5) 3043T68 McMaster 1 $ 5.89 $ 5.89 2" Eyebolts for use with electronics bay (pack of 4) 29629 Apogee 1 $ 4.73 $ 4.73 Electronics bay coupler 5.5" OD, bulkheads, rails 10526 Always Ready Rocketry 1 $ 56.95 $ 56.95 Igniter terminal block for easy igniter replacement 9191 Apogee 2 $ 3.41 $ 6.82 Crimp Connector - Radioshack 2 $ 5.00 $ 10.00 Ejection well 2-pack PVC wells for black powder 3068 Apogee 2 $ 3.15 $ 6.30 Parachute Protector 18" Nomex flameproof cloth 29314 Sunward Group, Ltd. 2 $ 10.49 $ 20.98 Tubular Nylon Recovery Harness 30351 Onebadhawk 60 $ 1.10 $ 66.00 Shock Cord Protector 30" flameproof sheath 29300 Madcow Rocketry 2 $ 12.95 $ 25.90 Rotary Switch lockable switch 9128 Apogee 2 $ 9.93 $ 19.86 LEDs Indicator lights for arming - Radioshack 2 $ 4.00 $ 8.00 Recovery Shear Pins Nylon, threaded (10 pack) 29615 Apogee 10 $ 3.10 $ 31.00 0.25" quick link for parachutes link eyebolts, chutes, and cord 29621 Apogee 6 $ 3.94 $ 23.64 36" Drogue Chute (Max Size Drogue) Elliptical, 1.5 Cd, Ripstop Nylon 29165 Fruity Chutes 1 $ 95.17 $ 95.17 96" Main Chute (Max Size Main) Torroidal, 2.2Cd, Ripstop Nylon 29184 Fruity Chutes 1 $ 346.53 $ 346.53 Stratologger CF Main & Backup 9200 Altus Metrum 2 $ 58.80 $ 117.60 Quest Q2G2 igniter 6-pack of igniters 3078 Quest 4 $ 5.00 $ 20.00 Black Powder - Gun Store 1 $ 20.00 $ 20.00 9 Volt Battery - Radioshack 4 $ 10.00 $ 40.00 22 Gague Wire - Radioshack 3 $ 1.00 $ 3.00 $ 978.37 Atlus Metrum TeleMega From csrocketry.com Atlus Metrum 21 1 $ 400.00 $ 400.00 Starter Pack From csrocketry.com Atlus Metrum 0 1 $ 100.00 $ 100.00 Arrow 440-3 Yagi Antenna get from link in start pack page Yagi 0 1 $ 50.00 $ 50.00 SMA to BNC adapter From csrocketry.com Atlus Metrum 0 1 $ 10.00 $ 10.00

ElectronicPayload $ 560.00 Estimated Maximum $ 500.00

Exact Components TBD Main Payload Main

$ 500.00

Educational Engagement Supplies TBA - - $ 300.00

Safety / Educational Engagement $ 300.00 RockSim Temporary, 1 Seat License 1123 Apogee 0 1 $ 20.00 $ 20.00 Shirts Notable Sponsors 3 $ 43.33 $ 130.00 Hotel (Professors) Apr. 5 - 8, Indv. Room (100/night) - - - 2 $ 300.00 $ 600.00 Hotel (Group A) Apr. 5 - 8, 2/Room, Avg. $120/night 10 People - - 5 $ 360.00 $ 1,800.00 Hotel (Group B) Two Nights, 2/Room, Avg $120/night 4 People - - 2 $ 240.00 $ 480.00 Fuel Reiumbursement 540mi/15mpg*$2.50/ga 5 Vehicles - - 5 $ 90.00 $ 450.00

Food $10 / Meal 15 People - - 4 $ 150.00 $ 600.00 Administrative / Travel / Administrative

$ 4,080.00 1515 Rail 1515 Extruded Al., 145" 16U252 Grainger 2 1 $ 131.50 $ 131.50 Rail Bracket 90 Degree 5 Hole Bracket 47065T271 McMaster 2 4 $ 9.74 $ 38.96

Bolts M10 x 20 x 1.5 91290A516 McMaster 2 1 $ 6.41 $ 6.41 Launch Pad Launch $ 176.87 Body Tube 3" CARBON FIBER TUBING 60 INCHES LONG CFT3.0-60 Wildman 30 days 1 $ 218.50 $ 218.50 Nose Cone 3" FILAMENT-WOUND FIBERGLASS OGIVE 4:1 NOSE CONE 20279 Apogee 1 $ 42.86 $ 42.86 Fins G10 FIBERGLASS SHEET 1/8" X 1 SQ FT 14152 Apogee 2 $ 27.00 $ 54.00 Rail Buttons LARGE AIRFOILED RAIL BUTTONS (FITS 1.5" RAIL - 1515) 13069 Apogee 2 $ 10.00 $ 20.00 Propulsion Estimate $ 300.00

ScaleModel Recovery Estimate $ 550.00

$ 1,185.36 58 | P a g e