School Informationwestrocketry.com/sli2012/SOW_MadisonWest2012_Diffusion.docx · Web viewEach altimeter will have its own power source, external arming switch and set of charges

September 19, 2011

A Study of Effects of Gravitational Forces and Flight-Induced Vibrations on Diffusion in Liquids

Madison West High School - New Team

Front row: Caitlin and AmelieMiddle row: Mia

Back row: Jack, Adrian, Han and Owen

SLI 2012 Statement of Work

Madison West High School New Team SLI 2012 SOW

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Contents

School Information........................................................................................................5

Student Participants......................................................................................................7

Facilities and Equipment...............................................................................................8

Facilities for Rocket Design and Testing.......................................................................8Personnel......................................................................................................................9Equipment and Supplies.............................................................................................10Section 508 Compliance.............................................................................................13

Safety............................................................................................................................ 14

Written Safety Plan.....................................................................................................14I. NAR Safety Requirements.......................................................................................14II. Hazardous Materials...............................................................................................15III. Compliance with Laws and Environmental Regulations........................................15IV. Education, Safety Briefings and Supervision.........................................................16V. Procedures and Documentation.............................................................................16Physical Risks.............................................................................................................17Toxicity Risks..............................................................................................................17Scheduling and Facilities Risks..................................................................................17Rocket/Payload Risks.................................................................................................18

Technical Design..........................................................................................................19

Vehicle Dimensions....................................................................................................19Entire Vehicle..........................................................................................................19Vehicle Parameters.................................................................................................19

Motors.........................................................................................................................20Primary Motor Selection..........................................................................................20Wind Speed vs. Altitude..........................................................................................21Thrust Profile...........................................................................................................22Velocity Profile........................................................................................................22Acceleration Profile.................................................................................................23Vehicle Flight Sequence.........................................................................................23

Deployment and Recovery..........................................................................................25Parachutes..............................................................................................................25Drift......................................................................................................................... 25Universal Avionics Platform - System Hermes........................................................26

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Performance Targets that Apply to Vehicle................................................................27

Payload.......................................................................................................................28Experimental Overview...........................................................................................28Experimental Setup.................................................................................................29Universal Avionics Platform - System Hermes........................................................31Experimental Sequence..........................................................................................31Data Analysis..........................................................................................................33Hypotheses.............................................................................................................33Post Flight Procedure.............................................................................................34

Performance Targets...................................................................................................35

Major Challenges and Solutions.................................................................................43Major Vehicle Challenges.......................................................................................43Major Payload Challenges and Solutions...............................................................43

Educational Engagement............................................................................................45

Community Support....................................................................................................45Outreach Programs.....................................................................................................46

Project Plan..................................................................................................................48

Schedule.....................................................................................................................48Budget........................................................................................................................ 49Educational Standards................................................................................................51Sustainability...............................................................................................................54

Appendices...................................................................................................................56

Appendix A: Resume for Adrian..................................................................................56Appendix B: Resume for Amelie.................................................................................57Appendix C: Resume for Caitlin..................................................................................58Appendix D: Resume for Han.....................................................................................59Appendix E: Resume for Jack.....................................................................................60Appendix F: Resume for Mia......................................................................................61Appendix G: Resume for Owen..................................................................................62

Appendix H: Model Rocket Safety Code.....................................................................63Appendix I: High Power Rocket Safety Code..............................................................65Appendix J: Section 508.............................................................................................67Appendix K: Material Safety Data Sheets...................................................................72Appendix L: Bibliography............................................................................................73

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School Information

School NameMadison West High School

Title of ProjectA Study of Effects of Gravitational Forces and Flight-Induced Vibrations on Diffusion in Liquids

Administrative Staff MemberWest High School Principal Ed HolmesMadison West High School, 30 Ash St., Madison, WI, 53726Phone: (608) 204-4104E-Mail: [email protected]

Team OfficialMs. Christine Hager, Biology InstructorMadison West High School, 30 Ash St., Madison, WI 53726Phone: (608) 204-3181E-Mail: [email protected]

Educators and Mentors

Pavel Pinkas, Ph.D., Senior Software Engineer for DNASTAR, Inc.1763 Norman Way, Madison, WI, 53705Work Phone: (608) 237-3068Home Phone: (608) 957-2595Fax: (608) 258-3749E-Mail: [email protected]

Brent Lillesand4809 Jade Lane, Madison, WI 53714Phone: (608) 241-9282E-mail: [email protected]

Jeffrey A. Havlena118 Richland Lane, Madison, WI 53705Phone: (608) 238-6880E-Mail: [email protected]

Matthew Lynch5322 Milward Dr, Madison, WI 53705E-Mail: [email protected]

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Section 508 Consultant: Ms. Ronda SolbergDNASTAR, Inc. (senior software designer)3801 Regent St, Madison, WI 53705E-Mail: [email protected]

Associated NAR Chartered Section #558President: Mr. Scott T. GoebelPhone: (262) 634-3971E-Mail: [email protected]://www.wooshrocketry.org

Wisconsin Organization Of Spacemodeling Hobbyists (WOOSH) is a chartered section (#558) of the National Association of Rocketry. They assist Madison West Rocketry with launches, mentoring, and reviewing.

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Student Participants

Delivery Team: responsible for vehicle design, flight safety parameters, altitude target, propulsion and launch operations

[email protected]

[email protected]

Deployment Team: responsible for deployment electronics, parachute selection and preparation, parachute and ejection charges calculation, ejection static testing

[email protected]

[email protected]

Telemetry Team: responsible for maintaining wireless contact with the rocket, receiving data from on-board GPS, avionics and payload, tracking and locating the rocket

AMELIETEAM LEADER

[email protected]

Payload Team: responsible for payload design, payload preflight preparations and activation, postflight payload data analysis

[email protected]

[email protected]

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Facilities and EquipmentFacilities for Rocket Design and Testing

1. Planning, discussion, design concept and writing will occur at UW Madison, Dept. of Physics, Room #2223, located at Chamberlin Hall, 1150 University Avenue, Madison, Wisconsin, 53705, on the weekends.

2. Construction of the rocket will occur at a workshop at 3555 University Ave, Madison, Wisconsin, 53705, on the weekends or as necessary. We have a 24/7 access to this facility.

3. Construction of the payload will also occur at a workshop at 3555 University Ave, Madison, Wisconsin, 53705, on the weekends.

4. Preparation of the payload contents will occur at a workshop at 3555 University Ave, Madison, Wisconsin, 53705, on the weekends.

5. Additional manufacturing of the payload and/or result analysis will occur at biology laboratories at Madison West High School, 30 Ash Street, Madison, Wisconsin, 53726, on weekdays, after school.

6. Team organizational meetings will occur during lunchtime every Monday in Room 365 of Madison West High School, 30 Ash Street, Madison, Wisconsin, 53726.

7. Launching of low-powered scale model rockets will occur on weekends from November through April, at Reddan Soccer Park located at 6874 Cross Country Road, Verona, Wisconsin, 53593. Large Model Rocket Launch notification will be made to comply with FAA regulations Part 101. NFPA code 1122 and NAR Model Rocket Safety Code will be followed during these launches. Mentors will supervise all launches.

8. Launching of high-powered rockets will occur at Richard Bong Recreational Area located in Southeast Wisconsin at 26313 Burlington Road, Kansasville, Wisconsin, 53189. We will obtain Power Rocket Altitude waivers from the FAA prior to high power launches. High power launches will coincide with the high power launch of WOOSH, Section 558 of the NAR. Mentors will supervise all launches.

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Scheduling and Facilities RisksRisks Consequences Mitigation

Workshop space unavailable

Unable to complete construction of rocket and/or payload

We will insure the availability of our workshop space for the times that we need it. We will also work at team members’ homes if necessary.

Design facilities unavailable

Unable to complete project design/description

We will insure the availability of our design facilities and work at team members’ homes if needed.

Team members unavailable

Unable to complete project

We will plan meetings in advance and insure that enough team members will be present to allow sufficient progress.

Table 1: Risks associated with scheduling and facilities

Personnel Ms. Christine Hager Main Advisor, Educational Supervisor Dr. Pavel Pinkas NAR Mentor, Scientific Advisor Mr. Jeffrey A. Havlena NAR Mentor, Scientific Advisor Mr. Brent Lillesand NAR Mentor, Vehicle Construction Supervisor Mr. Matthew Lynch Student Mentor Mr. Scott Goebel NAR Mentor, NAR Section 558 (WOOSH) Contact

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Equipment and Supplies

EQUIPMENT POWER TOOLS SUPPLIES ROCKET COMPONENTS

Soldering irons Drill press Cyanoacrylate glue (superglue)

G10 sheets of fiberglass

Band saws Dremel tool (with necessary attachments)

Accelerator and de-bonder for superglue

Kevlar and tubular nylon shock cords

Hacksaws Hand drill West Epoxy (resin, quick and slow hardener, various fillers)

Nomex Fabric

Hand saw Hydraulic press 5 Minute Epoxy Quick linksScroll saw Jig saw Masking tape Plywood centering

rings, sheets, bulkheads

Wire strippers Table saw Electric tape Screws, nuts, T-nuts, washers, etc.

Drill bits Belt sander Batteries of varying size and voltage to power electronic components

4-inch fiberglass tubing, 6-inch fiberglass tubing

Box cutters Table saw Various minor electronic components (resistors, capacitors, LEDs)

U-Bolts, I-Bolts

X-acto knives Jig saw JB Weld Glue Nose coneSandpaper and sanding blocks

Router Solder, flux Lock’N’Load motor retention kit

Rulers and yardsticks

Breathing masks (to be used when sanding or cutting fiberglass)

Rail buttons

Ring and C-clamps

Latex gloves, safety goggles

PerfectFlite altimeters

Pliers, clippers First aid kit PerfectFlite timersPhillips/flathead screwdrivers (various sizes)

Ethyl-alcoholIsopropyl-alcohol

Parallax Propeller Chips and development kits

Vices of varying sizes

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Table 2: Various equipment that will be used in the construction of our rocket and payload

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Computer Equipment

School Computers 500MHz-2GHz, 128MB-1GB RAM Windows 98, XP Able to use Apple G3-G5

Student Personal Computers’ Range 1.3 - 3.6 GHz Intel dual to quad core processor 512mb - 4 GB RAM 40 GB – 1 TB Hard Drive Windows XP, Vista, Windows 7 Max OS X Tiger, Leopard, Snow Leopard Team members posses 10 of laptops total

Web HostingOur websites are hosted by HostGator (a commercial hosting company). Our club website can be found at http://westrocketry.com.

Internet Connection School Computers - T3 connection for Internet DNASTAR - T3 connection and an internal wireless network (801b/g/n) Home – DSL 768Kbps-6.0Mbps (download), 256Kbps-1.5Mbps (upload)

Computer Accessible Programs Adobe Creative Suite 4 Design Premium Edition Adobe After Effects CS4 Apple Final Cut Express Eclipse Java IDE, XCode, Propeller Tool Octave 3.2.2 Apogee RockSim 8 Firefox, Safari, Chrome and Internet Explorer Browsers Google Sketchup 3D Design MS Outlook Microsoft Office 2003-2008

E-mail capabilityThe team will be communicating via email. All SLI members have personal email accounts. There is also a group e-mail address that allows addressing the whole team by sending a message to a single e-mail address ([email protected]). This format has worked with great efficiency for the last five years.

Presentation Simulation Software Microsoft Power Point 2003/2010

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Video Teleconferencing (Webcasting)Our SLI 2012 team will use the UW Extension at the Pyle Center for Video Teleconferencing facilities. We prefer to use Webex teleconferencing software. Contact Dr. Rosemary Lehman for information about firewall issues.

UW Extension Pyle Center 702 Langdon St. Madison WI, 53706 Fax: 608-236-4435 Phone: 608-262-7524 [email protected]

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Section 508 Compliance

Architectural and Transportation Barriers Compliance Board Electronic and Information Technology (EIT) Accessibility Standards (36 CFR Part 1194)The team will implement required parts of Section 508, namely

§ 1194.21 Software applications and operating systems (all items) § 1194.22 Web-based intranet and internet information and applications (all

items) § 1194.26 Desktop and portable computers (all items)

o § 1194.23 Telecommunications products (items (k)(1) through (4)) as referenced by § 1194.26

The team carefully reviewed the above listed sections and consulted the same with two senior software engineers at DNASTAR, Inc. (a bioinformatics software company).

Re: § 1194.21: The team is using MS Windows and Mac OS-X based computers. Both Microsoft and Apple are strong supporters of Section 508 and all installation of MS Windows and Mac OS-X are complete including the access assistive features. All third party software used in the SLI project is claimed as Section 508 compliant by the software company producing the software (Microsoft, Apple, and Adobe). Software and firmware developed by the students during the project will be verified for Section 508 compliance by senior software engineers from DNASTAR Inc. All found violations will be fixed prior software deployment.

Re: § 1194.22: The rocket club website (http://www.westrocketry.com) has been checked for Section 508 compliance using various automated validators (such as http://section508.info). No violations have been found. The website specific to the proposed project will be periodically subjected to the same selection of tests and the webmaster will remove all found violations in a timely manner.

Re: § 1194.26: All computers used by the team members and educators are Section 508 compliant. No computer has been modified beyond the manufacturer approved upgrades.

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Safety

Written Safety Plan

I. NAR Safety Requirements

a. Certification and Operating Clearances: Mr. Lillesand holds a Level 3 HPR certification. Dr. Pinkas has a Level 1 HPR certification and plans on having a Level 2 HPR certification by the end of February 2012. Mr. Havlena holds a level 1 HPR certification. He plans to complete his Level 2 by April 2012 and is our back-up launch supervisor. Mr. Lillesand has Low Explosives User Permit (LEUP). If necessary, the team can store propellant with Mr. Goebel, who owns a BATFE approved magazine for storage of solid motor grains containing over 62.5 grams of propellant.

Mr. Lillesand is the designated individual rocket owner for liability purposes and he will accompany the team to Huntsville. Upon their successful L2 certification, Mr. Havlena and Dr. Pinkas will become a backup mentors for this role.

All HPR flights will be conducted only at launches covered by an HPR waiver (mostly the WOOSH/NAR Section #558 10,000ft waiver for Richard Bong Recreation Area launch site). All LMR flights will be conducted only at the launches with the FAA notification phoned in at least 24 hours prior to the launch. NAR and NFPA Safety Codes for model rockets and high power rockets will be observed at all launches. Mentors will be present at all launches to supervise the proceedings.

b. Motors: We will purchase and use in our vehicle only NAR-certified rocket motors and will do so through our NAR mentors. Mentors will handle all motors and ejection charges.

c. Construction of Rocket: In the construction of our vehicle, we will use only proven, reliable materials made by well established manufacturers, under the supervision of our NAR mentors. We will comply with all NAR standards regarding the materials and construction methods. Reliable, verified methods of recovery will be exercised during the retrieval of our vehicle. Motors will be used that fall within the NAR HPR Level 2 power limits as well as the restrictions outlined by the SLI program. Lightweight materials such as fiberglass tubing and carbon fiber will be used in the construction of the rocket to ensure that the vehicle is under the engine’s maximum liftoff weight. The computer program RockSim will be utilized to help design and pre-test the stability of our rocket so that no unexpected and potentially dangerous problems with the vehicle occur. Scale model of the rocket will be built and flown to prove the rocket stability.

d. Payload: As our payload does not contain hazardous materials, it does not present danger to the environment. However, our NAR mentors will check the payload prior to

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launch in order to verify that there will be no problems.

e. Launch Conditions: Test launches will be performed at Richard I. Bong Recreation Area with our mentors present to oversee all proceedings. All launches will be carried out in accordance with FAA, NFPA and NAR safety regulations regarding model and HPR rocket safety, launch angles, and weather conditions. Caution will be exercised by all team members when recovering the vehicle components after flight. No rocket will be launched under conditions of limited visibility, low cloud cover, winds over 20mph or increased fire hazards (drought).

II. Hazardous MaterialsAll hazardous materials will be purchased, handled, used, and stored by our NAR mentors. The use of hazardous chemicals in the construction of the rocket, such as epoxy resin, will be carefully supervised by our NAR mentors. When handling such materials, we will make sure to carefully scrutinize and use all MSDS sheets and necessary protection (gloves, goggles, proper ventilation etc.).

All MSDS sheets and federal/state/local regulation applicable to our project are available online at

http://westrocketry.com/sli2012/safety/safety2012n.php

III. Compliance with Laws and Environmental Regulations All team members and mentors will conduct themselves responsibly and construct the vehicle and payload with regard to all applicable laws and environmental regulations. We will make sure to minimize the effects of the launch process on the environment. All recoverable waste will be disposed properly. We will spare no efforts when recovering the parts of the rocket that drifted away. Properly inspected, filled and primed fire extinguishers will be on hand at the launch site.

Cognizance of federal, state, and local laws regarding unmanned rocket launches and motor handling

The team is cognizant and will abide with the following federal, state and local laws regarding unmanned rocket launches and motor handling:

Use of airspace: Federal Aviation Regulations 14 CFR, Subchapter F, Part 101, Subpart C

Handling and use of low explosives: Code of Federal Regulation Part 55

Fire Prevention: NFPA1127 Code for High Power Rocket Motors

All of the publications mentioned above are available to the team members and mentors via links to the online versions of the documents.

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WRITTEN STATEMENT OF SAFETY REGULATIONS COMPLIANCE

All team members understand and will abide by the following safety regulations:

a. Range safety inspections of each rocket before it is flown. Each team shall comply with the determination of the safety inspection.

b. The Range Safety Officer has the final say on all rocket safety issues. Therefore, the Range Safety Officer has the right to deny the launch of any rocket for safety reasons.

c. Any team that does not comply with the safety requirements will not be allowed to launch their rocket.

IV. Education, Safety Briefings and SupervisionMentors and experienced rocketry team members will take time to teach new members the basics of rocket safety. All team members will be taught about the hazards of rocketry and how to respond to them; for example, fires, errant trajectories, and environmental hazards. Students will attend mandatory meetings and pay attention to pertinent emails prior participation in any of our launches to ensure their safety. A mandatory safety briefing will be held prior each launch. During the launch, adult supervisors will make sure the launch area is clear and that all students are observing the launch. Our NAR mentors will ensure that any electronics included in the vehicle are disarmed until all essential pre-launch preparations are finished. All hazardous and flammable materials, such as ejection charges and motors, will be assembled and installed by our NAR-certified mentor, complying with NAR regulations. Each launch will be announced and preceded by a countdown (in accordance with NAR safety codes).

V. Procedures and Documentation In all working documents, all sections describing the use of dangerous chemicals will be highlighted. Proper working procedure for such substances will be consistently applied, such as using protective goggles and gloves while working with chemicals such as epoxy. MSDS sheets will be on hand at all times to refer to for safety and emergency procedures. All work done on the building of the vehicle will be closely supervised by adult mentors, who will make sure that students use proper protection and technique when handling dangerous materials and tools necessary for rocket construction.

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Physical RisksRisks Consequences Mitigation

Saws, knives, Dremel tools, band saws

Laceration All members will follow safety procedures and use protective devices to minimize risk

Sandpaper, fiberglass

Abrasion All members will follow safety procedures and use protective devices to minimize risk

Drill press Puncture wound All members will follow safety procedures and use protective devices to minimize risk

Soldering iron Burns All members will follow safety procedures to minimize risk

Computer, printer

Electric shock All members will follow safety procedures to minimize risk

Workshop risks Personal injury, material damage

All work in the workshop will be supervised by one or more adults. The working area will be well lit and strict discipline will be required

Table 3: Risks that would cause physical harm to an individual

Toxicity RisksRisks Consequences Mitigation

Epoxy, enamel paints, primer, superglue

Toxic fumes Area will be well ventilated and there will be minimal use of possibly toxic-fume emitting substances

Superglue, epoxy, enamel paints, primer

Toxic substance consumption

All members will follow safety procedures to minimize risk. Emergency procedure will be followed in case of accidental digestion.

Table 4: Risks that would cause toxic harm to an individual

Scheduling and Facilities RisksRisks Consequences Mitigation

Workshop space unavailable

Unable to complete construction of rocket and/or payload

We will insure the availability of our workshop space for the times that we need it. We will also work at team members’ homes if necessary.

Design facilities unavailable


We will insure the availability of our design facilities and work at team members’ homes if needed.

Team members unavailable


We will plan meetings in advance and insure that enough team members will be present to allow sufficient progress.

Table 5: Scheduling risks that would inhibit our progress on our project

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Rocket/Payload RisksRisks Consequences Mitigation

Unstable rocket Errant flight Rocket stability will be verified by computer and scale model flight.

Improper motor mounting

Damage or destruction of rocket.

Engine system will be integrated into the rocket under proper supervision and used in the accordance with the manufactures’ recommendations.

Weak rocket structure

Rocket structural failure

Rocket will be constructed with durable products to minimize risk.

Propellant malfunction

Engine explosion All members will follow NAR Safety Code for High Powered Rocketry, especially the safe distance requirement. Attention of all launch participants will be required. Mentors will assemble the motors in accordance with manufacturer's instructions.

Parachute Parachute failure Parachute Packaging will be double checked by team members. Deployment of parachutes will be verified during static testing.

Payload Payload failure/malfunction

Team members will double-check all possible failure points on payload.

Launch rail failure

Errant flight NAR Safety code will be observed to protect all member and spectators. Launch rail will be inspected prior each launch.

Separation failure

Parachutes fail to deploy

Separation joints will be properly lubricated and inspected before launch. All other joints will be fastened securely.

Ejection falsely triggered

Unexpected or prematureignition/personal injury/property damage

Proper arming and disarming procedures will be followed. External switches will control all rocket electronics.

Recovery failure

Rocket is lost The rocket will be equipped with radio and sonic tracking beacons.

Transportation damage

Possible aberrations in launch, flight and recovery.

Rocket will be properly packaged for transportation and inspected carefully prior to launch

Table 6: Risks associated with the rocket launch

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Technical Design

We will use a single stage, K-class vehicle for our experiment. We will be observing the effects of gravitational forces and vibration on diffusion in liquids. The project code name of the vehicle is Hydros.

The rocket will be constructed from LOC Precision fiber tubing, using balsa/G10 sandwich for fins. The rocket will be robust enough to endure 20+g of acceleration and high power rocket flight and deployment stresses.

To have a successful mission the rocket must reach (but not exceed) altitude of one mile AGL and the payload must record all data necessary for our experiment. The rocket will be 108 inches long, with a 5.5 inch diameter for payload and recovery system sections, 4 inch diameter for the booster and fin assembly. It has estimated liftoff mass of 9 kilograms. The proposed vehicle and propulsion options are discussed in detail below. The primary propulsion choice is a K-class motor with total impulse of 2522 Ns. The vehicle can launch from a standard size, 8ft launch rail.

The rocket will use dual deployment to minimize drift.

Vehicle Dimensions

Entire Vehicle

Figure 1: A two dimensional schematic of the entire rocket. Stability margin for the entire vehicle is 3.06 calibers.

Vehicle Parameters

Length[in]

Mass[kg]

Diameter [in]

Motor Selection

Stability Margin

[calibers]Thrust to

weight ratio

108 8.9 5.5, 4.0 AT-K1050W 3.06 12.4

Table 7: The rocket’s dimensions, stability, and primary propulsion

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The figure below shows all compartments and section of our rocket. The rocket separates into three tethered parts (nosecone, main parachute compartment (including deployment e-bay and the rest of the vehicle). We will use standard dual deployment triggered by two fully redundant PerfectFlite MAWD altimeters.

Figure 2: A three dimensional schematic of the entire rocket

Letter Part

A NoseconeB Main parachuteC Drogue parachuteD PayloadE TransitionF Booster tube and motor mountG Fins and tail assembly

Table 8: Rocket sections and parts

Motors

Primary Motor SelectionBased on the results of computer simulations we have selected Aerotech K1050W (54mm) motor as our primary propulsion choice. Gorilla Motors K1075RT (54mm) and Aerotech K1750R (54mm) are our backup choices. Characteristic parameters for each motor are shown in the table below.

Motor Diameter [mm]

Total Impulse

[Ns]

Burn Time [s]

Stability Margin

[calibers]Thrust to

weight ratio

AT K1050W 54 2522 2.30 3 12.4GRM K1075RT 54 2408 2.24 3 12.4AT K1750R 54 2468 1.46 3 17.9

Table 9: Motor alternatives

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The graph below shows the simulated flight profile for the AT-K1050W motor. The vehicle reaches the apogee of 5207ft seventeen seconds (17s) after the ignition. For the purpose of this preliminary simulation the coefficient of drag is set to CD = 0.5 (we have flown this type of vehicle during our two prior SLI projects and all our experimental data indicate that CD = 0.5 is the correct estimate of overall drag coefficient for a boat-tailed vehicle).

Figure 3: Altitude vs. time graph for AT K1050W motor. The rocket reaches 5207ft at 17s after ignition.

Wind Speed vs. AltitudeThe effect of the wind speed on the apogee of the entire flight is investigated in the table below. Even under the worst possible conditions (wind speeds of 20mph, the NAR limit) the flight apogee will differ by less than 3% from the apogee reached in windless conditions.

Wind Speed[mph]

Altitude[ft]

Percent Change in Altitude

0 5207 0.00%5 5199 0.10%

10 5173 0.40%15 5128 1.60%20 5065 2.80%

Table 10: Flight apogee vs. wind speed

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Thrust ProfileThe graph below shows the thrust profile for the K1050W motor. The K1050W motor quickly reaches its maximum thrust of 1200Ns and remains at this thrust level for about 2s (the average thrust-to-weight ratio is 12.4). The rocket requires a standard eight-foot rail for sufficient stability on the pad and leaves the 8ft rail at about 55mph.

Figure 4: Thrust vs. time graph. The motor delivers maximum thrust of just over 1200 N and burns for 2.3s.

Velocity ProfileAccording to the velocity profile (next graph), the rocket will reach maximum velocity of 540mph shortly before the burnout (2.3s). The rocket remains subsonic for the entire duration of its flight.

Figure 5: Velocity vs. time graph. The motor burns out at 2.3s and the rocket reaches its maximum velocity of 540mph shortly before burnout. The rocket remains at subsonic speed range for entire duration of its flight.

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Acceleration ProfileThe graph below shows that the rocket will experience maximum acceleration of about 15g. Our rocket will be robust enough to endure the 20g+ acceleration shocks.

Figure 6: Acceleration [g] vs. time [s] graph. The rocket experiences maximum acceleration of approximately 15g.

Vehicle Flight SequenceThe vehicle flight sequence is shown on the figure below.

Figure 7: Vehicle flight sequence - 1. Ignition, 2. Burnout at 2.24s and 1000ft AGL, 3. Coast to apogee, 4. Apogee at 17s and 5,280ft (drogue parachute deployment), 5. Descent under drogue parachute to 700ft, 6. Main parachute deploys at 84s, 700ft, 7. Landing at 110s.

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# Event Altitude [ft] Time [s] Trigger Triggering Conditions

1 Ignition/Launch0 0.00

Launch control

rocket is ready,range and sky clear

2 Burnout 1000 2.243 Coast

4 Drogue deployment 5280 16.73 altimeter apogee

5 Drogue descent

6 Main parachute deploys 700 84.00 altimeter 700ft AGL reached

7 Landing 0 110.01Table 11: Flight events, triggers and conditions

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Deployment and Recovery

The rocket will use standard dual deployment technique for recovery. Two fully independent PerfectFlite MAWD altimeters will be used to fire the ejection charges. Each altimeter will have its own power source, external arming switch and set of charges. The drogue charges will be fired at apogee (5,280ft). The main parachute will be deployed as field conditions require to prevent excessive drift, most likely at 700ft or 900ft. The table below shows the estimated parachute sizes, descent rates and landing impact energy. As required, the rocket separates in no more than four tethered/independent sections (three (3) sections in our case) and the impact energy is no more than 75 ft-lbf for any of the parts (the impact energy for the entire rocket is 74.6 ft-lbf).

ParachutesThe table below shows the parachutes sizes, required ejection charges, descent rates and impact energy.

Parachute Diameter [in]

Descent Rate [fps]

Ejection Charge [g]

Deployment Altitude

[ft]

Descent Weight

[lbs]

Impact Energy [ft-

lbf]Drogue 18 68 2.4 5280 18.75 -Main 90 16 5.5 700 18.75 74.6

Table 12: Parachute sizes, ejection charges and descent rates

Drift The following table shows the estimated drift of the rocket considering the descent rates in the table above (total flight time 111s). As required, the rocket will not drift past 2,500ft at 15mph wind conditions.

Wind Speed[mph]

Drift[ft]

Drift[mi]

0 0 0 5 814 0.15

10 1630 0.3115 2444 0.4620 3259 0.62

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Universal Avionics Platform - System HermesIn order to speed-up development of our vehicles and payloads and to allow students to spend more time on the experiments, during past few years students from Madison West Rocketry have developed a universal and extensible payload-vehicle avionics platform named Hermes (the winged messenger). Beginning with 2011/2012 school year, system Hermes will be used in all Madison West Rocketry sounding rockets. The system has been flight-tested during Rockets For Schools 2011 launch.

System Hermes provides the following functionality out-of-box: Altitude and 3D acceleration data (100Hz, 8x oversampling, 12 or 16bit) Flight phases analysis (detects takeoff, burnout, staging, apogee, landing) Full duplex serial communication between rocket and ground (900MHz XBee) 96KB of built-in memory for experimental data (expandable as needed) GPS location (transmitted to the ground station over wireless link) Telemetry link (for experimental data transmissions) Extension ports for payload controllers or other devices Regulated DC voltage to power other components (+5V, +3.3V)

In this season we intent to use the Hermes system to replace the custom developed PCB boards to speed-up the payload development and to improve our tracking and recovery. The system will not be used for deployment purposes this year (we will continue to rely on proven PerfectFlite MAWD altimeters).

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Performance Targets that Apply to Vehicle

The following performance targets apply to the vehicle. These have been taken into account:

2. Vehicle altitude3. Recovery electronics requirements4. Velocity limit (must remain subsonic)5. Launch vehicle reusability6. Dual deployment requirement7. Proper shielding of recovery system electronics8. Mandatory shear pins9. Separation of vehicle into no more than 4 parts, impact energy, drift10. Prep time requirements11. Launch readiness time 12. Standard launch system requirement13. No external circuitry needed for launch15. Tracking requirements16. Certified solid propulsion requirement17. Motor total impulse limits18. Full scale launch requirement19. Prohibited items20. Safety checklist requirement21. Student work requirements

All performance targets (1-22) are described in detail later in this document.

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Payload

Experimental OverviewWe will be investigating the effects of gravitational forces and flight-induced vibrations on diffusion in liquids. A soluble dye will be used to track the movements of liquid during rocket flight. High definition video-camera (1920x1080 pixels at 30 or 60 fps will record movements of the dye front and changes in dye distribution). After the flight the standard image analysis methods will be applied to quantify the visual observations.

Figure 8: Proof of concept experiment. The leftmost picture shows stationary undisturbed liquid with tracking dye. On the center picture the liquid is subjected to vibrations and changes in dye distribution become apparent. The rightmost picture shows the dye distribution after the vibrations have ceased.

We have carried out several preliminary experiments using Royal Blue food coloring dye (soluble in water). Selected results of our preliminary experiments our shown on the picture above. We have found that the addition of the dye into solution allows us to easily track effects of vibrations on the body of the liquid. We have observed both local increases and decreases in dye concentration, including complete displacement of the dye by clear liquid at certain spots.

From engineering point of view, existence of non-uniform concentration profiles in liquid or gaseous reaction systems/mixtures can lead to creation of hot/cold reaction regions, both of which can present problems and dangers. For example an exothermic reaction that is under control in perfectly mixed system can create hot spots and go into a thermal runaway if severe concentration gradients are created by vibrations of the reaction vessel. Or, a crucial reaction can suddenly terminate if the reactants are not well mixed and in sufficient contact with each other.

Just a few years ago this kind of experiment was out of our reach because small video-recording devices with necessary resolution and recording capacity were outside our budget or nonexistent. Minimum focus distance of cameras was another problem as the space inside the rocket is very limited. Thanks to the rapid advances of photo and video industry, today we can easily afford a high definition video camera with a lens that will

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focus down to 1cm and will record more than 1 hour of high definition video before running out of memory/battery. Our preliminary design and calculations show that we will be able to observe diffusion patterns in a liquid system using a 5.5" diameter vehicle.

Experimental SetupA basic functional of our payload is shown on the figure bellow. The liquid is housed in a fully enclosed, leak-proof vessels made out of polycarbonate. The entire body of the liquid is evenly illuminated using white LEDs powered from on-board batteries. The dye injector is activated when the on-board avionics senses rocket liftoff (a servo will drive a plunger thus forcing the liquid dye out of its container into the clear liquid). High definition video camera will record movement of the dye in the liquid during the flight. At this moment we are considering Panasonic Lumix TS3 camera as the primary candidate for video-recording - the camera is capable of focusing down to 1cm and is also waterproof (aiding the survival of recorded data should the liquid container break during flight).

The liquid payload in the setup shown below is positioned horizontally (perpendicular to the flight trajectory) and we expect that this payload configuration will mostly record the effects of vehicle vibrations on the dye distribution.

Figure 9: Payload functional unit - liquid is in enclosed transparent vessel illuminated by white LED lights. The dye is injected instantly when the rocket avionics senses lift-off. Camera will record movement of the dye during rocket flight.

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The close focus capability of Lumix TS3 camera (and similar cameras) allows us to also use a vertical experimental setup where the dye is injected at either top or bottom end and the camera record the dye diffusion. An example from our preliminary experiment with vertical experimental setup is shown on the following picture.

Figure 10: Preliminary experiment with vertical setup: the dye was injected at the top of the liquid body and pictures of the system were taken every 0.3s.

The liquid dye has a higher density than the clear liquid (water) and thus in our lab-bench experiment the dye droplet moved from the top to the bottom of the vessel, leaving a diffusing trail of dye.

During the rocket flight a lot higher gravitational force will apply during boost (estimated acceleration is 12g) followed by negative acceleration and a short period of sub 1g gravity. We plan to have two vertical setups in the rocket (one camera will suffice to record both vertical setups) and inject the dye from the top in one of the setups and from the bottom end in the other setup. With the vertical setups we expect to observe primarily the effects of gravitational forces even though the rocket vibration will affect the dye diffusion as well. The vertical setup is shown on the drawing below.

Figure 11: Vertical setup - the same camera is watching two vessels with the liquid. The dye is injected from the top of one of the two vessels and from the bottom of the other vessel.

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Universal Avionics Platform - System HermesAs mentioned in the Vehicle section of this document, our payload will be aided by universal avionics platform, system Hermes. We will develop a simple payload controller to interface with Hermes system. Our payload controller will receive liftoff signal from Hermes and activate the servos driving the dye injectors and cameras. Upon receiving the apogee signal, the payload controller will terminate recording. Altitude and acceleration will be recorded by system Hermes itself and the liftoff/apogee signal transmission will be marked for later alignment with data recorded by the cameras.

Experimental Sequence1. As the rocket lifts off, the G-force sensor senses the gravitational forces and triggers the ejection of the blue dye into the liquid solutions, and the camera starts to take pictures of the diffusion.

2. During flight, the dye diffuses in the liquid and the video-camera records the dye diffusion.

3. Once the rocket reaches 700ft. while descending, the main parachute deploys and the rocket lands softly.

4. The image data will be downloaded from cameras and analyzed as described in the Data Analysis section.

5. The results will be reported in Post Launch Assessment Report.

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We plan to observe the dye diffusion in three different phases of the rocket flight: high-g phase, negative-g phase and low gravity phase. The first phase starts at ignition and the last phase ends at apogee. The graph below shows the phases (note: for brevity the graph is cut off at 10s, however the apogee does not occur until 17s). An on-board accelerometer will record acceleration on all three axes.

Figure 12: Flight phase: red - boost, high-g phase, blue - shortly after burnout, negative-g phase, yellow - coast until apogee, low gravity phase.

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Data AnalysisIdentical experimental setups will be placed in the rocket and on the ground. The ground setup will provide the baseline measurements (diffusion without flight-induced gravitational forces and vibrations). The data from both the ground setup and the on-board setup will be compared, the following variables will be measured and correlation constructed:

Independent variables

a Accelerationt Time after dye is released (flight time)

Dependent Variables

R Rate of diffusion (diffusion front speed)P Pattern of diffusion (qualitative classification)

Correlations

R = f(a) Rate of diffusion in relation to accelerationR = f(t) Rate of diffusion in relation to time after dye is releasedP = f(a) Pattern of diffusion in relation to accelerationP = f(t) Pattern of diffusion in relation to time after dye is released

Constants

Temperature inside of rocketAmount of dye injectedColor saturation of dyeVolume of liquid in container

Hypotheses

We make the following hypotheses:

1) We expect that the vibrations of the rocket will affect strongly the horizontal diffusion rate (horizontal = perpendicular to the flight trajectory).

2) We expect that the gravitational forces (acceleration/deceleration) will strongly affect the vertical diffusion rate.

3) We expect that there will be significant different between diffusion rates observed in on-board setups as opposed to the reference setups residing on the ground.

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Post Flight Procedure After a successful flight and rocket/payload recovery, we will download the data recorded by the cameras to a computer. The data will be analyzed as described in Data Analysis Section and the final report (PLAR) will be compiled and submitted to NASA.

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Performance Targets

The performance targets for the reusable launch vehicle and payload are as follows:

1. The launch vehicle shall carry a science or engineering payload of the team’s discretion.

The rocket carries a scientific payload to test the effects of gravitational forces and vibration on the diffusion of dye in water. A high definition video-cameras (1920x1080 pixels, 30/60 fps) will be used to record the diffusion process.

Figure 13: Payload unit schematics

2. The launch vehicle shall deliver the science or engineering payload to, but not exceeding, an altitude of 5,280 feet above ground level (AGL).

The current simulation predicts that the rocket will reach 5,207ft. The coefficient of drag is set to CD = 0.5. We have obtained this experimentally measured value from our previous experiments using boat-tailed K-class delivery vehicle very similar to our rocket.

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Figure 14: Altitude vs. Time graph

3. The recovery system electronics shall have the following characteristics:

a. The recovery system shall contain redundant altimeters. The term “altimeters” includes both simple altimeters and more sophisticated flight computers.

b. Each altimeter shall be armed with a dedicated arming switch.

c. Each arming switch shall be accessible from the exterior of the rocket airframe.

d. Each arming switch shall be capable of being locked in the ON position for the launch.

e. Te recovery system shall be designed to be armed on the pad.

f. The recovery system electronics shall be completely independent of the payload electronics.

g. Each altimeter shall have a dedicated battery.

h. Each arming switch shall be a maximum of six (6) feet above the base of the launch vehicle.

Our recovery system will have two fully redundant PerfectFlite MAWD altimeter. Each altimeter will be armed with an arming switch, accessible from the exterior of the rocket airframe. Each arming switch will be capable of being locked in the ON position for the launch. The recovery system will be designed to be armed on the pad. The recovery system electronics will be completely independent of the payload electronics and will be in a separate, fully shielded e-bay. Each altimeter will have a dedicated battery. Each arming switch will be a maximum of six feet above the base of the rocket.

4. The launch vehicle and science or engineering payload shall remain subsonic from launch until landing.

The rocket and scientific payload will remain subsonic from launch until landing. Simulations indicate the maximum velocity of 540mph.

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Figure 15: Velocity vs. Time graph

5. The launch vehicle and science or engineering payload shall be designed to be recoverable and reusable. Reusable is defined as being able to be launched again on the same day without repairs or modifications.

The rocket and scientific payload will be designed to be recoverable and reusable. Given sufficient amount of time for preparations, we will be able to launch the rocket again on the same day without repairs or modifications.

6. The launch vehicle shall stage the deployment of its recovery devices, where a drogue parachute is deployed at apogee and a main parachute is deployed at a much lower altitude. Tumble recovery from apogee to main parachute deployment is permissible, provided that the kinetic energy is reasonable.

The rocket will stage the deployment of its recovery devices, where a drogue parachute will be deployed at apogee and a main parachute will be deployed at a much lower altitude (700ft-900ft) during descent.

The descent rate under drogue is 68fps, the descent rate under main parachute is 16fps. The kinetic energy of the entire rocket at landing is 74.6ft-lbf.

Parachute Diameter [in]

Descent Rate [fps]

Ejection Charge [g]

Deployment Altitude

[ft]

Descent Weight

[lbs]

Impact Energy [ft-

lbf]Drogue 18 68 2.4 5280 18.75 -Main 90 16 5.5 700 18.75 74.6

Table 13: Parachutes, ejection charges and impact energy

7. The recovery system electronics shall be shielded from all onboard transmitting devices, to avoid inadvertent excitation of the recovery system by the transmitting device(s).

The recovery system electronics will be shielded from all onboard transmitting devices, to avoid inadvertent excitation of the recovery system by the transmitting device. The telemetry electronics will be located in payload e-bay, separate from the deployment e-bay. The deployment e-bay will be fully shielded.

8. Removable shear pins shall be used for both the main parachute compartment and the drogue parachute compartment.

Removable shear pins will be used for the main parachute compartment and the drogue parachute compartment. The number and size of shear pins will be determined during static and flight testing.

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9. The launch vehicle shall have a maximum of four (4) independent or tethered sections.

a. At landing, each independent or tethered sections of the launch vehicle shall have a maximum kinetic energy of 75 ft-lbf.

b. All independent or tethered section of the launch vehicle shall be designed to recover within 2,500 feet of the launch pad, assuming a 15 mph wind.

The entire launch vehicle weighing 18.75lbs lands at 16fps and has kinetic energy of 74.6ft-lbf at landing. During the return portion of the flight, the vehicle separates into three (3) tethered sections. All tethered sections of the launch vehicle are designed to recover within 2,500 ft of the launch pad, assuming a wind of 15 mph or less. Currently we calculate the under 15mph wind conditions and deployment of main parachute at 700ft, the vehicle will drift 2,444ft.

Wind Speed[mph]

Drift[ft]

Drift[mi]

0 0 0 5 814 0.15

10 1630 0.3115 2444 0.4620 3259 0.62

Table 14: Estimated drift distances

10.The launch vehicle shall be capable of being prepared for flight at the launch site within 2 hours, from the time the waiver opens.

The rocket will not take more than two hours to be prepared for flight at the launch site, from the time the waiver opens. The recovery system is a standard dual deployment arrangement with an estimated prep time of no more than two hours. The payload will be prepared prior the arrival to the launch site, fully encapsulated and inserted as a module prior the flight. The payload is fully independent of the vehicle.

11.The launch vehicle shall be capable of remaining in launch-ready configuration at the pad for a minimum of 1 hour without losing the functionality of any onboard component.

The rocket will be capable of remaining in launch-ready configuration at the pad for at least 1 hour without losing functionality of any onboard component. Currently we estimated minimum of 2-3 hours or available wait time.

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12.The launch vehicle shall be launched from a standard firing system (provided by the Range) using a standard 10-second countdown.

The rocket will be launched from a standard firing system. After arming, the vehicle and payloads are fully autonomous. After the rocket is prepared for launch, a 10-second countdown will be used prior to ignition.

13.The launch vehicle shall require no external circuitry or special ground support equipment to initiate the launch (other than what is provided by the Range).

The rocket will require no external circuitry or special ground support equipment to initiate the launch, other than what is provided by the Range. Both the vehicle and the payload are fully autonomous after arming.

14.Data from the science or engineering payload shall be collected, analyzed and reported by the team following the scientific method.

Data from the scientific payload will be collected, analyzed and reported by the team following the scientific method. We will analyze the variables according to the correlations explained under technical design.

15.An electronic tracking device shall be installed in each independent section of the launch vehicle and shall transmit the position of that independent section to a ground receiver. Audible beepers may be used in conjunction with an electronic transmitting device, but shall not replace the transmitting tracking device.

We will have a GPS tracker and a radio beacon on the vehicle. Additionally, we will use the 140dB sonic beacons. For GPS tracker we will utilize GPS feature of our universal avionics platform, system Hermes. The GPS data are continuously transmitted over full duplex 900MHz wireless link (XBee modem, line-of-sight range 6 miles) to our ground station.

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16.The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant (APCP) which is approved and certified by the National Association of Rocketry (NAR), Tripoli Rocketry Association (TRA) and/or the Canadian Association of Rocketry (CAR).

The rocket will use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant which is approved and certified by the National Association of Rocketry, Tripoli Rocketry Association and/or the Canadian Association of Rocketry.

Motor Diameter [mm]

Total Impulse

[Ns]

Burn Time [s]

Stability Margin

[calibers]Thrust to

weight ratio

AT K1050W 54 2522 2.30 3 12.4GRM K1075RT 54 2408 2.24 3 12.4AT K1750R 54 2468 1.46 3 17.9

Table 15: Propulsion options

17.The total impulse provided by the launch vehicle shall not exceed 2,560 Newton-seconds (K-class). This total impulse constraint is applicable to any combination of one or more motors.

The total impulse provided by the rocket will be less than 2,560 Ns (K-class). Our primary propulsion choice is AT-K1050W 54mm motor with 2,522Ns total impulse.

18.All teams shall successfully launch and recover their full scale rocket prior to FRR in its final flight configuration.

a. The purpose of the full scale demonstration flight is to demonstrate the launch vehicle’s stability, structural integrity, recovery systems, and the team’s ability to prepare the launch vehicle for flight.

b. The vehicle and recovery system shall have functioned as designed.

c. The payload does not have to be flown during the full-scale test flight.

i. If the payload is not flown, mass simulators shall be used to simulate the payload mass.

ii. If the payload changes the external surfaces of the launch vehicle (such as with camera housings and/or external probes), those devices must be flown during the full scale demonstration flight.

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d. The full scale motor does not have to be flown during the full scale test flight. However, it is recommended that the full scale motor be used to demonstrate full flight readiness and altitude verification.

e. The success of the full scale demonstration flight shall be documented on the flight certification form, by a Level 2 NAR/TRA observer.

f. After successfully completing the full-scale demonstration flight, the launch vehicle or any of its components shall not be modified without the concurrence of the NASA Range Safety Officer.

We will successfully launch and recover our full scale rocket prior to FRR in its final flight configuration. The vehicle and recovery system will function as designed. We intend to fly a full impulse motor for our last test flight. We expect plan to make 2-3 test flights with the full scale vehicle. If we do not fly the payload during the full-scale test flight, mass simulators will be used to simulate missing payload mass. The success of the full scale demonstration flight will be documented on the flight certification form by a Level 2 NAR/TRA observer. After completing the full-scale demonstration flight, the rocket or any of its components will not be modified without the concurrence of the NASA Range Safety Officer.

19.The following items are prohibited from use in the launch vehicle:

a. Flashbulbs. The recovery system must use commercially available low-current electric matches.

b. Forward canards.

c. Forward firing motors.

d. Rear ejection parachute designs.

e. Motors which expel titanium sponges (Sparky, Skidmark, MetalStorm, etc.)

The rocket will not contain flashbulbs, forward canards, forward firing motors, a rear ejection parachute design, or a motor which will expel titanium sponge (our primary propulsion choice is White Lightning).

20.Each team shall use a launch and safety checklist. The final checklist shall be included in the FRR report and used during the flight hardware and safety inspection and launch day.

Our team will use a launch and safety checklist. We will include the final checklist in the FRR report and use it during the flight hardware and safety inspection and launch day. The checklist will be developed and tested as our project progresses.

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21.Students on the team shall do 100% of the work on the project, including design, construction, written reports, presentations, and flight preparation with the exception of assembling the motors and handling black powder charges.

We will do 100% of the work on the project, including design, construction, written reports, presentations, and flight preparation. Mentors for the project have only advisory and supervisory roles.

22.The rocketry mentor supporting the team shall have been certified by NAR or TRA for the motor impulse of the launch vehicle, and the rocketeer shall have flown and successfully recovered (using electronic, staged recovery) a minimum of 15 flights in this or a higher impulse class, prior to PDR.

The rocketry mentor supporting our team (Mr. Brent Lillesand) has been certified by NAR for the motor impulse of the rocket, and has flown and successfully recovered (using electronic, staged recovery) more than 15 flights in this impulse class (L2) and some flights in impulse class L3.

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Major Challenges and Solutions

Major Vehicle Challenges

1. Booster section alignment: The rocket has a transition from 5.5" payload section to 4" booster section. An utmost precision during construction is necessary to prevent misalignment of the booster tube. We will user laser beams to align the tubes and dry fit entire assembly before applying the epoxy glue. Post-assembly measurement will be used to prove the success.

2. Large, heavy rocket: We know from our previous experiments with this type of vehicle that we will need a full K motor to deliver this rocket to one mile. Precise construction, including pursuit of all weight saving opportunities will be necessary. The rocket will be equipped with a conical motor retainer and finished with glossy paint to decrease the drag coefficient even further.

3. Heavy loads on anchors: successful construction and operation of a 5.5" vehicle is a drastically different task from the more traditional and manageable 4" vehicle. Special attention needs to be paid to all anchor points, coupler stiffeners and positive lock-in must be used on all load-bearing parts.

4. Coupling surfaces: coupling of 5.5" tubing is generally unforgiving to minor issues that would present no problem with 4" tubing. We will pay attention to perfect alignment and cleanliness of our coupling surfaces, using talcum powder to lubricate all separation points.

Major Payload Challenges and Solutions

1. Liquid payload: possibility of leaks and high density (weight) of payload need to be addressed during design. We will build our own reaction vessels and test them for leaks. The outer payload compartment will be sealed from the rest of the vehicle to prevent liquid leakage in case of payload damage. Payload electronics will not have any active role in rocket flight and will be in a different e-bay altogether.

2. Dye injection: we are facing the problem of building sufficiently fast and leak-proof dye injector. The injector must not introduce air bubbles into the system, permit leaks or sloshing and must function under high acceleration (during rocket liftoff). We are currently considering a system consisting of short throw servos and a piston.

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3. Timely payload activation: the colored dye needs to be injected into clear liquid as soon as the rocket starts moving. We will use short throw servos to execute the injection and finely tuned G-switch triggers to detect the liftoff.

4. False liftoff detection: maximizing the sensitivity of G-switch triggers for payload activation brings the problem of false positives in liftoff detection. To mitigate this issue we will only activate the G-switch triggers after the rocket has been placed on the pad and all personnel has retreated back. The G-switch triggers will be activated remotely via wireless link. The payload will also use the wireless link to report the liftoff detection so we have an indication of false trigger condition and can reset the payload. Lastly, redundant diffusion vessels will be prepared prior to the launch to quickly replace the falsely triggered vessels (should such mishap occur).

5. Data analysis: high definition video present serious challenge in data processing because of the size of collected information. We will use high performance Linux quad core computers for final image analysis.

6. Extensive preliminary lab work: While we have successfully carried out proof-of-concept experiments, much work remains before the payload can be finalized. We will need to optimize dye selection with respect to observed diffusion rates. We have already started experiments with more viscous liquids (such as corn syrup) should the need to slow down the diffusion rates arise.

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Educational Engagement

Community Support

After eight years of the club’s existence, we are well known at various departments of the UW and many researchers are eager to work with us. During our seven years of participation in SLI we have met with a number of people from various departments within the University of Wisconsin-Madison, including Professor McCammon from the department of Physics, Professor Eloranta from the department of Atmospheric Sciences, Professor Pawley from the department of Zoology, and Professors Anderson and Bonazza from the department of Mechanical Engineering. Last year we have added Prof. Fernandez and Prof. Gilroy from the department of Botany, and Prof. Masson from the department of genetics.These contacts have been incredibly helpful in designing and refining our original experimental ideas and creating an experiment that will return meaningful data.

We have finally achieved official affiliation with UW Madison and our research meetings are now held in Chamberlin Hall, Dept. of Physics.

Every year we raise funds by raking leaves during autumn in local neighborhoods. We find this is an excellent way to earn the support of the community and increase our visibility.

The club also provides a steady stream of volunteers for public television and public radio fundraising drives. While this is not a direct display of our work or interests, it gives us the opportunity to provide public service in the name of our club.

In 2009 many club members gave back to the community by helping build a fence in the local soccer park where we also happen to launch our TARC practice flights in the winter. We are currently discussing other soccer park improvements with their management.

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Outreach Programs

Last year we participated in many educational engagement opportunities, such as helping sizeable groups of young children at the local middle schools to build and fly Alka-Seltzer powered rockets. We launched about 300 rockets for an audience of about 150 kids during this program, as well as displaying some of our TARC, SLI and R4S rockets.

We will also be participating in our annual “Raking for Rockets” program, where we rake community lawns in order to simultaneously bring about an increased awareness in rocketry, and raise the funds necessary for our TARC and SLI programs.

Besides these programs, we also recruited new members for our club at Madison West High School (our current membership is above 50 students mark) in a number of recruitment events which included the daily announcements, organized recruitment events , and posters throughout the school advertizing the location and time of the first informational meeting. The new members will participate in TARC, along with a few returning members from our SLI teams. TARC club meetings have already started for this school year, with interested new members learning about the basics of rocket design, building, and operation.

The table below show the outreach programs that plan for this year. The programs target primarily elementary and middle schools. We will most likely add several events to this program as the year progresses (we have became well known for our outreach activities and we are already receiving requests from schools and organization that we have never worked with before).

Date School Outreach # of People (estimate)

Sept. 23, 2011 Randall Elementary School Homecoming

Parade

100

Dec. 10, 2011 Eagle Elementary Alka-Seltzer Rockets

50

Jan 14, 2012 Lincoln Elementary Alka-Seltzer Rockets

50

Feb. 11, 2012 O’Keefe Middle School

Super Science Saturday (Alka-Seltzer Rockets)

50

Mar. 11, 2012 Randall Elementary Super Science Saturday

(Alka-Seltzer Rockets)

100

Apr. 14, 2012 Lincoln Elementary Pneumatic Rockets 50Total: 450

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Table 16: Planned outreach events.

We are noticing a steady increase of club members graduating into engineering colleges, most notably:

Marina Parra (SLI-2009): Carnegie Mellon, intends majoring in aerospace engineering Benjamin Winokur (SLI-2008, 2009, 2010): University of St. Louis, aerospace major Rose Wang: (SLI-2008, 2009, 2010): Cornell University, working in the Nanosat program Thomas Ostby: University of Alabama, aerospace major John Schoech (SLI-2008, SLI-2009, SLI-2010): Stanford University, California Tenzin Sonam (SLI-2008, SLI-2009, SLI-2010): Stanford University, California David Aeschlimann (SLI2009, SLI2010): Stanford University, California Nhien Tran (SLI2011): Stanford University, California Enrique Olivas (SLI2010, SLI2011): University of Southern California Jacob Ediger: (SLI2010, SLI2011): Purdue University

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Project PlanSchedule

October 201117 Schools Notified of Selection21 SLI team teleconference (tentative)28 Preliminary Design Review (PDR) work begins

November 20114 Web presence established for each team

28 Preliminary Design Review (PDR) report and PDR presentation slides posted on the team website by 8:00 a.m. Central Time

December 20115-14 Preliminary Design Review Presentations (tentative)15 Acquire parts and supplies for scale model16 Begin work on scale model

24-31 Winter BreakJanuary 2012

7 Scale model completed14/15 Scale model test flight, acquire parts for full scale

22 Begin work on full scale23 Critical Design Review (CDR) reports and CDR presentation slides posted on the team

website by 8:00 a.m. Central TimeFebruary 2012

1-10 Critical Design Review Presentations (tentative)22 Full scale vehicle completed

28/29 Full scale test flight #1 – stress testMarch 2012

24/25 Full scale test flight #2 with payload26 Flight Readiness Review (FRR) reports and FRR presentation slides posted on the team

website by 8:00 a.m. Central TimeApril 2012

2-11 Flight Readiness Review Presentations (tentative)15 Rocket ready for launch in Huntsville18 Travel to Huntsville

19-20 Flight Hardware and Safety Checks (tentative)21 Launch day, full scale flight #322 Return Home

28/29 Full scale flight #4 (tentative)May 2012

7 Post-Launch Assessment Review (PLAR) posted on the team website by 8:00 a.m. Central Time

Table 17: Timeline of SLI 2011

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Budget

VehicleTubing, nosecone, bulkheads $ 300.00 Fin Material (G10 Fiberglass) $ 150.00 PerfectFlite MAWD Altimeter (x4) $ 400.00Parachutes, recovery gear $ - Walston Beacon $ 150.00 Miscellaneous supplies (tools, glues, batteries, wires) $ 400.00

Scale ModelPaper Tubing $ 100.00 Fin Material (G10 Fiberglass) $ 50.00

MotorsScale Model Motors $ 100.00 Preliminary Flight Motors $ 250.00

PayloadPolycarbonate sheets $ 200.00Payload controller + Hermes System $ 350.00LED Light Source x 5 $ 250.00G sensor $ 10.00Camera x 3 $ 1000.00Powder Food Coloring $ 5.00 Servos x 5 $ 60.00

Total $ 3,775.00

Table 18 : Budget for 2009-10 SLI Program (* - already in possession)

Flight$400/Person * 9 People $ 3,600.00

Rooms$119/Room * 5 Rooms * 5 Nights $ 2,975.00

Car Rental (Ground Support Vehicle)$500 rental+ $400 gas $ 900.00

Total $ 7,475.00

Cost per Team Member $ 1,067.86

Table 19: Budget for the travel to Huntsville, AL

Madison West Rocket Club has sufficient money earning opportunities to cover for possible discrepancies between the estimated budget and actual project expenses. Additionally, it is our policy to provide necessary economic help to all SLI students who cannot afford the travel expenses associated with the program. Every year we award several full expense travel scholarships both to our SLI and TARC students. The monetary amounts and the names of recipients are not disclosed.

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Educational Standards

A) Wisconsin’s Model Academic StandardsEnglish/Language Arts

Reading and LiteratureA.12.4 Students will read to acquire information

• Analyze and synthesize the concepts and details encountered ininformational texts such as reports, technical manuals, historical papers, and government documents• Draw on and integrate information from multiple sources when acquiring knowledge and developing a position on a topic of interest

WritingB.12.1 Create or produce writing to communicate with different audiences for a variety of purposes

• Prepare and publish technical writing such as memos, applications, letters, reports and resumes for various audiences, attending to details of layout and format as appropriate to purpose

B.12.2 Plan, revise, edit and publish clear and effective writing.Oral Language

C.12.1 Prepare and deliver formal oral presentations appropriate to specific purposes and audiences

LanguageD.12.1 Develop their vocabulary and ability to use words, phrases, idioms, and various grammatical structures as a means of improving communication

Media and TechnologyE.04.3 Create products appropriate to audience and purpose

• Write news articles appropriate for familiar mediaE.12.1 Use computers to acquire, organize, analyze, and communicateinformation

Research and InquiryF.12.1 Conduct research and inquiry on self-selected or assigned topics, issues, or problems and use an appropriate form to communicate their findings.

• Formulate questions addressing issues or problems that can be answered through a well defined and focused investigation• Use research tools found in school and college libraries, take notes collect and classify sources, and develop strategies for finding and recording information• Conduct interviews, taking notes or recording and transcribing oralinformation, then summarizing the results• Develop research strategies appropriate to the investigation, considering methods such as questionnaires, experiments and field studies• Organize research materials and data, maintaining a note-taking systemthat includes summary, paraphrase, and quoted material• Evaluate the usefulness and credibility of data and sources by applying tests of evidence including bias, position, expertise, adequacy, validity, reliability, and date

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• Analyze, synthesize, and integrate data, drafting a reasoned report that supports and appropriately illustrates inferences and conclusions drawn from research• Present findings in oral and written reports, correctly citing sources

MathematicsMathematical Processes

A.12.4 Develop effective oral and written presentations employing correctmathematical terminology, notation, symbols, and conventions for mathematical arguments and display of dataA.12.5 Organize work and present mathematical procedures and results clearly, systematically, succinctly, and correctly

Number Operations and RelationshipsB.12.6 Routinely assess the acceptable limits of error when

• evaluating strategies• testing the reasonableness of results• using technology to carry out computations

GeometryC.12.1 Identify, describe, and analyze properties of figures, relationships among figures, and relationships among their parts by constructing physical modelsC.12.2 Use geometric models to solve mathematical and real-world problemsC.12.5 Identify and demonstrate an understanding of the three ratios used in right triangle trigonometry

MeasurementD.12.1 Identify, describe, and use derived attributes (e.g., density, speedacceleration, pressure) to represent and solve problem situationsD.12.2 Select and use tools with appropriate degree of precision to determine measurements directly within specifies degrees of accuracy and error

Statistics and ProbabilityE.12.1 Work with data in the context of real-world situations by

• Formulating hypotheses that lead to collection and analysis of one and two variable data• Designing a data collection plan that considers random sampling, control groups, the role of assumptions, etc.• Conducting an investigation based on that plan• Using technology to generate displays, summary statistics, andpresentations

Algebraic RelationshipsF.12.2 Use mathematical functions (e.g., linear, exponential, quadratic, power) in a variety of ways, including

• using appropriate technology to interpret properties of their graphical representations (e.g., intercepts, slopes, rates of change, changes in rates of change, maximum, minimum)

F.12.4 Model and solve a variety of mathematical and real-world problems by using algebraic expressions, equations, and inequalities

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ScienceScience Connections

A.12.3 Give examples that show how partial systems, models and explanations are used to give quick and reasonable solutions that are accurate enough for basic needsA.12.5 Show how the ideas and themes of science can be used to make real-life decisions about careers, work places, life-styles, and use of resources

Science InquiryC.12.2 Identify issues from an area of science study, write questions that could by investigated, review previous research on these questions, and design and conduct responsible and safe investigations to help answer the questionsC.12.6 Present the results of investigations to groups concerned with the issues, explaining the meaning and implications of the results, and answering questions in terms the audience can understand

Motions and ForcesD.12.7 Qualitatively and quantitatively analyze changes in the motion of objects and the forces that act on them and represent analytical data both algebraically and graphically

Science ApplicationsG.12.1 Identify personal interests in science and technology, implications that these interests might have for future education, and decisions to be consideredG.12.2 Design, build, evaluate, and revise models and explanations related to the earth and space, life and environmental, and physical sciences

B) National Science Education StandardsScience and Technology (9-12)

Content Standard EStudents should develop

• Abilities of technological design• Understanding about science and technology

Science as Inquiry (9-12)Content Standard A

Students should develop• Abilities necessary to do scientific inquiry• Understandings about scientific inquiry

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Sustainability

The rocketry program at Madison West High School is now in its ninth year, and it provides a strong, compelling incentive for students to research unique science concepts and enhance their problem-solving skills.

Incoming students are enrolled in the TARC program, where they attend classroom sessions taught by the mentors in order to learn the basic rocketry knowledge and methodologies essential to the contest.

Rockets for Schools is the latest rocketry contest that our club has entered. For it, students are given a high-power rocket kit and asked to design a scientific payload to be flown from Sheboygan, WI over Lake Michigan. Not only does this project offer good training for the process of obtaining an SLI grant, it also gives an additional activity option to first-year club members: while they are not allowed to participate in SLI, our highest-level project, they may participate in the R4S competition. We have modeled our R4S program after the SLI program, placing emphasis on the scientific project and development process. All R4S students are encouraged to seek L1 HPR certification as a part of the R4S program. Our first two R4S teams (2010, 2011) consisted of all first-year members, and their high scores won additional SLI invitations for the club this for 2011 and 2012 seasons.

This year we have continued our summer HPR L1/L2 Certifications program. Two of our alumni, John Schoech and Alissa Chen, attained L2 Certification in addition to a number of L1 certifications obtained by younger club members. This highly successful summer L1 program (outside school year) was invented, coordinated and administered by the SLI-2008, SLI-2009 and SLI-2010 participant, Ms. Zoë Batson. Zoë also worked year-long as a junior mentor in our club, assisting members with their projects and she has participated in SLI Advanced Rocketry Workshop in New Mexico. We expect her to continue her involvement with our club.

Madison West Rocketry actively recruits new members in the fall season: the Freshman Club Carnival, West Fest, Homecoming parade, and daily announcements, all showcase our club’s achievements, appealing to interested individuals.

We collaborate extensively with experts at the University of Wisconsin (UW). During our meetings we are able to have analytical discussions with professionals regarding the feasibility and limitations of various potential experimental payloads. We have developed such relationships with eight different departments; this variety provides us with experiences perspectives on our design and objectives.

We now have five committed mentors who aid our group throughout all the stages of our well-established rocketry program. They patiently teach us and guide us in the planning, processing, writing, building, organization, and launching of our project. Our mentors dedicate much time and effort throughout the year- we greatly value their compassion and support.

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An increasing number of parents are taking interest in supporting our club’s meetings, fundraisers, outreach projects, and launches. They provide us with food and transportation during the cold winter events and launches, and are a great source of encouragement. Additionally, we are seeing an increase in students interested in taking on mentoring roles and work with younger club members. Ms. Zoë Batson (alumni, SLI2008, 2009 and 2010 participant) and Mr. Zuodian Hu (junior student, SLI2011 participant) accompanied our R4S team on their to Sheboygan to provide leadership and assistance as needed. Student mentors in our club enjoy position of authority and respect and their hard work allows senior educators to concentrate on further program developments.

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AppendicesAppendix A: Resume for Adrian

1157 Amherst DriveMadison, WI [email protected]

EducationShorewood Hills Elementary School (2001-2007)Velma Hamilton Middle School (2007-2010)Madison West High School (2010-Present)

Activities

RocketryRocket Club (2011-present)2010 TARC participant2011 Rockets for Schools, 2nd place

SportsShorewood Hills Swim Team (2002-present)Madison West Men’s Swimming (2010-present)Madison West Men’s Cross Country (2010-present)

LanguagesEnglishSpanish (4 years)

Volunteering

Community Service with Madison West Rocket ClubCommunity service with First Unitarian Society of Madison

Advanced/Honors Classes

Algebra honors (7th grade)Geometry honors (8th grade)Algebra 2 Trigonometry honors (9th grade)Pre-Calculus honors (10th grade)Biology honors (9th grade)

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Appendix B: Resume for Amelie

2244 Rowley Ave.Madison, WI [email protected]

Academic Experience:Charles-Dickens Grundschule (2000-2004)Randall Elementary School (2004-2006)Velma Hamilton Middle School (2006-2009)Madison West High School (2009-Present)

Languages:English, German, French (5th year)

Extracurricular Activities and Clubs:Piano lessons (2001-2010)Camp Randall Rowing Club (2009-2010)Madison Youth Choirs (2010)Madison West Rocket Club (spring of 2010-Present)

Achievements:Music:2006 and 2007 Sonatina Festival: Superior Rating2008 Sonatina Festival: Excellent Rating2007-2010 National Federation of Music Clubs Junior Festival: Superior RatingMAPTA composition competition: 1st Place (2010)

Rocketry:Team America Rocketry Challenge Finalist (2011)Rockets for Schools: 2nd Place (2011)

Other:2009 University of Wisconsin Law School Middle School Mock Trial Competition: 1st PlaceHamilton Pride Award (2007-2008)High Honor Roll (2006-2011)Member of the French Honors Society (2011)

Volunteer Work:Acolyting at Bethel Lutheran Church (2005-2010)Various piano recitals in nursing and retirement homes (2006-2010)Community service with Madison West Rocket ClubMission Trip to Benton Harbor, Michigan (2009)Mission Trip to New Orleans (2011)

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Appendix C: Resume for Caitlin

2205 West Lawn Ave.Madison, WI [email protected]

Academic ExperienceFranklin Elementary (2001-2004)Randall Elementary (2004-2007)Hamilton Middle School (2007-2010)West High School (2010-present)High Honor Roll since middle school

LanguagesFrench (2008-2010)Latin (2010-present)

MusicSchool Orchestra (2005-2011)Private Violin Lessons (2006-present)Private Piano Lessons (summers of 2008-2011)

Extracurricular ActivitiesScience Olympiad (2009-2011, nationals in 2010)Future Problem Solvers (2007-2010, 2nd individual at internationals 2010)Math Team (2008-present)National History Day (2009-2010)Club Gymnastics (1999-2010)School Gymnastics (2010-present)Club Soccer (2001-2010)School Track and Field (2010-present)Midwest Academic Talent Search Finalist (2008 and 2010)

Volunteer ExperienceCommunity Service Club (2009-2010)Peer Tutoring (2010-present)Monroe Street Fine Arts Center (summer 2011)Outreach through Rocket Club (2010-2011)Filming at Young Shakespeare Players (2011-present)

Rocketry ExperienceTARC Finals (2011)2nd Place Rockets for Schools (2011)Madison West Rocketry Club (2010-present)

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mailto:[email protected]


Appendix D: Resume for Han

5001 Sheboygan Ave #114Madison, WI [email protected]

Academic ExperienceHo-Su Elementary School (2001~2006)Bak-Suk Middle School (2007~2008)Saipan International School (2008~2009)Madison West High School (2009~Present)

LanGuage: Korean, English (3rd year), Japanese (2nd year)

Activities and Achievements Rocketry

- TARC Finalist (2011)- SLI(P) (2011~ Present)

Music- Cello (2004~2006)- Piano (2002~2004)- Guitar (2011~Present)- Violin (2011~Present)- 2nd place in Middle School city orchestra competition- Member of WYSO (2010~Present)- Church Youth Group Praising team Leader- Church Choir Bass- Ukulele (2008~Present)

Sports- Madison West Basketball Team (2009~Present)- Saipan International school Junior Varsity Basketball Team (2008)- Madison West Track Team (2011~Present)- Middle School City Competition Track 1st Place in 100m dash, 200m

dash, and 400m relay (2001~2008)

Others- Teacher Assistant at Korean Language School (2009~Present)- Making Food for poor (2006~2007)- Church Youth Group Vice President- Honor Roll (2006~Present)- Graduation Speech at Saipan International School- Madison West Varsity Math Team- Member of the The National Society of High School Scholary- Imaginitive Drawing Competition City 1st place (elementary school)

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Appendix E: Resume for Jack

1111 Lincoln St.53711 Madison, [email protected]

EducationWaynewood Elementary (2001-March 2004)Franklin Elementary (March 2004- June 2004)Randall Elementary (2004-2007)Velma Hamilton Middle School (2007-2010)West High School- currently sophomore (2010-present)

LanguagesEnglish, Latin (2nd year)

Activities and Clubs

RocketryMadison West Rocket Club (2010-present)TARC Nationals Participant (2010)R4S 2nd place (2010)SLI (2011-present)

OtherFuture Problem Solvers (2005-2010)

1st place state (2006/2007)3rd place state (2008)5th place International (2007)

Band (2007-2011)Mock Trial (2009)West High Freshman Baseball (2010)Peer Tutorial (2011)

Honors ClassesAlgebra 1 Honors (7th grade)Geometry Honors (8th grade)Algebra 2 Honors (9th grade)Accelerated Biology (9th grade)English 2 Honors (10th grade)

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Appendix F: Resume for Mia

1605 Jefferson St.Madison, WI [email protected]

Academic ExperienceFranklin Elementary (2001-2004)Randall Elementary (2004-2007)Asagao Japanese Language School (2004-2007)Hamilton Middle School (2007-2010)Hoshuko Japanese Language School (2008-2010)West High School (2010-present)

LanguagesFluent in English and Japanese

Rocketry ExperienceWest Rocketry Club (2010-present)Qualified for TARC finals (2010-2011)Second place at Rockets for Schools (2010-2011)

MusicPiano Group Classes (2001-2008)Private Piano Lessons (2008-present)School Orchestra- Viola (2005-present)

VolunteeringVolunteering at Hoshuko Japanese Language School (2010-present)Outreach through West Rocketry Club (2011-present)

AchievementsHigh Honor Roll at Hamilton Middle School (2007-2010)High Honor Roll at West High School (2010-2011)

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Appendix G: Resume for Owen

610 South Prospect AVEMadison, WI [email protected]

Academic Experiences: Franklin Elementary School (2001-2004) Randall Elementary School (2004-2007) Velma Hamilton Middle School (2007-2010)

o Graduated with high academic honors Madison West High School (2010-present)

o 4.0 cumulative GPA

Honors and Elective Courses: Honors Algebra, Honors Geometry, Honors Biology, Drawing and Design, Film Studies, Culinary Basics

Languages: English, entering fourth year of studying French

Extracurricular Activities: Velma Hamilton Middle School Community Service Club (2009-2010)

o Volunteered at Ronald McDonald Houseo Participated in community clean-up activitieso Participated in book drive

Boy Scouts of America Troops 122 and 2 (2008-present)Served as Scribe and Assistant Patrol LeaderParticipated in annual food drivesParticipated in adopt-a-highway clean-upOrganized troop fun nightParticipated in troop camp outingsBackpacked in Glacier National Park

West High Rocket Club (2010-present)Finalist in Rockets for Schools Program Participated in Team America Rocket CompetitionParticipated in fund-raising activities

Interests: Video games Reading comic books and fantasy novels Hiking/Biking Travel Internet research Baking

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mailto:[email protected]/


Appendix H: Model Rocket Safety Code

1. Materials. I will use only lightweight, non-metal parts for the nose, body, and fins of my rocket.

2. Motors. I will use only certified, commercially-made model rocket motors, and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer.

3. Ignition System. I will launch my rockets with an electrical launch system and electrical motor igniters. My launch system will have a safety interlock in series with the launch switch, and will use a launch switch that returns to the "off" position when released.

4. 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.

5. Launch Safety. I will use a countdown before launch, and will ensure that everyone is paying attention and is a safe distance of at least 15 feet away when I launch rockets with D motors or smaller, and 30 feet when I launch larger rockets. If I am uncertain about the safety or stability of an untested rocket, I will check the stability before flight and will fly it only after warning spectators and clearing them away to a safe distance.

6. Launcher. I will launch my rocket from a launch rod, tower, or rail that is pointed to within 30 degrees of the vertical to ensure that the rocket flies nearly straight up, and I will use a blast deflector to prevent the motor's exhaust from hitting the ground. To prevent accidental eye injury, I will place launchers so that the end of the launch rod is above eye level or will cap the end of the rod when it is not in use.

7. Size. My model rocket will not weigh more than 1,500 grams (53 ounces) at liftoff and will not contain more than 125 grams (4.4 ounces) of propellant or 320 N-sec (71.9 pound-seconds) of total impulse. If my model rocket weighs more than one pound (453 grams) at liftoff or has more than four ounces (113 grams) of propellant, I will check and comply with Federal Aviation Administration regulations before flying.

8. Flight Safety. I will not launch my rocket at targets, into clouds, or near airplanes, and will not put any flammable or explosive payload in my rocket.

9. Launch Site. I will launch my rocket outdoors, in an open area at least as large as shown in the accompanying table, and in safe weather conditions with wind speeds no greater than 20 miles per hour. I will ensure that there is no dry grass close to the launch pad, and that the launch site does not present risk of grass fires.

10.Recovery System. I will use a recovery system such as a streamer or parachute in my rocket so that it returns safely and undamaged and can be flown again, and I will use only flame-resistant or fireproof recovery system wadding in my rocket.

11.Recovery Safety. I will not attempt to recover my rocket from power lines, tall trees, or other dangerous places.

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http://www.nar.org/NARmrsc.html#sitedimensions


LAUNCH SITE DIMENSIONSInstalled Total Impulse (N-

sec)Equivalent Motor

TypeMinimum Site Dimensions

(ft.)0.00--1.25 1/4A, 1/2A 501.26--2.50 A 1002.51--5.00 B 2005.01--10.00 C 400

10.01--20.00 D 50020.01--40.00 E 1,00040.01--80.00 F 1,00080.01--160.00 G 1,000160.01--320.00 Two Gs 1,500

Table 20: Minimum launch site dimensions

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Appendix I: High Power Rocket Safety Code

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.

1. 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.

2. 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.

3. 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. If my rocket has onboard ignition systems for motors or recovery devices, these will have safety interlocks that interrupt the current path until the rocket is at the launch pad.

4. 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.

5. Launch Safety. I will use a 5-second countdown before launch. I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table, and that a means is available to warn participants and spectators in the event of a problem. I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable.

6. 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 if the rocket motor being launched uses titanium sponge in the propellant.

7. 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 one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch.

8. 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

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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.

9. Launch Site. I will launch my rocket outdoors, in an open area where trees, power lines, 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.

10.Launcher Location. My launcher will be at least one half the minimum launch site dimension, or 1500 feet (whichever is greater) from any inhabited 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.

11.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.

12.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.

MINIMUM DISTANCE TABLEInstalled Total

Impulse (Newton-Seconds)

Equivalent High Power Motor Type

Minimum Diameter of

Cleared Area (ft.)

Minimum Personnel

Distance (ft.)

Minimum Personnel Distance (Complex

Rocket) (ft.)0 -- 320.00 H or smaller 50 100 200320.01 -- 640.00

I 50 100 200

640.01 -- 1,280.00

J 50 100 200

1,280.01 -- 2,560.00

K 75 200 300

2,560.01 -- 5,120.00

L 100 300 500

5,120.01 -- 10,240.00

M 125 500 1000

10,240.01 -- 20,480.00

N 125 1000 1500

20,480.01 -- 40,960.00

O 125 1500 2000

Table 21: Minimum launch site dimensions

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Appendix J: Section 508

§ 1194.21 Software applications and operating systems.

(a) When software is designed to run on a system that has a keyboard, product functions shall be executable from a keyboard where the function itself or the result of performing a function can be discerned textually.

(b) Applications shall not disrupt or disable activated features of other products that are identified as accessibility features, where those features are developed and documented according to industry standards. Applications also shall not disrupt or disable activated features of any operating system that are identified as accessibility features where the application programming interface for those accessibility features has been documented by the manufacturer of the operating system and is available to the product developer.

(c) A well-defined on-screen indication of the current focus shall be provided that moves among interactive interface elements as the input focus changes. The focus shall be programmatically exposed so that assistive technology can track focus and focus changes.

(d) Sufficient information about a user interface element including the identity, operation and state of the element shall be available to assistive technology. When an image represents a program element, the information conveyed by the image must also be available in text.

(e) When bitmap images are used to identify controls, status indicators, or other programmatic elements, the meaning assigned to those images shall be consistent throughout an application's performance.

(f) Textual information shall be provided through operating system functions for displaying text. The minimum information that shall be made available is text content, text input caret location, and text attributes.

(g) Applications shall not override user selected contrast and color selections and other individual display attributes.

(h) When animation is displayed, the information shall be displayable in at least one non-animated presentation mode at the option of the user.

(i) Color coding shall not be used as the only means of conveying information, indicating an action, prompting a response, or distinguishing a visual element.

(j) When a product permits a user to adjust color and contrast settings, a variety of color selections capable of producing a range of contrast levels shall be provided.

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(k) Software shall not use flashing or blinking text, objects, or other elements having a flash or blink frequency greater than 2 Hz and lower than 55 Hz.

(l) When electronic forms are used, the form shall allow people using assistive technology to access the information, field elements, and functionality required for completion and submission of the form, including all directions and cues.

§ 1194.22 Web-based intranet and internet information and applications.

(a) A text equivalent for every non-text element shall be provided (e.g., via "alt", "longdesc", or in element content).

(b) Equivalent alternatives for any multimedia presentation shall be synchronized with the presentation.

(c) Web pages shall be designed so that all information conveyed with color is also available without color, for example from context or markup.

(d) Documents shall be organized so they are readable without requiring an associated style sheet.

(e) Redundant text links shall be provided for each active region of a server-side image map.

(f) Client-side image maps shall be provided instead of server-side image maps except where the regions cannot be defined with an available geometric shape.

(g) Row and column headers shall be identified for data tables.

(h) Markup shall be used to associate data cells and header cells for data tables that have two or more logical levels of row or column headers.

(i) Frames shall be titled with text that facilitates frame identification and navigation.

(j) Pages shall be designed to avoid causing the screen to flicker with a frequency greater than 2 Hz and lower than 55 Hz.

(k) A text-only page, with equivalent information or functionality, shall be provided to make a web site comply with the provisions of this part, when compliance cannot be accomplished in any other way. The content of the text-only page shall be updated whenever the primary page changes.

(l) When pages utilize scripting languages to display content, or to create interface elements, the information provided by the script shall be identified with functional text that can be read by assistive technology.

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(m) When a web page requires that an applet, plug-in or other application be present on the client system to interpret page content, the page must provide a link to a plug-in or applet that complies with §1194.21(a) through (l).

(n) When electronic forms are designed to be completed on-line, the form shall allow people using assistive technology to access the information, field elements, and functionality required for completion and submission of the form, including all directions and cues.

(o) A method shall be provided that permits users to skip repetitive navigation links.

(p) When a timed response is required, the user shall be alerted and given sufficient time to indicate more time is required.

Note to §1194.22:

1. The Board interprets paragraphs (a) through (k) of this section as consistent with the following priority 1 Checkpoints of the Web Content Accessibility Guidelines 1.0 (WCAG 1.0) (May 5, 1999) published by the Web Accessibility Initiative of the World Wide Web Consortium:

Section 1194.22 Paragraph WCAG 1.0 Checkpoint(a) 1.1(b) 1.4(c) 2.1(d) 6.1(e) 1.2(f) 9.1(g) 5.1(h) 5.2(i) 12.1(j) 7.1(k) 11.4

Table 22: Checkpoint consistent with the Web Content Accessibility Guidelines

2. Paragraphs (l), (m), (n), (o), and (p) of this section are different from WCAG 1.0. Web pages that conform to WCAG 1.0, level A (i.e., all priority 1 checkpoints) must also meet paragraphs (l), (m), (n), (o), and (p) of this section to comply with this section. WCAG 1.0 is available at http://www.w3.org/TR/1999/WAI-WEBCONTENT-19990505.

§ 1194.23 Telecommunications products.

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(a) Telecommunications products or systems which provide a function allowing voice communication and which do not themselves provide a TTY functionality shall provide a standard non-acoustic connection point for TTYs. Microphones shall be capable of being turned on and off to allow the user to intermix speech with TTY use.

(b) Telecommunications products which include voice communication functionality shall support all commonly used cross-manufacturer non-proprietary standard TTY signal protocols.

(c) Voice mail, auto-attendant, and interactive voice response telecommunications systems shall be usable by TTY users with their TTYs.

(d) Voice mail, messaging, auto-attendant, and interactive voice response telecommunications systems that require a response from a user within a time interval, shall give an alert when the time interval is about to run out, and shall provide sufficient time for the user to indicate more time is required.

(e) Where provided, caller identification and similar telecommunications functions shall also be available for users of TTYs, and for users who cannot see displays.

(f) For transmitted voice signals, telecommunications products shall provide a gain adjustable up to a minimum of 20 dB. For incremental volume control, at least one intermediate step of 12 dB of gain shall be provided.

(g) If the telecommunications product allows a user to adjust the receive volume, a function shall be provided to automatically reset the volume to the default level after every use.

(h) Where a telecommunications product delivers output by an audio transducer which is normally held up to the ear, a means for effective magnetic wireless coupling to hearing technologies shall be provided.

(i) Interference to hearing technologies (including hearing aids, cochlear implants, and assistive listening devices) shall be reduced to the lowest possible level that allows a user of hearing technologies to utilize the telecommunications product.

(j) Products that transmit or conduct information or communication, shall pass through cross-manufacturer, non-proprietary, industry-standard codes, translation protocols, formats or other information necessary to provide the information or communication in a usable format. Technologies which use encoding, signal compression, format transformation, or similar techniques shall not remove information needed for access or shall restore it upon delivery.

(k) Products which have mechanically operated controls or keys, shall comply with the following:

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(1) Controls and keys shall be tactilely discernible without activating the controls or keys. (2) Controls and keys shall be operable with one hand and shall not require tight grasping, pinching, or twisting of the wrist. The force required to activate controls and keys shall be 5 lbs. (22.2 N) maximum. (3) If key repeat is supported, the delay before repeat shall be adjustable to at least 2 seconds. Key repeat rate shall be adjustable to 2 seconds per character. (4) The status of all locking or toggle controls or keys shall be visually discernible, and discernible either through touch or sound.

§ 1194.26 Desktop and portable computers.

(a) All mechanically operated controls and keys shall comply with §1194.23 (k) (1) through (4).

(b) If a product utilizes touch screens or touch-operated controls, an input method shall be provided that complies with §1194.23 (k) (1) through (4).

(c) When biometric forms of user identification or control are used, an alternative form of identification or activation, which does not require the user to possess particular biological characteristics, shall also be provided.

(d) Where provided, at least one of each type of expansion slots, ports and connectors shall comply with publicly available industry standards.

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Appendix K: Material Safety Data Sheets

All MSDS sheets are available on our website


Propulsion and DeploymentAmmonium Perchlorate

Aerotech Reloadable MotorsAerotech IgnitersM-Tek E-matchesPyrodex Pellets

Black PowderNomex (thermal protector)

GluesElmer’s White Glue

Two Ton Epoxy ResinTwo Ton Epoxy Hardener

Bob Smith Cyanoacrylate Glue (superglue)Superglue Accelerator (kicker)

Superglue Debonder

SolderingFlux

Solder

Painting and FinishingAutomotive Primer

Automotive Spray PaintClear Coat

Construction SuppliesCarbon Fiber

KevlarFiberglass ClothFiberglass Resin

Fiberglass HardenerSelf-expanding Foam

SolventsEthyl Alcohol 70%

Payload MaterialsAluminum

AcrylicPolycarbonateFood coloring

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Appendix L: Bibliography

[1] Cussler, Edward L. Diffusion: Mass Transfer in Fluid Systems. Cambridge [etc.: Cambridge UP, 2009. Print.

[2] "Food Colour in Water." Science Photo Library. 2011. Web. 2 Sept. 2011. <http://www.sciencephoto.com/media/3749/enlarge>.

[3] Helms, Amelia. ""Blue Diffusion Pattern" by Amelia Helms | Flickr - Photo Sharing!" Welcome to Flickr - Photo Sharing. Yahoo, Flickr, 30 Mar. 2009. Web. 17 Sept. 2011. <http://www.flickr.com/photos/35232139@N07/3471847476/in/photostream/>.

[4] Lam, S. H. "Reduced Chemistry-Diffusion Coupling." 2007. Web. 2 Sept. 2011.

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