November 3rd, 2014
A Study of Muon Flux in Relation to Altitude
Madison West High School - Returning Team
SL 2015 Preliminary Design Review
Madison West High School
Returning Team
SL 2015 PDR
Contents
School Information........................................................................................................ 4
Student Participants ..................................................... Error! Bookmark not defined.
Facilities and Equipment .................................................. Error! Bookmark not defined.
Facilities for Rocket Design and Testing ...................... Error! Bookmark not defined.
Personnel ..................................................................... Error! Bookmark not defined.
Equipment and Supplies .............................................. Error! Bookmark not defined.
Section 508 Compliance .............................................. Error! Bookmark not defined.
Safety ........................................................................................................................... 43
Written Safety Plan .................................................................................................... 43
I. NAR Safety Requirements ...................................................................................... 43
II. Hazardous Materials .............................................................................................. 44
III. Compliance with Laws and Environmental Regulations ........................................ 44
IV. Education, Safety Briefings and Supervision ........................................................ 45
V. Procedures and Documentation ............................................................................ 45
Physical Risks ............................................................................................................ 46
Toxicity Risks ............................................................................................................. 46
Scheduling and Facilities Risks.................................................................................. 46
Rocket/Payload Risks ................................................................................................ 47
Technical Design ........................................................................................................... 5
Vehicle Dimensions ..................................................................................................... 7
Entire Vehicle ........................................................................................................... 7
Vehicle Parameters .................................................................................................. 7
Motors ........................................................................................................................ 10
Primary Motor Selection ......................................................................................... 10
Performance Predictions ........................................................................................ 10
Wind Speed vs. Altitude ......................................................................................... 11
Thrust Profile .......................................................................................................... 12
Velocity Profile ....................................................................................................... 12
Acceleration Profile ................................................................................................ 13
Vehicle Flight Sequence ........................................................................................ 14
Deployment and Recovery ......................................................................................... 16
Parachutes ............................................................................................................. 18
Drift ........................................................................................................................ 18
Universal Avionics Platform – Hermes ................................................................... 20
Performance Targets that Apply to Vehicle .................. Error! Bookmark not defined.
Payload ...................................................................................................................... 23
Scientific Background............................................................................................. 24
Muon Detector Design and Operation .................................................................... 26
Experimental Flight ................................................................................................ 32
Data and Correlations ............................................................................................ 33
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Hypotheses ............................................................................................................ 34
Performance Targets Compliance............................ Error! Bookmark not defined.
Challenges and Solutions .......................................................................................... 35
Major Vehicle Challenges ...................................................................................... 35
Major Payload Challenges and Solutions ............................................................... 35
Performance Targets Compliance ................................... Error! Bookmark not defined.
Educational Engagement ........................................................................................... 48
Community Support ................................................................................................... 48
Outreach Programs.................................................................................................... 50
Project Plan ................................................................................................................. 39
Schedule .................................................................................................................... 39
Budget ....................................................................................................................... 40
Educational Standards ................................................. Error! Bookmark not defined.
Sustainability .............................................................................................................. 41
Appendices ........................................................................ Error! Bookmark not defined.
Appendix A - Resume for Ben...................................... Error! Bookmark not defined.
Appendix B - Resume for Carl ..................................... Error! Bookmark not defined.
Appendix C - Resume for Ethan .................................. Error! Bookmark not defined.
Appendix D - Resume for Grace .................................. Error! Bookmark not defined.
Appendix E - Resume for Mathilda .............................. Error! Bookmark not defined.
Appendix F - Resume for Matthew............................... Error! Bookmark not defined.
Appendix G - Resume for Meghan............................... Error! Bookmark not defined.
Appendix H - Resume for Sebastian ............................ Error! Bookmark not defined.
Appendix I - Resume for Winor .................................... Error! Bookmark not defined.
Appendix J: Model Rocket Safety Code ....................... Error! Bookmark not defined.
Appendix L: Section 508 .............................................. Error! Bookmark not defined.
Appendix M: Material Safety Data Sheets ................................................................. 42
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Madison West High School
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School Information
School Name
Madison West High School
Title of Project
A Study of Muon Flux in Relation to Altitude
Administrative Staff Member
West High School Principal Beth Thompson
Madison West High School, 30 Ash St., Madison, WI, 53726
Phone: (608) 204-4104
E-Mail: [email protected]
Team Official
Ms. Christine Hager, Biology Instructor
Madison West High School, 30 Ash St., Madison, WI 53726
Phone: (608) 204-3181
E-Mail: [email protected]
Educators and Mentors
Pavel Pinkas, Ph.D., Senior Software Engineer for DNASTAR, Inc.
1763 Norman Way, Madison, WI, 53705
Phone: (608) 957-2595
Fax: (608) 258-3749
E-Mail: [email protected]
Brent Lillesand
4809 Jade Lane, Madison, WI 53714
Phone: (608) 241-9282
E-mail: [email protected]
Michael Westphall, Ph. D., UW Madison
Phone: 608-520-3306
E-mail: [email protected]
Jim Guither
Phone: 608-239-5268
E-mail: [email protected]
Prof. Mutlu Özdoğan, Ph. D., SAGE UW Madison
Phone: 608-262-0873
E-mail: [email protected]
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SL 2015 PDR
Madison West High School
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SL 2015 PDR
Section 508 Consultant:
Ms. Ronda Solberg
DNASTAR, Inc. (senior software designer)
3801 Regent St, Madison, WI 53705
E-Mail: [email protected]
Associated NAR Chartered Section #558
President: Mr. Mark Hackler
E-Mail: [email protected]
WOOSH
http://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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SL 2015 PDR
Changes Made Since Proposal
Changes to vehicle




Added dimensioned drawing of the vehicle
Updated drift table
Added vehicle verification section
Added payload-vehicle integration picture and discussion
Changes to Payload



Updated drift table and added discussion of payload deployment altitude
Added payload verification section
Added Payload Concept Features and Definition
Changes to Project Plan

No changes to Project Plan
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Technical Design
We will use a single stage, K-class vehicle to deliver our payload to the target altitude of
5,280ft. We will be measuring muon flux at different altitudes.
The rocket will be constructed from Giant Leap’s Dynawind tubing, using 3/32” G10
fiberglass sheets for fins. The rocket will be robust enough to endure 25+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 156 inches long, with a 4.0 inch diameter. It has estimated liftoff mass of 22 pounds.
The proposed vehicle and propulsion options are discussed in detail below. The primary
propulsion choice is a K-class motor (AT K440WT, 54mm) with total impulse of 2368Ns.
The vehicle can launch from a standard size, 10ft 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 6.87 calibers.
Vehicle Parameters
Length
[in]
156
Mass
[lbs]
22.2
Diameter
[in]
4.0
Motor
Selection
AT K1440WT
Stability
Margin
[calibers]
6.87
Table 1: The rocket’s dimensions, stability, and primary propulsion
-7-
Thrust to
weight
ratio
14.3
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Total Length: 156” Total Span: 10”
SL 2015 PDR
Liftoff Weight: 22.2lbs
The figure below shows all compartments and section of our rocket. The rocket separates
into four tethered parts (payload, drogue parachute compartment, bottom e-bay and solid
motor booster). We will use standard dual deployment triggered by two fully redundant
PerfectFlite StratoLogger altimeters. Payload separation and deployment is controlled by
another two fully redundant Perfectflite StratoLogger SL100 altimeters.
Figure 2: A three dimensional schematic of the entire rocket
Letter
A
Nosecone
Part
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Letter
B
C
D
E
F
G
H
I
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Part
Payload (separates from vehicle)
Deployment Electronics (Payload)
Payload Parachute
Rocket Drogue Parachute
Deployment Electronics (Rocket)
Rocket Main Parachute
Motor Mount (54mm/75mm capable)
Fins (3, 3/32” G10)
Table 2: Rocket sections and parts
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SL 2015 PDR
Motors
Primary Motor Selection
Based on the results of computer simulations we have selected Aerotech K1440WT
(54mm) motor as our primary propulsion choice. Our backup choice is Aerotech K1050W,
54mm motor. Characteristic parameters for each motor are shown in the table below.
Motor
Diameter
[mm]
AT K1440WT
AT K1050W
54
54
Total
Impulse
[Ns]
2368
2522
Burn
Time
[s]
1.64
2.37
Stability
Margin
[calibers]
6.87
6.34
Thrust to
weight ratio
14.3
10.1
Table 3: Motor alternatives
Performance Predictions
All performance predictions were calculated using OpenRocket version 14.09.
The graph below shows the simulated flight profile for the AT K1440WT motor. The
vehicle reaches the apogee of 5456ft in less than eighteen seconds (17.5s) after the
ignition. For the purpose of this preliminary simulation the coefficient of drag is set to CD
= 0.7 (we have flown this type of vehicle during our prior SLI projects and the collected
flight data indicate that CD = 0.7 is a reasonable estimate of overall drag coefficient for a
single diameter vehicle). The entire flight duration is estimated at 150s and the drift under
15mph wind conditions is 2800ft.
Figure 3: Altitude vs. time graph for AT K1440WT motor. The rocket reaches 5456ft at 17.5s after ignition and the entire flight
duration is estimated at 150s.
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SL 2015 PDR
The simulations indicate a small (3.3%) overshoot of the target altitude (5,280ft AGL)
however at this stage of the project we do not have enough information to decide whether
this is a real issue or just a simulation artifact (in our experience, RockSIM and
OpenRocket tend to provide rather optimistic apogee estimates). We will revise our
simulations and make ballast decisions after we carry out both scale model and full scale
vehicle test flights. Our final test flight before the SLI launch will use the same motor as
we will use for our flight in Hunstsville to make sure that the rocket will not exceed the
target altitude.
Wind Speed vs. Altitude
The 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 6% from the apogee reached in windless
conditions.
Wind Speed
[mph]
0
5
10
15
20
Altitude
[ft]
5456
5434
5371
5274
5157
Percent Change in
Apogee
0.00
-0.40
-1.56
-3.30
-5.48
Table 4: Flight apogee vs. wind speed
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SL 2015 PDR
Thrust Profile
The graph below shows the thrust profile for the AT K1440WT motor. The AT K1440WT
motor reaches its maximum thrust of 2168Ns after 0.02s and burns at approximately
constant thrust level for about 1.0s (the average thrust-to-weight ratio is 14.3). The rocket
requires a standard ten-foot rail for sufficient stability on the pad and leaves the 10ft rail
at about 108fps (73.9mph).
Figure 4: Thrust vs. time graph. The motor delivers maximum thrust of just over 2100N and burns for 1.64s.
Velocity Profile
According to the velocity profile (next graph), the rocket will reach maximum velocity of
496mph shortly before the burnout (1.6s). The rocket remains subsonic for the entire
duration of its flight.
Figure 5: Velocity vs. time graph. The motor burns out at 1.64s and the rocket reaches its maximum velocity of 496mph
shortly before burnout. The rocket remains within subsonic speed range for entire duration of its flight.
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Acceleration Profile
The graph below shows that the rocket will experience maximum acceleration of about
21g. Our rocket will be robust enough to endure the 25g+ acceleration shocks.
Figure 6: Acceleration [g] vs. time [s] graph. The rocket experiences maximum acceleration of 21g (206 m/s2).
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Vehicle Flight Sequence
The vehicle flight sequence is shown on the figure below.
Figure 7: Vehicle flight sequence - 1. Ready; 2.Ignition; 3.Burnout at 1.64s at 715ft AGL; 4. Coast to apogee; 5. Vehicle drogue
deployment at 17.5s at 5,456ft AGL; 6. Vehicle Descent on Drogue; 7. Payload Main Deployment (tentatively configured for
1,700ft and 79s); 8. Vehicle Main Deployment at 97s at 700ft; 9. Vehicle Descent on Main; 10. Vehicle Landing at 157s; 11.
Payload Descent on Main; 12. Payload Landing at t = 195s
The table below summarizes the flight events for the entire mission.
#
Event
1
2
3
4
5
6
7
8
9
10
Ready
Ignition/Boost
Burnout
Coast
Vehicle Drogue Deployment
Vehicle Descent on Drogue
Payload Main Deployment
Vehicle Main Deployment
Vehicle Descent on Main
Vehicle Landing
Time Altitude
[s]
[ft]
0
0
1.64
1.64
17.5
17.5
79
97
97
157
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0
0
715
715
5,456
5,456
1700
700
700
0
Trigger
Launch Controller
Altimeter
Altimeter
Altimeter
Altimeter
Altimeter
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#
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Event
11 Payload Descent on Main
12 Payload Landing
SL 2015 PDR
Time
[s]
Altitude
[ft]
79-195
195
1700
0
Trigger
Table 5: Flight events, triggers and conditions
The mission is configured to satisfy all applicable performance targets. The payload due
to its slow descent rate will be deployed at 1,250ft in order to remain within the confines
of the launch site (2,600ft from the launch pad) even under 15mph wind speed conditions.
The vehicle will also not drift more than 2,500ft from the launch pad under same
conditions.
The payload deployment altitude can be easily reconfigured at any time prior the launch
and if required by NASA, the payload may remain tethered to the main vehicle (this may
impair the quality of recorded data, however the experiment will still remain valid).
Because of the known constraints of the SL official launch site, we are also planning on
launching additional flights at other locations (Richard Bong Recreation Area in
Wisconsin, and Black Rock, NV) where we can deploy the payload at any altitude with no
constraints. At Black Rock launch the payload will travel onboard of a different vehicle,
with altitude reach of 40,000ft. Our PLAR will discuss data from both the official SL launch
in Huntsville and our additional flight in Bong Recreation Area (the flight at Black Rock
will occur later, in June 2015).
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Deployment and Recovery
The rocket will use standard dual deployment technique for recovery. Two fully
independent PerfectFlite StratoLogger altimeters will be used to fire the ejection charges.
Each altimeter will have its own power source, external arming switch and set of ejection
charges. The primary drogue charge will be fired at apogee (5,456ft) and the backup
apogee charge will fire 1s after apogee. The main parachute will be deployed as field
conditions require to prevent excessive drift, most likely at 700ft with backup charge
following 200ft lower. The backup charges are 25% larger than primary charges. If the
primary charge succeeds, the backup charge fires harmlessly into open air.
The payload will be deployed by its own altimeters (two fully redundant PerfectFlite
Stratologger SL100 altimeters) at 1250ft (official SL launch). There will be an additional
electronic lock on the payload deployment charge (altimeter will only succeed in firing the
charge if this lock is unlocked). The lock can be only unlocked by a radio signal from
ground and will be unlocked only after RSO gives the permission to separate payload
from vehicle. This is to satisfy the requirements 3.3 and 3.4.
To satisfy the constraint of 4 separate sections (requirement 1.3), the vehicle is configured
as shown on following illustrations.
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1 mile: Drogue Parachute Deployment
Drogue
Main
Parachute
Payload
Parachute
Bulkhead
Payload Bay
E-bays
= Ejection Charge Deployment
Figure 8: Apogee event: drogue parachute is deployed.
1775ft (Tentative): Payload Separation
Payload
Drogue
Main
Parachute
Bulkhead
Payload Bay
E-bays
= Ejection Charge Deployment
Figure 9: Payload deployment altitude – payload separates from the rest of the vehicle and deploys its main parachute. The
booster portion of the vehicle remains in drogue descent.
700ft: Main Parachute Deployment
Main Parachute
Drogue
Main
Parachute
Bulkhead
Payload
E-bay
= Ejection Charge Deployment
Figure 10: Main parachute deploys at preset altitude (700ft primary charge, 500ft backup charge)
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Parachutes
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 tethered sections and a separate payload in our case) and the impact
energy is no more than 75 ft-lbf for any of the parts or even entire rocket.
Table 6: Parachute sizes, ejection charges and descent rates
Drift
We originally planned to deploy the payload at the one-mile apogee; however, given the
restrictions of the launch site and how far the payload was drifting, we have calculate
deployment altitude of 1,700ft AGL to prevent the payload from drifting off-site at 15mph
winds. The following tables show the estimated drift of the rocket considering the descent
rates in the table above, at both original and revised deployments. With our original plan,
even a 10mph wind would let the payload drift outside the site. With our revised plan, we
can fly in up to 15mph wind and payload will still remain within the allowed ½ mile radius.
If deployed at apogee, the payload would descend for 386s. If deployed at 1,700ft, the
payload will descend for 115s.
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Deploy at 5,456ft
SL 2015 PDR
Deploy at 1700ft
Windspeed Drift Drift Windspeed Drift Drift
[mph]
[ft] [mi]
[mph]
[ft] [mi]
0
0
0
0
0
0
5 1818 0.34
5 877 0.17
10 3633 0.69
10 1755 0.33
15 5450 1.03
15 2631 0.50
20 7266 1.37
20 5308 1.01
Table 7: Payload drift calculated for deployment altitudes of 5,456ft (apogee) and 1,775ft (maximum deployment altitude that
would not result inf payload drifting outside the launch site under 15mph wind speed conditions).
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Universal Avionics Platform – Hermes
In 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. Beginning with 2013 school year, the original central processing unit of
system Hermes was replaced by a smaller and more capable Mach 1.5 unit (also
developed by our students). The Hermes system has been flight-tested during Rockets
For Schools projects and successfully used by several one of our SLI 2013 projects. Mach
1.5 unit was successfully premiered during our SLI 2013 project, team Sound. The system
will not be used for deployment purposes (we will continue to rely on proven PerfectFlite
StratoLogger altimeters).
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 (+3.3V)
In this season we intent to use the Hermes system with Mach 1.5 central unit to drive the
payload operations. The 900MHz telemetry will reinforced with our new CAT System
(Cloud Aided Telemetry) that relies on cellular networks and datacloud for data
transmission.
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Cloud Aided Telemetry (CAT)
The Cloud Aided Telemetry system (CAT) uses an on-board Android device and app to
transmit flight, tracking and payload data from an airborne rocket using any available
cellular network. CAT is an 'opportunistic uploader' and can store gigabytes of data onboard while searching for available connection. CAT system has been successfully tested
during our two stage flight to 8,050ft at LDRS 2014. CAT is also extensively tested on
ground and shown to work reliable across distances that cannot be covered by 900MHz
system.
Figure 11: CAT (Cloud Aided Telemetry) system schematics: the data travels along the orange route to our data cloud
(originally located in Houston, TX, now hosted by AgroGraph Inc., in Madison, WI) from where they can be retrieved via blue
route by any connected device (such as a cell phone, laptop or tablet) and aid the search for the rocket and payload. CAT
can transmit all experimental data as well and thus mitigate the potential loss of the payload.
Payload Vehicle Integration
Payload - vehicle integration is shown in the following picture:
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Payload
Parachute
Nosecone
E-Bay
Payload
E-Bay
The payload resides in the top section of the rocket, directly below the nosecone and
above its deployment electronics. The payload can be easily inserted and removed on
the ground. During descent, the top section of the rocket containing the payload
descends separately from the rest of the rocket in a horizontal orientation using y-yoke
deployment.
Vehicle Verification
Verification Tests
V1 Integrity Test:
V2 Parachute Drop Test:
V3 Tension Test:
V4 Prototype Flight:
V5 Functionality Test:
V6 Altimeter Ground Test:
V7 Deployment Test:
V8 Ejection Test:
V9 Computer Simulation:
V10 Integration Test:
applying force to verify durability.
testing parachute functionality.
applying force to the parachute shock cords to test
durability
testing the feasibility of the vehicle with a scale model.
test of basic functionality of a device on the ground
pressure chamber test
test to determine if the electronics can ignite the
deployment charges.
ejection charge size verification
use RockSim/OpenRocket to predict the behavior of
the launch vehicle.
ensure that the payload fits smoothly into the
vehicle, and is robust enough to withstand flight
stresses.
Tested Components
C1: Body (including construction techniques)
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C2: Altimeter
C3: Parachutes
C4: Fins
C5: Payload
C6: Ejection charges
C7: Launch system
C8: Motor mount
C9: Beacons
C10: Shock cords and anchors
C11: Rocket stability
Verification Matrix Key:
P: Planned
C: Completed
V1
V2
V3
C1
P
C2
C3
P
P
P
C4
P
C5
P
C6
C7
P
C8
P
C9
P
C10
P
C11
V4
P
P
P
P
P
P
P
P
P
P
V5
V6
P
P
V7
V8
P
V9
V10
P
P
P
P
P
P
P
P
P
P
P
P
Status: the verification will start after the PDR teleconference.
Vehicle Launch Procedures
Vehicle launch procedures will be developed after the rocket design is finalized in the
CDR cycle.
Vehicle Safety
Safety officer for the vehicle is Matthew Westphall. The detail description of the vehicle
safety is included in our written Safety Plan at the end of this document.
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Payload
The objective of our project is to measure the muon flux at different altitudes.
Scientific Background
Muons are generated when high-energy protons enter the atmosphere. When a highenergy proton impacts an atomic nucleus in the upper atmosphere the nucleus is
shattered and pions are created. Pions are unstable particles composed of a quark and
an antiquark bound by the strong force. They decay in approximately 26 nanoseconds,
producing muons in a matter of meters of distance travelled. Pions are significantly more
massive than muons and when they decay that extra mass is converted into the kinetic
energy of the muon. Resulting muons travel in the same direction as the proton that
created them.
P+
High velocity proton
impacts nitrogen nuclei.
Quarks and antiquarks
form a pion.
π
Pion decays into a muon.
µ
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Figure 12: A high velocity proton shatters a nitrogen atom generating a muon.
Muons travel very fast, approximately 98% the speed of light (0.98c). They have a charge
of -1 and a mass of about 200 times that of an electron. They decay via the weak
interaction. Because lepton numbers must be conserved, when muons decay they most
commonly produce an electron, an electron antineutrino, and a muon neutrino.
Figure 13: A muon (𝝁-) decays into an electron (𝒆− ), electron antineutrino (𝝂̅e), and muon neutrino (𝝂μ) via the weak
interaction.
Without relativistic effects muons would decay within 660 meters in atmosphere. Because
of the time dilation and length contraction effects of special relativity, muons can reach
Earth’s surface. In the muons time frame the Earth seems much closer because they are
moving so close to the speed of light. Muon decay is important to our experiement.
Because muons decay, our payload will see a higher rate of muon strikes at higher
altitudes.
Figure 14: Graph of muon strikes vs. altitude
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Our team will be using a scintillator to detect muons as they pass through our payload.
When a muon passes by a molecule of scintillator material, it excites that molecule’s
electrons, providing them with energy that will force them to a higher energetic state. After
the muon passes, the electron eventually returns to its original lower energy state,
releasing the extra energy in the form of light (photons). The increase in photon flux can
be measured using photomultiplier tubes. We will be using Hamamatsu HC124
photomultiplier tubes in our payload.
Muon Detector Design and Operation
Overview
Our payload is comprised of two layers of fiber optic, scintillator fiber that feed into two
separate photomultiplier tubes. When a muon strikes the scintillator it produces a small
amount of light that then is turned into an electrical signal by the photomultiplier tubes.
The individual layers are completely sealed off from each other as well as the outside
world to prevent light contamination.
Muon, unlike numerous other particles, has enough energy to pass through the scintillator
fiber and continue on its journey (other particles may decay completely when they
encounter an obstacle). Our payload uses two independent scintillator layers and only
when both layers indicate a particle passage at almost same time (muons move very fast,
0.98c), we increment the detected muons count. This method is called coincidence
counting and is widely used in experiments dealing with muon detection. The figure below
shows illustrates the coincidence counting method.
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Figure 15: Coincidence counter method – to increment the detected muons count, we require that both scintillator layers in
our payload detect a passage of particle at the same time (PMT1 and PMT2 both register a signal).
Design
The physical structure of the muon detector is comprised of a combination of
commercially available materials as well as three dimensionally printed parts. Three
different sizes of thin walled ABS plastic tubing are used to create walls separating the
two layers of scintillator fibers. Custom three dimensionally printed parts are then used to
position the fibers and hold the photomultiplier tubes in place. When assembled the
detector is comprised of two layers, one bigger and one smaller, that fit together
concentrically allowing for simplicity in assembly.
The payload is designed to be as light as possible, safe, and reliable. We had to find
materials that have enough strength to withstand the stresses of flight and still be light
enough to maintain sufficient performance of our rocket within the allowed impulse range.
Materials and components








200, 4ft long, fiber optic plastic scintillator fibers
2 Hamamatsu HC124 series multiplier setups
1 2.5in diameter, 25in long, thin walled ABS tube
1 3.00in diameter, 25in long, thin walled ABS tube
1 3.7in diameter, 25in long, thin walled ABS tube
1 4in diameter, 40in long, coupler
custom three dimensionally printed parts
custom printed circuit boards
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Madison West High School
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SL 2015 PDR
Figure 16: Sensor part of Hamamatsu HC124 photomultiplier tube. We will use HC124 PMTs in our payload.
Assembly and Configuration
The payload is comprised of two, completely separated layers of scintillator fibers
encircling the detector electronics, all enclosed in a 4 inch black fiberglass tube coupler.
The layers are separated by ABS plastic tubing with the photomultiplier tubes positioned
at either end.
Figure 17: Muon detector overall assembly. The scintillator fibers are divided into two independent layers (outer and inner),
each layer being monitor by its own photomultiplier tube (PMT).
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Madison West High School
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SL 2015 PDR
Figure 18: Payload cross-section – all payload electronics is housed inside two layers of scintillator fibers.
Due to the nature of how high velocity particles decay in the upper atmosphere, muons
primary enter the atmosphere perpendicular to the Earth’s surface. This dictates the
orientation of muon detector, in order to maximize the detection rate of muons. To
increase detector’s active area we are going orient the payload parallel to the Earth’s
surface. This will be achieved by using Y-yoke attachment of the payload parachute, as
illustrated below.
Figure 19: Payload descending horizontally to maximize the rate of payload detection.
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Madison West High School
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SL 2015 PDR
Parachute
Rest of
Rocket
Tether points
E-Bay
Payload Bay
Nosecone
Y-Yoke Deployment
Figure 20: Y-yoke parachute attachment.
We have successfully used the Y-yoke parachute attachment in our previous SLI project,
in 2006 (the payload section housed two DSLR cameras looking through the side of the
payload bay). Below is a picture of 2006 project in flight.
Figure 21: A practical implementation of Y-yoke parachute attachment in SLI 2006 project (infrared aerial photography).
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SL 2015 PDR
Payload Block Scheme
Muons are detected by scintillator based detector. The signals from photomultiplier tubes
are evaluated for coincidence of events by detection electronic and the results are fed to
the central processing unit (Mach 1.5 payload computer). The computer also monitors
and stores information from altimeters, accelerometers and GPS sensors. CAT (Cloud
Aided Telemetry) device (an Android phone with custom app) transmits all collected data
(including the location of the rocket and payload) via cellular network to our data cloud.
FLIGHT
& DEPLOYMENT
MUON
DETECTOR
Figure 22: Block scheme of the payload.
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Data Usage
The table below describes the predicted data usage of the payload and the calculations
that led to those predictions.
Condition
Expected Event Rate
Payload Area
Data Writing Rate
Payload Deployment
Altitude
Payload Descent Rate
Altitude data per second
Total Flight Time
Bytes(count)
Expected Capture Rate
And data per second
Xor data per second
Data Per Second
Total Data Usage
Calculation
Given
Given
Given
Given
Value
1 muon / cm2 / min
900 cm2
1 / sec
1700 ft
Given
Given
Altitude * Flight time
⌈𝑙𝑜𝑔2 (𝑐𝑜𝑢𝑛𝑡)⌉
Event Rate * Payload Area
14 ft/sec
2 Bytes / sec
122 sec
N/A
900 muons / min (15 /
sec)
2 Bytes / sec
(Bytes(Capture Rate)+1) *
Writing Rate
2 * (Bytes(4 * Capture Rate)
+1) * Writing Rate
Altitude + And + Xor
Data per Second * Flight
Time
4 Bytes / sec
8 Bytes / sec
970 Bytes
Table n: Data Usage Calculations
Experimental Flight
The rocket delivers the payload to the desired probe deployment altitude. The rocket then
separates into two sections: the booster and the payload bay. At separation, the payload
bay deploys its main parachute. The booster utilizes a dual deployment system with its
drogue parachute deploying at apogee and its main parachute deploying at 700ft. During
its descent, the payload measures the amount of muons in relation to altitude. In addition,
our payload sends its position to our datacloud via a smartphone running our Cloud Aided
Telemetry (CAT) app.
Note that the separation of payload and drogue parachute deployment are two separate
events and we can separate the payload at any preset altitude (not just apogee). We will
fully comply with launch site restrictions and separate payload at altitude that will
guarantee that the payload will land inside the launch site.
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SL 2015 PDR
Figure 23: Flight sequence – payload separates from the rocket at preset altitude (not necessarily at apogee) and descends
horizontally to maximize the detection rate of muons. Payload and vehicle land separately.
Data and Correlations
The following quantities will be measured and recorded:
Independent Variables
a
A
X
Acceleration
Altitude
Location (GPS)
Dependent Variables
µ
Muon Flux
Primary Correlations
µ = f(A) Muon Flux in relation to Altitude
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SL 2015 PDR
Hypotheses
Muon Count
We make the following hypothesis: As altitude decreases, muon flux will decrease at an
exponentially proportional rate.
Altitude
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SL 2015 PDR
Challenges and Solutions
Major Vehicle Challenges
1. Performance: Our payload is 4ft long and adds significant weight to the
vehicle. We will exercise care and proper techniques when building the delivery
vehicle to maximize the rocket’s performance. Additionally, payload position in
the front of the rocket increases the stability of the vehicle to 6.87 calibers and
we may experience significant weathercocking. We are considering using
canted fins or spin-tabs to induce spin around axial axis of rocket to minimize
the weathercocking.
2. Deployment Scheme: our payload section must descend separately from our
vehicle in a horizontal orientation. To achieve this, we will use a Y-yoke
deployment scheme for the payload section. Y-yoke scheme has been
previously tested during our SLI 2006 project. Our deployment scheme will
meet the requirement of a maximum of four (4) tethered or separate sections.
3. Launch Site Dimensions: the launch site in Huntsville allows for only 2,500ft
drift during recovery. We will have to carefully select the drogue and main
parachute sizes to ensure that the vehicle will not drift outside the launch site
yet it will have enough time to deploy main parachute and land safely with no
section of the vehicle exceeding the maximum impact energy of 75ft-lbf. We
will closely monitor the descent rates during our test flights and make
adjustments to parachutes and deployment schedule as necessary.
Major Payload Challenges and Solutions
1. Complex payload: Our payload requires custom electronics, precise structural
subsystem and detailed knowledge of methods of muon detection. We will use
3D printers to produce the structural subsystem, we will work UW electrical
engineers and our mentors to design and manufacture the custom printed
circuit boards and we are working with two experts on muon detection (Prof.
Dan McCammon from UW Dept. of Physics and Dr. Michael Westphall).
2. Tracking and recovery: if the payload is deployed at high altitude, it may drift
for long time. We will use our newly developed CAT (Cloud Aided Telemetry)
system to track and recover both the payload and the rocket. For the official
SLI launch the probe deployment altitude will be set according to NASA
instruction and to meet to limitations of the launch site.
3. Light Contamination: Our payload detects muons by measuring the small
amount of light emitted by scintillating materials when muons pass through
them. Any amount of light contamination would result in false detection of
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SL 2015 PDR
muons. To get accurate measurements, we require zero photon darkness. We
plan to achieve this by surrounding the payload with a single piece of black
fiberglass to reduce seams, and coating that fiberglass in a zero photon
emitting material.
4. Counting Rate: Muons enter the atmosphere at a relatively low rate, 1 muon
per square centimeter per steradian per minute. (60-1sr-1cm-2s-1). Our payload
will need to have a large surface area and remain airborne for a sufficient period
in order to get sufficient muon readings. Our payload will descend horizontally
to create a large surface area, and will descend under a large parachute to
increase time aloft.
5. Payload Durability: Our payload will use photomultiplier tubes to measure the
light emitted by scintillating materials when light passes through them.
Photomultiplier tubes contain fragile components that might be damaged by
high g forces. We will need to select a robust variety of photomultiplier tubes
capable of withstanding at least 25g of acceleration. Additionally, the
scintillating material must be light and robust enough to be able to be flown
effectively and to withstand the stresses of rocket flight. We have selected
scintillating optic fibers, which are light and durable, for this task.
Payload Concept Features and Definition
Creativity and Originality
There has not been significant research done on the effects of altitude on muon flux.
Our new research will allow us to analyze muon flux and we can draw conclusions
about muon flux based on altitude. The 3D printed aspects of the payload and
complexity of our analysis makes our project new and innovative.
Uniqueness or Significance
We chose to study muon flux at different altitudes because by studying this, we can
learn more about the manner in which muons decay. Muons are worth studying
because they enable us to trace their origins, helping us learn more about how the
universe began.
Level of Challenge
Given the complexity of our electronics and the precise structural subsystem and
detailed knowledge of methods of muon detection needed, our experiment and report
will be extraordinarily challenging. In addition the counting rate and payload durability
will provide a challenge. The tracking and recovery of the payload given its long period
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SL 2015 PDR
of descent will also make data collection very challenging. We will use our newly
developed CAT (Cloud Aided Telemetry) system to track and recover both the payload
and the rocket in order to ensure accurate collection of data.
Although the challenges are many, our experiences with rocketry have given us the
knowledge and ability to deal with the complicated experiments and design required by
our SLI project. Our mentors and UW electrical engineers (Prof. Dan McCammon from
UW Dept. of Physics and Dr. Michael Westphall) are also a source of advice and their
support will be critical for the project’s success.
Payload Verification
Verification Tests
V1 Functionality Test:
V2 Integrity Test:
V3 Calibration Test:
V4 Battery Test:
V5 Connection Test:
Test of basic functionality of a device on the ground
Applying force to verify durability
Calibration and test of accurateness and preciseness
Test for sufficient amount of battery power
Test of proper connection of components
Tested Components
C1:
C2:
C3:
C4:
C5:
C6:
C7:
C8:
C9:
C10:
Photomultiplier Tubes
Scintillator Optic Fibers
Detection Electronics
Central Processing Unit
Accelerometer
Altimeter
GPS
Cloud Aided Telemetry
Transmitter
Parachutes
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Verification Matrix Key
P: Planned
C: Completed
C1
C2
C3
C4
C5
C6
C7
C8
C9
C10
V1
P
P
P
P
P
P
P
P
P
V2
P
P
V3
P
V4
P
P
P
P
P
P
P
P
P
P
P
P
P
P
P
V5
P
P
P
P
P
P
P
P
P
P
Status: the verification will start after the PDR teleconference.
Payload Safety
The payload safety officer is Carl Cortright. The detailed discussion of payload safety is
include in the written Safety Plan section at the end of this document.
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SL 2015 PDR
Project Plan
Schedule
Table 8: Timeline of SL 2015
The schedule is subject to changes as the launch windows for 2015 are not confirmed
yet (the schedule shows our best estimate based on the launch site schedule from
previous years).
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Madison West High School
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Budget
Vehicle
Tubing, nosecone, bulkheads, rings
$400.00
Fin Material (G10 Fiberglass)
$150.00
Paint and Primer
$100.00
PerfectFlite Stratologger Altimeter (x4)
$300.00
Motor Retention
$50.00
Motor Casing
$450.00
Parachutes, recovery gear
$200.00
Epoxy
$200.00
CAT Enabled Smart Phones (x2)
$80.00
Walston Beacon (x2)
$300.00
Miscellaneous Supplies (tools, batteries,
wires, hardware)
$300.00
Scale Model
Tubing
$150.00
Parachutes and Shock Cord
$100.00
Fin Material (G10 Fiberglass)
$50.00
Motors
Scale Model Motors
$200.00
Full Scale Test Flight Motors
$20.00
Payload
Main Computer
$200.00
ABS Tubing
$100.00
Scintillator Fibers
$600.00
Photomultiplier Tube (x2)
$200.00
Fiberglass Coupler Tubing
$50.00
Total
$4,200.00
Table 9 : Budget for 2012-13 SLI Program (* - already in possession)
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Madison West High School
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Flight
$400/Person * 11 People
$4,400.00
Rooms
$119/Room * 6 Rooms * 5 Nights
$2,975.00
Car Rental (Ground Support Vehicle)
$500 rental+ $600 gas
$1100.00
Total
$8,475.00
Cost per Team Member
$
941.67
Table 10: Budget for the travel to Huntsville, AL
Madison West Rocket Club has sufficient money earning opportunities (raking
leaves/yardwork, donations from families or mentors) 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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Appendix M: Material Safety Data Sheets
All MSDS sheets are available on our website
http://westrocketry.com/sli2015/safety/safety2015m.php
Propulsion and Deployment
Ammonium Perchlorate
Aerotech Reloadable Motors
Aerotech Igniters
M-Tek E-matches
Pyrodex Pellets
Black Powder
Nomex (thermal protector)
Glues
Elmer’s White Glue
Two Ton Epoxy Resin
Two Ton Epoxy Hardener
Bob Smith Cyanoacrylate Glue (superglue)
Superglue Accelerator (kicker)
Superglue Debonder
Soldering
Flux
Solder
Painting and Finishing
Automotive Primer
Automotive Spray Paint
Clear Coat
Construction Supplies
Carbon Fiber
Kevlar
Fiberglass Cloth
Fiberglass Resin
Fiberglass Hardener
Self-expanding Foam
Solvents
Ethyl Alcohol 70%
Payload Materials
Aluminum
Acrylic
Polycarbonate
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Madison West High School
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SL 2015 PDR
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 2015. Mr. Guither holds a level 1 HPR
certification. He plans to complete his Level 2 by April 2015 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. Guither 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 and 15,000ft waiver for Princeton, IL, TRA QCRS 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 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 SL 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 programs RockSim
and Open Rocket 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
launch in order to verify that there will be no problems.
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e. Launch Conditions: Test launches will be performed at Richard I. Bong Recreation
Area or Princeton, IL, with our mentors present to oversee all proceedings. All launches
will be carried out in accordance with FAA, NFPA and NAR/TRA 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 Materials
All 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/sli2015/safety/safety2015m.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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http://westrocketry.com/sli2015/safety/safety2015m.php
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 Supervision
Mentors 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 prelaunch 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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Madison West High School
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SL 2015 PDR
Physical Risks
Risks
Saws, knives,
Dremel tools,
band saws
Sandpaper,
fiberglass
Drill press
Consequences
Laceration
Mitigation
All members will follow safety procedures and
use protective devices to minimize risk
Abrasion
Soldering iron
Burns
Computer,
printer
Workshop risks
Electric shock
All members will follow safety procedures and
use protective devices to minimize risk
All members will follow safety procedures and
use protective devices to minimize risk
All members will follow safety procedures to
minimize risk
All members will follow safety procedures to
minimize risk
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
Puncture wound
Personal injury,
material damage
Table 11: Risks that would cause physical harm to an individual
Toxicity Risks
Risks
Epoxy, enamel
paints, primer,
superglue
Superglue,
epoxy, enamel
paints, primer
Consequences
Toxic fumes
Toxic substance
consumption
Mitigation
Area will be well ventilated and there will be
minimal use of possibly toxic-fume emitting
substances
All members will follow safety procedures to
minimize risk. Emergency procedure will be
followed in case of accidental digestion.
Table 12: Risks that would cause toxic harm to an individual
Scheduling and Facilities Risks
Risks
Workshop
space
unavailable
Design facilities
unavailable
Consequences
Unable to complete
construction of
rocket and/or
payload
Unable to complete
project
Team members Unable to complete
unavailable
project
Mitigation
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.
We will insure the availability of our design
facilities and work at team members’ homes
if needed.
We will plan meetings in advance and insure
that enough team members will be present
to allow sufficient progress.
Table 13: Scheduling risks that would inhibit our progress on our project
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Rocket/Payload Risks
Risks
Consequences
Unstable rocket Errant flight
Improper motor
mounting
Damage or
destruction of
rocket.
Weak rocket
structure
Propellant
malfunction
Rocket structural
failure
Engine explosion
Parachute
Parachute failure
Payload
Payload
failure/malfunction
Errant flight
Launch rail
failure
Separation
failure
Parachutes fail to
deploy
Ejection falsely
triggered
Unexpected or
premature
ignition/personal
injury/property
damage
Rocket is lost
Recovery
failure
Transportation
damage
Possible
aberrations in
launch, flight and
recovery.
Mitigation
Rocket stability will be verified by computer
and scale model flight.
Engine system will be integrated into the
rocket under proper supervision and used in
the accordance with the manufactures’
recommendations.
Rocket will be constructed with durable
products to minimize risk.
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 Packaging will be double checked
by team members. Deployment of parachutes
will be verified during static testing.
Team members will double-check all possible
failure points on payload.
NAR Safety code will be observed to protect
all member and spectators. Launch rail will be
inspected prior each launch.
Separation joints will be properly lubricated
and inspected before launch. All other joints
will be fastened securely.
Proper arming and disarming procedures will
be followed. External switches will control all
rocket electronics.
The rocket will be equipped with radio and
sonic tracking beacons.
Rocket will be properly packaged for
transportation and inspected carefully prior to
launch
Table 14: Risks associated with the rocket launch
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Madison West High School
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SL 2015 PDR
Educational Engagement
Community Support
After twelve 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 nine 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. This year Prof. Özdoğan from Nelson Institute for Sustainability
and Global Environment will serve as an expert on remote sensing and image
analysis.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. This provides us with state of art
classroom, including projection technology and document camera that we can use during
our meeting. We are also participating in UW outreach activities, such as Physics Open
House, Super Science Saturdays (in summer) and most importantly Wisconsin Science
Festival, where we can reach over 2,000 people.
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.
In 2012 we have won TARC national contest for second time in our club history. This has
brought our club into spotlight and we have received communications from senators,
mayor, Dane County board and others. NBC channel broadcasted a 4 minute
documentary about our club and Wisconsin State Journal printed a full length article. We
are also scheduled for an hour long show at local community radio station (WORT
89.9FM).
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Madison West High School
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We have established our Twitter and Facebook presence and at peak times our postings
reach over 2,000 people.
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Madison West High School
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SL 2015 PDR
Outreach Programs
Each year we participate 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 are currently 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.
For a second year in a row we are invited to present our projects at Wisconsin Science
Festival, where we reach estimated 2,000 people. In addition to displaying several recent
and current SLI and R4S payloads, we will be offering ability to build and launch
pneumatic and Alka Seltzer rocket (including the ever popular Seltzurn V and Alkollo 13).
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 advertising 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 sessions provide interested new members
learning about the basics of rocket design, building, and operation.
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Madison West High School
Returning Team
SL 2015 PDR
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 become well known for our outreach activities
and we are steadily receiving requests from schools and organization that we have never
worked with before).
Date
Oct. 10, 2014
School
Randall Elementary
Oct. 18, 19, 2014
Wisconsin Science
Festival
Kids Express
Physics Open House
O’Keefe Middle School
–Super Science
Saturday
Franklin and Randall
Elementary
- Super Science
Saturday
Nov. 15, 2014
Feb. 21, 2015
Mar. 7, 2015
Mar. 14, 2015
Outreach
School Homecoming
Parade
Alka-Seltzer Rockets,
Pneumatic Rockets
Alka-Seltzer Rockets
Displays, presentations
Alka-Seltzer Rockets,
Pneumatic Rockets
# of People (estimate)
200
Alka-Seltzer Rockets,
Pneumatic Rockets
100
2000
50
200
80
Total: 2630
Table 15: Planned outreach events.
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