UNIVERSITY OF NORTH DAKOTA
FROZEN FURY
NASA STUDENT LAUNCH INITIATIVE
CRITICAL DESIGN REVIEW
February 28, 2014
I). Summary of CDR report

Team Summary
- Team Name and Mailing Address
University of North Dakota Frozen Fury
Witmer Hall, 101 Cornell Street Stop 7129
Grand Forks, North Dakota 58202-7129
-
-
-
Location
 Grand Forks, North Dakota 58202
Name of mentor, NAR/TAR number and certification level
 Dr. Timothy Young, NAR # 76791, Certification Level 2
Launch Vehicle Summary
 Length: 112.7528 in
 Diameter: 6.00 in
 Span diameter: 19.00 in
 Mass: 688.8463 Oz
 Motor choice: Aerotech L2200G
Recovery System
 Dual deployment upon separation of base section and payload section
 Drogue: 36 in. (3 seconds after apogee)
 Main: 72 in. (3 seconds after apogee)
Rail Size
 The launch rail is constructed of steel tubing, and the rail for use by the rocket
with a bead system is 12 feet to the base platform. The length of the rail can be
adjusted by moving a knuckle up and down on the rail so that the platform
moves either up or down decreasing or increasing the length of the rail to adjust
for conditions or for safety reasons. We plan to use 10 feet of the 12 foot rail,
so we will have the knuckle two feet from the base, making the total distance
traveled by the rocketed 10 feet total.
Launch Operations Procedures Checklist
 Setting up Launch Rail
Launch Rail Equipment:
 Extension cord (200 ft)
 6 foot tube
 2 launch rails (2 Allen bolts
already attached)
 1 Allen bolt
Stand:
 3 legs
 6 wing nuts
 Support angle iron
Rocket stop:
 Glat back
 2 / 2 ½ inch bolts
 2 hex nuts
 ½ inch bolt (through angle
iron and launch rail)
 2 hex nuts (both on 2 inch
bolt)
 Bracket for support angle
 2 / 2 inch bolts
 2 hex nuts
 Blast plate
 Shims
 Ballast for stability
Launch Rail Assembly
1. One of the removable legs is attached to the stand using two (2) wing nuts.
2. The 6 foot tube is attached to the bottom launch rail using 2 inch bolts and hex nuts.
3. The top launch rail and the bottom launch rail are slid together. The Allen bolt is used on the
4.
5.
6.
7.
8.
9.
top hole, and the 2 inch bolt with one hex nut in the bottom hole.
The blast plate is placed on top of the base.
The tube is screwed into the base, making sure that the support rail is aligned with the leg.
The support beam is attached to the launch rail and secured with a hex nut.
The remaining two legs are attached to the base with wing nuts.
The support rail is secured to the leg of the stand with the brace.
The stand is leveled.
 Recovery Preparation
Equipment:
 Main parachute
 Large Nomex sheet
 3 quick links
 Main shock cord
Altimeter Bay:
 2 Altimeters (one for
redundancy)
 2 9V batteries
 4 washers
 4 wing nuts




Drogue parachute
Small deployment bag
3 quick links
Drogue shock cord
 Zip ties for battery
 4 black powder ejection
charges (3 – 3g, 1 – 4g main)
 Painters tape for friction
fitting (as needed)

Sheer pins

Electrical tape
Folding Parachutes
1.
2.
3.
4.
5.
6.
7.
8.
When the parachute is folded in a half circle, at least 3 team members begin to lay
out the chute
One person holds the lines to prevent them from becoming tangled
The other two individuals hold the parachute along the folded edges
The chute is folded in half three (3) times
Starting from the top, it is folded into thirds by folding the tip of the chute to the
middle, then folding down again
The chute is placed into the bag.
The chute’s rip cords are connected to the large quick link in the middle loop of the main
shock cord
On the top of the chute, but still in the bag, the parachute rip cords and some of the
shock cord are carefully placed, to ensure they do not become tangled
Altimeter Bay
1. The altimeters are calibrated, making sure that all parachute deployment numbers are
correct.
2. Two (2) new 9-V batteries are placed on the altimeter board and secured.
3. Charges are placed in the charge cups, threading the electric matches through the
holes. The charge for the main is placed on the bottom altimeter bay cup. The charge for the
drogue is placed at the top of the altimeter bay cup.
4. The wires are connected to the altimeters, making sure the positive and negative wires are in
the appropriate places.
5. The batteries are attached.
6. The altimeter board is in place with wing nuts.
7. The area is cleared of unnecessary personnel and the continuity is checked by using
the switch on the exterior of the rocket. If there is good continuity, two (2) beeps will be
heard after the initial set of beeps. If the continuity is not good there will be
double beeps after the initial set of beeps.
8. The switches are turned off until the rocket is placed on the rail.
Parachute Assembly in the Rocket
1.
The appropriate side of the main shock is attached to the bottom of the altimeter bay using a
quick link
2. The Nomex sheet is attached to the bottom of the altimeter bay also.
3. The other end of the main shock cord is attached to the fin can.
4. The appropriate side of the drogue shock cord is attached to the top of the altimeter
bay using a quick link.
5. The drogue bag is also attached to the top of the altimeter bay.
6. The appropriate side of the drogue shock cord is attached to the payload bay.
7.

The rocket is pushed together, slowly.
Motor Preparation
Equipment:
 Motor casing
 Motor grain
 Motor retainer
Motor Assembly
1. The motor is placed into the metal casing, making sure the motor is placed fully in its casing
and the motor closure is tightened
2. The casing is inserted into the motor mount tube
3. The rocket is secured with the motor retainer
4. The red safety cap is left on until the rocket is placed on the launch pad
After rocket is assembled
1. The rocket is placed on the rail.
2. The rocket stop is put on the rail at the appropriate height.
3. Check to see if the altimeter is turned on and has the right number of beeps to
correspond to the altimeter working properly, as stated above.
When complete the stand will look similar to the picture below.

Igniter Installation
Equipment:
 Igniter
 Tape
Igniter Installation
1. Ask for confirmation from the range safety officer to begin.
2. The red safety cap is removed and wedge cut out of it.
3. The cap on the nozzle is replaced, threading the igniter through the wedge.
4. The igniter is slid up the motor.
5. Tape the igniter to bottom of rocket. Ensure the igniter is secure.
6. The launch clips are attached to the ends of the igniter, looping the excess copper wire
around the clip to make sure they don’t fall off.
7. The switch system is hooked up to the 12V battery.
8. The continuity of the igniter is tested at the launch rail.
9. The range safety officer is notified that preparation of the igniter is complete.

Launch Procedures
Instructions
1.
To check continuity, the main power button is turned on, the switch corresponding to
where the extension cord is hooked up is flipped, the key is turned to arm, the test button is
pressed, and we listen for the tone indicating continuity.
2. Everyone checks for aircraft in the vicinity. After the “all clear,” begin countdown
from 10 seconds.
3. At zero, the launch button is held down for 5 seconds.

Troubleshooting
Instructions
1. Unplug the battery/power source
2. Only Team Lead, Safety Officer or Advisor may approach the launch rail.
3. As walking towards the rail, check the extension cord.
4. At the rail, check the wiring of the igniter on the gator clips. If needed, rewrap the
wires around the positive and negative clips.
5. If needed, add tape to clips to ensure the wires are secure.
6. Check the igniter, make sure it is inserted completely in the motor, and there is tape to
secure it in place.
7. Attempt to launch rocket. If it still fails, replace igniter with a new one.

Post flight Inspection
Instructions
1. To assist in finding the rocket after it lands, use Rocket Hunter.
2.
Check to make sure no fires were started by the rocket and launch site, or at the landing site.
3. Examine the area for harmful debris.
4. Ensure that the ejection charges are spent before handling.
5. Check to make sure the motor casing is still in the rocket.

Payload Summary
- Payload Title
 Hazard Detection Payload (3.1)
 Payload Faring/Deployment System (3.2.2.1)
 Liquid Sloshing Analysis Payload (3.2.1.2)
- Summarize experiment
 The Hazard Detection Payload will consist of a camera and the necessary
electronics to scan the ground during decent and relay any landing hazards in
real time to a ground station. This payload will require static ground tests to
determine the abilities the camera and software in identifying potential landing
hazards.
 The Hazard Detection Payload will be deployed by a faring system; the payload
fairing system will consist of an altered payload bay that will be split into four
sections. The faring system will deploy the Hazard Detection Payload shortly
after apogee, when the payload bay parachute deploys. The deployment of the
camera will be done through the separation of the four subsections of the
cylinder encasing the payload. This mechanical system will require static ground
tests to determine the force required to separate the payload cylinder.
Problems with this system could arise if the drogue chute does not exert enough
force on the system, or another potential problem could occur if the cylinder
subsections do not separate enough to allow the hinges, that attach them to the
body tube, to lock.
 The Liquid Sloshing Analysis payload will be designed to collect and analyze fluid
flow patterns in microgravity. The purpose of this project is to research liquid
sloshing in microgravity to support liquid propulsion system upgrades and
development. Collection of this data will be done through the observation of
two tanks mounted in base of our rocket. The liquid in one cylindrical tank will
be allowed to move freely and the other cylindrical tank will be controlled by a
baffle system. The data for this payload will be collected by four cameras and
stored via the onboard electronics. The four (4) cameras will be positioned
inside the rocket airframe, and each oriented to focus on one of the two tanks.
This project requires that we have at several dynamic ground tests to measure
the liquid sloshing patterns, to determine liquid patterns in standard gravity.
The data we collect in-flight can then be compared to this base data. One of the
major challenges for this payload will be developing the appropriate software to
analyze the video taken by the cameras in this payload bay.
II). Changes made since PDR

Changes made to vehicle criteria
Component
a). Rocket Length
b). Unloaded Mass
c). CP
PDR
114 in
900.9002 Oz
77.6030 in
CDR
112.75 in
688.8462 Oz
82.7776 in
d). CG
e). Safety Margin
59.9158 in
2.4
68.1631 in
2.44
The reason for the changes made to the rocket such as the length and mass are due to
drastic changes to the design of our rocket, many fallacies were brought to our attention
during the PDR review and presentation. Due to these fallacies, an almost complete
overhaul of our rocket and its systems became necessary. As for the change in mass, this
was due to the decrease in the mass of the payloads. The change in mass and its distribution
caused changes in the CG and CP of the rocket. This led to changes in fin design and size, as
well as changes to individual components of the rocket.

Changes made to payload criteria
Our payloads will be very similar to our designs in the PDR however we had to make many
changes to size, position, and functions of the payloads. For the faring system we changed
the original system, which was designed to split the nose cone in half. However, we have
revised this system, in order to prevent the potential problems that could occur with the
splitting of the nose cone, we will instead be separating the payload encasing cylinder. We
have also altered the liquid payload, instead of using two half cylinders as tanks we will have
two smaller full cylinders as tanks. We have also decided to place the tanks in the base
section of the rocket instead of the payload bay.

Changes made to project plan
III). Vehicle Criteria


Design and Verification of Launch Vehicle
Flight Reliability and Confidence
- Mission Statement
 The primary objective of the 2013-2014 University of North Dakota Frozen Fury
rocket team is to design and construct a safe, stable rocket that will conduct
research in liquid sloshing to assist in the understanding of liquid sloshing in
microgravity. As well as develop a useful hazard detection system.
- Rocket Launch Success Criteria
 A successful rocket launch will consist of reaching an altitude at apogee within ±
3.00% of 7030.94 feet above ground level. This altitude is based on the altitude
predicted by simulations.
- Payload Success Criteria
 A successful payload system will consist of the Hazard Detection Payload,
Payload Faring/Deployment System, and Liquid Sloshing Analysis Payload. The
systems should operate successfully during and after the launch and be capable
of determining the location of hazardous objects within the field of view of the
rocket. The Liquid Sloshing Analysis Payload should provide detailed information
of the flow patterns of liquids in microgravity. The Faring system should
successfully deploy the hazard detection camera.


System Level Design Review
- Airframe Material
 The 2013-2014 Rocket design is projected to have an airframe composed of a
carbon fiber composite. Simulations have been conducted using RockSim for a 6
inch diameter and 112.75 inch length rocket. The simulations projected a peak
altitude of 7030.94 ft. with both a carbon fiber and fiber-glass rocket
(approximate dry weight 688.8463 oz.) using an Aerotech L2200G size motor.
- Fin Material
 Fins will be constructed out of the same material as the airframe (i.e. Carbon
Fiber). The innate strength of the material will ensure that the fins will not break
upon landing, which is something that the Frozen Fury Team has experienced in
the past.
- Bulk-Head/Centering-Ring Material
 Internal bulkheads/centering-rings will be constructed out of 0.5 in. cabinet
quality birch plywood purchased from a Grand Forks, ND local hardware
retailer. The rationale behind choosing birch plywood is that it has a very clean
face and very few knots. The use of higher grade wood ensures the bulkheads
and fins will have uniform wood grain and will be structurally strong in order
withstand the stress of flight. Bulkheads are cut from the plywood using a table
saw, and then sanded to fit securely in the 6.0 in. diameter rocket body tube.
The bulkheads are affixed inside the airframe with West Systems epoxy on both
the superior and inferior edges for added strength. The plywood bulkheads
make certain the rocket structure is rigid throughout its entire length.
- Motor type
 The current simulated motor type used for the 2013-2014 Frozen Fury Rocket is
an Aerotech L2200G. This motor has a moderate impulse and projects the
design’s max altitude at approximately 7030.94 ft. It was also verified that the
AeroTech L2200G motor was not of the Skid mark/metal filing variety so there
would be no additional fire hazard with its use.
- Workmanship
 The quality of work is very important to maintain a successful program. The
team has plans to stay neat in the construction process and all tools and
components will put away at the end of the day. This is propelling the team
toward success by keeping our workspace clean day-to-day, which helps
expedite work.
Subsystems
- The subsystems that are required to accomplish our mission include: 36 in. drogue
parachute which will deploy 3 seconds after apogee, and the 72 in. main parachute
which will deploy at 3 seconds as well. Both of these will be attached by nylon shock
cords to the inside fuselage and will deploy based on altimeter readings. We have
chosen to separate the two sections to allow for the most stable decent possible for our
Hazard Detection Camera payload.

Final Drawing

Verification Plan and Status
- Purpose
 The primary purpose of the 2013-2014 University of North Dakota Frozen Fury
rocket team is to design and construct a safe, stable rocket that will conduct
research in liquid sloshing to assist in the understanding of liquid sloshing in
microgravity. As well as develop a useful hazard detection system.
- Manufacturing, Verification, Integration, and Operations Plan
 For the process of which we will be completing our rocket, we will be using
equipment provided by the Physics and Engineering departments at the
University of North Dakota to manufacture and assemble our rocket. To verify
this process we will do functional testing’s, such as doing multiple practice
charges on the ground, payload data taken from rooftops and verified against
actual results, and practice flights throughout the assembly process to see what
areas we can improve in or modify. The integration of our payload and
subsystems (i.e. parachutes) will be done concurrently with the assembly
process to assure that proper size is accommodated for each component. Finally
operations will be done once all tests assure us that we are ready to launch our
finished product, and test its functionality.
- Confidence and Design Maturity
 The basis of our design is off of our 2012-2013 rocket that was done with the
SMD payload. This gave us a good starting point in determining how large a
diameter of rocket we wanted, as well as the overall length of the rocket. The
reason why we’ve gone with our length is because we are unsure of how our
payload will be incorporated, as in whether it will be more compact or

lengthened out along our shaft which it will rotate about. We know from the
2012-2013 rocket that their design length was slightly smaller than needed, so
from that, we determined that our finished rocket will be larger in length then
that design
Mass Statement
 The mass of the vehicle was estimated by Rocksim to be 688.8463 Oz. with a
margin of 2.44; Rocksim has projected that our rocket will hit an altitude of
7030.94 ft with our specified motor. A list of the weights for each component
and subsystems are as follows:
 Nose cone: 11.6069 Oz
 Centering ring: 5.8017 Oz
 Body tube: 14.2262 Oz
 Centering ring: 5.8017 Oz
 Transition: 26.8820 Oz
 Main Parachute: 5.5766 Oz
 Body tube: 32.2460 Oz
 Bulkhead: 4.8070 Oz
 Liquid Mass: 28.3744 Oz
 Bulkhead: 4.8070 Oz
 Liquid Mass: 28.3744 Oz
 Bulkhead: 4.8070 Oz
 Drogue Parachute: 2.2767 Oz
 Bulkhead: 4.8070 Oz
 Fin set: 78.90 Oz
 Bulkhead: 4.8070 Oz
 Body tube:10.5152 Oz

Subscale Flight Results
 Due to undesirable weather conditions; blizzards, high winds, and cold
temperatures we have not had a day that has been suitable for the launch of
our scale model, since its completion. The model is complete and ready for
launch, the first scale flight will happen the week of 03/02/2014. Simulations of
the scale model predict a maximum altitude of 5000 ft. The Scale model will use
an AeroTech H110 engine.


Recovery Subsystem
Description of Hardware
- Parachute
 Both of our parachutes will be made out of a nylon material.
 Main – 72 in. Deployment at 700 ft. Style: Round.
 Drogue – 36 in. Deployment 2 seconds after apogee. Style: Cross.
-
Harnesses

The shock cords are made of rip-stop nylon. The shock cord’s length will be large
enough to ensure that none of the rocket’s structural components will collide
during decent.
-
Bulkheads
 Internal bulkheads/centering-rings will be constructed out of 0.5 in. cabinet
quality birch plywood. Birch plywood is has a very clean face and very few knots.
The use of higher grade wood ensures the bulkheads uniform wood grain and
will be structurally strong in order withstand the stress of flight. Bulkheads are
cut from the plywood using a table saw, and then sanded to fit securely in the
5.75 in. inner diameter rocket body tube. The bulkheads are affixed inside the
airframe with West Systems epoxy on both the superior and inferior edges for
added strength. The plywood bulkheads make certain the rocket structure is
rigid throughout its entire length.
-
Attachment Hardware
 Shock cords and parachutes are all attached with quick links for ease of
assembly and removal. The quick links will also be attached to eye bolts which
are epoxied into place on the altimeter bay’s bulk head. Sheer pins will be used
in conjunction with small amount of friction fitted tape at the separation points.

Electrical Components
- Altimeters
 We will be using two Perfect Flight StratoLogger Altimeters. They will each be
connected to a 9 volt battery, and be located in the Altimeter bay. They are set
to go off 2 seconds after apogee to release the drogue, and at 700 ft. to release
the main parachute.

Kinetic Energy
1
-
Using the equation for kinetic energy𝐾 = 2 𝑚𝑣 2, where m is the mass and v is the
-
velocity of the rocket we can calculate the kinetic energy of the rocket. For the kinetic
energy when the rocket lands m=600.097 Oz and v=44.903 ft/sec.
Calculations:
0.0625 𝑙𝑏
600.097 𝑂𝑧 (
) = 37.506 𝑙𝑏,
1 𝑂𝑧

Drawings
-
Drogue Parachute
1
𝑙𝑏 𝑓𝑡 2
𝐾 = (37.506)(44.903)2 = 2,016.279
2
𝑠𝑒𝑐 2
-

Main Parachute
Test Results
At this current point in time we do not have test results for the full scale rocket, but here
is a list the tests we plan on conducting.
-
Black Powder Charges Testing
 We plan to test the charges that will separate the specific chambers of the rocket.
Prior to these testing, the entire rocket will need to be built to ensure the weight of
the rocket is the same as in flight. This includes that the parachutes, blast protection
bag (of the parachute), and the shock cords will all be packed inside their respective
chambers. This will most likely be one of the final tests before launch.
-
Main Parachute
 Once parachute is constructed, we will test the strength of the material to ensure
no rips will occur and everything was sewn correctly. We will also test the parachute
by dropping it a various heights to ensure it will work properly and the vehicle will
have a safe landing.



-
Drogue Parachute
 Once parachute is constructed, we will test the strength of the material to ensure
no rips will occur and everything was sewn correctly. We will also test the parachute
by dropping it a various heights to ensure it will work properly and the vehicle will
have a safe landing.
-
Drogue Parachute Force for Fairing Deployment System
 Once we can verify the Drogue Parachute will function properly, we will need to test
the integration of the Fairing Deployment System Payload. Since the Fairing
Deployment system will rely on a specific amount of force to push the nose cone
forward from the drogue parachute, we will need to figure out this exact amount of
force and ensure that the drogue parachute can perform the task, while not
interrupting the deployment.
Mission Performance Predictions
- Our performance predictions come from the software RocSim 9 the predictions are as
follows
 Altitude: 7030.94 ft
 Maximum Velocity: 794.661 ft/sec
 Maximum Acceleration: 510.392 ft/sec/sec
 Weight: 688.84 Oz
 Maximum Thrust: 3100.821 N
 CP: 88.7776 in
 CG: 68.1631 in
 Static Stability Margin: 2.44
Flight Profile Graphical representations
Altitude:
Altitude Feet
8000
7000
6000
5000
4000
Altitude Feet
3000
2000
1000
0
0

50
100
150
Velocity:
Velocity Feet / Sec
900
800
700
600
500
Velocity Feet / Sec
400
300
200
100
0
0

Acceleration:
50
100
150
Acceleration Total Feet/sec/sec
600
500
400
300
Acceleration Total
Feet/sec/sec
200
100
0
0
50
100
150
-100

Weight:
Mass Ounces
700
690
680
670
660
650
640
630
620
610
600
590
Mass Ounces
0

Thrust:
50
100
150
Thrust N
3500
3000
2500
2000
Thrust N
1500
1000
500
0
0

0.5
1
1.5
2
2.5
Static Stability Margin:
Static stability margin Calibers
4.5
4
3.5
3
2.5
Static stability margin
Calibers
2
1.5
1
0.5
0
0

Drag Force:
50
100
150
Drag force N
450
400
350
300
250
200
Drag force N
150
100
50
0
-50 0
50
100
150

Payload Integration
- For the payloads that require electronics those electronics will be contained in areas
separated from the actual payload itself. As for the liquid payload the entire payload will
be contained in one removable cylinder that will allow for easy removal this is shown
below.

Launch Concerns and operation procedures
Analysis of Item of
Function After Actions
Taken
Analysis of Current Item of Function
Item or
Function
Battery
Wiring
Potential
Failure
Mode
Altimeters
fail, and
parachute
s never
deploy
Potential
Effect(s) of
Failure
Unsafe return
results in
damages
Severity
Potential
Cause
10
Wiring from
the
batteries to
the
altimeters
wiggle
loose over
the flight
Motor
retainer
Motor
retainer
comes
loses
during
flight
Rocket could
become
unstable
8
Unpredicte
d flight
path, could
crash land
Structura
l Failure
any of the
fins or
structure
of the
rocket fail.
Energetic
deconstruction
.
10
Cracks or
unsecure
surfaces
Exterior
paint
failure
paint
could strip
off due to
high
velocities.
Striping of
paint from the
rocket.
1
High
velocities
over the
rocket skin,
and an
uneven
coat of
paint
Fins
Fins come
lose or
break off
during
flight
Rocket will go
off course of
projected flight
pattern
Nose
cone
Nose cone
separates
in flight
Entire
chamber will
deconstruct

Updated list of Hazards
4
Fins not
secure to
body.
8
Surfaces
not tightly
sealed
Expected
Occurrenc
e
Preventativ
e
Recommende
d Action
4
Solder end
of wires,
use
bindings to
keep the
wires from
wiggling
during the
flight
Shake test,
and addition
of hot glue
over joints
2
Ensure
plenty of
epoxy is
used on
holes,
ensure
bolts are
fastened
tightly
Light test to
inspect for any
holes or gaps
between the
surfaces.
3
Inspection
of gluing
areas.
Allow proper
time for drying
1
Even coats
of paint,
and
consider
limiting
velocity of
rocket
Paint Rocket
evenly, uses
of proper paint
on specific
materials.
2
Use plenty
of epoxy
when
attaching
the fins.
Inspect to
make sure
there are no
holes or gaps
between the
body and the
fins
4
Inspection
and test all
surfaces
remain tight
during flight
Testing in
wind tunnels
Completio
n
Listing of Personal Hazards
The following is a list of the most common personal hazards when constructing the
rocket. During this phase, communication to other team members of the potential risks
will be essential to ensure their safety.
Personal Hazards
Mitigations
Status
Skin contact when gluing
parts together using
epoxy and resin
Wear protective gloves
Have necessary
safety
equipment
Debris getting into eyes
Wear protective goggles
when cutting or sanding
parts
Have necessary
safety
equipment
Breathing powder when
mixing hardener with
epoxy and resin
Wearing mask to cover
mouth and nose when
mixing ingredients
Have necessary
safety
equipment
Skin irritation cause by
cutting material
(example: carbon fiber)
Wear long sleeves,
gloves and eye
protection
Have necessary
safety
equipment
Injury from small
explosive (example:
ejection charges)
Only have experienced
team member handle
explosives. Inform any
other team members of
risks, and to keep
enough distance
Complete
Injury from using
powered equipment
Only have experienced
member use machines
Complete
The MSDS information for the following products we will be using. The MSDS will not be
attached to the CDR for paper conservation, but the information can be found in the links below.
West Systems Epoxy
 Product Name: WEST SYSTEM® 105! Epoxy Resin.
 Product Code: 105
 Chemical Family: Epoxy Resin.
 Chemical Name: Bisphenol A based epoxy resin.
 http://www.westsystem.com/ss/assets/MSDS/MSDS105-resin.pdf
West Systems Hardener
 Product Name: WEST SYSTEM® 205! Fast Hardener.
 Product Code: 205
 Chemical Family: Amine.


Chemical Name: Modified aliphatic polyamine.
http://www.westsystem.com/ss/assets/MSDS/MSDS205.pdf
West Systems High Density Filler
 Product Name: WEST SYSTEM! 404" High-Density Filler.
 Product Code: 404
 Chemical Name: Calcium Metasilicate, silicon dioxide blend.
 http://www.westsystem.com/ss/assets/MSDS/MSDS405.pdf
West Systems Fiber Glass
 Product Name: WEST SYSTEM® 727 Episize! Biaxial 4” Glass Tape, WEST
SYSTEM 737Episize Biaxial Fabric, and WEST SYSTEM 738 Episize Biaxial
Fabric with Mat.
 Product Code: 727, 737, or 738.
 Chemical Family: No information.
 Chemical Name: Fibrous Glass.
 http://www.westsystem.com/ss/assets/MSDS/MSDS745.pdf
Ammonium Perchlorate – Obtained from Sciencelab.com
 Product Name: Ammonium perchlorate
 Catalog Codes: SLA2725
 CAS#: 7790-98-9
 RTECS: SC7520000
 TSCA: TSCA 8(b) inventory: Ammonium perchlorate
 CI#: Not available.
 Synonym:
 Chemical Formula: NH4ClO4
 http://www.sciencelab.com/msds.php?msdsId=9922929
Carbon Fiber
 MSDS Number: 439-3227-00SU-C000-12
 This product is not classified as a Hazardous Chemical as defined by the OSHA
Hazard Communication Standard.
 Statement of Hazard: May cause temporary mechanical irritation of the eyes, skin
or upper respiratory tract.
 Carbon fibers or dust are electrically conductive and may create electrical shortcircuits which could result in damage to and malfunction of electrical equipment
and/or personal injury.
 http://www.tapplastics.com/uploads/pdf/MSDS%20Carbon%20Fiber%20Sheet.p
df
When using any of these products, every team member will understand the dangers
and make sure they are following proper safety measure.
The following link is from the OSHA site precautionary measures for the use of power
tools.
 http://www.osha.gov/doc/outreachtraining/htmlfiles/tools.html

Environmental Concerns
The following is a table of environmental concerns and how we plan to mitigate them.

Environmental concerns
Mitigations
Status
Dissolution of rocket fuel
into open water causes
contamination of water
source.
Careful planning of launch
locations and recovery area.
Launch area are
open fields, away
from water sources.
Fume inhalation of
hazardous fumes due to
proximity to rocket.
Observe proper distances
for spectators and keep
minimum crew around
rocket.
Complete
Ignition produces sparks
capable of setting fire to dry
grass and other flammable
material.
Keep flammable material
away from rocket and ensure
the launch rail is metal.
Complete
Upon recovery, ground
destruction may be
discovered, such as loose
rocket propellant.
Prior to launch, all rocket
components will be checked
so that all materials are
secured and contained to
minimize potential ground
damage.
Pending
Potential hazard to
wildlife if small rocket pieces
are ingested.
Team will function as
cleanup crew at impact and
launch site to ensure all
rocket parts are recovered.
Complete if
necessary. Will bring
bag to gather all
pieces.
Rocket ash can have
hazardous effects on the
ground below the launch
pad.
An adequate blast shield
will be used and when clean
up occurs proper disposal of
the cleaning materials will
take place.
Blast shield will be
brought with to
launch site.
Safety and Environment (Vehicle)
- The Safety Officer is Nicole F.
- Analysis of Failure Modes
- The following is a list of potential failure modes for the rocket. This includes the
expected severity and plans for mitigating the risk.





Severity Ranking of Identified Hazards:
10 to 8: Catastrophic: A condition that may cause injury, total loss of rocket, or severe damage to systems
and equipment during launch or testing procedures. Constitutes a loss of greater than 50% of total cost.
7 to 5: Critical: A condition that may cause injury, damage to rocket, or damage to systems and equipment
during launch or testing procedures. Constitutes a loss between 15-50% of total cost.
4 to 2: Moderate: A condition that may cause minor injury, minor damage to rocket, or minor damage to
systems and equipment during launch or testing procedures. Constitutes a loss between 2-15% of total cost.
1: Negligible: A condition with no injury to persons, superficial damage to rocket, or superficial damage to
systems and equipment during launch or testing procedures. Constitutes a loss between 0-2% of total cost.
IV). Payload Criteria

Testing and Design of Payload Experiment
-
-
-
Hazard Detection Camera:
 The Hazard Detection Payload will consist of a camera and the necessary
electronics to scan the ground during decent and relay any landing hazards in
real time to a ground station. This payload will require static ground tests to
determine the abilities the camera and software in identifying potential landing
hazards.
Faring system:
 The faring system will be designed to deploy the hazard detection camera; this
system will be all mechanical and consist of few moving parts. The system will
draw the needed force from the deployment of the payload sections parachute.
It will do this through a simple system consisting of a tether running from the
chute to two pulleys the tether is then attached to a rod. Upon the deployment
of the chute the force from the air resistance will cause the rod to push the
nosecone up 1.5 inches, this will then allow the segmented cylinder housing the
hazard detection camera to separate. The four segments will be attached to the
body tube by locking hinges so; when the segments separate they will be folded
back towards the body tube and away from the nose cone, revealing the hazard
detection camera.
Liquid Sloshing Payload:
 The slosh liquid payload comprises of two tanks each partly filled with a nonhazardous liquid. These payloads are intended to provide information that can
give insight into the effect of sloshing of rocket fuel as it is depleted during
flight. One of the tanks contains slosh control devices and while the other does
-
not. The flow patterns developed during the rocket flight will be recorded on
camera to be used for further investigations.
 Perforated disc baffles are intuitively installed one on each of two locations (1/3
and 2/3) along the height of the sloshing fluid tank. The perforated disc pattern
has been selected because it is the easy to fabricate and could substitute for inflight adjustable baffle system. The tank has hole located at the center of the
top side that will serve both filling and emptying purposes.
 The design essentially reduces amount of space available for the free surface of
fluid to move. The perforated discs, hopefully, will damp out the fluid
movement otherwise due to sloshing and also redistribute the fluid flow
pattern. Since the purpose of the payload load is to collect data that will shed
light on the liquids slosh pattern during flight, the quantity of liquid is small
enough not to have any significant effect on the rocket’s flight trajectory.
 Tanks are fabricated from Plexiglas the parts being held by epoxy. The materials
have been selected because of they are light weight and have strength sufficient
to bear the loads.
Integration of Slosh Liquid Payload
 The flanged bases of the tank sit on a centering ring to which they are coupled
by means of bolts or screw keeping it firm during flight. The tanks are placed
parallel to each and have the same net weight for correct weight distribution
and will sit on the same centering ring.

Production Diagram of Slosh Payload

Safety and Environment (Payload)


The Safety Officer is Nicole F.
Analysis of Failure Modes
The following is a list of potential failure modes for the payloads. This includes the expected
severity and plans for mitigating the risk.
Severity Ranking of Identified Hazards:
10 to 8: Catastrophic: A condition that may cause injury, total loss of rocket, or severe damage to systems and
equipment during launch or testing procedures. Constitutes a loss of greater than 50% of total cost.
7 to 5: Critical: A condition that may cause injury, damage to rocket, or damage to systems and equipment during
launch or testing procedures. Constitutes a loss between 15-50% of total cost.
4 to 2: Moderate: A condition that may cause minor injury, minor damage to rocket, or minor damage to systems
and equipment during launch or testing procedures. Constitutes a loss between 2-15% of total cost.
1: Negligible: A condition with no injury to persons, superficial damage to rocket, or superficial damage to systems
and equipment during launch or testing procedures. Constitutes a loss between 0-2% of total cost.
Liquid Sloshing Analysis Payload
Liquid tank
Tank comes
loose during
flight
Sloshing
data not
collected,
changing
stability of
rocket
during flight
Cameras
Cameras fail to
collect data
No results
for
experiment
Wires
Baffles
3
Tightly
fasten
bolts, add
epoxy if
needed
Conduct
shake test
3
Camera
mounting
Test
recording,
conduct
shake test
Conduct
shake test
Conduct
shake test
8
Tank not
properly
secured to bulk
plate
3
Camera comes
loose during
flight, no
power
Wires come
loose during
flight
Power loss.
No results
for
experiment
3
Wire get
caught on
objects during
flight
3
Feed wires
through
tube or
secure
them to
wall
Baffles come
loose from tank
Experiment
is ruined
3
Baffles not
properly
secured
3
Test
baffles
after
Completion
Preventative
Expected Occurrence
Potential Cause
Severity
Potential Effect(s) of
Failure
Potential Failure Mode
Item or Function
Recommended Action
Analysis of Item
of Function After
Actions Taken
Analysis of Current Item of Function
placed in
tank
Liquid tank
Water leaking
out
Sloshing
data not
collected/
damage or
electronics
6
Top and
bottom of tank
not secure
7
Walls of nose
cone will not
fall out, Hazard
detection
camera view
ground
8
High forces
acting around
hinge causing
to break off
rocket
2
Inspection
of seals.
Add epoxy
if needed
Conduct
shake test
to see if
water
spills out
2
Testing of
force
provided
by drogue
parachute
is sufficient
Have a
backup
system to
ensure
nose cone
will move
forward
5
Proper
securing of
hinges.
Add extra
epoxy if
necessary
Conduct
tests in
wind
tunnel
5
Use tight
seals to
help
secure the
lips of the
walls
Conduct
tests in
wind
tunnel,
test
mechanics
of system
to ensure
they are
hold walls
tight,
squeeze
test
2
Test
locking
mechanism
on hinge
Test after
integration
of Hazard
detection
camera
3
Camera
mounting
Test
recording,
conduct
shake test
3
Feed wires
through
tube or
secure
them to
wall
Conduct
shake test
Faring Deployment Payload
Drogue
Parachute
Drogue
Parachute fails
to deploy
Fairing
system is
not given
any force to
push
forward the
nose cone
Hinges
Hinges break or
become
damaged
Nose cone
area
exposed
during flight
Walls
Hinges
Walls of nose
cone come
apart during
flight
Nose cone
area
exposed
during flight
Fail to lock
walls of nose
cone
Hazard
Detection
Camera's
view is
blocked, no
data
collected
9
High forces
acting on walls
cause them to
separate
3
Defective
hinge, or
damaged
during flight
3
Camera comes
loose during
flight, no
power
3
Wire get
caught on
objects during
flight
Hazard Detection Camera Payload
Cameras
Wires
Cameras fail to
collect data
No results
for
experiment,
system
cannot
detect
hazard
Wires come
loose during
flight
Power loss.
No results
for
experiment
Electronic
communicating
between
camera to
ground station

Communication
loss between
rocket and
ground station
No data
sent/
received,
cannot
detect
hazards
3
Body of rocket
prevents
communication
4
Testing of
equipment
at various
distances
Testing
after
integration
of all
systems
Updated list of Hazards
The lists of personal hazards when constructing the payload are similar to those of
constructing the rocket. Thus, all the information on the list of updated hazards can be found
in: III) Vehicle, Safety and Environment (Vehicle).

Environmental Concerns
The following is a table of environmental concerns for the three payloads and how we plan to
mitigate them.
Environmental concerns
Mitigations
Status
Potential hazard to
wildlife if small payload
pieces are ingested.
Team will function as
cleanup crew at impact
and launch site to
ensure all rocket parts
are recovered.
Complete if
necessary. Will bring
bag to gather all
pieces.
Batteries become broken
cause an exposure to
chemical waste (Ex: lead
mercury, and cadmium)
While wearing
gloves, member will
clean area. For alkaline
batteries use lemon
juice. For acid base
batteries, use baking
soda with water.
Complete if
necessary. Will bring
proper cleaning
supplies.
V). Project Plan

Budget Plan:
- The following is a chart of the cost of the entire rocketry project. As we have
found ways to save money, such as grants or by using previously owned
materials, we added it to the funded column. This way we know how much
money is needed for the rest of our expenses.
EXPENSES
QUANTITY
PRICE PER UNIT
COST
FUNDED
EXPENSES
OUTSTANDING
Travel / Gas
Van (mileage
and gas)
1
$700.00
Sub Cost
$700.00
yes - Space
Grant
$700.00
0
Lodging
May 13, 2014 Billings, MT
4
$85.00
$340.00
yes - Space
Grant
May 14, 2014 –Salt
Lake City, UT
4
$85.00
$340.00
yes - Space
Grant
May 15, 2014 - Salt
Lake City, UT
4
$85.00
$340.00
yes - Space
Grant
May 16, 2014 - Salt
Lake City, UT
4
$85.00
$340.00
yes - Space
Grant
May 17, 2014 - Salt
Lake City, UT
4
$85.00
$340.00
yes - Space
Grant
May 18, 2014 - Salt
Lake City, UT
4
$85.00
$340.00
yes - Space
Grant
May 19, 2014 Billings, MT
4
$85.00
$340.00
yes - Space
Grant
Sub Cost
$2,380.00
0
Rocket Supplies
Air Frame ( in)
2
$404.00
$808.00
$808.00
Centering Ring
3
$7.00
$21.00
$21.00
Motor Mount Tube
1
$14.00
$14.00
$14.00
Nose Cone
1
$49.45
$49.45
$49.45
Stiffy Tube
2
$9.95
$19.90
$19.90
Tube Coupler
2
$8.25
$16.50
$16.50
Parachute 96"
1
$89.95
$89.95
$89.95
1
$20.95
$20.95
$20.95
2
$2.65
$5.30
$5.30
6
$1.10
$6.60
$6.60
Drogue 36"
1000 Series Rail
Beads
Shockcord (per yard)
Casing
Motor Aerotech
L220G
Rocket Kit
previously
$450.00
own
1
$450
4
$215.00
$860.00
1
$40.00
$40.00
$860.00
scrapped
from
previous
rocket
PerfectFlite
2
$99.95
Sub Cost
$199.90
previously
own
$2,601.55
$1,911.65
Misc. Supplies
1/4" by 6' Plywood
1
$15.00
$15.00
$15.00
1/8" by 6' Plywood
1
$15.00
$15.00
$15.00
Nuts
20
$0.25
$5.00
$5.00
Washers
20
$0.25
$5.00
$5.00
Eye Bolts
4
$1.50
$6.00
$6.00
Xacto Knife
1
$1.97
$1.97
$1.97
Batteries
6
$5.00
$30.00
$30.00
Paint & gloss
6
$10.00
$60.00
$60.00
Paper towels
1
$3.99
$3.99
$3.99
Plastic cups
1
$5.99
Sub Total
$5.99
$5.99
$147.95
$147.95
Payload Supplies
Arduino Mega 2560
Mego Protoshield for
Arduino
D2523T Helical GPS
Receiver
Copernicus II DIP
Module
Xbee Pro 900 Wire
antenna
Xbee Pro 900 U.FL
Connection
LinkSprite JPEG Color
Camera TTL Interface
Open Log
TEMT6000 Breakout
Board
Mini Photocell
Light to Frequency
Converter - TSL235R
Polymer Lithium Ion
Battery - 6Ah
CamOne Infinity w/ gps
module
2 in. Plexiglas glass tube
48" long
2
$58.95
$117.90
$117.90
2
$14.95
$29.90
$29.90
2
$79.95
$159.90
$159.90
2
$74.95
$149.90
$149.90
4
$42.95
$171.80
$171.80
4
$42.95
$171.80
$171.80
2
$49.95
$99.90
$99.90
2
$24.95
$49.90
$49.90
2
$4.95
$9.90
$9.90
2
$1.50
$3.00
$3.00
2
$2.95
$5.90
$5.90
1
$39.95
$39.95
$39.95
2
$199.00
$398.00
$398.00
1
$50.00
$50.00
$50.00
Sheet of Plexiglas
1
$30.00
$30.00
$30.00
Hinges
CamOne GPS Module
4
$5.00
$20.00
$20.00
2
$50.00
$100.00
$100.00
$1,607.75
$1,607.75
$135
$135
$135.00
$135.00
$7,572.25
$3,802.35
Sub Total
Other Expenses
T-shirts
9
$15.00
Sub Total
Total Cost

Timeline:

February
- 10
- 28
- Full Scale Test Launch (tentative)
-CDR reports, presentation slides, and flysheet posted
March
- 3-7
- 12
- 13
-CDR Presentations
-Full scale test launch
- Flight Readiness Review Question and Answer Session
April
- 18
- 21-25
-FRR reports, presentation slides, and flysheet posted
-Present FRR (tentative dates)





May
-
14
15-16
-
17-18
June
- 2
- 13
-Arrive in Salt Lake City, Utah
-Launch Readiness Reviews
-Flight Hardware and Safety Check (tentative)
-Launch Day
-Post the -Post Launch Assessment Review (PLAR)
-Winning USLI team will be announced
Educational Engagement Plan and Status
- Schools: Valley Middle School and South Middle School.
- Dates of the Events: March 28th 2014 and April 16th 2014 respectively.
- Location of Events: Classrooms and auditorium of participating schools.
 Plan: For Valley Middle School we will be going into the classroom of a local
8th grade teacher who is currently covering physical sciences that relate to
space exploration. Around March 28th, the classes will be covering basic
physics principles such as gravity and momentum. We will be coming in and
giving a brief lecture about those topics and then following up with hands on
experiment. The experiment will be simple, but incorporates some of the
material covered in the lecture. We are thinking of doing a momentum
experiment that momentum is affected by mass and velocity by having kids
experiment with rolling balls at a target and seeing if a heavier ball or a faster
ball effects momentum more.
 For South Middle School, we are planning on going in and doing something
similar to what was done at Valley Middle School, except that we will be
focusing more on the trajectory since it pertains more to what they are
currently doing. The experiment that we plan on doing with them, following
the brief lecture, is have them find the optimal angle to maximize distance
for a projectile. We will do this by having them use old film canisters and
filling them up with water and antacids to create the force necessary for
liftoff. From there the students will experiment with the angle to see what
works best to maximize the distance. Afterwards, we will have a contest to
see who can get their projectile closest to a target. The students will use their
knowledge from the previous experiment to try and get their projectile
closest to the target.
- Number of Students: If all goes according to plan, we will reach about 125-150
students depending on attendance on those days. We are still in talks with teachers
to see if they would be interested in more presentations in the future if it fits into
their curriculums.
VI). Conclusion