UNIVERSITY OF NORTH DAKOTA
FROZEN FURY
UNIVERSITY STUDENT LAUNCH INITIATIVE
CRITICAL DESIGN REVIEW
JANUARY 14, 2013
Contents
I) Summary of PDR Report ......................................................................................................... 5
Team Summary ........................................................................................................................ 5
 Team Name and Mailing Address .................................................................................... 5
 Location ............................................................................................................................ 5
 Team Mentor .................................................................................................................... 5
Launch Vehicle Summary ....................................................................................................... 5
 Size and Mass ................................................................................................................... 5
 Motor Choice.................................................................................................................... 6
 Recovery System .............................................................................................................. 6
 Rail Size ........................................................................................................................... 6
 Milestone Review Flysheet .............................................................................................. 6
Payload Summary .................................................................................................................... 8
 Payload Title .................................................................................................................... 8
 Summarize Experiment .................................................................................................... 8
II) Changes Made Since Proposal ............................................................................................. 9
 Changes Made to Vehicle Criteria ................................................................................... 9
 Changes Made to Payload Criteria ................................................................................... 9
 Changes Made to Project Plan ......................................................................................... 9
III) Vehicle Criteria........................................................................................................................ 9
Design and Verification of Launch Vehicle .......................................................................... 9
 Flight Reliability and Confidence .................................................................................... 9
 Major Milestone Schedule ............................................................................................. 10
 System Level Design Review ........................................................................................ 11
 Performance Characteristics for Systems ....................................................................... 12
 Approach to Workmanship ............................................................................................ 14
 Component, Functional, and Static Testing ................................................................... 14
 Manufacturing and Assembly Status and Plans ............................................................. 15
 Design Integrity .............................................................................................................. 15
 Safety and Failure Analysis ........................................................................................... 16
Subscale Flight Results ......................................................................................................... 17
 Flight Data ...................................................................................................................... 17
 Flight Model Comparison to Actual Flight .................................................................... 17
 Subscale Flight Design Impact ....................................................................................... 17
Recovery Subsystem ............................................................................................................. 17
 Parachute, Harnesses, Bulkheads, and Attachment Hardware ....................................... 17
 Drawings/sketches, Block Diagrams, and Electrical Schematics .................................. 18
 Kinetic Energy at Significant Mission Phases ............................................................... 19
 Test Results .................................................................................................................... 19
 Safety and Failure Analysis ........................................................................................... 19
Mission Performance Predictions ........................................................................................ 21
 Mission Performance Criteria ........................................................................................ 21
 Flight Profile Simulations .............................................................................................. 21
 Validity of Analysis, Drag Assessment, and Scale Modeling Results ........................... 24
 Stability Margin, CP and CG Relationship and Locations............................................. 24
Payload Integration ................................................................................................................ 24
 Payload Integration Plan ................................................................................................ 24
 Installation and Removal, Interface Dimensions, and Precision Fit .............................. 25
 Compatibility of Elements ............................................................................................. 25
 Simplicity of Integration Procedure ............................................................................... 25
Launch Concerns and Operation Procedures ................................................................... 25
 Draft of Final Assembly and Launch Procedures .......................................................... 25
 Recovery Preparation ..................................................................................................... 27
 Motor Preparation .......................................................................................................... 28
 Igniter Installation .......................................................................................................... 28
 Setup on Launcher .......................................................................................................... 28
 Troubleshooting ............................................................................................................. 30
 Post Flight Inspection ..................................................................................................... 30
Safety and Environment (Vehicle) ....................................................................................... 30
 Team Safety Officer ....................................................................................................... 30
 Preliminary Failure Modes Analysis .............................................................................. 30
 Safety Hazards Analysis................................................................................................. 34
 Environmental Concerns ................................................................................................ 38
IV) Payload Criteria .................................................................................................................... 39
Testing and Design of Payload Experiment ....................................................................... 39
 System Level Design Review ........................................................................................ 39
 System-Level Functional Requirements ........................................................................ 42
 Approach to Workmanship ............................................................................................ 42
 Component Testing, Functional Testing, or Static Testing ............................................ 42
 Manufacturing and Assembly Status and Plans ............................................................. 43
 Integration Plan .............................................................................................................. 43
 Instrumentation Precision and Repeatability of Measurements ..................................... 45
 Payload Electronics and Transmitters ............................................................................ 50
 Safety and Failure Analysis ........................................................................................... 52
Payload Concept Features and Definition.......................................................................... 53
 Creativity and Originality............................................................................................... 53
 Uniqueness or Significance ............................................................................................ 53
 Suitable Level of Challenge ........................................................................................... 54
Scientific Value ....................................................................................................................... 54
 Payload Objectives ......................................................................................................... 54
 Payload Success Criteria ................................................................................................ 55
 Experimental Logic, Approach, and Method of Investigation ....................................... 55
 Tests, Measurements, Variables, and Controls .............................................................. 56
 Data Relevance and Accuracy/Error Analysis ............................................................... 56
 Experiment Process Procedures ..................................................................................... 56
Safety and Environment (Payload)...................................................................................... 56
 Safety Officer ................................................................................................................. 56
 Preliminary Failure Modes Analysis .............................................................................. 56
 Safety Hazards Analysis................................................................................................. 58
 Environmental Concerns ................................................................................................ 58
V) Project Plan ............................................................................................................................ 58
Schedule and Status of Activities ........................................................................................ 58
 Budget Plan .................................................................................................................... 58
 Funding Plan .................................................................................................................. 61
 Timeline ......................................................................................................................... 61
 Educational Engagement Plan and Status ...................................................................... 64
VI) Conclusion............................................................................................................................. 65
I) Summary of PDR 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

Team Mentor
Dr. Timothy Young, NAR # 76791, Certification Level 2
Launch Vehicle Summary

Size and Mass
Vehicle Dimensions
Length: 108.5 in. / 9.04 ft.
Diameter: 6.0 in.
Span: 22.0 in.
Unloaded mass: 180.4223 oz. / 11.27 lbs.
Loaded Mass: 258.8363 oz. / 16.177 lbs.
CP: 90.86 in.
CG: 74.4185 in.
Margin: 2.74
Fin Dimensions
Root: 12.0 in.
Tip: 6.0 in.
Sweep length: 3.0 in.
Semi Span: 8.0 in.

Motor Choice
Aerotech K828FJ
Diameter: 54 mm
Length: 22.7953 in.
Burn: 2.50 sec.
Thrust: 862.878 N/193.98 lbs.
Impulse: 2157.195 N*Sec. / 484.95 lbs.*Sec

Recovery System
Dual Deployment from 2 Perfect Flite Stratologger altimeters.
Drogue: 36 in. (Apogee)
Main: 72 in. (at 700 ft.)

Rail Size
120 in. slotted rail to fit 0.25 in. rail beads. 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.

Milestone Review Flysheet
Milestone Review Flysheet
PDR, CDR, FRR
Institution Name
University of North Dakota
Vehicle Properties
Milestone
CDR
Motor Properties
Diameter (in)
6
Motor Manufacturer
Aerotech
Length (in)
Gross Liftoff Weight
(lb)
108.5
Motor Designation
K828FJ
Launch Lug/button Size
16.177
0.25 inch
Max/Average Thrust (N)
Total Impulse (N-sec)
1303.79/862.878
2157.195 N-sec
Sust: friction Bost: PML
Retainer
Motor Retention
Mass pre/post Burn (g)
Stability Analysis
2223.0/1373.0
Ascent Analysis
Center of Pressure (in from nose)
90.860
Rail Exit Velocity (ft/s)
95.95
Center of Gravity (in from nose)
74.4185
Max Velocity (ft/s)
839.38
Static Stability Margin
2.74
Max Mach Number
0.7518
Thrust-to-Weight Ratio
11.99
Max Acceleration (ft/s^2)
554.03
Rail Size (in) / Length (in)
120 in
Peak Altitude (ft)
5,250
Recovery System Properties
Recovery System Properties
Drogue Parachute
Main Parachute
Manufacturer/Model
TBD
Manufacturer/Model
TBD
Size
36 in.
Size
72 in.
Altitude at Deployment (ft)
Apogee (5,250)
Altitude at Deployment (ft)
700
Velocity at Deployment (ft/s)
7.17
Velocity at Deployment (ft/s)
49.77
Terminal Velocity (ft/s)
49.77
Landing Velocity (ft/s)
27.82
Recovery Harness Material
Rip Stop Nylon
Recovery Harness Material
Rip Stop Nylon
Harness Size/Thickness (in)
1
Harness Size/Thickness (in)
1
Recovery Harness Length (ft)
TBD
Harness/Airframe
Interfaces
Kinetic
Energy
During
Descent (ftlbf)
Epoxied to aft altimeter mount
and fin can motor mount.
Section 1
Section
2
Section
3
6905.53
1123.34
5650.78
Section
4
Recovery Harness Length (ft)
TBD
Epoxied to fore altimeter mount
and tied to nosecone.
Harness/Airframe
Interfaces
Kinetic
Energy
Upon
Landing
(ft-lbf)
Section 1
Section
2
Section
3
2157.62
350.99
1765.58
Recovery System Properties
Recovery System Properties
Electronics/Ejection
Electronics/Ejection
Altimeter(s)
Make/Model
Stratologger (Manuf:
PerfectFlite)
Redundancy Plan
Contingency e-charges for
both Apogee and Main Chute
separations
5 hrs
Pad Stay Time (Launch
Configuration)
Rocket Locators
(Make, Model)
PR-100 Reciever, AT-2B
Transmitter
Transmitting
Frequencies
222.250MHz
Black Powder Mass
Drogue Parachute
(gram)
TBD
Black Powder Mass
Main Parachute (gram)
Milestone Review Flysheet
Section
4
TBD
PDR, CDR, FRR
Institution Name
University of North Dakota
Milestone
PDR
Payload/Science
Succinct Overview of
Payload/Science Experiment
Identify Major Components
The payload shall gather data for studying the atmosphere during descent and after
landing, including measurements of pressure, temperature, relative humidity, solar
irradiance and ultraviolet radiation and transmit this information to a ground station. Also
to determine the location of a predetermined object by analyzing the frames of a video .
Arduino Mega 2560 R3, Copernicus II DIP Module, XBee Pro 900 Wire Antenna, LinkSprite JPEG
Color Camera TTL Interface, OpenLog, Humidity and Temperature Sensor SHT15, Barometric
Pressure Sensor - BMP085, Light to Frequency Converter - TSL235R, UV Photodiodes JEC 0.3 A,
CamOne Infinity
~18.16 oz.
Mass of Payload/Science
Test Plan Schedule/Status
Ejection charge tests will be done in January and Feburary.
Ejection Charge Test(s)
One failed half-scale flight. Next flight will occur between January 15-21.
Sub-scale Test Flights
Multiple full scale launches are planned for the month of March.
Full-scale Test Flights
Payload Summary

Payload Title
NASA Science Mission Directorate (SMD) Payload
Visual Aerial Locator Rocket (VALOR) Payload

Summarize Experiment
The primary payload is the NASA Science Mission Directorate Sensory
Array/Horizon Camera. The payload is designed around the Arduino Mega
2560 prototyping platform. Four different sensors and a data logger will be
integrated into this platform. Through this design we will complete the SMD
criteria.
The secondary payload is the Visual Aerial Locator Rocket (VALOR)
payload. This payload is designed around the integration of the Arduino
Mega prototyping 2560 platform, an inertial measurement unit (IMU), and a
high resolution camera. Through this design, we aim to determine the precise
location of predetermined objects within the increased visual field of the
rocket as it approaches apogee. This will be done through recording and
analyzing each frame of video as well as the corresponding movement of the
rocket.
II) Changes Made Since Proposal

Changes Made to Vehicle Criteria
The fin design was iterated upon due to the analysis of the sub-scale
flight. This structural change therefore caused a change in mass as well as
changes in the CG and CP of the rocket.

Changes Made to Payload Criteria
N/A

Changes Made to Project Plan
N/A
III) Vehicle Criteria
Design and Verification of Launch Vehicle

Flight Reliability and Confidence
Mission statement
The primary objective of the 2012-2013 University of North Dakota Frozen
Fury rocket team is to design and construct a safe, stable rocket that will
reach approximately 5,280ft in altitude to optimize the effectiveness of the
onboard SMD and VALOR payloads.
Rocket Launch Success Criteria
A successful rocket launch will consist of reaching an altitude at apogee
within ± 3.00% of one mile above ground level.
Rocket Recovery Success Criteria
A successful recovery of the rocket will consist of the recovery system
ejecting at the appropriate time and altitude and recovering the rocket on the
ground such that it is deemed reusable for future launches.
Payload Success Criteria
A successful payload system will consist of the NASA SMD payload and
VALOR payloads fully integrated onboard the rocket. The system should
operate successfully during and after the launch and be capable of
determining the location of predetermined objects within the field of view of
the rocket.

Major Milestone Schedule
Below are specific tasks in our timeline that pertain to launch vehicle. It included
the additional comments of the status of what has been completed, what will be
completed, and what still remains to be done.
#
Task
Constructi
9 on of Subscale rocket
Assigned
Completion
Time
Start Date
End
Date
Comments
Design /
Construction
100%
16 days
11/1/201
2
11/22/20
12
Kit for subscale was
selected, purchased
and built. Design
plans for full-scale
rocket were
completed.
Payload
Team
10%
3 month
11/16/20
12
2/15/201
2
Final selection of
parts were submitted
for both payloads
100%
16 days
11/23/20
12
12/14/20
12
10%
20 days
1/1/2013
1/20/201
3
13
Begin
Construction
of Payload
14
Launch
dates of
subscale
15
Rebuild
Sub-scale
rocket
All
Members
16
Launch
2nd Subscale rocket
All
Members
10 days
1/21/201
3
1/31/201
3
17
Work on
Construction
of full-scale
Design /
Construction
10 days
12/3/201
2
12/14/20
12
All
Members
Conducted black
powder charge tests
prior to launch.
Launched on Dec 9.
*Task was added
because of
unsuccessful flight.
Kit is purchased and
needs to be built.
*Task was added
because of previous
unsuccessful flight.
Also will be
conducting black
powder charges tests
before launch.
Final selection of
parts was made.
Construction of the
rocket was put on
hold for any
modifications based
on the subscale
results.
19
Continue
construction
of full-scale
rocket
Design /
Construction
22
Tentative
launch dates
of Full-scale
rocket
24
Second
Launch of
full-scale

2/21/201
3
We plan to start
building after we
complete the
subscale. Note:
During the 2/16 -2/21
we plan to integrate
the payload and the
full scale rocket.
11 days
2/22/201
3
3/8/2013
Before Launch of
rocket, we will
conduct black powder
charges testing.
19 days
3/18/201
3
4/11/201
3
If time and weather
permits.
31 days
1/10/201
3
All
Members
All
Members
System Level Design Review
Airframe Material
The 2012-2013 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 108.5 inch length rocket. The simulations
projected a peak altitude of 5303 ft. with both a carbon fiber and fiber-glass
rocket (approximate dry weight 11.6795 lbs.) using an Aerotech K828FJ 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 5.75 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 2012-2013 Frozen Fury
Rocket is an Aerotech K828FJ. This motor has a moderate impulse and
projects the design’s max altitude at approximately 5303 ft. This motor type is
still under discussion due to the payload component weights being unknown.
It was also verified that the AeroTech K828FJ motor was not of the Skid
mark/metal filing variety so there would be no additional fire hazard with its
use.

Performance Characteristics for Systems
The launch vehicle shall…
carry a science payload
deliver the science payload to 5,280
feet
have recovery system electronics
remain subsonic
recoverable and reusable
have a drogue and main parachute
have a max of 3 sections
be assembled within 2 hours
be able to sit on the launch pad for up
to an hour
have data that can be collected and
How we will satisfy the requirement
We will include the SMD and VALOR
payloads
We have simmed our rocket so that
the apogee is around 5,304 feet. This
will be verified with onboard altimeter
readings.
The rocket will be equipped with two
altimeters that will be activated by a
switch on the exterior of the rocket.
The maximum velocity reached in our
sim is 797.96 ft/s
All components of the rocket will be
recovered after flight. This will be
verified by inspection of the rocket
components after flight.
The rocket design will have a drogue
that will deploy at apogee and a main
that will deploy at a lower altitude.
There will be four sections upon
landing: the motor section, the
altimeter section, and the
nosecone/payload bay.
We will have the launch procedures
defined so that we can assemble
necessary components within the
time allotted.
The payload will be programmed to
be able to take data for over an hour.
The payload will be tested to perform
this requirement before competition.
Data will be collected on board, and
analyzed
have a tracking device
use a commercially available solid
motor
have a successful test launch
have a safety checklist
be built entirely by students
not exceed $5000 in total
Critique
Is this design safe?
Score 1/5
1 = Bad
5 = Good
4
Is this design limiting?
4
Does this design meet
the requirements of the
payload/rocket?
3
Will this design land
safely? Parachute sizes,
impact absorbing
design?
Does this design
maximize
performance?
4
3
will be transferred to a computer by
USB after landing.
The rocket will be tracked using a
Rocket Hunter.
Rocket motor will be from Aerotech
We have planned for 1 half scale
launch and 3 full scale launches
We have compiled a list of safety
precautions that we will bring to all
launch events.
All components of the rocket will be
assembled by the Frozen Fury team
members. Our mentor is available for
questions, but will not be involved
with the actual assembly.
The projected cost is approximately
$3,200
Comments
This design will allow for ease of construction
and eliminate safety concerns associated with
more complex construction methods
Altitude is expected to be reached and the design
will accommodate larger motors and payload
components
This current rocket design satisfies the
requirements for the projected payload.
However, the camera component of the VALOR
payload has not been decided upon, integration
ability is still in question.
The current size rocket and parachutes have the
rocket descending rapidly under drogue, but
slowing to under 25 ft/s under main.
The rocket has been designed to accommodate
the payload as well as larger motors as the design
is refined.
Are the materials
4
selected the best for this
scenario?
Any additional
comments?

-------
Carbon fiber is a strong yet lightweight material
that we have had success with in years prior. Past
experience with phenolic tubing has yielded
structural failure.
Conduct
additional
tests and
review plan to
ensure
continued
safety
Approach to 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.
Throughout the building process, multiple team members will be
collaborating and verifying the building procedures and insuring that the
results are satisfactory.

Component, Functional, and Static Testing
Black Powder Charges Testing
In both the subscale and full-scale rocket 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. For the
subscale rocket, it will lay parallel to the ground. We will be testing charges of 1g
for each section. The full-scale rocket can be in either a perpendicular or parallel
position from the ground. Also for the full-scale we will be using 2 charges in
each section as a precautionary. There charges will be 1.97 and 2.65 g, with
backups of 2 and 3 grams. The Safety Officer will ensure that any members
present are adhering to any safety precautions.
Static Testing
Before the first launch of the full scale rocket, we will conduct a static test of the
motor. The motor will lay parallel to the ground, and will be placed in a mock set
of the motor retainer. In the previous years, we attached this to a cinder block
that was nailed into the ground. We will follow similar safety procedures as if it
were an actual launch. The test will occur on the grounds of one of our
designated launch sites.

Manufacturing and Assembly Status and Plans
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.
Construction of a second sub-scale rocket is currently being finished
concurrently with the building of the full scale payload. Once a successful
sub-scale flight has occurred, construction of the full scale vehicle will
commence.

Design Integrity
The basis of our design is off of our 2010-2011 rocket that was also done
with the SMD payload. This gave us a good starting point in determining how
large of a diameter of rocket we wanted, as well as the overall length of the
rocket.
Through the iterative design of the sub-scale vehicles, our full-scale
design has matured and our construction methods have become more
efficient and our workmanship has improved. This has especially allowed us
to determine a suitable shape and fin style for the mission as well as practice
proper assembly procedures and solid connections.
The estimated mass is 180.4223 oz. / 11.27 lbs unloaded and 258.8363
oz. / 16.177 lbs loaded. While this may seem light, the carbon fiber
components have proven to be extremely lightweight. While some extra
mass was added for the simulations in order to account for epoxy and paint,
accuracy will improve as the actual components are measured during
construction.
If the mass increases by more than a few pounds, the launch will still be
successful, but it will not reach the desired height. Our motor mount has
been design to accept a larger motor casing and there are several motors in
the K range that can provide more thrust.

Safety and Failure Analysis
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.
Friction
Fit or
Sheer
Pins
If the sheer
pins or
friction
fitting is too
tight, the
rocket will
not
separate.
Unsafe
deployment of
parachute
results in
damages or
injuries.
10
The friction
fitting is too
tight, or too
many sheer
pins
3
Utilize
techniques
to ensure
the rocket is
properly
friction fit,
and the
sheer pin
amount will
break
properly.
The lifting
test for
friction
fitting, and
a blast test
for sheer
pins
Completion
Preventative
Expected
Occurrence
Potential Cause
Severity
Potential Effect(s)
of Failure
Potential Failure
Mode
Item or Function
Analysis of Current Item of Function
Recommended
Action
Analysis of
Item of
Function After
Actions Taken
Subscale Flight Results

Flight Data
An electronics failure during the flight led to a failure of the recovery
system. Flight data was destroyed.

Flight Model Comparison to Actual Flight
N/A

Subscale Flight Design Impact
The flight appeared slightly unstable which led to redesigning the fins.
Recovery Subsystem

Parachute, Harnesses, Bulkheads, and Attachment Hardware
Parachutes: Main and Drogue
The rocket will utilize a drogue parachute deployment at apogee, and a main
parachute deployment at 700 ft AGL. The drogue chute is a 36-in nylon round
parachute. This allows the rocket and payload to descend at a velocity of 49.77
ft/s. This has been considered fast enough for recovery area purposes. The main
parachute is an 72-in PML chute with a 12-inch spill hole. The spill hole lets the
rocket descend in a more stable fashion while maintaining a relatively safe
descent rate of 27.82 ft/s.
Harness: Shock Chord
The parachutes will be connected to a rip-stop nylon shock chord. They will have
quick links attached at each end 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 bulkhead. The shock cord’s length will be large enough to ensure
that none of the rocket’s structural components will collide during decent. Sheer
pins will be used in conjunction with a small amount of friction-fitted tape at the
separation points.
Bulkhead
Internal Bulkheads will be constructed out of ¼ in. cabinet quality birch plywood
purchased from a local Grand Forks, ND 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 will have uniform wood grain
and will be structurally strong in order to 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.
Attachment Hardware
We use quick links and eye-bolts to attach the shock chords and parachutes to
the bulkhead. We will also be using washers to support the screws, (such as an
eye bolt), to the material.

Drawings/sketches, Block Diagrams, and Electrical Schematics
Please see Appendix.

Kinetic Energy at Significant Mission Phases
1
𝐾𝐸 = 2 𝑚1 𝑣 2
Where, 𝑚1 = 5.5756 𝑙𝑏𝑠, 𝑚2 = 0.9070 𝑙𝑏𝑠, 𝑚3 = 4.5625 𝑙𝑏𝑠,
𝑣𝑑𝑒𝑠𝑐𝑒𝑛𝑡 = 49.77 𝑓𝑡/𝑠, 𝑣𝑙𝑎𝑛𝑑𝑖𝑛𝑔 = 27.82 𝑓𝑡/𝑠
m1(fin section)
m2 (coupler section)
m3 (nose section)

Kinetic Energy of Rocket Sections
KEdescent (ft-lbf)
6905.53
1123.34
5650.78
KElanding (ft-lbf)
2157.62
350.99
1765.58
Test Results
Black powder ejection charge testing for the sub-scale was completed and
was successful. Test results for the full-scale are pending.

Safety and Failure Analysis
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.
Parachute
Parachutes fail,
or tangle.
Quick
Links
Links are open
and detach from
eyebolt/parachut
e
Bulkhead
s
Shock
cords
Unsafe return
results in
damages or
injuries
Section of rocket
will have a crash
landing
Plate or eyebolt
breaks off
Section of rocket
will have a crash
landing
Cord rip or
become tangled
Section of rocket
will have a crash
landing/parachut
e fails to deploy
10
Improper
folding of
parachutes
, and
stuffing into
rocket
7
Experience
d members
handle
parachute
folding and
stuffing.
2
Ensure
every link
that is
opened is
closed
tightly
7
Link is not
completely
fastened
7
Plate or
eyebolt
was not
secured to
the
adjoining
surface
3
Use plenty
of epoxy
around the
bolts and
the plates
8
Use of old
cord/cords
were
jammed
into rocket
3
Replace
old cords
Pair new
team
members
with old,
have
Safety
Officer
oversee
Safety
Officer
will
inspect
prior to
placing
in the
rocket
Conduct
a pull
test to
ensure
the parts
can
withstan
d the
weight of
the
rocket
Safety
Officer
inspect
cords for
any
knots
Completion
Preventative
Expected
Occurrence
Potential
Cause
Severity
Potential
Effect(s) of
Failure
Potential
Failure Mode
Item or
Function
Analysis of Current Item of Function
Recommend
ed Action
Analysis of
Item of
Function
After
Actions
Taken
Mission Performance Predictions

Mission Performance Criteria
The first stage must fire and sustain to burnout. The StratoLogger altimeter
will initiate drogue parachute deployment at apogee and main parachute deployment
at a predetermined altitude. The vehicle should land safely on the ground and be
reusable by the standards of the NAR and must protect the onboard payloads.

Flight Profile Simulations
Frozen Fury Full Scale - Simulation results
Engine selection
[K828FJ-None]
Simulation control parameters
•
Flight resolution: 800.000000 samples/second
•
Descent resolution: 1.000000 samples/second
•
Method: Explicit Euler
•
End the simulation when the rocket reaches the ground.
Launch conditions
•
Altitude: 0.00000 Ft.
•
Relative humidity: 50.000 %
•
Temperature: 59.000 Deg. F
•
Pressure: 29.9139 In.
Wind speed model: Calm (0-2 MPH)
o
Low wind speed: 0.0000 MPH
o
High wind speed: 2.0000 MPH
Wind turbulence: Fairly constant speed (0.01)
o
Frequency: 0.010000 rad/second
•
Wind starts at altitude: 0.00000 Ft.
•
Launch guide angle: 0.000 Deg.
•
Latitude: 0.000 Degrees
Launch guide data:
•
Launch guide length: 120.0000 In.
•
Velocity at launch guide departure: 95.9518 ft/s
•
The launch guide was cleared at : 0.207 Seconds
•
User specified minimum velocity for stable flight: 43.9993 ft/s
•
Minimum velocity for stable flight reached at: 23.3844 In.
Max data values:
•
Maximum acceleration:Vertical (y): 554.032 Ft./s/sHorizontal (x): 2.940
Ft./s/sMagnitude: 554.032 Ft./s/s
•
Maximum velocity:Vertical (y): 839.3799 ft/s, Horizontal (x): 2.7217 ft/s,
Magnitude: 839.5440 ft/s
•
Maximum range from launch site: 140.85007 Ft.
•
Maximum altitude: 5250.62337 Ft.
Recovery system data
•
P: Parachute - Main Deployed at : 105.911 Seconds
•
Velocity at deployment: 49.7703 ft/s
•
Altitude at deployment: 699.94423 Ft.
•
Range at deployment: 60.14403 Ft.
•
P: Parachute - Drogue Deployed at : 16.276 Seconds
•
Velocity at deployment: 7.1662 ft/s
•
Altitude at deployment: 5250.62337 Ft.
•
Range at deployment: -140.85007 Ft.
Time data
•
Time to burnout: 2.500 Sec.
•
Time to apogee: 16.276 Sec.
•
Optimal ejection delay: 13.776 Sec.
Landing data
•
Successful landing
•
Time to landing: 130.664 Sec.
•
Range at landing: 96.69587
•
Velocity at landing: Vertical: -27.8161 ft/s , Horizontal: 1.2956 ft/s , Magnitude:
27.8463 ft/s
Simulation plot shown below:
The engine file provided by AeroTech for the K828FJ is shown below. This graph is
from ThrustCurve.org, an online, user submitted database of motor information. This
graph was done with the Rocket Altitude Simulation Program (RASP). The impulse of
the rocket has an average of 828.0 Newtons of thrust. The horizontal blue line marks
the average thrust, and the vertical blue line denotes the end of the engine burn.

Validity of Analysis, Drag Assessment, and Scale Modeling Results
Wind Speed
Model
(MPH)
Simulation Data for Various Wind Speeds
Max Altitude Range at
Velocity
(ft)
Landing
Magnitude at
Landing
(ft/s)
5250.62
130.66
27.85
5246.59
239.93
34.33
5147.87
1740.32
35.34
Calm (0-2)
Light (3-7)
Slightly
Breezy (8-14)
4988.87
Breezy (1525)

1906.16
38.38
Landing
Success
Successful
Successful
Successful
Successful
Stability Margin, CP and CG Relationship and Locations
Stability Margin: 2.74
CP: 90.86 in. from nose
CG: 74.4185 in. from nose
Distance between CP and CG: 16.4415 in.
Payload Integration

Payload Integration Plan
Our primary payload (SMD payload), estimated to weigh approximately
one and a half pounds, will be mounted on an aluminum rod centered in the
forward section of our rocket. It will be able to swivel around the vertical axis
to take pictures of the horizon during the rocket’s descent.
In the aft section of our rocket, three centering rings made out half inch
birch plywood (Outer Diameter: 6 inches, Inner diameter: 2.5 inches) will be
used to correctly mount our motor tube. The bottom two rings will also be
used to securely mount four carbon fiber fins. In the forward section, one
bulkhead also made out of half inch birch plywood will be used as a base to
mount an aluminum rod 24 in long vertically in the center of the rocket.
The secondary payload (VALOR payload) will be housed above the SMD
payload and will remain fixed in position. A small mirror will be mounted on
the outside of the rocket to reflect the field of view below the rocket to the
camera.

Installation and Removal, Interface Dimensions, and Precision Fit
See Appendix for Diagram of Payload Integration System.
Ease of integration will be insured through friction fitting components.
Each component will then be connected internally through 1” shock cording
that is attached to eye-bolts and adhesive to allow for easy assembly and
disassembly. These interfaces all fit the 5.9 in. inner diameter of the body
tubes and will be sanded for a precision fit.
The onboard electronics/payloads shall be activated by a switch that is
mounted to the outside of the rocket. Wireless transmitting of data will be
accomplished by using the Xbee pro 900 wireless transmitter/receiver. The
rocket will be loaded into the launch rail using 0.25” size launch buttons.

Compatibility of Elements
All elements will be compatible in form, fit, and function and all the
electronics will be made compatible through the programming and software
used.

Simplicity of Integration Procedure
The integration procedure is simplified through the ease of access of the
components and the simple assembly methods. The procedure will be
practiced and a complete checklist will be created to insure a safe, efficient,
and simple integration.
Launch Concerns and Operation Procedures

Draft of Final Assembly and Launch Procedures
Checklist
Recovery Equipment
● Main parachute – 72 inches
● Large deployment bag
● 3 large quick links
● Main shock cord
● Drogue parachute – 36 inches
●
●
●
●
●
Small deployment bag
2 large quick links
1 small quick link
Drogue shock cord
Recovery preparation
Altimeter Bay Equipment
● 2 Altimeters (one for redundancy)
● 2 9V batteries
● 8 washers
● 4 wing nuts
● battery holder
Motor Equipment
● Motor casing
● Motor grain
● Motor retainer
● 3 screws
● Electric Match
Launch Rail Equipment
● Extension cord (200 ft)
Launch pad
● 6 foot tube
● 2 launch rails (2 Allen bolts
already attached)
● 1 Allen bolt
● ½ inch bolt (through angle iron
and launch rail)
● 2 hex nuts (both on 2 inch bolt)
Stand
●
●
●
●
●
●
3 legs
6 wing nuts
Support angle iron
Bracket for support angle iron
2 / 2 inch bolts
2 hex nuts
Rocket stop
●
●
●
●
●
●
Glat back
2 / 2 ½ inch bolts
2 hex nuts
Blast plate
Shims
Ballast for stability

Recovery Preparation
Instructions
1.
2.
3.
4.
5.
6.
7.
8.
Folding Parachutes
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
Parachute Assembly in the Rocket
1. The appropriate side of the main shock cord is attached to the fin can. The
appropriate side of the drogue shock cord is attached to the payload bay.
2. The main bag is attached to the bottom of the altimeter bay.
3. The drogue bag is attached to the bottom of the payload bay.
4. The rocket is pushed together, slowly.
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 secured 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 appropriate side of the main shock is attached to the bottom of the altimeter
bay using a large quick link.
9. The appropriate side of the drogue shock cord is attached to the top of the
altimeter bay using a large quick link.

Motor Preparation
Motor Assembly
1. The booster section is attached to the main rocket.
2. The motor is placed into the metal casing, making sure the motor is placed fully
in its casing and the motor closure is tightened
3. The casing is inserted into the motor mount tube
4. The rocket is secured with the motor retainer and three screws
5. The red safety cap is left on until the rocket is placed on the launch pad

Igniter Installation
Igniter Installation
Ask for confirmation from the range safety officer to begin.
The red safety cap is removed and wedge cut out of it.
The igniter is slid up the motor.
The cap on the nozzle is replaced, threading the igniter through the wedge.
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.
6. The switch system is hooked up to the 12V battery.
7. The continuity of the igniter is tested at the launch rail.
8. The range safety officer is notified that preparation of the igniter is complete.
1.
2.
3.
4.
5.

1.
2.
3.
4.
Setup on Launcher
Launch Rail Assembly
One of the removable legs is attached to the stand using two (2) wing nuts.
The 6 foot tube is attached to the bottom launch rail using 2 inch bolts and hex
nuts.
The top launch rail and the bottom launch rail are slid together. The Allen bolt is
used on the 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.
5. The tube is screwed into the base, making sure that the support rail is aligned
with the leg.
6. The support beam is attached to the launch rail and secured with a hex nut.
7. The remaining two legs are attached to the base with wing nuts.
8. The support rail is secured to the leg of the stand with the brace.
9. The stand is leveled.
After rocket is assembled:
10. The rocket is placed on the rail.
11. The rocket stop is put on the rail at the appropriate height.
When complete the stand will look similar to the picture below.
Launch Procedure
1. 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.
2. 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.
3. Everyone checks for aircraft in the vicinity. After the “all clear,” begin countdown
from 10 seconds.
4. At zero, the launch button is held down for 5 seconds.
5. To assist in finding the rocket after it lands, use Rocket Hunter.

Troubleshooting
1.
2.
3.
4.
Unplug the battery/power source
Only Team Lead, Safety Officer or Advisor may approach the launch rail.
As walking towards the rail, check the extension cord.
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
Post Flight Inspection
1. Check to make sure no fires were started by the rocket and launch site, or at the
landing site.
2. Examine the area for harmful debris.
3. Ensure that the ejection charges are spent before handling.
4. Check to make sure the motor casing is still in the rocket.
Safety and Environment (Vehicle)

Team Safety Officer
Nicole F. is the Safety Officer.

Preliminary Failure Modes Analysis
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.
Battery
Wiring
High Level,
altimeters
fail, and
parachutes
never
deploy
Unsafe return
results in
damages or
injuries
10
Wiring from
the batteries
to the
altimeters
wiggle loose
over the
flight
7
Solder end
of wires, and
use bindings
to keep the
wires from
wiggling
during the
flight
Shake
test, and
addition of
hot glue
over joints
Light test
to inspect
for any
holes or
gaps
between
the
surfaces.
Motor
retainer
Motor
retainer
comes
loses
during flight
Rocket could
become
unstable
7
Unpredicted
flight path,
could crash
land
2
Ensure
plenty of
epoxy is
used on the
centering
rings to the
body.
Structural
Failure
High level,
if any of the
fins or
structure of
the rocket
fail.
Energetic
deconstruction.
10
Failure to
inspect
gluing
surfaces,
3
Supervision
of gluing
surfaces.
Pairing of
new team
members
with old
Exterior
paint
failure
Low level,
the paint
could strip
off due to
high
velocities.
1
High
velocities
over the
rocket skin,
and an
uneven coat
of paint
1
Even coats
of paint, and
consider
limiting
velocity of
rocket
Paint
Rocket
evenly,
uses of
proper
paint on
specific
materials.
Striping of paint
from the rocket.
Completion
Preventative
Expected
Occurrence
Potential Cause
Severity
Potential Effect(s)
of Failure
Potential Failure
Mode
Item or Function
Analysis of Current Item of Function
Recommended
Action
Analysis of
Item of
Function After
Actions Taken
Fins
Fins come
lose or
break off
during flight
Rocket will go
off course of
projected flight
pattern
4
Fins not
secure to
body.
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
Potential Failure Modes of the Propulsion Systems (Launch Operation)
Key:
Green – completed
Yellow – pending
Red – severe
Propulsion Risks
Propulsion Mitigations
Propellant failure would cause the delay of
the launch.
Double check prior to
launching
Motor casing failure can cause the rocket to
burn up or not reach anticipated height and
would cause a delay of the launch.
Double check the
structure of the motor
casing prior to installing
the engine in to the rocket
Double check it to be
fully installed prior to
launch and if the ignition
does burn out wait the
approved time before
approaching the rocket to
replace the igniter.
Check that the mount is
properly installed during
construction and
installation.
Make sure that the
propellant cells are of the
right size and fit properly
into the casing without
sliding on launch day
Igniter failure could cause a delay in the
launch because either the igniter burned out
or was not connected properly to the
system.
If the Motor mount fail to do its intended
job, the motor could fly out the top of the
rocket and cause the rocket to have a rapid
deconstruction mid flight
Reloadable motor rocket system failure
could stem from the propellant not fitting
properly in to the motor casing and could
fall out the back.
Status
Launch day, and launch travel provide a lot of risks, below is a table outlining some of the risks
that could be associated with those events.
Key:
Green – completed
Yellow – pending
Red – severe
Launch risks and their accompanying
consequence
Mitigations for
consequences
Traveling failure, like a flat tire would
cause the team to arrive late, thus having a
late start setting up and launching the
rocket
Launch failure would cause the rocket to
malfunction while on the pad
Plan for such events and
adjust travel plans in
advanced if possible
If the incorrect weight was calculated for
the rocket the designated height might not
be reached along with the safety margin
might not be correct
Parachute failure would cause the rocket to
fall uncontrollable towards the ground
Dual deployment failure could cause the
rocket to fall faster than desired and
potentially have a hard landing
Structural damage while traveling down to
launch site could cause a recovery failure
along with damage to the payload section
Motor/Propellant problems could cause the
rocket to fail to reach projected altitude or
be under powered
Conducting test launches
to get all of the kinks out
of the system would be
beneficial
Adequate test simulations
and rocket components
weights taken while
building
Double check that the
recovery system on
launch day and how the
parachute is folded to
make sure it will not
tangle
Double check the
altimeters on launch day
to make sure all wires are
hooked up correctly
Double check the rocket
for any damages or cracks
on launch day to ensure
that the integrity is still
there
Simulations be conducted
to make sure that the
correct engine is use and
do safety check on launch
day to insure the motor is
still useable
Status
If there was an ignition failure on launch
day it would cause the rocket to stay on the
pad after the go button was pushed
Double check that the
igniter is install properly
and that all wires are
hooked up while exiting
the launch area
Wind conditions on launch day could cause
the rocket to drift in dangerous direction
towards a group of people
Make sure that the rocket
can perform as intended
in different wind speeds
during simulations
Double check the weather
while preparing the
rocket so it can perform
its job safely under the
current conditions , If not
met scrub the attempt
If the weather is not behaving properly it
could cause a launch delay or cancellation
of the launch entirely

Safety Hazards Analysis
The following is a list of personnel hazards and data demonstrating that
safety hazards have been researched, such as material safety data sheets,
operator’s manuals, and NAR regulations, and that hazard mitigations have
been addressed and enacted.
The MSDS information for the following products we will be using. The
MSDS will not be attached to the PDR 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
Below is translated from the NAR website, under the high powered rocketry safety code,
the following information is important both for the scale test flight and full scale test
flight. Current plans do not include the use of a motor larger than an L class.
Total
Impulse
(NewtonSeconds)
0 -- 320.00
320.01 –
640.00
640.01 –
1,280.00
1,280.01 –
2,560.00
2,560.01—
5,120.00
Minimum
Diameter of
Cleared Area
(ft.)
Minimum
Personnel
Distance (ft.)
H or
small
er
I
50
100
Minimum
Personnel
Distance
(Complex
Rocket) (ft.)
200
50
100
200
J
50
100
200
K
75
200
300
L
100
300
500
Moto
r
As given by these rules, all team members were at least 100 feet away from the rocket
at launch during the scale flight, and will be at least 300 feet away during the full scale
test flight. This is a strict minimum distance. The team will use, at a minimum, three 100
foot long extension cords to run power from the ignition box to the rocket’s motor igniter.
The following list contains mitigations towards the High Powered Rocket Safety Codes
on the NAR website:
1. Certification.
Team mentors Dr. Tim Young is certified within the NAR. He will present at each
and every flight. He will also be obtaining the motors for us, as well as assisting
in their construction.
2. Materials.
We will use only lightweight materials such as paper, wood, rubber, plastic,
fiberglass, or when necessary ductile metal, for the construction of the rocket.
Our rocket will be constructed of carbon fiber tubing with carbon fiber fins. The
only metal present will be in the form of small rods, bolts, other small hardware,
motor casing and any that is in the commercially available camera.
3. Motors.
The Aerotech K828FJ motor we will use in our rocket. Proper safety will be
observed by our team in regards to the motor, supervised by Nicole F., our
Safety Officer, that handled the motor last year. Our mentor will be present
during all motor handling phases.
4. Ignition System.
Our rocket ignition systems will not be active until it has arrived at the launch site
and is adequately prepared for flight. The electric igniter provided with the motor
will be the only igniter type used.
Misfires
The NAR members present will ensure that the misfire guidelines are
followed, as well as the team leaders to ensure that all team members and
spectators in the area understand the dangers and will not approach the
rocket for any means.
5. Launch Safety.
The team will ensure all individuals present at a launch know the dangers
present and will treat each flight attempt as a “heads up flight.” Meaning that,
during the countdown and flight, someone will direct everyone to keep an eye on
the rocket, and be alert for its descent back to the frozen fields of North Dakota.
A 10 second count down will be used.
6. Launcher.
Our rocket will be launched vertically, and we will take necessary precautions if
wind speed will affect our launch. We have a steel blast shield to protect the
ground from rocket exhaust. If dry grass is present around our launch pad, it will
be sufficiently cleared. The rail is long enough, and has been simulated, to
ensure the rocket reaches stable flight before exiting.
7. Size.
The motor we will use has a thrust of 193.983 pound-force, and an impulse of
484.957 pound-force-sec. The overall size of our motor is 2.12598 inches in
diameter, and 22.7953 inches in length.
8. Flight Safety.
Tim Y. has details on our FAA altitude clearance. We will refrain from launching
in high winds or cloudy conditions. There remains many flight paths around
Grand Forks due to the UND being a large aviation school. A Waiver and/or
NOTAM will be submitted prior to flight to ensure all aviation matters are directed
away from our area.
9. Launch Site.
Our launch site is of an adequate size for our planned altitude.
10. Launcher Location.
Our launch site is 10 miles North of Fargo, ND. This location provides an
adequate amount of space to satisfy minimum distance requirements. The
agricultural area provides miles of flat, baron land.
11. Recovery System.
We will use a 36 inch parachute for drogue, and a 72 inch with a 12 inch spill
hole main parachute in order to ensure rocket recovery. The main parachute and
drogue parachute will both be placed in flame-retardant Nomex bags.
12. Recovery Safety.
Power lines are scarce in the vicinity of our launch site, but we will refrain from
recovering it should it happen to land in a dangerous location such as up a tree
or tangled in power lines. If such an event happens, the local power company will
be notified.

Environmental Concerns
Environmental concerns and their
explanations.
Mitigations
Dissolution of rocket fuel into open
water causes contamination of water
source.
Careful planning of
launch locations and
recovery area.
Fume inhalation of hazardous fumes
due to proximity to rocket.
Observe proper
distances for
spectators and keep
minimum crew around
rocket.
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.
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.
Status
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.
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.
IV) Payload Criteria
Testing and Design of Payload Experiment

System Level Design Review
Our sensor system is based off of the Arduino Mega 2560. We chose the
use this platform because it allows us to easily control data flow and storage
from sensors. The design specification and reference schematic for this
controller platform are listed below.
Design Specifications:
 Microcontroller
 Operating Voltage
 Input Voltage (recommended)
 Input Voltage (limits)
 Digital I/O Pins
 Analog Input Pins
 DC Current per I/O Pin
 DC Current for 3.3V Pin

Flash Memory



SRAM
EEPROM
Clock Speed
ATmega2560
5V
7-12V
6-20V
54 (of which 14 provide PWM output)
16
40 mA
50 mA
256 KB of which 8 KB used by
bootloader
8 KB
4 KB
16 MHz
As the sensors and data logger are integrated and controlled using this
system all of the specifications of the sensors and logger must fall under
these system requirements. We chose our sensors based off of these system
requirements. Each of the sensors input and output parameters are listed
below. All of the information was acquired from the sensors respective data
sheets.
The electrical and general items chart shows that the Arduino will have to
provide a source voltage of about 3.3 volts and communicate via the two wire
digital interface. The wiring configuration is displayed under electrical and
general items and the serial communication will be initiated and transferred
over the data and SCK lines. This sensor was chosen because it readily
interfaces with the Arduino while providing both temperature and humidity
sensing capabilities. It is also provides very precise readings for the cost of
the sensor.
BMP085 Pressure Sensor:
The system requirements of this sensor are shown in the Electrical
characteristics chart below. The recommended supply voltage is listed to be 2.5 volts,
as the Arduino does not output this voltage we purchased a breakout board that uses a
simple voltage divider. This voltage divider is designed over the SDA and SCL I 2C data
lines as shown below. This sensor was chosen because it easily integrates with the
Arduino and is also fairly accurate for the cost of the sensor.
TSL235R Light to Frequency Converter:
According to the Operating conditions below this sensor easily interfaces with the
Arduino. The output is determined by analyzing the frequency of the sensor. Under the
Operating condition table the one feasible schematic for the control of the sensor is
shown.
UV Photodiodes JEC 0.3 A
This photodiode is very easy to implement and it will create a voltage difference.
This will be powered using the 3.3 voltage supply on the Arduino and referencing it to
ground. This sensor was chosen because it is a cheap alternative to the vast majority
of UV sensors that are out of our budget but can still provide an accurate reading.
VALOR Payload – GoPro Hero3 and IMU
The payload will consist of an IMU which is TBD. It will record the rockets
acceleration and rotation as it ascends and will stamp this information on each frame of
video recorded by the video camera. The pixels will later be analyzed to locate
predetermined targets.
Schematic
PCB Prototype
The light and imaging module will consist of a separate PCB, connected to the main
PCB with wires which will allow the module to spin freely. The UV Photodiode will be
wired as follows:
UV Photodiode

System-Level Functional Requirements
The design at a system level is very straight forward. The power
requirements must be met and the components must be compatible with the
controller. The Arduino microcontroller makes this very simple with its pin
configuration that includes digital, analog, and serial communications, as well
as many features that we will not be using. The schematics have been
discussed in the system level design section and all of these configurations
have been verified to be operational except for the UV sensor, which we
believe will just require one analog pin to be functional. The power
requirements of the system has been discussed in the integrity of the design
section above and the system will be functional for a long duration of time
given the low power requirements.

Approach to Workmanship
To avoid difficulties with our payload circuit becoming damaged because
of wires become unsoldered, we would like to have a PCB printed for our
boards. The image below is the preliminary design and schematic for the
board that will be directly above the Arduino unit. This does not include the
Light and imaging module board, as this will be separate.

Component Testing, Functional Testing, or Static Testing
Component testing is pending. Testing will consist of various computer
testing of electrical components as well as tests in actual and simulated flight
environments. To verify the operation of our payload we will connect each
sensor one by one using a bread board and run a quick program for each to
test the function of each sensor, the microcontroller, and the data logger. We
will set up an experiment for each sensor accordingly. We will verify the
function by reading the SD card to see if any data was recorded correctly.
The microcontroller has built in TX and RX LEDs that will flash when a
program is being uploaded which will verify that operation. Once we test
each individually we will construct the entire payload on a bread board and
run a full test of the entire system to make sure all the sensors work and that
our program is functioning properly and our data logger is logging data.
The status of our verification is not yet complete. We are still in this
process of testing the sensors. We have already tested the data logger and it
is functioning fine. Once the payload is completely assembled we will start
our formal testing. We will conduct bench testing in which the readings of
temperature, humidity, and pressure will be compared with the reading of
other accurate devices. The temperature reading will be compared with any
standard mercury thermometer, the humidity will be compared using a
hygrometer available in the physics department, and the pressure reading will
be compared with the calculated air pressure at our given altitude. To test the
irradiance and UV reading, we will take measurements at different intensities
of light outdoors and compare them with expected values. Operation of the G
switch will initially be tested by shaking the payload. The total current
consumption will also be measured using a multi-meter. Once this is
complete we will implement the payload in the full scale test launch and
analyze the results.

Manufacturing and Assembly Status and Plans
Manufacturing and assembly of the payload is pending. This will follow
the successful testing of each electrical component. The payload bay is
planned to be constructed separate from the rest of the vehicle and will be
integrated with it upon completion. The payload is currently being tested
through hardware implementation on breadboards. Once the programming is
complete the sensors will be soldered and wired directly onto the controller
board. Temperature sensors will be placed clear of heat inducing
components and light sensing components will be placed in a position that
allows for easy measurement of light. The parts for the payload housing will
then be constructed and attached to the payload.

Integration Plan
The arduino ATmega2560 will be the base of our design. Everything else
will be built off of this board. The data logger shield was designed to plug into
the arduino duemilanove thus we will not be able to plug it directly into the
ATmega so we will be using a separate development board for this. The
development board will allow us the freedom to play with the configuration
and construct any circuit as necessary.
Our integration plan has been developed based off of the success criteria
of the payload. The most difficult requirement of the payload to meet is to
maintain an orientation that will give the optimal readings on the sensors and
a camera position that has the horizon in the bottom of the frame. This
requires that the payload and the camera used be able to rotate freely inside
the rocket while at the same time having the ability to freely receive all of the
physical parameters that affect the sensors and the camera. To achieve this
we have decided to mount the payload on a central vertical axle inside the fin
can section of the rocket, around which a clear material will be used to
construct the body of the rocket.
This axle with be firmly attached to a large bulkhead above the engine
section of the rocket. The top of this axle will not be attached using a
bulkhead but instead secured using a thin rod that runs horizontally through
the cross section of the rocket. To seal the top of the fin can off from the rest
of the rocket we have designed a two piece bulkhead that will create a seal
during flight and be removed upon the ejection of the drogue parachute. This
bulkhead will consist of two layers. The bottom layer will be a tapered ring
with a radius of outer – inner equal to approximately 1.5 cm and will be firmly
secured to the outer shell of the rocket just as a normal bulkhead would be.
The top layer will be a solid cylinder with a tapered wall as well. This part of
the tapered bulk head will also have a rubber gasket encompassing the
circumference as to insure a snug fit with the bottom portion of the bulkhead.
When the parachute is inserted into its bay it will push against the top layer
and the two layers will compress. This will effectively shield the payload and
camera from the high pressure required to eject the parachute. This,
however, creates a problem with the design of the shock cord. To work
around this we decided to attach four strings from lower bulkhead through
upper bulkhead to central point that is washer like. At the center of the washer
an eyebolt will be mechanically fastened with nuts on top and bottom of
washer. Also, the nuts will be glued to insure it won’t go anywhere. The shock
cord will then be tied to this eyebolt fastened to our parachute and then back
up to another eyebolt positioned in the opposing side of our rocket. This will
allow it to discharge with the top half of the rocket upon parachute
deployment. As this bulkhead removes it will expose the sensors to all of the
external physical properties of the surrounding environment, allowing for
accurate readings.
The payload and camera will be secured to this axle using three fitted
bearings. One large bearing will be secured onto the axle in a position Z that
is vertically required by the dimensions of the payload and the camera. This
bearing will allow for free rotation around the axle, or in the plane
perpendicular to the rocket. Two more, but smaller, bearings will be fitted
onto this bearing on opposing sides. This will allow for rotation in the vertical
plane of the rocket. The payload and camera will be attached to these
bearings and each weighted separately at the bottom. The camera can be
weighted on the bottom using the weight of the batteries needed, either one
or two nine volt batteries, and the camera will be weighted by bolting a mass
to the built in tri-pod mount. This means that if axle were place on a z axis of
a Cartesian coordinate system the camera would be pointing in the xy plane
at any angle and the light dependent sensors would be pointing in the positive
z direction. This setup will, in almost all cases, provide a field of view to the
camera in which the horizon is always in the bottom and allow the sensors to
read what is approximately the external readings of the surrounding
environment.
The video camera and IMU for the VALOR payload will be mounted closer
to the nose-cone/body tube interface and be connected with the Arduino. A
small mirror will be mounted to reflect the image of the field of view below the
rocket to the camera for recording.

Instrumentation Precision and Repeatability of Measurements
Many components are factory calibrated and others will be calibrated
following the specific instructions for each sensor. All electronics will be tested
multiple times and compared to known values in order to insure precision and
repeatability of measurements.
SHT15 Temperature and Humidity Sensor:
The electrical and general items chart shows that the Arduino will have to provide
a source voltage of about 3.3 volts and communicate via the two wire digital interface.
The wiring configuration is displayed under electrical and general items and the serial
communication will be initiated and transferred over the data and SCK lines. This
sensor was chosen because it readily interfaces with the Arduino while providing both
temperature and humidity sensing capabilities. It is also provides very precise readings
for the cost of the sensor.
The performance characteristics for this sensor are shown in the two tables
below. To verify the operation we will first integrate the sensor using a breadboard and
evaluate the readings. After the sensor is determined to be functional we will be using
the below characteristic chart to assess the precision and accuracy.
BMP085 Pressure Sensor:
The system requirements of this sensor are shown in the Electrical
characteristics chart below. The recommended supply voltage is listed to be 2.5 volts,
as the Arduino does not output this voltage we purchased a breakout board that uses a
simple voltage divider. This voltage divider is designed over the SDA and SCL I 2C data
lines as shown below. This sensor was chosen because it easily integrates with the
Arduino and is also fairly accurate for the cost of the sensor.
Electrical Characteristics
TSL235R Light to Frequency Converter:
According to the Operating conditions below this sensor easily interfaces with the
Arduino. The output is determined by analyzing the frequency of the sensor. Under the
Operating condition table the one feasible schematic for the control of the sensor is
shown.
UV Photodiodes JEC 0.3 A
This photodiode is very easy to implement and it will create a voltage difference.
This will be powered using the 3.3 voltage supply on the Arduino and referencing it to
ground. This sensor was chosen because it is a cheap alternative to the vast majority
of UV sensors that are out of our budget but can still provide an accurate reading.

Payload Electronics and Transmitters
See Appendix for Payload Schematic.
Transmitters: Our GPS module consists only of a GPS unit, the one we have selected is
the Copernicus II. This module will use a U.FL antenna on the exterior of our rocket.
This unit will be connected to the Arduino via serial. The transmission module is
composed of an Xbee 900 Pro. This is also a serial device, and we are still working on a
way to shield the altimeters in our rocket from the 900 MHz signal. This unit will be
complimented by a second Arduino unit on the ground with an Xbee pro, plugged into a
laptop. The Xbee uses a U.FL antenna that will be mounted on the exterior of the
rocket.
BMP085 Pressure Sensor:
The system requirements of this sensor are shown in the Electrical
characteristics chart below. The recommended supply voltage is listed to be 2.5 volts,
as the Arduino does not output this voltage we purchased a breakout board that uses a
simple voltage divider. This voltage divider is designed over the SDA and SCL I 2C data
lines as shown below. This sensor was chosen because it easily integrates with the
Arduino and is also fairly accurate for the cost of the sensor.
TSL235R Light to Frequency Converter:
According to the Operating conditions below this sensor easily interfaces with the
Arduino. The output is determined by analyzing the frequency of the sensor. Under the
Operating condition table the one feasible schematic for the control of the sensor is
shown.
UV Photodiodes JEC 0.3 A
This photodiode is very easy to implement and it will create a voltage difference.
This will be powered using the 3.3 voltage supply on the Arduino and referencing it to
ground. This sensor was chosen because it is a cheap alternative to the vast majority
of UV sensors that are out of our budget but can still provide an accurate reading.
VALOR Payload – GoPro Hero3 and IMU
The payload will consist of an IMU which is TBD. It will record the rockets
acceleration and rotation as it ascends and will stamp this information on each frame of
video recorded by the video camera. The pixels will later be analyzed to locate
predetermined targets.
The payload has not been altered much since the PDR, but it is still very much still in a
planning phase. It still consists of multiple modules plus the VALOR payload. These
modules are power and control, atmosphere, light and imaging, GPS and transmission,
data storage and IMU.
The power and control module consists of the battery pack, and the Arduino MEGA
2650. This board was chosen due to its large number of hardware serial ports, which is
ideal for applications like data storage, GPS and transmission/receiving. This module
also contains a secondary voltage regulator to supply our 3.3v modules which require
more current than the Arduino can supply though its regulator.
The atmosphere module consists of temperature, pressure and humidity sensors. We
have chosen to use factory calibrated sensors for this entire module, as testing and
calibrating accurately is difficult. All of these devices will be on the I2C bus.
In the light and imaging module, we have 3 devices. These are a small serial JPEG
camera, a UV photodiode and a light to frequency converter. The UV photodiode and
light to frequency converter are both analog devices and will need to be calibrated by
us. This module will be mounted in a clear plastic section of our rocket which will be
weighted and allowed to spin as the rocket changes orientations. We hope this will
provide the best circumstances for our light sensors to collect their data.
For data logging we are using a simple serial data logger, but we are not yet sure if this
will allow us to store our photos as well. The data logger will simply store everything on
a SD card.
IMU is a module for keeping a log of the rockets orientation through its flight, this data
will be paired with the video we capture with our VALOR payload to complete that
payloads objectives.

Safety and Failure Analysis
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.
Batteries
Electronics
fail to work
No data is
collected
Transmitters
Not able to
pick up
signal
No data is
collected
Camera
Fails to
take
pictures
Sensors
Fails to
collect data
No data is
collected
No data is
collected
4
Used a
weak or
dead battery
3
6
Weak signal
2
6
Poor wiring,
bad
batteries,
bad
programming
2
Not placed
in ideal
location
3
2
Check
charge of
battery
before use
Test
strength of
transmitters
Testing of
camera
before and
after
integration
to rocket
Test
sensors
after
installation
Carry spare
batteries
Test at
varying
distances.
Check all
connections
of camera to
power
source
Ensure
payload
team and
construction
is
collaborating
Completion
Preventative
Expected
Occurrence
Potential
Cause
Severity
Potential
Effect(s) of
Failure
Potential
Failure Mode
Item or
Function
Analysis of Current Item of Function
Recommend
ed Action
Analysis of
Item of
Function After
Actions Taken
Payload Concept Features and Definition

Creativity and Originality
We have decided to build the payload based upon an Arduino controller
board. As this board is an open source prototyping platform a multitude of
projects have already been completed and documented using this board. As
our team does not a background in embedded systems development this will
make the design and development of the payload more feasible through
making the research much easier. With this board we will be using sensors of
different output forms and an open source data logging structure on a small
SD card. The creativity and originality of this project lies in its uniqueness as
this project has not yet built nor documented using this platform. All of our
hardware organization will be unique to this project as will our code that will
be developed by the team.
Our team has decided to design and fly a small secondary payload
(VALOR payload) to verify an innovative concept. We will aim to develop a
payload that is capable of visually locating specific targets within its field of
view and relaying back the distance and direction the target is from the launch
site. As the rocket ascends, the camera will capture the image of several
easily distinguishable fluorescent-colored flags placed at varying distanced
from the launch pad. Original computer programs will be written to locate
these colored flags in the images as well as stamp them with the information
gathered from the altimeter and IMU.

Uniqueness or Significance
In this project we aim to develop a hardware structure that is most suitable
for this project’s given requirements. This typical sensor environment has not
yet been implemented on an Arduino platform. We will be documenting all of
the steps that we take to build this payload and add to the vast amount of
documentation available on the open source Arduino platform. Although we
will be using this documentation to learn how to log data and read individual
sensor values we will have to configure the device into an operable payload
using the knowledge we have acquired from research. This unique project is
significant for a couple of reasons. One, it will take a large amount of
research from the team, adding to our amount of knowledge on hardware
organization and coding. Second, it will add to the amount of documentation
available on the Arduino, providing aid in the design of future sensor
environments.
The VALOR payload is significant in that the rocket can provide a wider
view of the surrounding environment and relay back important information.
53
This could be a useful safety tool in a scenario where a lost astronaut could
obtain a birds-eye view of the landscape and be able to locate rovers,
habitats, or other astronauts. Visual observation on Earth often relies on
using fixed or rotary winged aircraft to maneuver through the atmosphere.
However, on the lunar or Martian surface, where there is little or no
atmosphere to generate lift, the application of rocket technology could be
valuable.

Suitable Level of Challenge
Diving into this project, this team has very little experience with hardware
organization and software development. By the end of this design the
members of the team involved with the payload will have to exercise both of
the skills fluently. As our design is completely unique we will have to conduct
research and perform tests. Throughout this process we will have to focus on
the many different aspects of design efficiency. This constitutes developing a
payload that is small, light, and consumes very little power. These variables
will be depending on our ability to design and code. With our limited
background using these technologies, researching and integrating these
technologies will prove to be a difficult task. Also, integrating an IMU with a
video feed can prove difficult as these measurements will be used to
determine the direction and distance from the launch site while accounting for
any pitch, roll, or yaw changes in the flight of the rocket.
Scientific Value

Payload Objectives
The objective of the SMD payload is to design a sensing environment that
logs readings from five different sensors and a camera. The payload will also
be situated through a means that allows it to always rotate to a position that
will orient the horizon in the bottom of the frame and the radiation sensors
towards the sky. If time allows we hope to integrate remote transmission of
the sensor values to a computer into the payload.
The objective of the VALOR payload is to visually locate predetermined
targets within its field of view and relaying back the distance and direction the
target is from the launch site.
54

Payload Success Criteria
Our payload will be successful if it meets the requirements defined by the
NASA SMD criteria an additional criteria for the secondary payload. These
criteria are listed as follows:






The payload shall gather data for studying the atmosphere during descent
and after landing. Measurements shall include pressure, temperature,
relative humidity, solar irradiance and ultraviolet radiation. Measurements
shall be made at least every 5 seconds during descent and every 60
seconds after landing. Surface data collection operations will terminate 10
minutes after landing.
The VALOR payload should record and integrate the necessary
information from the video camera, altimeter, and IMU.
The payload shall take at least 2 pictures during descent and three after
landing.
The payload shall remain in an orientation during descent and after
landing such that the pictures taken portray the sky towards the top of the
frame and the ground towards the bottom of the frame.
The data from the payload shall be stored onboard and transmitted to the
team’s ground station after the completion of surface operations.
Experimental Logic, Approach, and Method of Investigation
Our method of investigation will be simulation. We will simulate our
operating environment as close as possible. This will include our temperature,
light, humidity, ect. Through our investigation we will consider extreme
situations within our projected operating environment and observe how the
system reacts. If our investigation leads to any problems that we see might
occur or do occur we will make any and all adjustments to our design to solve
the problem. The success of our payload also relies on the mechanical
properties of the rocket. If the rocket does not separate and expose our
sensors, the system will not log the correct data for that environment, which
will ultimately lead to a failure in terms of our objectives. We will test this
portion by conducting test flights and though simulation of drogue and main
shout deployment in the lab. This stage of development is a crucial step in our
overall design. It is here where we will be able to foresee any problems and
make corrections. Without experimental logic, the success of our final design
would be a shot in the dark.
55

Tests, Measurements, Variables, and Controls
Our test and measurements will be done mostly on computers. We will be
testing our circuit variables with multi-meters. The only way to really test and
measure our system is by simulating the operating environment and using the
data gathered by the data logger to see how close our measurements are to
the environment. In this part we will have to ensure that the sensors are
calibrated correctly by cross referencing them with expected values provided
on the data sheets

Data Relevance and Accuracy/Error Analysis
The data relevance and accuracy/error analysis will be done once
preliminary testing of the payload has commenced. We will be performing
small tests for each sensor but most of our accuracy/error analysis and
expected data will come from the data sheets for each sensor. All of the
relevant tests have already been performed on the sensors by the
manufacturer and those results are provided in the data sheets. These data
sheets will be our base from which we will base our results upon.

Experiment Process Procedures
Preliminary experiment process procedures will follow initial testing an
accuracy/error analysis. Our experiments are to be conducted in the lab on a
bread board. The bread board is a useful tool that we are using to help
develop our circuits. By coupling a few together, we get a large area from
which to work off of. We will first construct individual circuits for each sensor
and perform any test needed to verify its functioning as expected. Once we
have tested individual sensors, and they all perform well, we will construct a
full mock up of the payload. Next we will perform any tests needed to verify its
performance as a whole. The payload will also be tested in prelaunch flights.
Safety and Environment (Payload)

Safety Officer
Nicole F. is the Safety Officer.

Preliminary Failure Modes Analysis
The following is a table of analyzing any of the failure modes of the
proposed design payload integration
56
Note: The following scale for Severity and Expected Occurrence is from 1-10,
with 1 being very low, and 10 being extremely high.
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.
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.
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 1550% 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.
payload
would not
operate
properly
during the
period of
time that
the bridge
exists
power
event
power loss
due to a
break made
between
the power
source (the
batteries)
and the
circuitry
payload
could be
damaged
payload
would fail
to operate
7
bridge may
be created
between
wires from
used in
payload
10
Wiring
from the
batteries to
the wiggle
loose over
the flight
57
5
5
wires that
are added
external to
the circuit
board will
have very
little
exposed
metal and
will be cut
short so
they are
fastened
snugly
batteries
will be
very firmly
attached
Shake
test, and
addition
of hot
glue
over
joints
Completion
Preventative
Expected Occurrence
Potential Cause
Severity
Potential Effect(s) of
Failure
Potential Failure
Mode
Item or Function
bridge
may be
created
between
wires used
to build
the
payload
Recommended Action
Analysis of Item
of Function After
Actions Taken
Analysis of Current Item of Function

Safety Hazards Analysis
Listing of personnel hazards and data demonstrating that safety
hazards have been researched, such as material safety data sheets,
operator’s manuals, and NAR regulations, and that hazard mitigations
have been addressed and enacted.
The listing of personal hazards has been researched above, which
include a listing of MSDS sheets and NAR regulations.
The payload proposed presents no safety hazards. The power
levels that are being worked with are not hazardous

Environmental Concerns
Our main environmental concern for the payload is if the rocket
were to explode or crash. This could potential cause the batteries in
the payload to be broken and exposed to the environment. This would
cause an exposure to chemical waste, such as: lead mercury, and
cadmium. Although it would be a rather small amount, these materials
are considered toxic metal pollution. Besides the batteries, the payload
is environmentally friendly. Also in the case the rocket was to explode
or crash, the payload would be destroyed into a plethora of small
pieces. It is important that we gather all pieces of rocket and payload to
not leave any of the remains. This could cause danger to any small
animals if swallowed.
V) Project Plan
Schedule and Status of Activities

Budget Plan
The following is our budget for the year. Several items such as the
parachute can likely be recycled from previous rockets, so the total
cost may be less than projected, or more if there are repairs that need
to be made. Regardless, we plan on monitoring our budgets and
evaluating it every month. The majority of our expenses will be for the
58
travel and lodging to and from Huntsville.
EXPENSES
Travel / Gas
Van
QUANTITY
1
PRICE PER UNIT
$2,600.00
Sub Cost
COST
$2,600.00
$2,600.00
Lodging
April 15, 2013 - Kansas City, MO
7
$85.00
$595.00
April 16, 2013 - Huntsville, AL
7
$84.00
$588.00
April 17, 2013 - Huntsville, AL
April 18, 2013 - Huntsville, AL
7
$84.00
$588.00
7
$84.00
$588.00
April 19, 2013 - Huntsville, AL
7
$84.00
$588.00
April 20, 2013 - Huntsville, AL
7
$84.00
$588.00
April 21, 2013 - Kansas City, MO
7
$85.00
$588.00
Sub Cost
$4,123.00
Rocket Supplies
Air Tube
2
$142.00
$284.00
Centering Ring
3
$7.00
$21.00
Motor Mount Tube
1
$14.00
$14.00
Nose Cone
1
$49.45
$49.45
Stiffy Tube
2
$9.95
$19.90
Tube Coupler
2
$8.25
$16.50
Parachute 96"
1
$89.95
$89.95
Drogue 36"
1
$20.95
$20.95
1000 Series Rail Beads
2
$2.65
$5.30
Shockcord (per yard)
6
$1.10
$6.60
Casing
1
$450
$450
Motor
5
$190.00
$950.00
Rocket Kit
2
$120.00
$240.00
PerfectFlite
2
$99.95
$199.90
Sub Cost
$2,367.55
Misc. Supplies
1/4" by 6' Plywood
1
$15.00
$15.00
1/8" by 6' Plywood
1
$15.00
$15.00
Nuts
20
$0.25
$5.00
Washers
20
$0.25
$5.00
Eye Bolts
4
$1.50
$6.00
59
Xacto Knife
1
$1.97
$1.97
Batteries
6
$5.00
$30.00
Paint
1
$62.00
$62.00
Sub Total
$139.70
Payload Supplies
Arduino Mega 2560
1
$58.95
$58.95
Mego Protoshield for Arduino
1
$14.95
$14.95
D2523T Helical GPS Reciever
1
$79.95
$79.95
Copernicus II DIP Module
1
$74.95
$74.95
Xbee Pro 900 Wire antenna
2
$42.95
$85.90
Xbee Pro 900 U.FL Connection
2
$42.95
$85.90
LinkSprite JPEG Color Camera
TTL Interface
1
$49.95
$49.95
Open Log
1
$24.95
$24.95
Humidity and Temp. Sensor SHT15 Break out
1
$49.95
$49.95
Barometric Pressure Sensor
1
$19.95
$19.95
TEMT6000 Breakout Board
1
$4.95
$4.95
Mini Photocell
Light to Frequency Converter TSL235R
1
$1.50
$1.50
1
$2.95
$2.95
UV Photodiodes JEC 0.3 A
1
Rosco Permacolor Glass UV Pass
Woods-type Filter - 2x2"
1
$9.00
$9.00
Polymer Lithium Ion Battery 6Ah
1
$39.95
$39.95
CamOne Infinity w/ gps module
1
$199.00
CamOne GPS Module
1
$50.00
$199.00
$50.00
n/a
n/a
$852.75
Sub Cost
Other Expenses
T-shirts
15
$10.00
Sub Cost
$150.00
$150.00
$10,233.0
0
Total Cost
60

Funding Plan
Thus far, our fundraising efforts have included:
Requesting funds from various departments - We expect to receive
about $300.00 from the Physics, Mathematics, and Engineering
Departments.
North Dakota Space Grant Consortium - Over the past years, we
have received funding from the Space Grant. We anticipated for the
funding to continue this year, which will cover 100% of our traveling
and lodging expenses.
ATK Armament Systems Division – Agreed to fund our material
costs for the project.

Timeline
In order for us to be successful, we need to make sure that we are
balancing the time for outreaches with the construction and launching
of the rockets. Within the next few months, it is very important that we
accomplish all the tasks that we have set. With time management and
delegation, we should be able to accomplish everything. To note, the
largest amount of time set aside is for the construction of the full-scale
rocket. This is factored around semester breaks. It is critical that we
are able to complete this in a timely manner since we will need to allow
ourselves plenty of time for launches since the weather in North
Dakota is not always cooperative. As we move forward we will add
tasks and evaluate the schedule as needed.
61
This is a screen shot of the GANTT chart that we are using.
Note: Because of the unsuccessful flight of our subscale rocket, we had to add
two new tasks regarding the construction and launching. Those new tasks are 14
and 15.
#
Task
Assigned
1
Request for Proposal
Advisor
100%
1 day
8/1/2012
8/1/2012
2
Submit Proposal to NASA
All Members
100%
5 days
8/27/2012
8/31/2012
3
Notice of Selection
100%
1 day
9/27/2012
9/27/2012
Team Lead
100%
1 day
10/4/2012
10/4/2012
Website Team
100%
13 days
10/4/2012
10/22/201
2
Team Lead
100%
1 day
10/4/2012
10/4/2012
All Teams
100%
7 days
10/18/201
2
10/26/201
2
4
USLI team teleconference
w/ NASA
5
Have web page completed
6
Reorganization of Team
Members
Completion
Time
Start Date
End Date
7
Assign Tasks for the PDR
8
Complete PDR report and
post on website
Team Lead &
Website
100%
1 day
10/29/201
2
10/29/201
2
9
Construction of Sub-scale
rocket
Design /
Construction
100%
16 days
11/1/2012
11/22/201
2
All Teams
100%
8 days
11/7/2012
11/16/201
2
1
0
PDR Presentation
62
1
1
Physics Day
Outreach
Team
100%
1 day
11/12/201
2
11/12/201
2
1
2
Outreach to Middle School
in Grand Forks
Outreach team
pending
16 days
11/15/201
2
12/6/2012
1
3
Begin Construction of
Payload
Payload Team
10%
3 month
11/16/201
2
2/15/2012
100%
16 days
11/23/201
2
12/14/201
2
10%
20 days
1/1/2013
1/20/2013
10 days
1/21/2013
1/31/2013
10 days
12/3/2012
12/14/201
2
12 days
12/26/201
2
1/10/2013
31 days
1/10/2013
2/21/2013
1 day
1/14/2013
1/14/2013
All Teams
7 days
1/23/2013
1/31/2013
All Members
11 days
2/22/2013
3/8/2013
All Teams
11 days
2/28/2013
3/14/2013
All Members
19 days
3/18/2013
4/11/2013
Team Lead &
Website
1 day
3/18/2013
3/18/2013
FRR presentation
All Teams
8 days
3/25/2013
4/3/2013
Travel to Huntsville, AL
All members
2 days
4/15/2013
4/16/2013
1 day
4/17/2013
4/17/2013
1 day
4/22/2013
4/22/2013
2 days
4/21/2013
4/22/2013
1
4
1
5
Launch dates of subscale
Rebuild Sub-scale rocket
All Members
1
6
Launch 2nd Sub-scale
rocket
1
7
Work on Construction of
full-scale
1
8
Assign Tasks for CDR
report
1
9
Continue construction of
full-scale rocket
Design /
Construction
2
0
Submit CDR report and
post on website
Team Lead &
Website
2
1
2
2
CDR presentations
Tentative launch dates of
Full-scale rocket
2
3
Assign tasks of FRR
2
4
Second Launch of fullscale
2
5
Submit FRR and post on
Website
2
6
2
7
2
8
2
9
3
0
3
1
Team Lead meeting, and
LRR
Travel to Grand Forks, ND
All Members
Design /
Construction
All Teams
Team Lead,
Advisor
All members
Launch Dates
100%
100%
Assign Tasks of PLAR
All Teams
6 days
4/25/2013
5/2/2013
3
2
Submit PLAR and post on
website
Team Lead &
Website
1 day
5/6/2013
5/6/2013
3
3
Winning USLI team
announced
1 day
5/18/2013
5/18/2013
63

Educational Engagement Plan and Status
In the next few months, we plan on having at least two educational
outreach activities. This includes:
Physics Day at UND - November 12, 2012
This is a program for local middle school to high school students to
learn about the many different facets of physics.
○ We gave a presentation about rocketry.
○ Introduced them to the USLI program and share our past history
with the competition.
○ Displayed rockets from the previous years.
○ Have a Q & A session
○ Reach about 180 students and faculty.
Outreach at Grand Forks Area middle school
Our team is in the process of scheduling a date to visit the local
middle schools.
○ For an entire day, we will teach a science class.
○ Give a brief lecture about rocketry
○ Prior to us visiting, we will have the students design rockets out of 2
liter pop bottles.
○ We will supervise and moderate the launch water rockets
○ Have a Q & A session on why some rockets did work and other did
not.
○ Expect to reach about 30-80 students.
64
Other educational plans include:
○ Colloquiums to the University on rocketry and other space related
topics
○ Inviting the community to view our launches.
○ Guest lectures in different classes.
VI) Conclusion
The Frozen Fury Team and members of the community have shown a
renewed interest in the USLI competition with the construction and launch of subscale rockets. The team has been extremely involved in meetings, educational
outreach, and has shown dedication to working on the project even during winter
break.
The Frozen Fury team has begun testing some payload components,
accomplished milestone goals, and has successfully gained community
involvement and support for the project. Although the first sub-scale flight failed,
the team has learned and practiced important manufacturing and assembly
techniques that will allow for more efficient operations in the future. We look
forward to the NASA Teleconferences and CDR Presentation!
65
VII) Appendix
Pro-E Launch Rail Schematic:
66
Diagram of Payload Integration System:
67
Payload Schematic:
68