NASA USLI
Critical Design Review
Atomic Aggies
Critical Design Review
Submitted by: New Mexico State University Rocket Team
January 14, 2013
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Table of Contents
I) Summary of CDR report ............................................................................................................... 3
Team Summary ........................................................................................................................... 3
Launch Vehicle Summary ............................................................................................................ 3
Payload Summary........................................................................................................................ 3
II) Changes made since PDR ............................................................................................................ 4
Changes Made to Vehicle Criteria ............................................................................................... 4
Made to Payload Criteria ............................................................................................................ 4
III) Vehicle Criteria........................................................................................................................... 5
Design, and Verification of Launch Vehicle ................................................................................. 5
Subscale Flight Results .............................................................................................................. 12
Recovery Subsystem ................................................................................................................. 12
Mission Performance Predictions ............................................................................................. 16
Payload Integration ................................................................................................................... 18
Launch Concerns and Operation Procedures........................................................................... 19
Safety and Environment ............................................................................................................ 21
IV) Payload Criteria ....................................................................................................................... 23
Testing and Design of Payload Experiment ............................................................................... 23
Payload Concept Features and Definition................................................................................. 31
Science Value............................................................................................................................. 31
Safety and Environment of Payload .......................................................................................... 32
V) Project Plan ............................................................................................................................... 33
Budget ....................................................................................................................................... 33
Funding ...................................................................................................................................... 35
Timeline ..................................................................................................................................... 36
Educational Engagement........................................................................................................... 37
VI) Conclusion ............................................................................................................................... 38
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I) Summary of CDR report
Team Summary
Atomic Aggies
1060 Frenger Mall
Las Cruces, New Mexico 88003
Mentor: John Demar, TRA Level III, #10273
Launch Vehicle Summary
Payload Summary
Payload Title: Scientific Environment Measurements Payload
The payload will incorporate sensors that will be used to measure solar irradiance, ultraviolet
radiation, atmospheric pressure, temperature, and humidity once apogee is reached by our
rocket. The payload bay will contain one camera taking video throughout the duration of the
flight, where still shots will be obtained of the horizon. The payload will include a GPS unit to
provide spatial data and to provide a tracking unit to aid in vehicle recovery. A DE0- Nano FPGA
Development and Education Board will be used to control data collection operations and
provide data logging. Data will be sampled and stored at a frequency of 1Hz starting at apogee
until ten minutes after landing. The data will be transmitted wirelessly from the vehicle to a
ground receiving station where it will be stored and processed on a personal computer.
3
II) Changes made since PDR
Changes Made to Vehicle Criteria
The following data is from our unloaded RockSim vehicle design. We have revised our motor
from the Loki L930-LW to the Cesaroni L800. Motor length has increased to 19.13 inches. The
burn time has increased to 4.68 seconds. The total impulse has increased to 3723 N/s and
average thrust has changed to 795 Newtons, leading to a change in our altitude. We now have
an estimated altitude of 5278 feet. The fin set has also changed to fiber glassed reinforced 3/8
inch plywood with a fin span of 23.4 inches. The margin of stability has increased to 6.25. The
center of pressure and center of gravity has changed to 93.3 inches and 58.8 inches.
Made to Payload Criteria
The GPS system is the BRB900 TX/RX Base GPS Telemetry system with a LCD hand held receiver
and Smart Data Controller connected to the ground station computer.
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III) Vehicle Criteria
Design, and Verification of Launch Vehicle
The mission is to launch a vehicle with a scientific payload to an altitude of 5280 feet, collect
data every five seconds from each sensor and wirelessly transmit data to a ground station ten
minutes after landing.
Redundant altimeters will record altitude during flight and sound off a series of beeps to be
used for official scoring.
The vehicle will carry two altimeters in the recovery bay and a separate altimeter in the payload
bay which will be used to trigger recovery events as well as the payload events. The vehicle will
use an 8’ 1” rail. Launch vehicle will use a 12 volt direct current firing system. Spools of bailing
wire will be secured in our nosecone as ballast. The total amount of ballast will be less than 10%
of the vehicle’s un-ballasted vehicle mass. A mass simulator will be used for the missing
payloads weight and full ballast will be flown during fight readiness demonstration. A level 2 or
3 NAR/TRA observer will certify fight readiness and rocket stability.
The drogue parachute will be deployed at apogee and a separate altimeter, in the payload, will
send a signal to the DE0 – Nano board starting the collection of data at that time. The payload
will begin to collect temperature, barometric pressure, humidity, UV radiation, and solar
irradiance data every five seconds. Four cameras will capture video throughout the flight. The
main parachute will deploy at 500 ft. AGL reducing our landing energy to meet the 75 ft-lbf
requirement. A separate altimeter, in the payload, will send a signal to the DE0 – Nano board
starting the collection of data.
Weighing of all flight system components has verified our total weight, therefore the mass
override on RockSim software was used to verify simulated weight matched our actual weights.
Simulations were done to confirm that the selected motor will achieve the desired altitude. We
have amassed a database of historical atmospheric data and have used this data in all of our
RockSim simulations.
Performance will be verified by a successful launch. The criterion is based on:






Successful remote launch sequence system tested, works to specifications.
Deployment of drogue parachute at apogee, system tested, works to specifications.
Data collection from apogee up to ten minutes after landing
Successful deployment of main parachute at 500 ft. AGL reducing landing force as
needed
Capture images of the horizon and ground during flight and on landing
Transmission of data to base station
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Figure and Specifications displays Unloaded Design
Figure Displays Loaded Design and Specifications
The final motor selected is the Cesaroni L800. The motor specifications retrieved from
canadainrocketry.org are stated below followed by thrustcurve.org simulated data.
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Based upon the RockSim simulations from above the maximum altitude would be 5480 feet.
We have covered our after action review, after the launching of the subscale. We have
discussed our motor selection and fin set width length with our mentors to ensure proper
safety and construction of our full scale rocket design. It has been decided that the Cesaroni
L800 will suit our rocket needs. Our mentors walked us through the building of the subscale
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rocket to familiarize us with the steps of rocket construction. We are using these steps with the
mentor’s oversight for the full scale.
The first full scale static testing will be conducted in February. This test will help ensure that the
flight systems will work properly when in flight. The key components that will be tested that
day will be the recovery system, GPS, external cameras and stage separation.
Full scale construction is at thirty percent of completion and is due to be fully constructed by
February 16th, in preparation for our static testing that day. Our fin set design has been
approved by our mentors. A jig has been made to ensure the accuracy of the mounting of the
fin set.
A standard three fin set was selected for this mission. It will be a 3/8 inch fiberglass reinforced
birch plywood. A jig has been made to ensure proper alignment during construction. The shape
of our fin set is a custom trapezoidal design that will reach our desired stability margin. Our
mentor’s will be on hand during the build to oversee the construction process.
3/4 inch plywood is being used for the bulkheads to ensure structural integrity of our payload
and recovery bays. Blue tube was selected for its light weight and structural durability.
Two 7.5” to 5.38” plywood centering rings will be used to secure the 3 inch blue tube motor
mount to the 5.5 inch blue tube body. The centering ring will be adhered to the motor mount
by use of 6 minute epoxy resin and epoxy clay will be used as filler. Our mentor’s will be on
hand during the build to oversee the construction process.
Verification
Description
Scientific Payload
Requirement
• Payload will take measurements
every 5 seconds during decent of
the following sensors: pressure,
humidity, temperature, solar
irradiance and ultraviolet
radiation.
•Payload will take video after
apogee up to ten minutes after
landing.
•Payload data will be stored
onboard and transmitted
wirelessly to the team’s ground
station at the completion of all
surface operations.
Launch Vehicle
Altitude
•Launch vehicle shall deliver the
payload to an altitude of 5,280
Verification
•Sensors are interfaced to the DE0Nano FPGA and programmed to take
measurements every 5 seconds
following apogee. The Stratologger
will be used to trigger the program.
•Cameras - three small cameras and a
main camera will be capturing video
during the takeoff of the rocket. We
will attain still photos of the horizon
from the video.
•Data from the sensors will be stored
onto the DE0-Nano until 10 minutes
after landing where it will be
transmitted wirelessly to ground
station.
• RockSim simulations have been
tested to achieve the target altitude
8
feet (AGL).
Recovery Electronics •Shall be designed to be armed on
the pad
•Shall be completely independent
of the payload electronics
•Each altimeter shall be armed by
a dedicated arming switch
•Each altimeter shall have a
dedicated battery
•Each arming switch shall be
accessible from the exterior of the
rocket airframe
•Each arming switch shall be
capable of being locked in the ON
position for launch
•Each arming switch shall be a
maximum of six feet above the
base of the launch vehicle.
Recovery system
•Recovery system electronics shall
shielded
be shielded from all onboard
transmitting devices.
Subsonic launch
vehicle
Stage deployment
Removable shear
pins
Independent or
tethered sections
•The launch vehicle and payload
shall remain subsonic from launch
until landing.
•Drogue parachute shall deploy at
apogee
•Main parachute is deployed at a
much lower altitude.
•Removable shear pins shall be
used for the main parachute
compartment and the drogue
parachute compartment.
•Maximum of 4 tethered sections
•At landing; maximum kinetic
energy of 75 ft-lbf.
•All sections shall be designed to
recover with 2500 feet of the
launch pad, assuming 15mph
wind.
taking into account the altitude of
Huntsville.
•One full scale launch and possibly
more will be done to determine
altitude with an altimeter.
•recovery bay is completely
independent of payload electronics.
•The recovery bay will contain two
rotary switches on exterior of the
rocket, at least six feet above base of
rocket, to arm each altimeter.
• The recovery bay will be shielded
from RF transmitting with ArgenMesh
shielding material.
The recovery bay will be tested with a
handheld ham radio transmitter
(5Watts set to 100 MHZ to 3GHz).
•The motor size is an L800 therefore it
will be considered a subsonic launch
vehicle.
•The altimeter will be used to
determine apogee to trigger the
Drogue parachute to deploy.
•The main parachute will deploy at
500ft.
•Removable shear pins will be used for
the main, and drogue parachute
compartment.
•The rocket will contain three tethered
sections.
•Main parachute size was chosen to
slow decent rate to meet the 75 ft-lbf.
requirement.
•Drift will be observed and analyzed
on RockSim to ensure that the rocket
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Capable of being
prepared at site
within 2 hours
•Launch vehicle shall be capable
of being prepared for flight at the
launch site within 2 hours from
the time the waiver opens.
Launch ready
configuration
•Shall be capable of remaining
launch-ready configuration at the
pad for a minimum of 1 hour
without losing the functionality of
any onboard component.
•Shall be launched from a
standard firing system using a
standard 10- second countdown.
•Shall require no external circuitry
or special ground support
equipment to initiate the launch.
•Data from the payload shall be
collected, analyzed, and reported
by the team following the
scientific method.
•An electronic tracking device
shall be installed in each
independent section of the launch
vehicle and shall transmit the
position of the independent
section to a ground receiver.
•Shall use a commercially
available solid motor propulsion
system using ammonium
perchlorate composite propellant
which is approved and certified by
the National Association of
Rocketry.
•Total impulse shall not exceed
5,120 Newton-seconds.
•All teams shall launch and
recover their full scale rocket prior
to FRR in its final flight
configuration.
•No Flashbulbs, forward canards,
forward firing motors, rear
ejection parachute designs,
motors which expel titanium
sponges, hybrid motors.
Standard firing
system
No external circuitry
Data collected
Electronic tracking
device
Motor
Total impulse
Successful launch
and recovery
Prohibitions
will land within 2500 feet with the 15
mph wind.
•Practice will be done at the full-scale
launches to prepare the rocket within
2 hours.
•Motor will be assembled by an
experienced level two NAR mentor.
•Payload circuitry will not be turned on
until triggered by the payload
altimeter.
•A standard 10 second countdown will
be used for all our launches.
•Our rocket will not contain any
external circuitry.
•Data will be collected at ground
station and will be analyzed and will be
documented in final report.
•The rocket will contain a GPS that
transmits the position of the rocket.
•The motor we will be using is a
Cesaroni L800.
•Total impulse will be calculated at
3723 Newton-Seconds.
• Full scale launches will be done to
ensure a successful flight.
•Our rocket will not include any of
these items.
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Safety checklist
Work on the
project
Mentor
Budget
•Each team shall use a launch and
safety checklist.
•Students shall do 100% of the
work on the project.
•Mentor must be certified by NAR
for the motor impulse of the
launch vehicle, and shall have
flown and successfully recovered a
minimum of 15 flights in this or a
higher impulse class, prior to PDR.
•Maximum amount teams may
spend on the rocket and payload
as it sits on pad is $5000 total.
(Included donated components
and materials).
Pre-launch Safety checklist will include;
•Structures
•Recovery Propulsion
•Documentation
Launch Pad Checklist will include;
•Launch Pad
•Propulsion
•Documentation
•Atomic Aggies team members will do
100% of the work on this project.
•Mentor John Demar has a Level Three
Certification from the National
Association of Rocketry.
•Our budget officer is keeping records
of all orders and donations to ensure
we will not go over the $5000 limit.
After weighing every component and our rocket body the total weight was estimated at 440
ounces and is now at 443 ounces, we feel confident that our mass growth will be less than 10
percent of our final product. Even with the addition of 10 percent of growth our engine
selection will still meet our mission goal.
All members have read and signed safety requirement of the mission. Risks include but not
limited to the following;
Electrical shock, mechanical injuries from use to hand tools, noise and eye protection
shall be worn during all construction and testing of vehicle.
Areas will be kept clear of tripping and slip hazards.
Vehicle construction will be verified by a level 2 or 3 NAR/TRA observer to ensure
vehicle is safety assemble in each stage of construction.
The design has been simulated on RockSim and approved by a level 2 or 3 NAR/TRA observer.
The motors for the full scale rocket engines will be purchased handled and stored by our level 2
or 3 NAR/TRA observer. The full scale rocket motor will be shipped to our NAR mentor at the
hotel in Huntsville.
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Subscale Flight Results
A successful subscale fight was done November 17, 2012, in Alamogordo New Mexico. Below
shows the data received from the altimeter. The rocket reached an altitude of 1,974 feet with
the drogue deploying at apogee and the main deploying at 449 feet.
The RocSim predicted an altitude of 1095 feet and the actual flight data was above 900 feet
higher than expected. These results showed us the importance of having exact weight of all
components and the difference that atmospheric conditions make. We have made a data base
of weather conditions and have taken great care in weighing all components.
Recovery Subsystem
Avionics
The Avionics bay contains two PerfectFlite Stratologger altimeters that will be completely
independent from the payload electronics bay. The two altimeters in the avionics bay are for
redundancy to ensure a successful flight. The altimeters will be used to trigger the electric
matches that will trigger the ejection of the parachutes. One of the altimeters will serve as a
backup to ensure deployment of the parachutes. The drogue parachute will be deployed at
apogee while the main parachute will be deployed at 500 feet. The second altimeter will have
an apogee delay for the drogue and a set ejection trigger at 450 feet for the main parachute.
The two altimeters will be powered by individual 9 volt Duracell batteries and will be connected
independently each having its own charges and electric matches. The altimeters will be
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mounted on a plywood section that slides into the avionics bay with the use of two threaded
rods that attach to the bulkheads. Four static pressure sampling holes will be placed in the
airframe around the circumference to minimize pressure variations due to the wind currents
perpendicular to the rockets direction of travel. Two rotary switches will be located on exterior
of the bay and rocket body to power up the altimeters and safeguard from accidental ignition.
On each end of the avionics bay, two PVC caps on each end of bay bulkheads will be used to
house the black powder. E –matches will be connected by the terminal blocks that are also on
the bulkheads. The avionics bay will be protected from electric fields (payload bay) outside of
the avionics bay with Argenmesh fabric that will be epoxied to the inside of the bay.
Argenmesh provides level grounding, static discharge, electric field shielding, and
radiofrequency shielding with 50 dB from 100MHz to over 3 GHz and a surface conductivity of
<1 ohm per square. Below shows the Avionics bay as well as the wiring diagram.
Avionics bay
Recovery system
The length of the avionics bay will be 12 inches long and will fit into the rocket body as a
coupler. The recovery system that will be used is a dual deployment recovery system that
contains a 24inch drogue parachute and a 96 inch main parachute. A Nomex parachute
protector will be used for each of the parachutes to prevent damage from ejection charges. The
parachutes will decrease the decent velocity upon landing to around 20 feet per second. Two
U-bolts will be used on each end of the avionics bay which is rated to withhold 880 pounds. A
1/2 inch thick tubular nylon shock cord will be connect other sections( nosecone/payload and
booster) of the rocket to the avionics bay by connecting to the U-bolts that are on each end.
The length of the shock cord will be three times that of the rocket.
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Analysis
The analysis of the recovery system begins with the specification of maximum kinetic energy
required by the USLI handbook at 75 foot-pounds. The equation for kinetic energy is:
𝑚𝑎𝑠𝑠
1𝑙𝑏𝑓𝑠 2
2)
(𝑣𝑒𝑙𝑜𝑐𝑖𝑡𝑦
𝐾𝐸 = (
)
(
)
2
32.2 𝑙𝑏𝑚 𝑓𝑡
Plugging in the requirement for KE and using the mass from the heaviest section, then solving
for maximum landing velocity at landing results in:
𝑀𝑎𝑥 𝑙𝑎𝑛𝑑𝑖𝑛𝑔 𝑣𝑒𝑙𝑜𝑐𝑖𝑡𝑦 = √(
75𝑙𝑏𝑓
) = 19.45 ft/s
1𝑙𝑏𝑓𝑠 2
12.76𝑙𝑏𝑠
(
)(
)
2
32.2 𝑙𝑏𝑚 𝑓𝑡
The size of the parachute was determined by alternating different sizes of main parachutes on
RockSim until the desired decent rate was found. With a main parachute of 96 inches the
decent upon landing was 18.66 ft/s which is well within our limits.
Going back to the kinetic energy requirement each section will need to be calculated to ensure
the recovery system meets the specification of 75lbf.
KE for Main parachute:
Section1 (nosecone/payload):
7𝑙𝑏𝑠
𝑓𝑡 2
1𝑙𝑏𝑓𝑠 2
𝐾𝐸 = (
) (18.66 ) (
) = 37.85 𝑙𝑏𝑓
2
𝑠
32.2 𝑙𝑏𝑚 𝑓𝑡
Section 2 (E-bay):
6.5𝑙𝑏𝑠
𝑓𝑡 2
1𝑙𝑏𝑓𝑠 2
𝐾𝐸 = (
) (18.66 ) (
) = 35.14 𝑙𝑏𝑓
2
𝑠
32.2 𝑙𝑏𝑚 𝑓𝑡
Section 3 (bottom/motor):
12.8𝑙𝑏𝑠
𝑓𝑡 2
1𝑙𝑏𝑓𝑠 2
𝐾𝐸 = (
) (18.66 ) (
) = 69.20 𝑙𝑏𝑓
2
𝑠
32.2 𝑙𝑏𝑚 𝑓𝑡
KE for drogue parachute:
Section1 (nosecone/payload):
7𝑙𝑏𝑠
𝑓𝑡 2
1𝑙𝑏𝑓𝑠 2
𝐾𝐸 = (
) (57.27 ) (
) = 356.5 𝑙𝑏𝑓
2
𝑠
32.2 𝑙𝑏𝑚 𝑓𝑡
Section 2 (E-bay):
6.5𝑙𝑏𝑠
𝑓𝑡 2
1𝑙𝑏𝑓𝑠 2
𝐾𝐸 = (
) (57.27 ) (
) = 331.04 𝑙𝑏𝑓
2
𝑠
32.2 𝑙𝑏𝑚 𝑓𝑡
14
Section 3 (bottom/motor):
12.8𝑙𝑏𝑠
𝑓𝑡 2
1𝑙𝑏𝑓𝑠 2
𝐾𝐸 = (
) (57.27 ) (
) = 651.89 𝑙𝑏𝑓
2
𝑠
32.2 𝑙𝑏𝑚 𝑓𝑡
To find the amount of black power needed for the ejection charge the Ideal Gas Law was used
then solving for N =
PV=NRT
350lbf
P = absolute pressure of gas in pounds per square inch (π(2.75in)2 = 14.732psi)
V = volume occupied by gas in cubic inches (Vdrouge = πR2L = 273.22 in3) (Vdrouge = πR2L =
403.891 in3)
N = the mass in pounds (black powder)
R = gas constant in inch pound-force per pound-mass (266 in-lbf/lbm)
T = absolute temperature in degrees Rankine (3307 R)
PV
Ndrouge(RT) = .004576 p = 2.0756 grams
PV
Nmain(RT) =.006764 p = 3.068 grams
Testing
The testing process started by simulating a change in altitude by changing the pressure around
the altimeter using a jar and syringe. Both the altimeters were placed inside the jar, one
wrapped in paper so it doesn’t interfere with the other. A syringe was placed into a hole on top
of the lid of the jar to depressurize the jar. The data from this test was used to make sure that
both the altimeters had similar readings. The test concluded that both the altimeters had
similar readings therefore both will be used in flight.
We will test the shear pins and BP stage separation on each stage with a standard launch
controller. Before every full-scale test flight a ground test will be done to ensure the correct
amount of black powder is utilized to eject the main and drogue parachute. The rocket will be
placed horizontally on the ground making sure that nothing is in front or behind the rocket. A
vacuum will be applied to the static sampling port which will trigger the altimeter to simulate a
flight by the change in pressure. The main point of this test is to make sure that the separation
of the sections takes place.
To ensure that the rocket landing velocity is safe and will meet the kinetic energy specification
of 75lbf, several tests will be ongoing on Rocksim whenever there is any change in weight or
design of the rocket.
15
Mission Performance Predictions
The vehicle will carry barometric altimeters used to send signals to vehicle recovery and the
payload bay. The electronic modules will have separate barometric altimeters. A readiness
launch review using the barometric altimeter shall record readings to be used for official
scoring. The vehicle will use an 8’ 1” rail. Launch vehicle will use a 12 volt direct current firing
system. We have decided to use spools of bailing wire that we have measured into accurate
weight sizes which will be secured in our nosecone as ballast. The total amount of ballast will be
less than 10% of the vehicle’s un-ballasted vehicle mass. A mass simulator will be used for the
missing payloads and full ballast will be flown during fight readiness demonstration. A level 2 or
3 NAR/TRA observer will certify fight readiness and rocket stability.
A drogue parachute will be deployed at apogee being triggered from recovery bay while the
payload altimeter will trigger FPGA to collect temperature, barometric pressure, humidity, UV
radiation, and solar irradiance data every five seconds. Four cameras will capture video
throughout the flight.
Below are the flight profile simulations, along with altitude predictions and the simulated motor
thrust curve. Based upon our RockSim simulations from above our maximum altitude would be
5480 feet.
Figure and Specifications displays Unloaded Design
16
After calculating the weight to thrust ratio, we feel confident that our rocket will have enough
stability off the launch pad. We calculated a weight to thrust ratio of 6 and this is above the
acknowledged stability margin. As mentioned earlier we put our simulation through various
wind conditions that the rocket has tolerated. Above is our stability margin, simulated CP and
CG.
17
Payload Integration
As members of the USLI students will be integrating the DE-0 Nano microcontroller to take
analog readings given from five specific atmospheric sensors to collect and store data for future
analysis. The scientific payload will be independent of recovery electronics so that there is no
interference between the two systems. The sensors that are mentioned in the payload criteria
section will be the measurement acquisition tools to gather the different analog readings to be
converted through an on-board analog to digital converter. There will be a Strato-Logger
Altimeter on board the payload to trigger the data collection once apogee has been reached.
Each of the sensors will be soldered on a printed circuit board that can be easily removed if
necessary and interfaced to the DE0-nano Development and Education Board via a 26-pin
ribbon connected to the 2 X 16 header. Once all of the data has been collected, the data stored
on the FPGA board will then be transmitted to the receiver where the ground station will
interpret and analyze the data. There will be a signal sent to turn off the GPS system before
transmission of the data to eliminate interference. The payload bay will be inserted into the
rocket body by sliding it in the air frame and held in place by a piece of blue tube cut to the
radius of 2.68” place below the payload inside of the air frame. The payload will be aligned with
a hole on the exterior of the airframe for the HD video camera to get shots of the horizon and
video throughout the rocket flight. The payload will be encased in a blue tube coupler that will
be cut to fit inside of the air frame allowing for easy access to the internal components and
circuitry of the payload.
18
Launch Concerns and Operation Procedures
Pre-Launch Checklist:
Complete this checklist prior to launch attempt and under the supervision of an appropriately
certified NAR member. This checklist is to be completed by the certifying individual.
Structures:
Inspect each component for security and flight worthiness.
[ ] Nosecone
[ ] Airframe
[ ] Fins
[ ] Rail Buttons
[ ] Motor Retainer
Recovery:
Inspect each component for security and flight worthiness.
[ ] Shock Cord – Secured between nosecone and forward ring eye-bolts.
[ ] Chute Protector
[ ] Parachute
[ ] StratoLogger Checklist
Propulsion: Inspect each component for security and flight worthiness.
[ ] Motor Case – Inspect for cleanliness.
[ ] Motor Reload – Install into motor case per manufacturer’s instructions.
[ ] Motor Retainer – Remove retainer cap, install motor, and reinstall retainer cap securely.
[ ] Igniter – Locate and retain igniter until needed. ***DO NOT INSERT IGNITER***.
Documentation:
[ ] Complete this checklist below and inform NAR mentor for review.
Checklist is completed by: [name]
Checklist is reviewed by: [name]
[date]
[date]
Proceed to Range Safety Officer (RSO) for final inspection and further instruction. Fill in
appropriate fields on a flight card. Declare to the RSO the actual level of your flight.
19
Launch Pad Checklist:
Complete this checklist at the launch pad under the supervision of a Launch Safety Officer (LSO)
or appropriately certified NAR member. This checklist is to be completed by the certifying
individual.
Launch Pad:
[ ] Launch Rail – Inspect launch rail for excessive corrosion or snags that would risk the rocket
jamming on the rail.
[ ] Rocket – Slide the rocket down onto the rail until it is against the rest.
Propulsion: The Launch Control System (LCS) pad bank must be switched “OFF”.
[ ] Insert igniter fully into the rocket motor through the nozzle and install the nozzle cover.
[ ] Strip 1” – 2” of the wire’s sheath to expose both wire cores.
[ ] Short LCS circuit by tapping both alligator clips together.
[ ] Connect one wire core to each alligator clip wrapping the excess wire around the clip.
NOTE: The LSO may ask you to do any number of these steps in a different order. Be prepared
to deviate from this checklist. If you feel you are being asked to do anything unsafe, respectfully
ask for clarification on the reason for the change.
NOTE: You may also change the launch angle on the launch pad up to 20 degrees off of vertical
depending on the winds.
[ ] Before returning to the RSO tent, switch the LCS pad bank “ON” if you are the last person
leaving the area.
Documentation:
[ ] Complete this checklist below and inform a NAR mentor for review.
Checklist is completed by: [name]
Checklist is reviewed by: [name]
[date]
[date]
Return to the RSO tent with your Flight Card pad number filled in. After flight, remain behind
RSO line until the field is reopened.
20
Safety and Environment
Safety and Quality Assurance:
The safety officer for the Atomic Aggies will be Crystal Escamilla. All atomic aggie team
members have been briefed on all safety rules and precautions and have signed a sheet proving
that they have read all safety rules and will abide by them. All hazardous materials will be used
and disposed of according to the Material Safety Data Sheets which will be posted in our lab as
well as the team website. Hazards in building the rocket include the use of power tools, epoxy,
glue, solder iron, and solder. Anyone using power tools must be properly trained before use.
Precautions that must take place with epoxy glue and solder because inhalation of such items
can cause respiratory problems as well as be a skin and eye irritant. When using epoxy, glues,
and solder, the area where it will be used will be well ventilated. Protective gloves, goggles, and
masks will be used when applying glue or epoxy and special care will be used when soldering.
The main hazards associated with this project are the use of black powder and rocket motors.
All explosives will only be handled by Level II NAR certified mentors.
Two NAR certified mentors will be available to answer any NAR safety rules during design,
building, and launching of our rocket. Our safety checklist will be used at all subscale and fullscale launches and will be signed by the safety officer and a NAR certified mentor certifying that
the vehicle is safe to fly. All motors as well as explosives will only be handled by a NAR Level II
certified mentor. All components must be inspected so that the rocket can be launched as
safely as possible, without any problems. Components and subcomponents must be inspected
for security and flight worthiness. If anything appears to be unsafe for launch, it is the
responsibility of that team member to make the Safety Officer aware of such problem, who will
then seek guidance from NAR mentor to decide if continuation of the launch would be safe.
Potential risks and mitigation procedures may include:
Risk
Consequence
Mitigation
Probability of occurrence
Center of gravity
and center of
pressure is off.
Unstable flight
Black powder
ignites causing
explosion.
Loss of rocket as
well as possible
death or serious
injury.
Do calculations
properly and review
the flights on RockSim
to ensure weights are
distributed in the right
places.
Assure that only Level
II NAR Mentor handles
all black powder. Two
rotary switches will be
used to arm the rocket.
Propellant burns
out prematurely
Altitude not reached
Low – design will be run
multiple times in RockSim.
Before competition at least one
subscale and one full scale
flight will need to be
successfully completed.
Low- safety is the number one
priority. As with all explosives,
potential hazard does exist, but
under the guidance of NAR
mentor, this is an unlikely
occurrence.
Low - under the guidance of
experienced NAR mentor, this
is an unlikely occurrence.
Level II NAR
experienced mentor
will assemble motor.
21
Motor detaches
from casing upon
ignition.
Parachutes get
damaged due to
heat of the motor
Main parachute
deploys at apogee
Parachute failure
Possible loss of
rocket sub-systems
as well as
unsuccessful flight.
Death or serious
injury possible.
Parachutes fail
resulting in fast
decent rate of
rocket causing
possible destruction
of rocket.
Unable to recover
rocket
Damage/loss to
rocket. Possible
injury to bystanders.
Test and inspect
durability of the
security of casing prior
to launch.
Low- vehicle will be inspected
during construction and prior
to launch for security within
booster section.
Use parachute
protectors as well as
dog barf to protect
parachutes from heat.
Ground testing will be
done.
Use enough shear pins
to hold parachute in
place until ejection.
Test ejection charges.
Make sure altimeter is
set correctly and has
fresh batteries.
Low- due to the use of
parachute protectors and dog
barf being properly used.
Low – several shear pins will be
used to hold the rocket in place
Low- recovery will be
thoroughly tested to ensure
successful flight.
Environmental Concerns:
Disposal of toxic materials, such as epoxies and paints will be done in accordance with waste
disposal methods as set forth in appropriate Material Safety Data Sheets. Chemicals will not be
disposed of down the drain at any time. In doing so, potential for any environmental concerns
are minimal and do not pose a significant threat or impact to the environment.
22
IV) Payload Criteria
Testing and Design of Payload Experiment
The payload will fulfill the requirements set by NASA for the University Student Launch Initiative
(USLI) by measuring pressure, relative humidity, solar irradiance, temperature, and ultraviolet
radiation after the rocket reaches apogee. Each measurement will be taken every five seconds
for the remainder of the flight and also ten minutes after the rocket has landed. We will be
using VHDL to program the DE-0 Nano board to take these measurements and store them to
the on-chip memory for future analysis. There will be an altimeter on board that will be used to
trigger data collection. The Stratologger altimeter measures barometric pressure and
temperature. Internal circuitry onboard and the altimeter calculate the altitude from these
readings. Our separate circuit board providing pressure and temperature data will provide a
means for proving our data. The data from the pressure and temperature sub-circuit can also
provide a means to compute altitude. The scientific payload and components will be mounted
on a 5.36” x 18” piece of ½” ply board. To accommodate the mounting of the camera and
sensors inside the payload, we will be fitting pieces of Blue-Tube coupler material split
lengthwise around the payload making a 5.36” diameter encasing the internal circuitry and
components. Brackets will be placed inside the payload attaching the coupler to the ply board
to allow access in to the payload. The three Esky Lighter cameras will be mounted to the fins of
the rocket. The GearCam HD camera mounted to the payload structure will be aligned with a
hole on the exterior of the airframe. This will make it possible to slide the payload into the
airframe of the rocket without having to reach into the rocket and align the cameras to the
holes on the airframe.
The DE-0 Nano FPGA board and printed circuit board with our sensors and wiring will be
mounted to the ply-board payload bay with small screws. The DE0-Nano will be powered by
Enercell Nickel metal hydride rechargeable 5 volt battery pack at 800 mA . To ensure that the
battery pack will power the Nano board for at least 3 hours, we will test the fully charged
battery pack by letting the system collect data for several hours until the battery pack is unable
to power the board.
The temperature, pressure, and humidity sensors will be soldered to the printed circuit board
(PCB). The ultraviolet sensor SU-100 and solar irradiance sensor SP-110 will mounted on
brackets on top of the payload bay with wires attaching down into the payload bay. The analog
output wires from each sensor will be soldered to PCB where we have a 26-pin ribbon that is
used to connect to the DE-0 Nano board. There is an eight-channel CMOS 12-bit analog-todigital converter on the board that will be used to convert the analog values given from the
sensors. The Nano board provides a 3.3 V power output that will be used to power the sensors
as well as a common ground for all the circuitry. The sensors outputs will be connected to the
on board ADC through the ribbon cable to display the measured values on the seven segment
module as shown below.
23
Top is the DE-0 Nano board connected to the seven segment module for testing, and to the right
is the PCB with temperature, pressure, and humidity sensors soldered on. The seven segment
display above shows what channel (sensor) is being displayed along with the converted analog
value. To display this data we also converted the digital measurements to HEX values for testing
purposes making sure we are receiving the correct data information.
The following image shows the pin layout and connections for the sensors.
24
Payload diagram is shown below.
25
Payload Dimensions 5.36”X 18” piece of 1/2” thick plywood board.
DE0 Nano Board (Dimensions 45 mm X 75 mm) Top and bottom views
26
DE0 Nano Board GPIO, General Pins I/0 for the ADC, Analog to Digital Converter layout. The pins
are located on the bottom view of the board as seen above so the board will be mounted to the
payload bay upside down.
The data will be stored in memory on the DEO-Nano and will be transmitted with the X-Bee Pro
XSC RF Module to the ground station at the completion of all surface operation.
The GPS system is the BRB900 TX/RX Base GPS Telemetry system with a LCD hand held receiver
and Smart Data Controller connected to the ground station computer. The sensor data
transmitter unit will be located within the payload bay will also be located in the payload, but
will not be turned on at the same time.
All safety precautions shall be followed when working on all areas of rocket project. Bench
testing each component separately will be done in lab. The humidity sensor will be tested by
taking a reference reading then changing the condition by placing it by a humidifier to see the
change in humidity. The temperature sensor will be tested by taking a reference reading with a
thermometer then changing the temperature by holding the sensor in our fingers to see the
change in temperature. Pressure will be tested by placing the sensor in a jar that has been
designed that created a change in pressure by using suction (same as altimeter). Cameras have
been tested during subscale launch where video data was collected. We have successfully
tested measured values of the previously discussed sensors by collecting and displaying the
converted digital measurements to a seven segment display that allows us to see exactly what
channel (sensor) we are reading and making sure that the displayed value matches the actual
environmental conditions here in the laboratory.
GPS testing will be done by changing location within the building and tracking with the receiver.
Transmitter will be tested by sending known data from transmitter and receiving that same
data with no loss or incorrect bits.
Full scale launch testing will also be done on February 16, 2013 in order to analyze results for
Flight Readiness Review. Once satisfied with all testing results of each electrical components
and the interfacing, they will be soldered on the PCB to be mounted on the payload bay. A
piece of Blue Tube coupler will be placed below payload bay to ensure that payload bay stays in
place. When the payload bay slides into the rocket body, it will be stopped by the piece of Blue
Tube coupler. Once the payload is inside the rocket body it will be orientated to fit the camera
lens with the hole that is precisely cut into the rocket body. Measurements of all sensors will be
done repeatedly to ensure accurate results. Extensive testing will be done to ensure consistent
results from each sensor. References will be used to ensure correct results are being gathered.
27
Components and Precision
Component
Thermistor – MCP9700
Precision
±2°C from 0°C to +70°C
Humidity - HIH-5030
11% RH to 89% RH
Camera/Video Gear Cam HD - DVR,
Esky Lighter Camera HD – DVR.
Pressure - TruStability Silicon Pressure sensor
Main camera HD 1280x720 @30 fps
3 Backups 720 x480, 28-30FPS
Solar Irradiance - SP - 110 Pyranmometer
Ultraviolet Radiation - SU - 100
GPS –BRB900 TX/RX Base GPS
Transmitter/ Receiver
Total error band of 2% full scale span
maximum ( 1 psi to 150 psi)
Cosine Response
• 45º zenith angle: ± 1%
• 75º zenith angle: ± 5%
Absolute Accuracy
• ± 5%
Uniformity
• ± 3%
Repeatability
• ± 1%
Absolute Accuracy
• ± 10%
Uniformity
• ± 5%
Repeatability
• ± 1%
900 MHz
Receiver Sensitivity -100 dBm (1% packet
error rate)
Field Programmable Gate Array (FPGA) – We selected the DEO – Nano
Development and Educational Board developed by Terasic to be programmed for taking
measurements from the sensors once apogee has been reached. The DEO – Nano board
will be powered by a 5 – volt battery pack.
Pressure – The pressure will be taken by a TruStability Silicon Pressure sensor (SSC
Series). The SSC Series is calibrated and temperature compensated for sensor offset,
sensitivity, and temperature effects. It has an amplified compensated analog output and
measures from 1 psi to 150 psi.
Relative humidity – Humidity will be measured with the HIH – 5030/31 sensor from
Honeywell. This sensor is a covered integrated circuit humidity sensor that uses a laser
trimmed thermoset polymer capacitive sensing element with on-chip integrated signal
conditioning. The sensors multilayer construction gives protection from most application
hazards such as condensation, dirt, oils, or anything that may damage the sensor or cause
a misreading.
28
Solar Irradiance – Solar irradiance measurement will be taken using the Apogee
pyranometer instrument SP-110. This device is self-powered and will take measurements
every 5 seconds after apogee. To collect the data read by the sensor it needs to be
interfaced with a meter or a data logger. We have decided to interface the sensor with
the DE0 board’s analog to digital converter to collect and store the data output from the
pyranometer.
Temperature – The temperature sensor being used in this design is an MCP9700/9700A
low-power linear active thermistor integrated circuit. This is an analog temperature
sensor that converts temperature to analog voltage.
Ultraviolet Radiation – UV radiation data is collected using the Apogee Instruments UV
sensor SU-100. The device is self-powered and will take measurements every 5 seconds
after apogee.
Cameras – (1) Gear Cam HD - DVR, (3) Esky Lighter Camera HD – DVR.
Altimeter – The Stratologger altimeter will be used to track the flight of our rocket.
Altitude can also be calculated by using the pressure measurement with the following
𝟏
equation: Altitude = 𝟒𝟒𝟑𝟑𝟎 ∗ [𝟏 −
𝑷 𝟓.𝟐𝟓𝟓
(𝑷𝒐)
].
GPS – The GPS system is the BRB900 TX/RX Base GPS Telemetry system operating at
900MHz. The data will be received by a LCD hand held receiver and Smart Data
Controller connected to the ground station computer.
Transmitter/Receiver – The Xbee Pro 900 transceiver will transmit and receive the
stored data from the DE0 – Nano board to the ground station.
Camera positioning:
Main
Camera
29
Ubication
Three small cameras and a main camera self-contain manually operated will be taking video
during the takeoff of the rocket. The main camera will be located on top of the payload just
under the hook that is used for the parachute.
The main camera (Gear Cam HD-DVR-RM) records digital video at 1280x720 High Definition
along with audio. The main DVR-RM can run for over 2 hours on the built rechargeable battery
and stores the data in the Micro-SD-Card; up to 32gig in size.
The purpose of using the other three small cameras is as a backup, in case the main camera
runs out of power or incase were not able to get a clear shot of the horizon, then we can obtain
the video from one of the other three small ones. These three cameras can record around 2
hours before you need to recharge the battery. The three mini cameras (Esky Lighter Camera)
takes pictures at 1280 x 960 pictures and records 720x480 video, audio and a built-in mini DVR.
No drivers or outside power source needed. These cameras will be located on the fins pointing
vertically.
30
Payload Concept Features and Definition
The creativity and originality embedded in this design is the use of the DE0 – Nano board to
record and store data from the rocket flight and after the rocket has landed as well as transmit
this data for further analysis. The biggest challenge for the payload team is the integration of
the sensors with the DE0-Nano board and storing the data that is to be analyzed. Also we must
transmit this data one byte at a time; there are two bytes for each data measurement. Each
sensor measurement is giving a twelve-bit ADC reading as well as a three bit value for the
channel that is being read. Since there are only 15 bits, it was necessary to concatenate the ADC
reading, and the channel that is being read, with a ‘0’ so that we have a 16-bit value, two bytes,
to store and transmit for each measurement. This requires understanding of VHDL
programming to successfully program the board and to ensure that we are receiving the correct
data. Understanding and interpreting results is a necessity to report final data gathered from
the payload.
Science Value
The scientific mission of the payload is to gather data on the temperature, pressure, humidity,
light intensity once apogee is reached and take video during flight for later use. In order for the
payload to be successful, the internal circuitry and its components will record and store the
data gathered during the flight without being affected by the thrust of the rocket and other
outside conditions. There is a relationship between the temperature and pressure where
altitude can be calculated so as the altitude changes, so does the temperature and pressure.
Correlating our measurements to the altitude of the altimeter will prove that this is actually the
case. The GPS will be used to track the position of the rocket and the video will show the
conditions outside the rocket. Data will be analyzed to study the immediate conditions in the
atmosphere and the air from apogee to ground. The data gathered during decent will be
transmitted wirelessly to the ground station at the time of completion of all surface operations,
ten minutes after landing.
31
Safety and Environment of Payload
Safety officer: Crystal Escamilla
Risk
Payload data does not match
projected data.
Damage to payload during
test flight
Battery failure
Damage during final launch
Airframe becomes loose
Center of Gravity is off
Consequence
Unusable data
Prevention
Thoroughly test payload data before launch.
Broken components
Have extra components ready to rebuild. Secure
payload and components tightly.
Testing will be done to determine the total life of
batteries to ensure that batteries are able to last.
No power to DE0-Nano,
therefore no measurements
will be taken.
Components could be
damaged or come loose.
Data will be compromised
and camera/measurement
holes will be unaligned.
Unsuccessful flight
Secure payload and components tightly.
Make sure there is a way to tightly secure the
payload bay where it cannot come loose.
Make sure the mass if figured correctly and given
to the design team before flight takes place.
Hazards
Hazard
Use of solder and solder iron
Effect of Hazard
Burns, inhalation of toxic fumes.
Use of Nickel metal hydride
batteries
Exposure to the ingredients contained
within or their combustion products
could be harmful.
Contents of an open battery can cause
respiratory irritation. Hypersensitivity
to nickel can cause allergic pulmonary
asthma.
Contents of an open battery can cause
serious chemical burns with contact of
skin and eyes as well as of mouth,
esophagus, and gastrointestinal tract if
ingested.
May cause severe irritation in eyes,
and skin. If inhaled, Can cause
irritation of the respiratory tract.
Cuts or other injuries, damage to
equipment, or flying debris.
Use of Epoxy
Use of power tools
Electricity
Burns, shocks
Mitigation
Follow safety rules concerning the use
of solder and solder irons. Use non
lead solder.
Battery will not be opened or burned.
Batteries will be placed away from the
motor of the rocket.
All safety precautions will be followed
when using Nickel metal hydride
batteries.
Use gloves when using epoxy as well
as safety glasses. Epoxy will be used in
a well-ventilated area.
Follow manufactures safety
instructions, wear goggles; do not
operate without supervision.
Take all safety precautions when
working with electricity. Keep all
food and drinks away from work area.
Make sure components are not being
powered while making adjustments.
32
V) Project Plan
Budget
Electronics Recovery System
Main Parachute
Rail Buttons
Drogue Chute
Stratologger Altimeter
Black Powder
Batteries
Nomex Chute Protectors
Shock Cords
Shock Cord Protector
Electronics Bays
Rotary Switches
1
2
1
2
1
9
2
24
4
2
2
240.00
3.07
39.10
35.95
20.00
2.50
6.37
1.10
12.95
54.95
0.88
$240.00
$6.14
$39.10
$71.90
$20.00
$22.50
$12.74
$26.40
$51.80
$109.90
$1.76
1
3
2
1
1
1
1
1
1
1
1
2
1
1
1
1
1
4
1
59.00
14.99
79.95
16.93
36.47
11.01
24.95
9.95
66.95
4.95
299.00
2.50
104.25
42.1
22.74
129
500
4.31
55
$59.00
$44.97
$159.90
$16.93
$36.47
$11.01
$24.95
$9.95
$66.95
$4.95
$299.00
$5.00
$104.25
$42.10
$22.74
$129.00
$500.00
$17.24
$55.00
1
2
1
2
4
2
3
1
1
1
1
1
1
1
1
1
59.65
7
55.95
15.01
3.75
56.95
30
42.75
9.05
29.95
72.01
4.43
28.01
289.95
169.95
185
$59.65
$14.00
$55.95
$30.02
$15.00
$113.90
$90.00
$42.75
$9.05
$29.95
$72.01
$4.43
$28.01
$289.95
$169.95
$185.00
Pay Load
DEO-Nano
Lighter Camera
Alt15K Altimeter
Temperature Sensor
Pressure Sensor
Humidity Sensor
Xbee USB Reciever
Xbee Explorer Reciever
Xbee Pro 900 Transmitter
Interface Cable
BRB900 GPS
Batteries
Fiberglass Sheets
Photo Diode
RF Sheilding
GearCam Hi-Def Modular Camera & digital recorder
Laptop computer
Memory Cards
Miscellaneous (resistors, cables, etc.)
Design
Nose Cone
Centering Rings
Blue Tube Coupler
Bulkhead
Quick Links
Blue Tube
G-10 Sheets
Aeropoxy Adhesive
Fiberglass Cloth
Blue Tube Motor Mount
Fin Set
Aft Rail Button
Aft Centering Ring
Cesaroni 75mm 3 Grain Hardware Set
Cesaroni 75mm 3-Grain Casing
Cecaroni L800 engine
Grand Total
$3,421.27
33
Other Expenses
Ground Station
Dell Precision Labtop
Communication Cable
Xbee USB Transciever
Interface Cable
1
1
1
1
500.00
49.00
54.95
10.95
Total Ground Station
500.00
49.00
54.95
10.95
$614.90
Travel(12)
Meals(4 days x 3 meals x 12)
Airline tickes
Lodging(4 days x 6)
Rocket Transport
144
12
24
21
6
450
120
45
Total Travel
864.00
5,400.00
2,880.00
945.00
$10,089.00
Other Activites
Fundraising
Educational Engagement
Test materials
Total Other
Total Rocket
Grand Total
1
1
1
100
100
500
100.00
100.00
500.00
$700.00
$2,842.87
$13,631.87
34
Funding
The team has raised $2000.00 in fund raising events thus far.
We have set up a donation button on our web site along the with a formal donation letter (see
below). Every team member has pledged to use the letter to garner at least one corporate
sponsor.
We organized a bake/raffle sale during NMSU homecoming week (October 26th. We will do this
at key times each semester (see flyer below).
Additionally our faculty mentor plans on submitting a matching travel/equipment grant from
the Space Grant Consortium. They will match up to $5000.00.
Other plans could include:
Car wash
Dog wash
Volleyball tournament
Pizza fundraiser
Rummage sale
Coffee, hot chocolate stand
35
Timeline
36
Educational Engagement
New Mexico State University Atomic Aggies will be partnering local Boys and Girls Club of Las
Cruces, local elementary schools, local middle schools. The Atomic Aggies have worked with
local children with hands on STEM associated project. Where we helped the children design
film canister, where we used a chemical reaction to propel the rocket. This event took place
December 4th, 2012 with 23 students at the Boys and Girls Club of Las Cruces. The next
engagement is also with Boys and Girls Club of Las Cruces on December 19th, 2012 where
members of the atomic aggies will help 20 -30 children correctly construct model rockets, and
promote safety to students when working with rocketry. In early spring 2013 the atomic aggies
will also team up with Lynn Middle school of Las Cruces, NM for the local science night for the
school which discusses the science value of NMSU Atomic Aggies program. For the elementary
schools Atomic Aggies will assist students in after school programs to develop knowledge of the
rocket flight with film canister experiments. Hopefully by the end of it all we will have plenty
more than the minimum of engagement of 100 students.
37
VI) Conclusion
In Conclusion, the Atomic Aggies will work hard and strive for a successful launching. We are
keeping track of our timeline to make sure we meet are deadlines to ensure all milestones for
the project are achieved. To accomplish this team members have dedicated our time during
scheduled class hours and out of class to complete our goals. We have made safety our number
one priority, all safety rules and precautions will be followed and noted with a check list used.
All simulations and launches of the rocket will be tested thoroughly to ensure a successful
flight.
The Atomic Aggies Team understands the importance of teamwork and leadership, we are
confident that we can accomplish each task effectively and efficiently. The Team has shared
their knowledge, skills, and responsibilities to complete the challenge of our ultimate goal,
which is to comply and launch a successful designed rocket that meets the specifications and
expectations the ULSI Program.
38