NASA USLI CDR
Atomic Aggies
Submitted by: New Mexico State University Rocket Team
January 25, 2012
USLI PDR
Atomic Aggies
New Mexico State University
Contents
I) Summary of Critical Design Report ..................................................................................................4
Team Summary ..............................................................................................................................4
Launch Vehicle Summary ................................................................................................................4
Payload Summary ..........................................................................................................................5
II) Changes since PDR .........................................................................................................................6
Vehicle Criteria Changes .................................................................................................................6
Payload Criteria Changes ................................................................................................................6
Activity Plan Changes .....................................................................................................................6
III) Vehicle Criteria .............................................................................................................................7
Mission Statement .........................................................................................................................7
Vehicle Verification Plan and Status ................................................................................................7
Verification ....................................................................................................................................8
Flight Reliability and Confidence ................................................................................................... 11
Atomic Aggies Rocket Model ........................................................................................................ 13
Subscale Flight Results.................................................................................................................. 14
Recovery Subsystem..................................................................................................................... 14
Parachute Packing and Harness.................................................................................................. 15
Avionics ...................................................................................................................................... 16
Avionics Bay ............................................................................................................................... 17
Altimeter Testing ........................................................................................................................ 19
Ejection Charge and Deployment Testing ................................................................................... 19
Ejection Charge Sizing Calculations ........................................................................................... 20
Mission Performance Predictions.................................................................................................. 24
Interfaces and Integration ............................................................................................................ 25
Launch Operations ....................................................................................................................... 26
Safety and Environment ............................................................................................................... 27
Team Safety and Awareness ......................................................................................................... 28
Testing and Design of Payload Experiment .................................................................................... 31
Payload Concept Features and Definition ...................................................................................... 38
Science Value ............................................................................................................................... 39
Payload Verification ..................................................................................................................... 39
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USLI PDR
Atomic Aggies
New Mexico State University
Safety and Environment (Payload) ................................................................................................ 40
V) Activity Plan ................................................................................................................................ 42
Budget plan.................................................................................................................................. 42
Timeline ....................................................................................................................................... 44
Outreach...................................................................................................................................... 46
VI) Conclusion .................................................................................................................................. 47
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USLI PDR
Atomic Aggies
New Mexico State University
I) Summary of Critical Design Report
Team Summary
Team Name: Atomic Aggies
Location:
New Mexico State University
Ed and Harold Foreman Engineering Complex III
Las Cruces, NM 88003
Team official:
Professor Lynn Kelly
Safety Officer:
Mentor: John DeMar
Safety Officer:
Christopher Herrera
NAR Level 3 Team Mentor: John DeMar
Launch Vehicle Summary
Rocket Specifications:
The specifications for this rocket will be as follows: The overall length will be 124.01 inches.
The diameter of the rocket will be 5.5 inches. The nosecone will be ogive. The approximate
loaded weight of the vehicle is 29.879 oz. and the unloaded weight is 22.432 oz. The rail size
will be 1x1in/72in.
The motor will be the L789RT motor from Gorilla Rocket Motors. Specifications include:
Diameter:
75mm
Length:
19.5669in.
Burn time:
4.17s
Impulse:
3285.197 N-s
Thrust:
794.6 N
RockSim Altitude: 5178.54ft
Recovery System:





Dual Deployment
o Two PerfectFlite StratoLogger Altimeters
Main Parachute Descent Rate=20 ft./s
Main Parachute Type: Elliptical Custom 84”
Drogue Descent Rate=160ft./s
Drogue: 12” Nylon Parachute or 4” by 40”
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Atomic Aggies
New Mexico State University
Payload Summary
The science payload will adhere to all the requirements of the USLI Science Mission Directorate.
The payload will have sensors to measure solar irradiance, ultraviolet radiation, atmospheric
pressure, temperature, and humidity. The payload will also contain four cameras, one taking
video and three taking still shots. The payload will include a GPS unit to provide spatial data and
to provide a tracking unit to aid in vehicle recovery. Two DE0- Nano FPGA Development and
Education Boards will be used to control data collection operations and provide data logging.
Data will be sampled at a frequency of 1Hz from shortly before take-off to landing and there
after sampling at 1 minute for ten minutes after landing. The data will transmit wirelessly from
the vehicle to a ground receiving station where it will be stored and processed on a personal
computer.
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Atomic Aggies
New Mexico State University
II) Changes since PDR
Vehicle Criteria Changes
The main Parachute has changed from a 60” size to an 84” to meet the requirements of the 20ft/s
decent rate, also to ensure a safe descent.
The fins have been changed from a clipped delta shape, to a more trapezoidal shape in order to
provide the drag needed to achieve the required altitude of 5280 feet. This needed to be changed
because the mass of our rocket is about 10 lbs less than the initial CDR design.
Payload Criteria Changes
The payload will be changing its GPS to the BRB900 Telemetry System. The BRB900
Telemetry System consists of a GPS receiver and a RF 900 MHz spread spectrum transmitter
paired with a matching receiver that interfaces through USB at ground station. The receiver will
decode the data, which will show the location of the rocket in real time. The reason for changing
the GPS telemetry system is for the simplicity of its use. The BRB900 comes preconfigured and
ready to run. The XBee-Pro 900 XSC module will be used to transmit the data to the ground
station. The Stratologger will not be included in the design of the payload due to a change in the
GPS. Humidity Sensor, HIH-4030 to HIH-5030 will be used because of power requirements.
Activity Plan Changes
There have been a few date changes in the Gantt chart due to incorrect dates on Gantt chart in the
PDR. Please refer to the updated Gantt chart on page There were no changes to the educational
engagement plan. The outreach plan changes include presenting our team to the media and visits
to local companies for possible sponsorships.
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Atomic Aggies
New Mexico State University
III) Vehicle Criteria
Mission Statement
To explore the world of rocketry and enhance our learning experience as university students by
building a reusable rocket that meets the requirements of the SMD payload and adhering to all of
the safety standards of NAR. We hope to achieve a successful launch and recovery by reaching
an altitude of one mile.
Vehicle Verification Plan and Status
The launch vehicle has been designed to reach an altitude of approximately 5280 ft. and will be
dual deployment. At apogee the rocket will deploy a drogue parachute, and will then descend to
500 ft. where it will deploy a secondary chute to gently place the rocket back on the earth within
a half-mile from where it was launched. The rockets airframe will be constructed from three
separate sections of blue tube 5.5 inches in diameter. This material was chosen because of its
extreme durability, strength, and lightweight properties as well as pricing. Two 12-inch sections
of blue tube coupler will couple the three sections. The nose cone will be made of polycarbonate
with an overall length of 21-inches. The overall length of the rocket will be approximately 9.5
feet. The fins will be made of G-10 fiberglass with epoxy fillets, and then covered by an
additional layer of fiberglass for maximum strength and stability. The fin tabs will be located
around the motor mount between two secured centering rings filled with epoxy in the aft of the
rocket. The motor mount is 14” long with an inside diameter of three inches. All aspects of
launch have been simulated in Rocksim 9. A subscale model has been launched twice, and the
data from those launches has been used to further refine the accuracy of our full scale RockSim
model. The Cd was adjusted from the first launch to better reflect the altitude reached during that
launch, and as a result, our second launch was much closer to the RockSim model’s altitude at
apogee. This data and information gained will better help us satisfy the competitions
requirements and goals.
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Atomic Aggies
New Mexico State University
Verification
Description
SMD 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 at least 2
pictures during descent and 3
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
feet (AGL).
Recording Altitude
•Launch vehicle shall deliver the
payload to an altitude of 5,280
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
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Verification
•Sensors will be interfaced to the DE0Nano FPGA and will be programmed to
take measurements every 5 seconds
following apogee, then every 60
seconds after landing. Programming is
still being done and testing will be
done in the lab to ensure program
takes measurements at the right
increments.
•Cameras will be interfaced to another
DE0-Nano FPGA and will be
programmed to take pictures following
apogee as well as after landing. Testing
of the cameras will be done on the
subscale launch.
•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. Testing will be done in lab.
•We will be doing RockSim simulations
to try to achieve the target altitude.
•We will test fly our rocket and
determine altitude with an altimeter. If
the altitude does not meet our
requirements then weight and/or
motor will be adjusted.
•We will be doing RockSim simulations
to try to achieve the target altitude.
•We will test fly our rocket and
determine altitude with an altimeter. If
the altitude does not meet our
requirements then weight and/or
motor will be adjusted.
•Rotary switches will be used to arm
the recovery bay.
•Our rocket will be designed so that
the recovery bay is completely
independent of the payload, arming
switch will be located on the exterior
of the rocket airframe, and each
arming switch will be six feet above the
base of the launch vehicle.
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Atomic Aggies
Recovery system
shielded
Subsonic launch
vehicle
Stage deployment
Removable shear
pins
Independent or
tethered sections
Capable of being
prepared at site
within 2 hours
Launch ready
configuration
Standard firing
system
No external circuitry
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New Mexico State University
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 electronics shall
be shielded from all onboard
transmitting devices.
•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.
•Launch vehicle shall be capable
of being prepared for flight at the
launch site within 2 hours from
the time the waiver opens.
•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
• Each altimeter will have a Duracell 9
volt battery.
• To avoid inadvertent excitation of
the recovery system by the
transmitting devices, the recovery bay
will be shielded from RF transmitting
with ArgenMesh shielding material.
•We will make sure our motor size is
an L or below to keep it subsonic.
•The altimeter will be used to
determine apogee which will trigger
the Drogue parachute to deploy right
after apogee.
•The main parachute will be deployed
at 500ft.
•Removable shear pins will be used for
the main, and drogue parachute
compartment.
•We will have three tethered sections.
•Drift has been calculated at 468
assuming 15mph wind.
•Payload bay will be designed to easily
slide into rocket body.
•Motor will be assembled by an
experienced level two NAR mentor.
•Batteries will be tested to ensure
longevity.
•A standard 10 second countdown will
be used for all our launches.
•Our rocket will not contain any
external circuitry.
USLI PDR
Atomic Aggies
Data collected
Electronic tracking
device
Motor
Total impulse
Successful launch
and recovery
Prohibitions
Safety checklist
New Mexico State University
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.
•Each team shall use a launch and
safety checklist.
Work on the
project
•Students shall do 100% of the
work on the project.
Mentor
•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.
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•Data will be collected at ground
station and will be analyzed and
reported at launch site.
•The rocket will have a GPS that will
transmit the position of the rocket
using the BigRedBee BRB900.
•We will be using a L789RT Motor
from Gorilla Rocket Motors.
•Total impulse was figured at 3285.197
Newton-Seconds.
•Subscale and full-scale launch will be
done to ensure a successful launch and
recovery before competition.
•Our rocket will not include any of
these items.
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 two
certification from the National
Association of Rocketry.
USLI PDR
Atomic Aggies
Budget
New Mexico State University
•Maximum amount teams may
spend on the rocket and payload
as it sits on pad is $5000 total.
(Included donated components
and materials).
•Our budget officer is keeping records
of all orders and donations to ensure
we don’t go over the $5000 limit.
Flight Reliability and Confidence
The highest degree of accuracy has been maintained throughout all construction of both our full
scale and subscale rockets. By using precise measurement tools (dial calipers) and the proper
machining tools (provided to us by the university’s student workshop). All of our critical
components (main tube, couplers, motor mounts, etc.) have been test fitted and re-test fitted to
ensure a tight fit tolerance.
There will be at least one test launch of the full scale rocket, using an identical back-up rocket.
Both will be built to the same tight tolerances and specifications as discussed above. The data
gained from this launch will help us to better adjust our RockSim models, as well as verify that
our choice in motor was a legitimate one.
All main air-frame components have been cut (as per both our RockSim and SolidWorks
models) and mocked together as of 1/24/12. The fin can construction will take place on 1/27/12
and the final design will be complete by 1/30/12.
The fin shape has been revised, given that our rocket has been re-evaluated and determined to be
about 10 lbs less than our initial design. Our initial plan was to use a clipped delta shape, but as
our rocket lost weight, more drag was needed. As a result, we have chosen to go with a
trapezoidal wing shape for our final design. The added drag will help us better achieve our 5,280
foot altitude goal.
All fin, bulkhead, and structural materials have been chosen for their specific strengths and
weight combinations. The fins will be constructed of G10 fiberglass because it is lightweight and
strong, yet easily cut to the desired shape. All bulkheads will be either 3+ ply craft wood, or
aluminum depending on the placement. Again, these materials were chosen for their strength and
weight properties as well as their ability to be cut to specs. The main structural element of the
entire rocket is Blue Tube, once again, chose for its strength and weight. We understand that,
historically, there have been some problems with this material and moisture absorbency and
warping. To prevent this, we will seal it with a resin, both inside and out, as well as a coat of
paint for further protection from the elements. The resin shall also provide a slight increase in
strength for the overall rocket.
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Atomic Aggies
New Mexico State University
All airframe components have been cut using only the sharpest saws to provide the cleanest cuts
possible. All measurable safety precautions were taken during cutting, and all parts were
measured twice before any cuts were made. The parts were then test fitted for flushness/flatness
and sanded down as needed to obtain the closest tolerance possible. All load paths will be
secured with heavy duty epoxies, and screws where needed. Shear pins will be used at all points
where the tube needs to separate to ensure they stay together before any deployment events.
The motor mount and fin can design is a 14 inch long motor mount tube, with a fin through the
body design (i.e. the fins will be slid in from the sides of the tube to ensure they do not move
laterally up or down the rocket body). This will ensure that entire fin can/motor mount assembly
is secure from any movement in any direction. The motor retention system will use an aeropack
quick-change retainer, with the flanged section secured to the airframe by screws secured to
threaded inserts on the lower centering ring.
In an effort to lower the weight, many adjustments have been made to decrease the weight from
an initial loaded weight of 32 lbs, to the current weight of 29 lbs. We have weighed every
possible component up to this point (all cut tubes, nose cone, fins, motor with and without
propellant, payload, and recovery components). Because we have physically weighed every
component, we are fairly confident in our final mass estimate. In doing so, we have been able to
more accurately build our RockSim models, which in turn, have allowed us to settle on a final
motor choice, as well as fin design choice. Every ounce is critical to the altitude requirements of
the competition. In just the transition from the 32 lb mass to the current 29 lb mass, our entire fin
shape needed to be changed to induce more drag and bring our rocket down a few hundred feet.
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New Mexico State University
Atomic Aggies Rocket Model
Figure 1 : Assembled Rocket
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Figure 2 : RockSim
Model and
Specifications
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Atomic Aggies
New Mexico State University
Subscale Flight Results
On January 21, 2012 Atomic Aggies performed a successful subscale test flight at the
Alamogordo New Mexico, Launch Site. The rocket was scaled down to ½ of the full scale
rocket. The recovery system was designed to be similar to the full scale bay but scaled down in a
smaller model with the same settings. The deployment for the main parachute was set at apogee
while the drogue parachute was set at 500 feet. ½ inch Tubular Nylon shock cords were used to
connect the parachute to the rocket. The full scale rocket will be using 5/8 shock cords to hold
the weight of the rocket better. A 12-inch drogue parachute was used at apogee and two 24 inch
parachutes were used for the 500 feet altitude setting. The target altitude at apogee was 2640 feet
(1/2 mile). Apogee was determined at 2317 feet with the PerfectFlite Stratologger.
Prior to the January 21st test launch, the subscale rocket was launched with a smaller H motor
(the 2nd launch used an I motor). From that, we used RockSim to adjust our Cd to more
accurately reflect the results of the first launch. We changed the Cd and did repeated simulated
launches until the simulation matched the actual flight data. From this, we were able to simulate
the use of the I motor used on the 21st. As a result, our flight and simulation were within 10% of
one another. We accepted this as a pretty accurate result given that there were some wind gusts
the day of the launch, as well as some drag induced by the use of a washer for a motor retainer.
This will prove to be incredibly useful in our full scale rocket tests.
Recovery Subsystem
Objective
The Atomic Aggies agree to fulfill our mission statement as safely as possible. We will do so by
having a dual deployment recovery system that will deploy at apogee and 500 feet. The purpose
of a dual deployment system is to minimize drifting of the rocket from the Launchpad and to
ensure the safety of spectators. We have taken close precaution on determining our parachute
sizes to insure a safe rocket landing. In order to safely land our rocket, we will test each
component in the whole recovery system.
Parachute sizing and style
The size of the parachute was determined with the assurance of a safe landing for the rocket. We
calculated a safe descent rate to slow down the rocket to 20 ft. /sec. To accomplish the safe
descent rate, a parachute with a diameter of 84 inches was chosen for the main parachute. The
main parachute will deploy at 500 feet before landing. The deployment at apogee will either be
deployed by a drogue parachute with a diameter of 12 inches or a streamer; the weather will
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New Mexico State University
determine which one we will use. We determined to use an elliptical style for both of the
parachutes. The reasoning is the elliptical parachutes are available throughout the market and
they are more stable. The apex vent is a small hole on the top of the parachute that allows small
amounts of air to be released from the top of the parachute thus allowing more stability in the
parachute rather than swinging the rocket from side to side.
Main Parachute Sizing Calculation
𝐒=
𝟐∗𝐠∗𝐦
𝛒 ∗ 𝐂𝐝 ∗ 𝐕 𝟐
𝐦
𝟐 ∗ 𝟗. 𝟖𝟏 𝟐 ∗ 𝟏𝟑, 𝟓𝟓𝟐. 𝟖𝟖𝟔𝟒𝐠
𝐬
𝐒=
𝐠
𝟎. 𝟕𝟔𝟒𝟒 𝟑 ∗ 𝟏. 𝟓 ∗ 𝟑𝟕. 𝟏𝟔𝟏𝟐𝟏𝟔𝟐
𝐦
S=6240.64𝐦𝟐
𝟖∗𝐦∗𝐠
D =√𝛒∗𝐂
𝐝 ∗𝐕
𝟐 ∗𝐫
𝟖∗𝟏𝟎.𝟏𝟕𝟒𝟗𝟖𝟒∗𝟗.𝟖𝟏
D=√𝛑∗𝟏.𝟓∗(𝟔.𝟎𝟗𝟔)𝟐 ∗𝟏.𝟐𝟐
D=1.93521 m= 76.1894 inches
After calculating the above parachute size, we talked with our mentors and they advised
us to use an 84 inch main parachute instead. Due to manufacturers not having a 76 inch
parachute available, we went with the next size up.
Kinetic Energy at all Main Phase
WEIGHT (lbs)
VELOCITY
(ft/s)
KINETIC
ENERGY (ft
lbf)
LAUNCH
29.879 lbs
28.54 ft/s
APOGEE
26.392 lbs
3.54 ft/s
DECENT/DROGUE DECENT/MAIN
26.392 lbs
26.392 lbs
159 ft/s
20 ft/s
378.21 ft lbf
5.1397 ft lbf
10369 ft lbf
164.06 ft lbf
Parachute Packing and Harness
For the packing of the parachute, we will follow the guidelines from the manufactures
instructions provided at www.fruitychutes.com. We have tested the parachute packing with the
half scale launch and feel confident in a safe and fast deployment. The reason why parachute
packing is so important is to insure the parachute can be deployed easily and safely.
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New Mexico State University
To increase the safety for the parachutes, they will be shielded with a Nomex Parachute protector
from the ejection charges. It is a fire-resistant protector cloth that will keep the parachute from
being melted or damaged by the heat. To prevent damage from the ejection charges a Nomex
Shock Cord protector with the length of 58 inches on part of the shock cords will be placed near
the ejection charges. Another safety precaution we will use is inserting dog barf to further protect
the entire recovery system from ejection charges. Dog barf is made to be biodegradable and fire
resistant.
To connect sections of the rocket and to our parachutes we are using a 5/8 inch thick Tubular
Nylon Shock Cord. The shock cords will be tied onto the quick links that are rated for 880lbs.
that will connect onto the U-Bolts on the recovery system and also onto the other ends of the
rocket which are the nosecone/payload and booster. The U-bolts are connected onto a ¼ inch
thick plywood bulkhead that is attached to the electronics bay. The length of the electronics bay
is 12 inches long that serves as a coupler of the rocket. The length of the shock cords will
roughly be three times the length of our rocket. We chose Tubular Nylon for our shock cord
because of the strength, durability, and weight. The ¼ inch thick plywood bulkheads each have a
PVC cap on it to house the black powder and e-matches. The J-Tek e-matches will be connected
by the terminal blocks that are also on the bulkheads.
Avionics
The recovery system will be comprised of two PerfectFlite StratoLogger Altimeters for the dual
deployment system. The two altimeters will be connected independently each having its own
batteries, charges, and electric matches. Having the two altimeters independently connected will
help insure against failure of the first deployment. The main purpose is to have one primary and
one back-up altimeter. The altimeter will be programmed to deploy the drogue or streamer at
apogee and 500 feet for the main parachute. The StratoLogger is a programmable barometric
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New Mexico State University
altimeter that will measure the air pressure surrounding our rocket. Once it detects a change in
pressure referenced from ground and during the rocket flight it will eject the deployment system
by sending current to an electronic match that will ignite the first ejection charge. The second
ejection charge will be ignited in the same manner at an altitude of 500 feet above ground level
to deploy the main parachute. The two PerfectFlite StratoLogger Altimeters will each have its
own power up switch, which will be a Rotary switch that is turned on by using a flat screwdriver.
Using this switch helps insure failure of an unwanted power up. We will be using a 9- Volt
Duracell Battery for the altimeters. We have chosen Duracell Batteries because of its reliability
of connectors.
Having a dual deployment system helps insure a safe recovery of the rocket by deploying two
parachutes. One that will quickly bring down the rocket to a closer recovery range (drogue) and
the other will slow the rocket down to a safe descent rate of 20 ft. /s, keeping the rocket intact,
and prevent damage. To insure a successful deployment of the parachutes we are putting two
redundant PerfectFlite StratoLogger Altimeters. One altimeter will be the primary while the
other will be the back-up. The primary altimeter will be set to deploy at apogee and 500 feet,
while the back-up altimeter will be set to have an apogee delay and at 450 feet. Again these two
altimeters will each have its own ejection charges in case of failure of the other.
Avionics Bay
The avionics bay houses the deployment electronics and protects the electronics from any
damages. There will be two rotary altimeters mounted on the outside of the avionics bay on the
coupler tube that will power up the recovery system. The altimeters will be mounted on a
plywood avionic sled that slides right into the avionics bay. We will be placing (4) static
pressure sampling holes in the airframe. They will be placed at 90 degree intervals around the
airframes circumference. This will minimize the pressure variations due to the wind currents
perpendicular to the rockets direction of travel. The equation we used for four ports:
Diameter * Diameter * Length * 0.0008 = Four Ports, each hole
5.5” * 5.5” * 12” * 0.0008 = 0.2904” each hole size
The avionics sled lies on two threaded rods that attach to the bulkheads to safely be protected
from the pressure of ejection and remain intact during the flight. The avionics in the bay will be
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New Mexico State University
shielded by a silver mesh fabric known as Argenmesh. This material provides level grounding,
static discharge, electric field shielding, and radiofrequency shielding with nearly 50 dB from
100MHz to over 3 GHz and a surface conductivity of <1 ohm per square. The Argenmesh will
be epoxied to the inside of the bay. The batteries will be on the backside of the plywood and
housed in a casing that will insure no movement during the flight. The length of the bay is 12
inches long that serves as a coupler and compartment for the electronics. The bay has two
bulkheads connected at each end of the tube that will connect the terminal block to the altimeters
by the electric matches. The electric matches will then ignite the ejection charges and insure
deployment. The bulkheads have eye-bolts mounted to them to connect the quick links and shock
cords for the parachutes.
The figure below shows an overview of the components used for the recovery system in the
rocket body.
E-bay Housing
Description
E-bay Compartment
PerfectFlite StratoLogger
Altimeter
Duracell Batteries
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Quantity
Weight
1
2
994.4 grams
12.76 grams (each)
2
46 grams (each)
USLI PDR
Atomic Aggies
J-Tek ematches
PVC CAPS
Terminal Blocks
Rotary Switch
New Mexico State University
4
2
2
2
Total Weight of Bay
11 grams (each)
7 grams (each)
1147.92 grams
Altimeter Testing
The 2 PerfectFlite Stratologger altimeters we chose to use for our rocket were tested among
several other altimeters using a jar. These altimeters were marked to identify them from others
and all were put into the jar. We then put a syringe into the top of the lid to depressurize the jar,
simulating a rocket launch. Once the syringe has reached its maximum point (apogee), we than
opened the jar slowly making sure not to interfere with the MachLock feature and spike rejection
from the altimeter. Once opened, we then removed all altimeters to than listen and record the
altitudes and compare them with each other. The altimeters with the closest recorded altitudes
were the ones chosen to be reliable. Thus we used both altimeters when we launched our
subscale model. Based on our successful flight we will use these again for our full scale model.
Ejection Charge and Deployment Testing
On January 7, 2012 we performed an ejection charge and deployment test at the Waterfalls
Launch Site in Las Cruces, NM. We decided to perform an actual test flight to make sure the
ejection charges would work. The ejection charges work fine, except a little delay on the main
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parachute deploying. The reasoning is not putting enough black powder. Thankfully, we have
performed this test and fixed this issue for the subscale launch flight.
Ejection Charge Sizing Calculations
With help from the website info-central.org we were able to decide to use 4 grams of 4F Black
Powder for both compartments of the parachutes.
C * D * D * L = grams of BP Where:


C - one of the values listed below
o 0.002 = 5 psi
o 0.004 = 10 psi
o 0.006 = 15 psi
o 0.0072 = 18 psi
o 0.008 = 20 psi
 D = airframe diameter, in inches
L = length of the cavity to be pressurized, in inches
Main Parachute Charge Sizing
0.006 * 5.5 * 5.5 * 20 = 3.7 grams
Here we used a higher pressure because of the weight of the main parachute. The force
required to pressurize the main parachute compartment is 363 Lbf.
Drogue Parachute Charge Sizing
0.004 * 5.5 * 5.5 * 30 = 3.7 grams
Since the drogue parachute is lighter in weight we went with a lower pressure. The force
required to pressurize the drogue parachute compartment is 242 Lbf.
Risks
Risk
Probability of Risk
Result
Parachutes fail to
deploy
Low
Rocket Damaged
Altimeter Fails
Early Deployment
Low
Medium
Deployment Fails
Rocket Damaged,
Damage to others
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Failure Prevention
Method
Redundant Altimeters
Redundant Altimeters
Kill-Switch
USLI PDR
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Damages to
Parachute
Low
Rocket Damaged
Parachute Protectors,
Correct Parachute
Packing
Igniters Fails
Medium
Rocket Damaged,
Deployment Fails
Redundant Altimeters,
Charges, E-matches
Shock Cord
Failure/Tangling
High
Damaged Rocket, Un Correct Packing, Shock
proper Landing
Cord Protectors
Inaccurate
calculations of
decent rate
High
Possible rocket
damage; risk to
individuals on
ground
Verify the testing of the
recovery system and
redundant testing of
calculated weight and
numerous simulations
Parachutes
inadequately
protected
Medium
Damages to
parachute; rocket
damage
Weak charge
Medium
Parachute does not
deploy; rocket
damage/loss
Faulty battery
connections
Medium
Weather
High
Failure to deploy;
altimeters lose
power
Rocket damage;
change of decent
rate; possible injury
to
individuals/property;
Calculate the amount of
protection needed for
the size of charge used;
redundant ground
testing
Calculate necessary
battery voltage; check
batteries with a volt
meter
Battery casing
inspection
Check conditions before
flight; simulation of the
rocket in different
environments
Below is a list of tests that will be performed during the building of our rocket and in
preparation for any flights. Each test will be prepared by the recovery system group to ensure
the safety of the rocket.
Test 1: Avionics
 The purpose of testing the avionics is to insure the dual deployment. A test will take
place using the instructions from the manufacturer to ensure proper results. Another
test will be run for the pressure sensor by attaching LEDs to the altimeter to indicate
deployment of main and drogue. During this test there will be no use of black powder
ejection charges. The main purpose of this test is to insure the wiring, battery, and ePage | 21
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matches are correct. Any indications of failures will results in retesting or replacement
of the altimeter.
Test 2: Main and Drogue Charges
 The main purpose of this test is to ensure the correct amount of black powder utilized
to eject the main and drogue parachute. Tests will be conducted one parachute at a
time by attaching the ejection charge for the main first and then the drogue after that
test. We will lay the rocket down horizontal and make sure nothing is in front of the
nose cone or behind the motor. Once the ejection charge has been connected the
power will be turned on to the altimeter and wait to hear from the beeps that it is
ready. Then a vacuum will be applied to the static sampling port that will trigger the
altimeter. Close attention will be monitored to the force of the ejection and separation.
If by any chance the ejection is unclear our mentor will than apply more black powder.
Once assured a good ejection for the main parachute has taken place the same test will
be administered to the drogue.
Test 3: Parachute Size
 In order to make sure the rocket lands at a safe speed multiple tests will be run using
RockSim.
Once tests have been verified tests will be conducted to all electronics in the electronics bay to
determine they are not damaged and are safely secured. Doing so will make sure the altimeters
are harnessed down on the electronics sled and that all wires are not damaged and are safely
installed. An additional a check will take place to see if the batteries for the altimeters are
locked in the battery compartment and undamaged. Any damage or missing hardware will
result in more in depth look and securing in bay. Below is a list that will be checked by the
recovery team before any rocket flights.
Preflight Recovery Checklist
 Verify all switches are set to safe settings!
 Visually inspect all wiring, terminal screws are tight and wires are secured for altimeter
and connected to correct terminals.
 Check Duracell Battery is attached properly to battery clip and secured and sealed in the
bay.
 Securely connect Shock Cords onto the U-bolts of the avionics bay and to the other two
ends of the rocket (payload/motor). Make sure all recovery harnesses are connected
securely.
 Pack and install drogue and main parachute also with their chute protectors.
 Making sure Switches are still OFF; install ejection charges to PVC caps that you will then
add black powder.
 Connect ejection charge leads to terminal blocks on the avionics bay. Make sure not to
short any wires together.
 Verify rocket is ready with the supervisor of our mentor.
 Power on altimeter with rotary switch. Verify power up sequence with the StratoLogger
Checklist. If error tone is heard, power off altimeter and fix issue.
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
New Mexico State University
Now altimeter is powered on, Keep Everyone Clear since Ejection Charges are Armed.
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Mission Performance Predictions
A successful rocket launch mission will be one that includes the safe delivery of the rocket and all its
components to the desired altitude of 5280ft. During the flight path of the rocket many different
readings will be taken ranging from solar radiation to temperature. The rocket will be dual deployment,
with the drogue chute deploying at apogee and the main chute deploying at 500ft.
Full Scale Altitude, Velocity, Acceleration, and Thrust Curves
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Interfaces and Integration
The payload bay will be inserted into the rocket body by sliding it into the airframe where it will
be configured to match pre-drilled holes in the airframe for the cameras. The cameras will be
attached to a circular structure that will be designed to line up with the holes rocket body. A
piece of Blue Tube coupler will be secured in the rocket body below the payload to hold it in
place. The payload will be mounted on a 5.36” x 18” piece of ½” ply board. To accommodate
the mounting of the cameras and sensors, we will be fitting pieces of Blue-Tube coupler material
split lengthwise around the payload making a 5.36” diameter.
Simulati
on
Engine
Loaded
Max.
Altitude
(Ft.)
Max.
Velocity
(Ft/Sec)
Max.
Acceler
ation
(Ft/Sec/
Sec)
Time
to
Apogee
Velocity
at
Deployme
nt
(Ft/Sec)
Altitude
at
Deployme
nt
(Ft.)
Windage
(Mph)
1
2
3
4
5
L789RT
L789RT
L789RT
L789RT
L789RT
5383.73
5366.93
5308.1
5200.59
5046.23
598.09
598.00
597.73
597.33
596.80
1204.55
1204.55
1204.54
1204.54
1204.53
19.32
19.29
19.18
18.99
18.71
0.03
26.14
55.72
86.63
117.15
5383.72
5366.91
5308.11
5200.59
5046.23
0
5
10
15
20
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Launch Operations
Before any launch the use safety checklist will be enforced to ensure the rocket is safe.
Pre-launch Safety checklist will include:




Structures
1. Nosecone
2. Airframe
3. Fins
4. Rail Buttons
5. Motor Retainer
Recovery
1. Shock Cord
2. Chute Protector
3. Parachute
4. StratoLogger Checklist
a. Power up
b. Flight mode report
c. Main deploy altitude report
d. Last flight altitude
e. Battery Volt report
f. Continuity
Propulsion
Documentation
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1. Signature of completed checklist from a certified NAR mentor for review.
Launch Pad Checklist will include:



Launch Pad
1. Launch Rail
2. Rocket
Propulsion
1. Insert igniter into the rocket motor through the nozzle and install the nozzle cover.
2. Strip 1” – 2” of the wire’s sheath to expose both wire cores.
3. Short LCS circuit by tapping both alligator clips together.
4. Connect one wire core to each alligator clip wrapping the excess wire around the
clip.
5. Before returning to the RSO tent, switch the LCS pad bank “ON” if you are the
last person leaving the area.
Documentation
1. Signature of completed checklist from a certified NAR mentor for review.
Safety and Environment
Risk
Consequence
Prevention
Black powder fails to
ignite.
Black powder ignites
causing explosion.
Motor detaches from
casing upon ignition.
Unsuccessful flight.
Assure Level II NAR Mentor
handles all black powder.
Assure Level II NAR Mentor
handles all black powder.
Test and inspect durability of the
security of casing prior to launch.
Vehicle encounters
damage during test
flights prior to
competition.
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Loss of rocket as well as
possible death or injury.
Possible loss of rocket subsystems as well as
unsuccessful flight.
Damage beyond repair/loss of
rocket.
Have multiple components for
replacement in case of potential
loss.
USLI PDR
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New Mexico State University
Proper motor fails to be
received prior to
competition.
Inability to compete.
Order multiple motors and have
them shipped in advance.
Hazard
Use of black powder
Effect of Hazard
Burns, serious injury, and
possible death.
May cause severe irritation in
eyes and skin. If inhaled, Can
cause irritation of the
respiratory tract.
Possible respiratory failure
due to excess inhalation. May
also cause severe irritation in
eyes and skin
Cuts, loss of limbs, serious
injury, or possible death.
Damage to equipment, or
flying debris.
Mitigation
Assure Level II NAR Mentor
handles all black powder.
Use gloves when using epoxy as
well as safety glasses. Epoxy will
be used in a well-ventilated area.
Use of Epoxy
Use of paint
Use of power tools
Electricity
Burns, shocks
Use of fiberglass
May cause possible abrasions
as well as irritation of the
skin, eyes, and lungs.
Use of proper personal protective
equipment such as safety masks,
goggles, and gloves. Also, use in
well-ventilated area.
Follow manufacturer’s safety
instructions. Do not operate
equipment you have not been
trained to use. Use of all proper
personal protective equipment.
Take all safety precautions when
working with electricity. Keep all
food and drinks away from work
area.
Use of proper personal protective
equipment such as safety masks,
goggles, and gloves at all times.
Team Safety and Awareness
All members of the New Mexico State University rocket team are responsible for ensuring that
all proper safety precautions are met for the duration of this project. If any member feels a
situation is unsafe in any way, shape, or form they will immediately notify their team leader,
safety officer, or mentor of such situation. All members of the Atomic Aggie team will be given
various safety briefings on possible safety hazards and mitigation procedures throughout the
duration of the project, and will be responsible for attending such briefings. Any absence from
such briefings can be made up at a later time and date, if excused through their team leader and
arrangements are made with the Safety Officer to make up any missed briefings. All members
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traveling for the competition will be responsible for completing all necessary safety training by
no later than April 12, 2012.
The Safety Officer for the Atomic Aggies is Christopher Herrera. Mr. Herrera is responsible for
ensuring that all members are properly briefed on laboratory and machine safety guidelines,
materials handling, airspace regulations, safety/risk mitigation precautions, and emergency
response procedures prior to departure.
All members of the NMSU rocket team will be made aware of relevant federal, state, and local
laws regarding unmanned rocket launches and motor handling. Motor and black powder will be
handled by Level II NAR Safety Mentor, John DeMar. Safety measures involving, but not
limited to the proper use of airspace and the regulations involving the launching of different
classes of rockets will be studied by the team. The handling and use of energetic materials will
also be explained to all team members.
In order to ensure proper safety issues and risk mitigation techniques are followed in accordance
with NASA USLI guidelines, the following steps will be taken:
1. A Safety Officer will be appointed. As stated prior, the NMSU rocket team Safety Officer
is Christopher Herrera, who will be responsible for not only the safety of the project, but
also that all team members are properly briefed of all safety issues and risk mitigation
processes.
2. A briefing will be given to all members of the team as it pertains to laboratory and
machine shop safety guidelines, materials handling, risk prevention and safety mitigation.
3. First aid kits will be available in all labs.
4. A team website will be made available, which will include safety documentation and
other relevant information, as it pertains to the project.
5. Safety information, such as Material Safety Data Sheets (MSDS) and component
handling procedures will be posted in all labs, as well as posted on the team website, as
mentioned above. Team members will be made aware of where information can be
located.
6. Above noted information will also be taken along with the team to launch functions to
ensure that proper procedure and precautions are met. Safety information will be used as
primary guidance, but it is up to individual team members to act accordingly and take all
proper precautions under all given situations. Mitigation procedures should be followed
in order to ensure team member safety in certain situations.
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7. All team members will be required to sign a safety agreement stating that they are aware
of the USLI guidelines and codes pertaining to the project. Under this agreement, team
members will also be made aware that they must attend all safety briefings, or make plans
to attend alternate briefings prior to the competition in April. If these briefings are not
attended, then the team member will not be allowed to participate with the team at the
competition.
8. Team members should also be advised to make themselves aware of the following safety
regulations:
a. Federal Aviation Regulations 14 CFR, Subchapter F, Part 101, Subpart C
(involves use of airspace).
b. NFPA 1127, the National Fire Protection Association code for High Power
Rocketry (involves fire prevention regulations and guidelines for high power
rockets).
c. Handling of energetic materials such as black powder, ammonium perchlorate
composite propellant (APCP), E-matches, and igniters.
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IV) Payload Criteria
Testing and Design of Payload Experiment
The payload fulfills the requirements of the Science Mission Directorate by measuring
temperature, pressure, relative humidity, solar irradiance and ultraviolet radiation. There will be
an altimeter for redundancy. The payload bay will be located below the nosecone with the light
detection circuitry and associated hardware will be located within the nose cone. The payload
will be mounted on a 5.36” x 18” piece of ½” ply board. To accommodate the mounting of the
cameras and sensors, we will be fitting pieces of Blue-Tube coupler material split lengthwise
around the payload making a 5.36” diameter. Brackets will be placed inside the payload
attaching the coupler to the ply board to allow access in to the payload. To ensure accurate data
will be gathered, ventilation holes will be added to the rocket body where payload bay is located.
The cameras will be mounted to the Blue-Tube structure around the payload. The cameras on
this structure will be aligned with holes on the exterior of the airframe. Two cameras will be on
side on of payload and two will be on side two of payload equidistant from each other. 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 FPGA boards will be mounted to the plywood by screws. One FPGA board will be
controlling the sensors while the other will be controlling the cameras. The DE0-Nano will each
be powered by Nickel metal hydride batteries at 4.8volts at 800 mA. A break wire will be
hooked to the DE0-Nano to detect liftoff and power up the payload.
The sensors will be placed on prototype board and mounted to the plywood inside the payload
bay then wired directly to the DE0-Nano. The ultraviolet sensor and solar irradiance sensor will
located in the nose cone with wires attaching down to the payload bay to communicate with the
DE0-Nano FPGA board. The GPS will be located in the nose cone with the ultraviolet sensor
and solar irradiance. The transmitter will be located in the payload on side two of the plywood
and attached to DE0-Nano board on side one away from sensors to address noise. Payload
diagram is shown below.
Sensors have been interfaced to the DE0-Nano FPGA. Data has been written to memory and read
back out to the LED’s on a DE2 FPGA to be analyzed. Testing is still being conducted for
further analysis. The next step is to transmit the data wirelessly to the receiver.
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Altimeter
Ply-board – side one
oneone
Ss
Ply-board – side two
twoononeone
Ss
Payload Diagram
Plywood dimensions: 5.36” x 18” x ½”
DE0-nano: 49 mm X 75 mm
Two sensors inside payload bay: 1 inch square
Xbee transmitter: 34.14 x 24.38 mm
UV/ irradiance sensors located outside payload bay in the nosecone
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The requirements of the SMD payload are to measure pressure, temperature, relative humidity,
solar irradiance and ultraviolet radiation. Our program will consist of multiple clocks to fulfill
the requirement of retrieving data every 5 seconds during flight and every 60 seconds after
landing for ten minutes. The cameras will be connected to a DE0-nano board that will have a
HDL program that sends out a clock pulse to each camera to capture pictures and video. 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. Multiple cameras will
be located to take the pictures portraying the sky toward the top of the frame and the ground
toward the bottom of the frame.
Each payload team member has a specific duty to perform. Duties are to include attending
meetings, and performing tasks that are given to them. Communication skills between team
members needs to be at its best to get overall task completed in a timely manner. 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 a blow dryer on it 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. Cameras have been tested with a HDL program
that sends pulses to the camera to first turn on the camera than another pulse every 1 or 2
seconds to take pictures. 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. Testing of the components will be
completed in lab along with the whole payload bay circuit. Full scale launch testing will also be
done 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 a prototype
board 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 lenses with the holes that are in 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.
Component
Precision
BMP085
+/- 1% to +/- 1.5 depending on pressure and
temperature
HIH-5030
Repeatability +- .5%
Accuracy +- 3%
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Camera/Video
New Mexico State University
720 x 480 resolution image format
1280 x 960 resolution camera format
Below is the pin layout and connections for the first DE0-Nano board.
Below is the pin layout and connections for the second DE0-Nano board.
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FPGA – A DE0-Nano Development and Education Board by Terasic will be
programmed to read the sensors at a frequency of 1Hz. The sensors will be connected to
the GPIO pins shown above. The two DEO-Nanos will each be powered by Nickel metal
hydride batteries at 4.8volts at 800 mA.
Temperature/Pressure - The temperature and pressure will be measured by BMP085
digital pressure sensor. The BMP085 has a serial I2C interface which makes it easy to
integrate with the FPGA. Altitude can also be calculated by using the pressure
𝟏
measurement with the following equation: Altitude = 𝟒𝟒𝟑𝟑𝟎 ∗ [𝟏 −
𝑷 𝟓.𝟐𝟓𝟓
(𝑷𝒐)
].
The
precision of the BMP085 is; +/- 1% to +/- 1.5 depending on pressure and temperature.
Humidity - HIH-4030 to HIH-5030 from Honeywell will be used to determine humidity.
The HIH-4030 is a covered integrated circuit humidity sensor that uses a laser trimmed,
thermoset polymer capacitive sensing element with on-chip integrated signal
conditioning and near linear output.
Cameras - The camera that will be used is the 1280*960 HD Mini key chains Spy
Camera Video. The payload will consist of four cameras to take two pictures during
descent, and three after landing. One video camera will be in operation throughout the
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New Mexico State University
entire flight. There will be additional holes located in the payload bay and rocket body
where the cameras will be mounted to fit in order to take pictures. This camera was
picked for its small size and the high definition resolution. The camera takes still pictures
as well as video. Precision of the cameras are as follows 720 x 480 resolution image
format 1280 x 960 resolution camera format.
Solar irradiance and ultraviolet radiation - The circuit will be built using a FDS100
photodiode for light detection and an OP27 low impedance operational amplifier to
convert the output current of the photodiode to a voltage
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UV/ irradiance sensor housing
GPS - The BRB900 Telemetry System consists of a GPS receiver and a RF 900 MHz
spread spectrum transmitter paired with a matching RF receiver that interfaces through
USB at ground station. This system operates on 900 MHz radio band that is license free.
This unit has a power output of approximately 100mW; along with a maximum range of
6 miles. The transmitter dimensions are as follows: 1.25” wide x 2.85” long, excluding
transmit antenna and battery.
The Antenna to the GPS is as follows: Reverse Polarity SMA, 3dbi gain, approximately
4.25” long. The GPS RF Transmitter: 100mW, 900MHz Spread Spectrum. Receive
Current: 115mA. Transmit Current: 315mA. GPS Power Supply uses: Single cell
Lithium Poly battery (3.5V to 4.2V). Range: 6 miles (line of sight). Data is transmitted at
9600 baud and approximately 1200 data points can be saved to the on board non-volatile
memory. The GPS will then compute the position of the transmitter using
geosynchronous satellites and will transmit this information to the receiver via RF data
link. To read the data received we will use software called Trimble Studio. The receiver
will decode the data, which will show the location of the rocket in real time.
Transmitter/Receiver –
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The XBee-Pro 900 XSC module will be used to transmit the data to the ground station.
Payload Concept Features and Definition
Under the direction of the Science Mission Directorate (SMD), the Atomic Aggie Rocket will
contain an atmospheric payload to measure air pressure, temperature, humidity, solar irradiance
and ultraviolet radiation. There will be four cameras around the circumference of the coupler
material aligning with holes in the rocket body in order to take clear pictures. There will be a
GPS to locate the rocket which contains its own transmitter and receiver pair. There will also be
a transmitter to transmit the data gathered from the sensors.
The main challenge of the payload is the integration of the sensors with the DE0-Nano board. It
requires understanding of a hardware description language (HDL) to successfully program the
board. Understanding and interpreting results is a necessity to report final data gathered from the
payload, therefore studying the data sheets and learning about analog to digital conversions will
be done. The internal memory of the DE0-Nano will be used to store the data gathered from the
sensors. Another DE0-Nano will be programmed to control the cameras. The two DE0-nanos
will each be powered by Nickel metal hydride batteries at 4.8volts at 800 mA. DE0 Nano FPGA
into micro controller and data logger.
Our HDL program will allow the board to retrieve values form the analog to digital converter,
store the values in memory, read back the stored value and send it to a serial output pin to be
used by the transmitter. There is a select channel that uses an “if” statement in the coding. The
channel selection is being incremented by a clock that we have program for the right time period.
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When that channel is selected the analog to digital converter reads one bit at a time from the
channel it is on at a rate of 50 kSPS to 200 kSPS to gather the data from each sensor. As for
digital sensors we will use existing input pins that will accept a digital. Once the data has been
read it will be then be stored to memory. When the flight has completed, it will then go through
its reading process and be transmitted to our ground station. A case statement is acting as our
state machine to accomplish each requirement for the SMD payload.
Another challenge is designing and building a custom Ultraviolet and solar irradiance sensor. A
plano-convex lens with a focal length of 75mm will focus the sunlight on the detector. The lens
will be mounted in an aluminum lens tube with the detection circuit built into the bottom. The
focal assembly will keep the system rigidly mounted in the vehicle during flight and also shield
thermal noise from polluting the detector. The lens is coated with a band pass filter, allowing
absorption of radiation in the 290-370nm region.
The circuit will only directly measure radiation in the narrow range of 290-370nm. The total
solar irradiance measurement will be interpolated from the blackbody characteristic curve of
600K by integrating the known function over the wavelengths measured. The nosecone will
consist of a clear tip which will allow a 360 degree viewing angle and allow unhindered solar
radiation to strike the lens and provide for a more accurate reading than if the detector was
simply in the side of the airframe.
Testing the photo sensor will be accomplished using ultra violet LEDs of known bandwidth and
output power. The irradiance measurement will be determined by comparing the output to a
pyrometer.
Science Value
The main purpose of the payload is to gather data on the temperature, pressure, humidity, and
light intensity with in the SMD payload requirements. There is a relationship between the
temperature and pressure where altitude can be calculated. As the altitude changes, so does the
temperature and pressure. Correlating our measurements to the altitude of the GPS will prove
that this is actually the case. The GPS will be used to track the position of the rocket and the
camera and 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.
Payload Verification
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USLI PDR
Atomic Aggies
New Mexico State University
Risk
Consequence
Prevention
Payload data does not
match projected data.
Un-interpretable data
Thoroughly test payload data
before launch
Damage to payload
during test flight
Broken components
Have extra components ready to
rebuild. Secure payload and
components tightly.
Battery failure
No power to DE0-Nano, therefore
no measurements will be taken.
Testing will be done to
determine the total life of
batteries to ensure that batteries
are able to last.
Damage during final
launch
Components could be damaged or
come loose.
Secure payload and components
tightly.
Airframe becomes
loose
Data will be compromised and
camera holes will be unaligned.
Make sure there is a way to
tightly secure the payload bay
where it cannot come loose.
Safety and Environment (Payload)
Hazard
Use of solder and
solder iron
Use of Nickel metal
hydride batteries
Use of Epoxy
Page | 40
Effect of Hazard
Burns, inhalation of toxic fumes.
Mitigation
Follow safety rules concerning
the use of solder and solder
irons. Use non lead solder.
Exposure to the ingredients
Battery will not be opened or
contained within or their
burned. Batteries will be placed
combustion products could be
away from the motor of the
harmful.
rocket.
Contents of an open battery can
All safety precautions will be
cause respiratory irritation.
followed when using Nickel
Hypersensitivity to nickel can cause metal hydride batteries.
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, Use gloves when using epoxy as
and skin. If inhaled, Can cause
well as safety glasses. Epoxy
USLI PDR
Atomic Aggies
New Mexico State University
irritation of the respiratory tract.
Use of power tools
Cuts or other injuries, damage to
equipment, or flying debris.
Electricity
Burns, shocks
Page | 41
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.
USLI PDR
Atomic Aggies
New Mexico State University
V) Activity Plan
Budget plan
Electronics Recovery System
Description
Sky Angle Classic II Parachute
Rail Buttons
Drogue Chute
StratoLogger Altimeter
Black Powder
Batteries
Nomex Chute Protectors
Shock Cord
Shock Cords Protector
Electronics Bay
Toggle Switches
Quantity
1
2
1
2
1
9
2
24
4
2
4
Unit Cost
99.00
3.07
39.10
35.95
20.00
2.50
6.37
1.10
12.95
54.95
0.88
Cost
99.00
6.14
39.10
71.90
20.00
22.50
12.74
26.40
51.80
109.90
3.32
Quantity
2
5
2
1
1
1
1
1
1
1
1
2
1
2
1
1
3
Unit Cost
59.00
14.99
79.95
20.00
19.99
16.93
24.95
9.95
66.95
4.95
299.00
2.50
104.25
13.10
4.49
22.74
4.31
Cost
118.00
74.95
159.90
20.00
19.99
16.93
24.95
9.95
66.95
4.95
299.00
5.00
104.25
26.20
4.49
22.74
12.93
1
75.00
75.00
Pay Load
Description
DE0-Nano
Key Chain Camera
Alt15K Altimeter
Temperature
Pressure Sensor
Humidity/Temp Sensor
XBee USB (Receiver)
XBee Explorer(Receiver)
XBee Pro 900 Transmitter
Interface Cable
BRB900 GPS
Batteries
Fiberglass Sheets
Photodiode
Op-amp
RF shielding
Memory Cards
Miscellaneous
(resistors, cables, etc.)
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USLI PDR
Atomic Aggies
New Mexico State University
Design
Description
Nose Cone
Centering Rings
Tube coupler
Bulkhead
Flight Electric Bulkhead
Quick Links
Body Tube
Forward Rail Button
G-10 Sheets
Aeropoxy Adhesive
Fiberglass Cloth
Motor Mount
Fin Set
Aft Rail Button
Aft Centering Ring
Grand Total
Page | 43
Quantity
1
5
1
1
1
4
1
1
3
1
1
1
1
1
1
Unit Cost
59.65
7.00
55.95
15.01
15.01
3.75
56.95
4.43
30.00
42.75
9.05
29.95
72.01
4.43
28.01
$1599.38
Cost
59.65
35.00
55.95
15.01
15.01
15.00
56.95
4.43
90.00
42.75
9.05
29.95
72.01
4.43
28.01
USLI PDR
Atomic Aggies
Timeline
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New Mexico State University
USLI PDR
Atomic Aggies
New Mexico State University
Educational Engagement:
The Atomic Aggies did an educational engagement with the middle school and high school aged
kids of A. Fielder Memorial Safe Haven. Quest model rockets were built and launched. All
flights were successful although some of the payloads did not survive (egg).
The NMSU Atomic Aggies will team up with the local SEMMA instructors and the local
National Association of Rocketry club, FLARE to do class workshops in their after school
programs. The workshops will consist of team members helping middle school children build
Advanced Egg-lofter kits that Mentor Thomas Kindig from FLARE designed by using Rocksim.
The Advanced Egglofter Light utilizes lightweight components to produce a rocket which will
launch and recover a standard weight medium hen’s egg in a safe manner. The rocket is designed
for and Estes D12 motor. This project presents SEMMA students with challenging construction
project which includes computer modeling and instruction on basic rocket flight dynamics. All
modeling software and kit design components are contained on memory sticks to be distributed
to the teams. The modeling software is Open Rocket. The program may be run on any Windows
computer and does not require software installation on the computer. The Atomic Aggies team
and FLARE educators will guide students through the project in two to three one hour sessions.
The Advanced Eggloft Rocket Light (LT)
The Atomic Aggies will also be assisting with SEMMA rocket launches as well as additional
hands on activities in March at a commemoration of the 40th Anniversary of the Apollo 16
mission on March 9th, 2012 at the New Mexico State University campus. This event will
celebrate the 40th anniversary of the Apollo 16 mission. It is estimated that there will be over
1000 children present. (See Apollo40.org)
Atomic Aggies teamed up with the local NAR organization FLARE, for lessons in basic
rocketry. Team members attended a rocket launch hosted by FLARE. Level one certified
members got additional experience building HPR rocket motors while the rest of the team
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USLI PDR
Atomic Aggies
New Mexico State University
observed. The recovery team learned how a dual-deployment altimeter in a payload bay is
expected to perform in flight. They armed and packed an altimeter prepared by a FLARE
mentor. The team learned safety, rocket handling, and launch procedures required for an HPR
launch under NAR safety guidelines.
Outreach
Local newspaper, Las Cruces Sun News was contacted to announce our team in participating in
the University Launch Initiative.
Atomic Aggies plan to go to local business in acquiring sponsors for our team to help with funds
for travel.
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USLI PDR
Atomic Aggies
New Mexico State University
VI) Conclusion
In conclusion, the Atomic Aggies will work hard for a successful mission. The timeline was put
in place to ensure that all milestones in the project are achieved. In order to accomplish this,
team members will work on the USLI project though all school breaks. All operations of the
rocket will be tested thoroughly to guarantee a successful flight. Safety will be our number one
priority, therefore all safety rules and precautions will be followed and a check list will be used
in all launches.
The Atomic Aggies Team has understood the importance of teamwork and leadership.
We feel that we have accomplished each task effectively and efficiently. The team members
have shared their encouragement, competency, efforts, knowledge, skills, financial
responsibilities, resources, and expertise in the challenge of accomplishing our ultimate goal,
which is to comply with a complete, and successful high powered model rocket to all
specifications, and expectations the USLI Program.
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