NASA USLI PDR
Atomic Aggies
Submitted by: New Mexico State University Rocket Team
November 28, 2011
USLI PDR
Atomic Aggies
New Mexico State University
Contents
I) Summary of Preliminary Design Report ...........................................................................................3
Team Summary ..............................................................................................................................3
Launch Vehicle Summary ................................................................................................................3
Payload Summary ..........................................................................................................................4
II) Changes since Proposal ..................................................................................................................5
Vehicle Criteria Changes .................................................................................................................5
Payload Criteria Changes ................................................................................................................5
Activity Plan Changes .....................................................................................................................5
III) Vehicle Criteria .............................................................................................................................7
Mission Statement .........................................................................................................................7
Preliminary Vehicle Design .............................................................................................................7
Atomic Aggies Rocket Model ..........................................................................................................9
Preliminary Recovery System Design ............................................................................................ 10
Vehicle Verification Plan and Status .............................................................................................. 13
Mission Performance Predictions.................................................................................................. 14
Interfaces and Integration ............................................................................................................ 15
Safety and Environment ............................................................................................................... 15
Team Safety and Awareness ......................................................................................................... 15
IV) Payload Criteria .......................................................................................................................... 18
Selection, Design, and Verification of Payload Experiment ............................................................ 18
Verification .................................................................................................................................. 19
Payload concept Features and definition ...................................................................................... 22
Science Value ............................................................................................................................... 23
Safety and Environment ............................................................................................................... 23
V) Activity Plan ................................................................................................................................ 25
Budget plan.................................................................................................................................. 25
Timeline ....................................................................................................................................... 27
Educational engagement .............................................................................................................. 28
VI) Conclusion .................................................................................................................................. 30
Page | 2
USLI PDR
Atomic Aggies
New Mexico State University
I) Summary of Preliminary Design Report
Team Summary
Team Name:
Location:
Atomic Aggies
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 527.0639 oz. and the unloaded weight is 407.9085 oz.
Motor Specifications:
Engine
Diameter
Manufacturer Class/Model (mm)
Length
(in)
Burn
Time
(s)
Animal Motor
Works
L777WW
75
19.5669
4.05
3136.622
774.475
4819.72
Gorilla Rocket
Motors
L789RT
75
19.5669
4.17
3285.197
787.817
5383.66
Animal Motor
Works
L900RR
75
19.5669
3.79
3440.907
907.891
5719.96
Recovery System:
Page | 3
(N-s)
Avg.
Thrust
(N)
RockSim
Altitude (ft)
Impulse
USLI PDR
Atomic Aggies





New Mexico State University
Dual Deployment
o Two PerfectFlite StratoLogger Altimeters
Main Parachute Descent Rate=20 ft./s
Main Parachute Type: Classic II (SkyAngle) 60”
Drogue Descent Rate=208ft./s
Drogue: 12” Nylon Parachute or 4” by 40”
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 still cameras and one video camera and a
GPS unit to provide spatial data and to provide a tracking unit to aid in vehicle recovery. The payload
layout will include two DE0- Nano FPGA Development and Education Boards to control data collection
operations and provide data logging. Data will be sampled at a frequency of 1Hz from shortly before
take-off to 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.
Page | 4
USLI PDR
Atomic Aggies
New Mexico State University
II) Changes since Proposal
Vehicle Criteria Changes
Nose cone was changed from conical to Ogive in order to adjust the aerodynamics of the rocket.
The second section of the rocket or “payload” section was separated from the rest of the rocket
and joined by a coupler that will be attached by shear pins to accommodate the black powder
charge that was added so that none of the electronics are interfered with. The electronics
section was also separated and a two in section was added to the center of the rocket for easy
access to the electronics in the components section. One of the centering rings was removed in
order to reduce weight.
Parameter
Main Parachute
Deployment Height
Drogue Deployment Height
Drogue Parachute Size
Electronics Bay size
Proposal
Not Specified
PDR
500 feet
Apogee
Not specified
Not specified
Apogee (within 1280 feet)
12 inch
16 inch
Payload Criteria Changes
Parameter
GPS
Temperature/Pressure
Humidity
Cameras
Solar irradiance and
ultraviolet radiation
Transmitter/Receiver
Proposal
Not Specified
Not Specified
Not Specified
Not Specified
Not Specified
PDR
Parallax RXM-SG
BMP085
HIH-44330
1280*960 HD
Circuitry includes:
FDS100
OP27
Not Specified
TXM-900-HP3-SPS
RXM-900-HP3-SPS
Activity Plan Changes
Educational
Engagement
Proposal
PDR
Lynn Middle School
Science Night
Oct. 5th set up an activity booth at Lynn
Middle Schools Science Night.
Atomic Aggies did attend and set
up an activity booth for the
Page | 5
USLI PDR
Atomic Aggies
New Mexico State University
SEMMA
Team up with SEMMA after
school program
Egg-lofter kits
Apollo 40 Activity
Additional educational
outreach activity
N/A
Atomic Aggies learning
experience
N/A
Page | 6
Science Night and was able to
reach over 100 middle school aged
children. The activity did not
count due to the early date.
Atomic Aggies still plan to team up
with SEMMA after school
programs as well as go into the
classrooms to give workshops to
the students in how to build Egglofter rockets. Once built, the
team will assist the students with
the launch that will take place for
the 40th Anniversary of the Apollo
16 mission.
A. Fielder Memorial Safe Haven
activity- Atomic Aggies will help
the children build and launch
small model rockets.
Atomic Aggies will team up with
the local NAR organization FLARE
for lessons in basic rocketry.
Team members attended a rocket
launch hosted by FLARE.
USLI PDR
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, collecting atmospheric data, safely returning to the surface, and
transmitting and receiving the recorded data.
Preliminary Vehicle Design
1
2
3
4
5
6
7
8
9
Requirement
Payload
Humidity,
Temperature,
pressure, solar
irradiance and UV
radiation data
acquisition
5 Pictures
Description
Verification
Status
Acquired sensors(see payload
criteria for exact devices)
Repetitive testing and
analysis of data
On-going
Multiple cameras
On-going
Stored Data
Acquired cameras(see payload
criteria for exact model) and
orientation maintained
SDRAM on Nano Board
On-going
Transmit wirelessly
GPS
Altitude 5,280
LINX transmitter/receiver
RXM-SG GPS
Prelaunch
Record and store readings
to memory and compare to
reference values
Ground testing
Ground/PC testing
Stratologger Altimeter
Recovery System
Shielding Recovery
System
Subsonic limitation
Recover/Reusable
See recovery criteria
Ground and test flight
Parachute
deployment
Removable Shear
Pins
Tethered Sections
kinetic energy
Page | 7
On-going
On-going
Mid
March
On-going
Motor size
Vehicle Design
On-going
On-going
Altimeter controlled
L size preventing supersonic
Pre competition test
Launch
Ground and test flight
Recovery Design
Ground and test flight
On-going
Calculations confirm limitations
Ground and test flight
On-going
On-going
USLI PDR
Atomic Aggies
10
11
12
13
Competition flight
readiness
Collection and
Analysis of data
Tracking
Approved NAR
Motor
Page | 8
New Mexico State University
Time limitations on setting up
Pre-Launch test
On-going
Computer software analysis
Compare expected results
On-going
GPS system
L class motor
Ground and test flight
On-going
On-going
USLI PDR
Atomic Aggies
New Mexico State University
Atomic Aggies Rocket Model
Figure 2 : Assembled Rocket
Figure 1 : Exploded view
Figure 3 : RockSim Wireframe
Page | 9
USLI PDR
Atomic Aggies
New Mexico State University
Preliminary Recovery System Design
A dual deployment recovery system was agreed upon by our team to be used in the rocket.
The purpose of this is to minimize drifting of the rocket from the Launchpad and to ensure the
safety of spectators. The size of the parachute was determined with the assurance of a safe
landing for the rocket. To slow down the rocket to 30ft./sec, a parachute with a diameter of 60
inches was chosen.. The main parachute will deploy at 500 feet before landing. The
deployment of apogee will either be deployed by a drogue parachute with a diameter of 12
inches or a streamer. When the deployments of the parachutes occur the avionics bay will be
tethered to the other sections of the rocket by an inch thick Nylon Shock Cord.
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
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.
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.
The avionics bay houses the deployment electronics and protects the electronics from any
damages. The altimeters will be mounted on a plywood avionic sled that slides right into the
avionics bay. 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 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 eyebolts 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.
Page | 10
USLI PDR
Atomic Aggies
New Mexico State University
E-bay Housing
Description
Quantity
E-bay Compartment
PerfectFlite StratoLogger
Altimeter
UltraLife Lithium Batteries
Weight
1
2
994.4 grams
12.76 grams (each)
2
59.534 grams (each)
Total Weight of Bay
1139.0798 grams
Risks
Risk
Probability of Risk
Parachutes fail to
deploy
Altimeter Fails
Early Deployment
Low
Page | 11
Low
Medium
Result
Rocket Damaged
Deployment Fails
Rocket Damaged,
Damage to others
Failure Prevention
Method
Redundant Altimeters
Redundant Altimeters
Kill-Switch
USLI PDR
Atomic Aggies
New Mexico State University
Damages to
Parachute
Low
Rocket Damaged
Igniters Fails
Medium
Shock Cord
Failure/Tangling
High
Rocket Damaged,
Deployment Fails
Damaged Rocket,
Un proper Landing
Parachute Protectors,
Correct Parachute
Packing
Redundant Altimeters,
Charges, E-matches
Correct Packing, Shock
Cord Protectors
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 ematches 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.
Page | 12
USLI PDR
Atomic Aggies
New Mexico State University
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 24-inches. The
overall length of the rocket will be approximately 10.5 feet. The fins will be made of G-10 fiberglass with
epoxy fillets, and then covered by an additional layer of fiberglass for maximum 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 24” long with an inside diameter of three inches. All aspects of
launch have been simulated in Rocksim 9, A sub scaled model will be launched in order to obtain data
that we will analyze in order to make corrections and more accurately compensate for aspects of error
that were unforeseen within simulations of the launch.
Page | 13
USLI PDR
Atomic Aggies
New Mexico State University
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.
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
Page | 14
USLI PDR
Atomic Aggies
New Mexico State University
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.
The vehicle will have two single pole single throw DC switches connected in parallel for powering up the
payload circuitry. There will be a transmitter that will be interfaced with the PC ground station.
The vehicle will have two single pole single throw dc switches connected in parallel for power to the
payload. There will be a transmitter that will be interfaced with the PC ground station.
Safety and Environment
A Redundancy and Kill-Switch is for the safety of others and the rocket. A toggle switch utilized on the
outside of the body of the rocket that will power on the dual deployment altimeter. This switch will
power on and off all the electronics in the recovery system. For redundancy, there will be two
independent toggle switches that both power on an altimeter. The purpose of this is to have a primary
and back-up recovery system in our rocket in case of any failures of deployment.
NRA Certified project advisors for the New Mexico State University rocket team, we are privileged to
have John DeMar as a mentor for our program. Mr. DeMar is a Level 3 certified member of both the
National Association of Rocketry (NAR) and the Tripoli Rocketry Association, and brings with him
valuable prior TARC and SLI experience to our team. Mr. DeMar also brings over 20 years of knowledge
to our team, having been high-power certified since 1991. We also have Thomas Kindig who will be
serving as an advisor to the NMSU USLI team. As not only president of the Fellowship of Las Cruces Area
Rocketry Enthusiasts (FLARE), but also as a NAR Level 1 certified member, Mr. Kindig brings much
appreciated knowledge in the information technology field as well as past TARC experience. Mr. Kindig
plans on becoming a certified Level 2 NAR member by the end of 2011. Both gentlemen will help ensure
compliance of NAR safety code requirements and handling of hazardous materials and operations
throughout the duration of the project and, as previously stated, are NAR certified members.
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 feel a situation is unsafe in
any way, shape, or form they will immediately notify their team leader, safety officer, or mentor of such
Page | 15
USLI PDR
Atomic Aggies
New Mexico State University
situation. All members of the Atomic Aggie team will be given various safety briefings throughout the
duration of the project, and will be responsible for attending such briefings. Any absence may 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 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. 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.
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.
Page | 16
USLI PDR
Atomic Aggies
New Mexico State University
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.
Page | 17
USLI PDR
Atomic Aggies
New Mexico State University
IV) Payload Criteria
Selection, Design, and Verification of Payload Experiment
The payload fulfills the requirements of the Science Mission Directorate by measuring temperature,
pressure, relative humidity, solar irradiance and ultraviolet radiation. The payload will contain the
following;
FPGA – A DE0-Nano Development and Education Board by Terasic will be programmed to read
the sensors at a frequency of 1Hz. Another DE0-Nano will be programmed to control the
cameras. They will each be powered by six 1.5 volt ‘AA’ batteries regulated to output +5 volts.
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 measurement with the following
𝟏
equation: Altitude = 𝟒𝟒𝟑𝟑𝟎 ∗ [𝟏 −
𝑷 𝟓.𝟐𝟓𝟓
(𝑷𝒐)
]
Humidity - Humidity will be measured with a Honeywell HIH-4030/31 sensor pre-mounted on a
breakout board. The HIH-44330 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.
This camera was picked for its small size and the high definition resolution. The camera takes
still pictures as well as video.
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. Lenses will be used to focus the sunlight on the detector. A
geometrical optical analysis known as ray tracing will also be simulated in software to aid in
determining the focal length and diameter of the lenses. The final determining equation for
𝒇𝝀
choosing the lenses will be in the form 𝒓 = 𝟏. 𝟐𝟐( 𝒅 ) where r is the cell size of the photodetector, f is the focal length of the lens, λ is the center wavelength under detection and d is
the diameter of the lens.
GPS – The RXM-SG GPS Module w/Ext Antenna (#28505) will be used for tracking information.
This GPS can connect to a microcontroller via USB. A graphical display of the GPS data can show
the rockets location on Google Maps.
Transmitter/Receiver –
Page | 18
USLI PDR
Atomic Aggies
New Mexico State University
TXM-900-HP3-SPS – is a RF transmitter with a frequency range of 902MHz- 928MHz. It will be
used to transmit data and GPS telemetry. It is capable of FM and FSK modulation. Power output
is in a range of {-3dBm to 3dBm} while the transmitted current is 14mA with a data rate of
56kbps. This will be transmitting on a whip dipole antenna.
RXM-900-HP3-SPS- is a RF receiver with a frequency range of 902MHz- 928MHz. It will be used
to receive the transmitted data and GPS telemetry. The receiving current is 18mA with a data
rate of 56kbps. The receiver will be received on a whip dipole.
Component
BMP085
Precision
+/- 1% to +/- 1.5 depending on pressure and
temperature
+/-1.2%
720 x 480 resolution image format
1280 x 960 resolution camera format
HIH-44330
Camera/Video
The payload will be located below the nosecone with the light detection circuitry and associated
hardware will be located within the nose cone. There will be three focal lenses embedded around the
circumference at 120º intervals and along the shoulder as this area of the vehicle will allow the widest
viewing angle of the sun. These lenses will create a light spot by focusing the radiation on the
photodiode. The exact location is still under debate because the optimal spot for light gathering
purposes is not necessarily the best place to leave the integrity of the nosecone intact. The internal
memory of the DE0-Nano will be used to store the data gathered from the sensors. To ensure accurate
data will be gathered, ventilation holes will be added to the payload bay. 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 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.
Verification
The payload will be thoroughly and repeatedly tested to ensure it payload operates correctly. Each
sensor will be tested individually and then together as a whole system. To test the GPS, the payload
team will take the GPS around Las Cruces and verify the coordinates with another GPS system or map. A
standard light source and UV filter will be set up in a laboratory to measure radiation using the light
detection circuit. The transmitter will be turned on next to the parachute ejection charge circuitry to see
if it will make it induce a current.
Risk
1. Payload data does not
match projected data.
Page | 19
Consequence
Un-interpretable data
Prevention
Thoroughly test payload data before
launch
USLI PDR
Atomic Aggies
2. Damage to payload
during test flight
3. Battery failure
4. Damage during final
launch
5. Airframe becomes loose
6. Center of Gravity is off
Payload layout design
Page | 20
New Mexico State University
Broken components
No power to DE0-Nano,
therefore no
measurements will be
taken.
Components could be
damaged or come loose.
Data will be compromised
and camera holes will be
unaligned.
Unsuccessful flight
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.
Secure payload and components tightly.
Make sure there is a way to tightly secure
the payload bay where it can not come
loose.
Make sure the mass if figured correctly
and given to the design team before flight
takes place.
USLI PDR
Atomic Aggies
New Mexico State University
The payload will be mounted on a 5.36” x 18” piece of ½” plyboard (the inside diameter of the rocket it
is 5.36”). At each end of the board there will be a plyboard disc wafer mounted perpendicular to the
board. These discs will have a diameter of 5.36” to fit the inside diameter of the rocket. To
accommodate the mounting of the cameras and sensors, we will be fitting pieces of Blue-Tube coupler
material split lengthwise around the payload. The cameras will be mounted to this structure around the
payload. The cameras on this structure will be aligned with holes 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.
Page | 21
USLI PDR
Atomic Aggies
New Mexico State University
DE0- Nano Board:
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. The payload will also contain a dedicated altimeter that will provide a means to correlate
recorded values to altitude. The GPS unit included in the payload will provide a graphical representation
of the flight.
The Stratologger altimeter measures barometric pressure and temperature. Internal circuitry onboard
the altimeter calculates altitude from those readings. These values will be recorded to the datalogger for
the experiment. A separate circuit board providing pressure and temperature data will also be logged.
This will provide a means for checking these data. The data from the pressure/temperature sub-circuit
can also provide a means to compute altitude. The humidity sensor will provide analog data that will be
converted by the ADC contained on the controller hardware for logging and transmission.
The light detection circuit shall measure solar irradiance and ultraviolet radiation. The final data gleaned
from the circuit shall represent solar irradiance in the form
𝐰
𝐦𝟐
and the power density of the near
ultraviolet spectrum, specifically 350-400nm, in the form 𝐰/(𝐦𝟐 · 𝛍𝐦).
Page | 22
USLI PDR
Atomic Aggies
New Mexico State University
The detection circuit will employ a broadband photodiode. The FDS100 was chosen because of its ability
to measure wavelengths in the near UV region. An OP27 trans-impedance amplifier was chosen to
convert the current output of the photodiode to a voltage. Its low impedance characteristics were also a
factor in determining its employment. A study of the effect of background noise on the circuit will
determine the resistance values in the current to voltage conversion section of the circuit. The signal to
noise ratio will be considered an electrical current induced by the thermal noise, the shot noise and the
flicker noise, in equation form
𝐢𝐧 = √𝐢𝟐𝐭𝐡 + 𝐢𝟐𝐬𝐡 + 𝐢𝟐𝐟𝐥 . The power supply for the circuit will be
provided by a 9 volt battery electrically isolated from the rest of the payload circuitry to further aid in
noise reduction.
The main challenge of the payload is the integration of the sensors with the DE0-Nano board. It requires
understanding of Verilog, 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.
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.
Safety and Environment
Usage of Lithium Polymer rechargeable batteries can be dangerous due to the power density. If the
battery is punctured or the leads get sorted these batteries will release energy rapidly. These batteries
will need to be given extra protection in the air frame to ensure that they are protected. Also if
batteries explode if kept in high temperature range therefore batteries must be kept away the motor.
Soldering irons can be dangerous to use, therefore safety measures are put in place to ensure no injuries
occur. Some soldering safety precautions include:
Hold components in pliers or clamps to avoid burns.
Return the soldering iron to its stand when not in use.
Keep cleaning sponge wet during use.
Page | 23
USLI PDR
Atomic Aggies
New Mexico State University
Work in well-ventilated area.
Never leave solder iron unattended.
Wash hands after handling solder.
For soldering all electrostatic components technicians will be grounded to the bench.
Page | 24
USLI PDR
Atomic Aggies
New Mexico State University
V) Activity Plan
Budget plan
Electronics Recovery System
Description
Sky Angle Classic II Parachute
Drogue Chute
Altimeter
Black Powder
Batteries
Nomex Chute Protectors
Shock Cords Protector
Electronics Bay
Toggle Switches
Electric & Charges(Donated)
Quantity
1
1
2
1
2
2
4
1
4
Unit Cost
$99
$32
$85.55
$20
$2.50
$6.37
$12.95
$54.95
$0.88
Cost
$99
$32
$171.10
$20
$5
$12.74
$51.80
$54.95
$3.32
1
$0
$0
Quantity
2
4
1
1
1
1
1
1
2
2
2
1
2 lin ft.
Unit Cost
$59.00
$9.99
$40
$20
$14
$80
$45
$45
$2.50
$50
$13.10
$4.49
$16
Cost
$118
$39.95
$40
$20
$14
$80
$45
$45
$5
$100
$26.20
$4.49
$32
1
$75
$75
Quantity
1
Unit Cost
$80
Cost
$80
Pay Load
Description
DE0-Nano
Key Chain Camera
Altimeter
Temperature/Pressure Sensor
Humidity Sensor
GPS System
RF Transmitter
RF Receiver
Batteries
Fiberglass Sheets
Photodiode
Op-amp
RF shielding
Miscellaneous
(resistors, cables, etc.)
Design
Description
Nose Cone
Page | 25
USLI PDR
Atomic Aggies
Tube coupler
Bulkhead
Flight Electric Fixed Bulkhead
Body Tube
Flight Electric Removable Bulkhead
Forward Rail Button
Motor Mount
Fin Set
Aft Rail Button
Aft Centering Ring
Grand Total
Page | 26
New Mexico State University
1
1
1
1
1
1
1
1
1
1
$55.95
$15.01
$15.01
$56.95
$15.01
$4.43
$29.95
$72.01
$4.43
$28.01
$1469.82
$55.95
$15.01
$15.01
$59.95
$15.01
$4.43
$29.95
$72.01
$4.43
$28.01
USLI PDR
Atomic Aggies
Timeline
Page | 27
New Mexico State University
USLI PDR
Atomic Aggies
New Mexico State University
Educational engagement
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)
The Atomic Aggies will be building and launching small rockets with the middle school and high school
aged kids of A. Fielder Memorial Safe Haven. The A. Fielder Memorial Safe Haven is a free after school
center to get children off the street. They provide after school snacks and supervision as well as
homework and reading assistance for children of all ages. Our goal is to interest them in not only
rocketry but all types of science and engineering.
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 observed. The recovery team learned
how a dual-deployment altimeter in a payload bay is expected to perform in flight. They armed and
Page | 28
USLI PDR
Atomic Aggies
New Mexico State University
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.
Page | 29
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 ULSI 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 ULSI Program.
Page | 30