Harding University Flying Bison 2010 USLI Team Team Official Project Progress Manager Safety Officer Edmond Wilson Cortney Mgr Edmond Wilson Airframe Motor Science Payload Avionics Launch Operations ID: 778156
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Slide1
Measuring Radiation as a Function of Altitude Using a Hybrid Rocket Platform
Harding
University Flying Bison 2010 USLI Team
Slide2Team Official
Project Progress Manager
Safety Officer
Edmond Wilson
Cortney, Mgr.
Edmond Wilson
Airframe
Motor
Science Payload
Avionics
Launch Operations
Recovery
Outreach
Greg, Mgr.
Matt G., Mgr.
Darah
, Mgr.
Chi, Mgr.
Matt I., Mgr.
Patrick, Mgr.
Elizabeth, Mgr.
Elizabeth
Libby
Chi
Hunter
Matt G.
Shailer
Cortney
Libby
Josh
Libby
Lisa
Meredith
Hunter
Nathan
Hunter
Lisa
Elizabeth
Patrick
Josh
Meredith
Matt G.
Nathan
Cortney
Shailer
April
Hunter
Slide3Mission Statement
Design, build, test and fly a high powered hybrid rocket
Reach exactly an altitude of 5280 feet
Carry a science payload to measure alpha, beta and gamma radiation as a function of altitude
Measure temperature, pressure and x-, y-, z- acceleration during the flight
Complete such activities without damage to life and property
Recover rocket vehicle in a reusable condition
Slide4This presentation includes reports from:Airframe Division
Motor Division
Science Payload Division
Avionics Division
Launch Operations Division
Recovery Division
Outreach Division
Slide5Airframe Division ReportGreg, Manager
Team Members
Elizabeth
Libby
Hunter
Matt G.
Slide6Harding Flying Bison 2010 USLI Competition Rocket
Slide7Vehicle Dimensions
General Dimensions:
90.3” total length
4.09” OD, 3.9” ID
16.8” nose cone
~7.5” boattail
No transitions or irregular protrusions are present along the airframe.
Slide8Airframe Division
Slide9Fin Dimensions
Aft Fin Set (Trapezoidal):
4” semi span
8” root chord
4” tip chord
Mid Fin Set (Triangular):
4” semi span
6.5” root chord
Slide10RockSim V9 Simulation
Slide11Vehicle Materials
The vehicle body is composed of pre-fiberglassed phenolic tubing, avalible from Public Missiles.
Material weighs more than standard phenolic or Quantum tubing.
Overall integrity of the airframe will be greatly improved.
K888 motor allows for extra weight.
Slide12Vehicle Materials
All bulkheads and centering rings are composed of 5-ply aircraft plywood.
The 75mm motor mount tube is composed of phenolic tubing.
Both sets of fins are composed of G10 fiberglass, available from PML.
Fins will be mounted using through-the-wall method, and reinforced with carbon fiber and fiberglass cloth.
Slide13Static Stability Margin
CP: 58.16” from nose
CG: 51.94” from nose
Stability Margin:
6.22”
1.55 body calibers
Overstable within the desired margin.
Slide14Vehicle Safety Testing
Plans for component verification:
Tensile strength testing of all load-bearing components of the recovery system (excluding the parachutes).
Compression strength testing of airframe tubing and other relevant components.
Ejection charge testing.
Test launch of both scale model and full launch vehicle are planned.
Slide15Motor Division ReportMatt G., Manager
Team Members
Libby
Josh
Lisa
Slide16Motor Selection
Contrail Rockets Certified K-888-BM Hybrid
Motor with medium nozzle
2050 cm
3
N
2
O Tank
10 in Combustion Chamber
40 in long
Fuel Grain – Medium Black
Total
weight
4173 g
Total impulse 2400
N
.
m
Average Thrust 895 N
Maximum Thrust 3024 N
Burn time 2.67 seconds
Slide17Motor Justification
We have several years of hybrid rocket motor sensor development
We are able to further our research on hybrid rocket motor exhaust plume characterization
Increased safety and more friendly on the environment than the traditional solid motor
Potential uses for delivering payloads in low Earth orbit
Slide18Science Payload Division Report
Darah
, Manager
Team Members
Chi
Libby
Elizabeth
Nathan
Slide19The primary mission of the Payload Division is to measure alpha, beta, and gamma radiation as a function of altitude using a Geiger radiation sensor. Our secondary mission is to measure temperature, atmospheric pressure, and acceleration in the x, y, and z direction.
Payload Mission
Slide20Radiation is a concern of every day life.
Radiation levels approximately double for every 5000 feet in altitude.
This can be a serious problem for travel in jet aircraft or rockets low to Earth orbit.
Radiation is harmful to both humans and electronic equipment.
Single Event Phenomena, or SEP, can cause burnout of electrical circuits of bit flips in logic circuits. These are serious problems.
Science Background
Slide21There is little data concerning radiation available for suborbital space.
Surface Radiation – 14 Counts per second
Increases many fold due to environmental factors
Cosmic radiation affects power grids and communication satellites.
Our rocket will travel to 1 mile high. We expect the radiation level to be approximately twice what it would be at sea level.
Slide22Alpha rays are high speed helium nuclei. They are the least penetrating type of radiation. They can be stopped with a single sheet of paper or a few centimeters of air.
Beta rays are high speed electrons. They are more penetrating than alpha rays.
Gamma rays are particles of energy and are the most penetrating. They can penetrate several centimeters of steel or hundreds of meters of air.
Radiation Types Measured
Slide231. Geiger radiation sensor2. X, Y, and Z accelerometer3. Pressure Sensor
4. Temperature Sensor
5. AVR® Microcontroller
Components of the Payload
Slide24The experiment is to measure radiation using a Geiger radiation sensor. A g-switch will initiate data collection at the time of launch.
The data from the Geiger counter will be digitized and stored in the memory of an embedded computer.
Summary of Experiment
Slide25Radiation events closer than 2 milliseconds will not be recorded. We will be measuring alpha, beta, and gamma radiation.We will primarily be measuring beta and gamma radiation.
Only the highest energy alpha particles will be detected through our experiments.
Summary of Experiment, cont.
Slide26The Geiger Counter used in our payload is the GCK-05 from Images SI, Inc.It will detect the following radiation:
Alpha particles above 3.0
MeV
Beta particles above 50
KeV
Gamma particles above 7
KeV
The Radiation Sensor
Slide27Slide28National Semiconductor LM50CIM3 transducerReads directly in degrees C (10mV/⁰C)
Nonlinearity is less than 0.8 ⁰C over its temperature range of -40 ⁰C to +125 ⁰C
The accuracy at 25 ⁰C is ±2% of the reading
Temperature Transducer
Slide29ASDX015A25R Honeywell device
Measuring range of 0 to 15 psi
Burst pressure of 30 psi
Operates in temperature ranges from -20⁰C to +105⁰C
Pressure Transducer
Slide303 Accelerometers:
One 1-axis low range accelerometer and two 2-axis accelerometers
All accelerometer devices have an output full-scale range of 37g
Operational range of -40⁰C to +105⁰C
Maximum rating of 4000g acceleration for any axis
Accelerometer
Slide31Before the competition flight in April, our team plans to conduct experiments in the laboratory using known radioactive samples to calibrate the Geiger counter and ensure that it is functioning properly.
It is especially important to calibrate the Geiger counter so that our results will be as accurate as possible.
We must also calibrate the pressure sensor, temperature sensor, and the accelerometers.
Experimental Plans
Slide32Personnel hazards include:
Injury to eyes or hands while machining payload parts. All will wear protective eyewear and instruction on preventing injury to the body during work periods will be conducted repeatedly for each phase of the work.
Proper use of hand tools will be explained as needed for each process undertaken.
Instruction on how to solder properly will be given when electrical circuits are being assembled.
No chemicals are used in constructing or operating the payload.
Safety Considerations
Slide33All components of the science payload and its power source will fit inside a 12 inch coupler with a 3.78 inch inner diameter.
Power switches, LED indicators and connectors to the various computers will be through the middle of the coupler tube wall.
A ring of airframe tubing glued to the middle of the coupler will reinforce this connection area.
Science Payload Integration
Slide34Safely recover all components of the science payload in operable conditionWe must gather, retrieve, and store data from the entire flight of the rocket.
Success Criteria
Slide35Slide36Avionics Division ReportChi, Manager
Team Members
Hunter
Patrick
Lisa
Slide37Missions for Avionics Division
To deploy parachutes at desired altitude for a safe recovery process.
To obtain information about the flight regarding the maximum altitude, velocity and acceleration of the rocket.
Slide38Primary Altimeter
PerflectFlite
–
MiniAlt
/WD
A
– Altitude Sensor
B
– Speaker for Post-flight report
C
– Port to PC for data transferring
D
– Non-volatile memory
E
– Igniter for parachute deployment
F – Deployment altitude control
Slide39Primary Flight Computer
G-Wiz MC2
Pyro
output:
Fire at Apogee using accelerometer data or barometric data.
Programmable fire at low altitude
Status LED and speakers to signal readiness at launch and provide flight information after landing.
USB connection for data transferring
Slide40Launch Division ReportMatt I., Manager
Team Members
Matt G.
Meredith
Shailer
Josh
No Report at this Time
Slide41Recovery Division ReportPatrick, Manager
Team Members
Hunter
Shailer
Slide42G-Wiz MC2 Flight Computer
The flight computer will send a code to the igniters which will then set off the charges at the programmed altitudes.
G-Wiz will also serve as our backup recording Altimeter.
Slide43PerfectFlite miniAltimeter
PerfectFlite
miniAltitmeter
will be used as our primary altimeter.
It will also serve as our backup flight computer in case the G-Wiz fails.
Slide44Parachutes
Drogue Parachute:
24” Classic II Sky Angle Parachute
Deploys at Apogee
Weighs 6 ounces
Main Parachute:
60” Classic II Sky Angle Parachute
Deploys at 800 feet
Weighs 18.2 ounces
Slide45Outreach Division ReportElizabeth, Manager
Team Members
Cortney
Nathan
Meredith
Shailer
Hunter
Slide46Educational Outreach
Westside Elementary School in Searcy, Ar. (conduct a rocket launch with 1
st
grade students)
Arkansas Space Grant
Consortium (Team does Oral or Poster presentations)
Ouachita Council of Girl Scouts of America
in Bradford, Ar. (GSA Troop 76)
Quapaw Area Council of the Boy Scouts of
America
Mid-South Rocket Society NAR
Secton
#
550 (NAR section is our mentoring sponsoring section)
Jack
Frederick/Raytheon/Rockets – STEM topics
Rocket display in Harding University Library
Do Chapel announcement at Harding University
Put up a poster section up in the
Pryor – England Science and Engineering Building
in the Main
Lobby in
April
Matt built portable and fixed launch stands for our rocket team
Slide47Educational Outreach
We have solicited the support and help of Mr. David
Stair (
retired NASA model maker
)
plan to ask BEI Systems and Space
Division
to Sponsor us and give us technical
support (Little Rock, Ar.)
we have sought to get to know the key scientists and engineers at NASA centers who are involved in rocket
research we
visit with the rocket scientists and engineers at Marshall Space Flight Center and at University of Alabama at
Huntsville in June 2009
Slide48The End
We acknowledge the Arkansas Space Grant Consortium, ASGC, for funding this project.