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October 5, 2012
Mitchell Community College
MCC Aerospace Engineering and Technology
http://www.mitchellcc.edu/programs/rocket-projects/index.html
http://www.facebook.com/MCCA.E.T.team
CONCEPTUAL DESIGN REVIEW ROCKSAT-C
ROCKSAT-C 2013 1
MCC Aerospace Engineering & Technology
Goal Statement:
The goal of Mitchell Community College’s
aerospace engineering and technology team is to
educate and prepare students for careers based in
science, technology, engineering, or math related
occupations. Through contextual and collaborative
projects, individuals will develop their teamwork and
organizational skills. These projects will foster
innovative thought through hands-on research and
development activities which will lead to improved
opportunities for success in the workforce.
ROCKSAT-C 2013 2
ROCKSAT-C 2013 3
Mission Overview
Mission Overview Minimum Success Criteria
Theory and Concepts Concepts of Operations
Mission Requirements Expected Results
Systems Requirements
Conceptual Design Overview
Mechanical Shared Can Logistics
Electrical RockSat-C User’s Guide Compliance
Testing
Management
Team Organization Budget
Mentors Facilities
Schedule Legacy Plan
Conclusions
Mission Overview
PEGASIS II
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Mission Overview
Our goal is to power space-based instrumentation
systems by passively generating energy from transducers
of a proprietary design. Energy will be harvested from the
rocket flight, solar rays, and other sources. This will be
accomplished by building a more robust and simplistic
payload using transducers with increased efficiency and
improved design characteristics. Results may lower cost
and power requirements for space science by reducing the
weight of electrical components.
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Theory and Concepts:
• Electromagnetic transducers will utilize Faraday’s
Law.
• Solar transducers will utilize Photoelectric effect.
• Peltier coolers will use solar transducer to act as a
heat sink for microprocessors
• Piezoelectric effect
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Mission Overview
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Past Research
• Electrodynamic tethers tested with the Space Shuttle
• MEMS based micro-engineered motion energy harvesting
devices (Imperial College of London, 2007)
• MIDE out of Boston, Ma., founded in 1989, develops
vibration energy harvesting devices
• PEGASIS II is a continuation of our 2012 RockSat-C
Project, PEGASIS.
Mission Requirements
Objectives:
• Harvest electrical energy from various sources
during flight.
• Measure various environmental factors
throughout flight such as humidity, magnetic field
and acceleration.
• Use energy harvested to power electronic device
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Mission Overview
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System Requirements
• Energy generators
• Data collection & retention
• Electronic operation control
• Control & experiments (sensing board)
• Simplified structure design
Mission Overview
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Minimum Success
• Voltages are successfully read from
each transducer and recorded to
memory
• Control sensing board records data of
various environmental aspects
Concepts of Operations
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Expected Results
CONTROL
A sensing board will be powered by a fixed battery. It will
record and save data of different environmental variables.
EXPERIMENT
A sensing board will be powered by energy gathering
devices. The energy used from both sensing boards will be
recorded and saved for comparison. Energy produced by
transducers will also be recorded and saved.
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Conceptual Design Overview
PEGASIS II
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Mechanical Design Overview
PEGASIS II
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Design Overview
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Major Components
SUBSYSTEM DEFINITIONS
“EM Pendulum” Magnet suspended on a pendulum over
multiple copper coils will use horizontal
vibrations and angular velocity
“Aubade” Photovoltaic panel
“Jerk” Magnet surrounded by a copper coil will use
vertical vibrations
“Bristol” Magnets in a circular track will use angular
velocity
“Diving Board” Piezoelectric cantilever will use horizontal
vibrations
Design Overview
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Mechanical - Major Components
Will have a pendulum mounted that rotates
with the rocket from the center rotation
surrounded by semispherical wire coils.
Design Overview
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Mechanical - Major Components
Photovoltaic panel that will be constructed of
efficient solar cells
Solar Rays
N - type
P - type
Junction
Design Overview
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Mechanical - Major Components
Will create energy through a copper wire coil
wrapped around a cylinder with a magnet
between two springs using the R axis.
Design Overview
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Mechanical - Major Components
Design based on idea of circular motion resembling
a race track where the magnet travels 360 degrees
inside a tube surrounded by coil wire
Design Overview
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Mechanical - Major Components
Will vibrate vertically on the z axis of the rocket;
composed of a piezoelectric cantilever
Design Overview
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Mechanical - Major Components
• Other past transducers will receive further testing for
possible inclusion
• New transducer designs are being considered and will be
tested
• Other producers of energy will be considered for the
payload
Design Overview
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Mechanical - Structure
• 2 Makrolon Plates, top & bottom
• Circular to match canister
• Components mounted on either the top of the bottom plate or the
bottom of the top plate.
• Aluminum hex standoffs, 4 or 5
• Components made of plastic using rapid prototype or of aluminum
using CNC machines
Design Overview
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Mechanical - Structure
Green: Electronics Package
•Data Collection
•Data Retention
•Sensing Board (Controlled)
Grey Box: Battery
Grey Cylinder: Jerk
Blue & Red unit: EM Pendulum
Gold: Bristol
Yellow: Aubade
Purple: Diving Board
Pink: Sensing Board (Experiment)
Design Overview
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Mechanical - Summary
Electrical Design Overview
PEGASIS II
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Design Overview
Electrical - Major Components
• The electrical system will use 1.SYS.1 activation
system at approximately T-5mins.
• An internal counter will begin for further on board
control.
• An Arduino will be used for main processing work and
data acquisition.
• Data will be collected until power is disconnected.
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Design Overview
Electrical - Major Components
• Sensing board(SB) design form the 2012 mission will
be improved for the 2013 mission.
• Dual SB’s will be used for comparative data.
• One SB will be powered from battery, the control.
• One SB will be powered directly from transducers, the
experiment.
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Design Overview
Electrical - Major Components
• Openlogs will be used for data retention.
• 2012 mission showed no flaws in operation.
• Open-source licensing will allow
For full integration into SB
design instead of using
daughter cards.
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Design Overview
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Transducer
#1
#2 #3
#4
#5
Processor Sensing Board
Control
Battery
Sensing Board
Experiment
Design Overview
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Electrical - Summary
Test Design Overview
PEGASIS II
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Design Overview
Testing
The goal of our testing plan is to ensure the payload
will perform to design and improve the efficiencies from
Pegasis 2012 transducers. Each test will be used to verify
the payload can withstand high G forces and strong
vibrational forces. Hardware mounts, electrical connectors,
circuit boards and transducers will need to remain
functional after testing.
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Design Overview
Will consist of :
Vibration analysis
• Via shake-table
Simulation Testing
• Component test rocket
• Complete payload
test rocket
Plans to include:
Temperature functionality
• In design process
Electrical System testing
• In design process
Further tests will be designed as
needs arise
Testing
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Design Overview
Testing
Shake Table Specs
• Frequency: 200-3000Hz
• 0.1 inch amplitude
• 200-1750 RPM
• Functional spin table: 0-500RPM
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Design Overview
Testing
Component Rocket Specs
• Length – 42 inches
• Diameter – 4 inches
• Cesaroni – H 400 Motor
• Max Acceleration – 26 (gees) (approx.)
• Max Altitude – 1600 ft (approx.)
• Equipment from last year
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Design Overview Testing
Full Scale Rocket Specs
•Length – 93 inches
•Diameter – 10 inches
•Cesaroni – J 1520 Motor
•Max Acceleration – 25 (gees) (approx.)
•Max Altitude – 1900 ft (approx.)
•Equipment from last year.
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Shared can logistics
• Project PEGASIS II will use half a canister and require a partner.
• The optic port will be used, but atmospheric port shall will not be needed.
• Center of mass and all other requirements shall be fulfilled in compliance with RockSat-C 2012-2013 Payload Canister User’s Guide.
• Communication will be done via email
• Solidworks files will be shared with canister partner using Dropbox
• Aluminum hex standoffs will be used to integrate with canister partner
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RockSat-C user's guide compliance
• Project PEGASIS will use half a canister and require a partner.
• Useable payload space = 9.3” Diameter x 4.75” high.
• Center of gravity
• Payloads must conform to a center of gravity that lies within a 1x1x1
inch envelope of the geometric centroid of the integrated RockSat
payload canister.
• Approximate weight < 5 lbs without cap head screws.
• Total weight of canister = 20+/- 0.2 lb.
• Cannot modify canister.
• Must be able to pass vibration test.
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Design Overview
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Testing - Summary
Management
Pegasis II
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http://www.mitchellcc.edu/programs/rocket-projects/team2.html
Faculty Advisor – Sharon Rouse
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1987 Diploma Machining Technology
A.A.S. Manufacturing Engineering Technology
1999 A.S. Associate of Science
2003 CAD Drafting Certificate
2004 B.S.I.T. Industrial Systems minor in Manufacturing
2007 M.S.I.T. Technology Systems minor in Manufacturing
2013 Ph.D. Technology Management minor in
Manufacturing
Manual and CNC machining, quality assurance, product
engineering, blueprint reading, engineering materials.
Management
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Doug Knight Ph.D.
Clint Halsted
Shawn Fraver
Ron Davis
Mentors
Schedule • 10/8 – RockSat-C meeting
• 10/15– RockSat-C meeting
• 10/17 – Payment and online progress report due
• 10/26-10/27 – PDR and PDR teleconference
• 10/29 – RockSat-C meeting
• 11/1– Small scale test flights begin
• 11/5 – RockSat-C meeting 11/14 – Online progress report due
• 11/18 – RockSat-C meeting
• 11/16 or 11/30 – CDR Due- discuses with team based on finals schedules
• 11/28 – CDR and then CDR teleconference
• 12/3 – RockSat-C meeting, begin legacy equipment testing
• 12/10 – RockSat-C meeting
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Facilities
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Electronics Lab
Machine Shop
Rapid Prototyping Printer
Management
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• A Safety officer will train team members on safe guidelines and
practices.
• A test will be administered to each team member to certify that each
member understands the proper procedure.
• Rocket test flights
• Materials- use non-flammable material.
• Motors- use certified motors.
• We will strictly follow the TRIPOLI HIGH POWER SAFETY CODES.
Safety
Management
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Legacy Plan
It is a goal of this team to set up a plan to
where new members will join each year and
be taught by experienced members. Also, we
wish to create a long term financial plan to
support the team projects.
Further considerations
• Software development
• Selection of transducers
• Individual or group voltage measurement
• Battery selection
• Possible replacement of Arduino with in-house built data
collection device
• Coil design
• Develop test methods as conditions change
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CONCLUSION
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October 5, 2012
Mitchell Community College
MCC Aerospace Engineering and Technology
http://www.mitchellcc.edu/programs/rocket-projects/index.html
http://www.facebook.com/MCCA.E.T.team
