Transcript Mid Term Report PPT

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An Kim
Cian Branco
David Warner
Edwin Billips
Langston Lewis
Thomas Work
Mackenzie Webb
Benjamin Cawrse (CS)
Jason Harris (TCC)
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Thousands of man made objects in earth
orbit (mostly junk).
Debris can be a serious hazard to satellites.
A paint flake threatened the Space Shuttle; a
Russian Satellite disabled an Iridium satellite
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CubeSats are picosatellites used by universities
and institutions for research in space.
Pending international treaty will require future
launch stages and LEO satellites to deorbit within
25 years of mission completion.
Objective: design and test a de-orbit system to deorbit CubeSats within 25 years of mission
completion.
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Demonstrate commercial viability
Prove it is a robust and viable system
Achieve these objectives with a minimum cost
◦ Orbital demonstrator
◦ Suborbital flight
◦ High altitude balloon flight
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Demonstrate commercial viability
Prove it is a robust and viable system
Achieve these objectives with a minimum cost
◦ Orbital demonstrator
◦ Suborbital flight
◦ High altitude balloon flight
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Demonstrate commercial viability
Prove it is a robust and viable system
Achieve these objectives with a minimum cost
◦ Orbital demonstrator
◦ Suborbital flight
◦ High altitude balloon flight
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Demonstrate commercial viability
Prove it is a robust and viable system
Achieve these objectives with a minimum cost
◦ Orbital demonstrator
◦ Suborbital flight
◦ High altitude balloon flight
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The RockSat-X program
out of Wallops Flight
Facility is currently
considered the best
option for our test flight
RockSat-X utilizes the
Terrier-Improved
Malemute suborbital
sounding rocket
The sounding rocket will
reach apogee at
approximately 160 km
altitude from the Earth.
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300 seconds of microgravity flight
Power and telemetry on deck provided for
timing devices, communication between
ground and payload, and data storage
Direct access to orbital space after second
stage burn-out when the skin of the
sounding rocket is ejected.
Adequate space and weight capacity available
to mount the deployment device and
necessary telemetry for the mission of our
CubeSat
Langston Lewis
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Lithium-Ion batteries will be used to supply
power to the board and release mechanism.
Can sustain high amounts of continuous
current discharge in order to run the camera
and communications devices.
Mass of batteries is a concern
•Stable operation between 6-20
volts
•14 digital and 6 analog pins
•Board has built in accelerometers
•Mounted on aero brake
support structure.
•Voltage differences can be
converted to strain and then
used to calculate drag
coefficient produced by
balloon
•160x120 resolution
•Support capture JPEG from
serial port
•Default baud rate of serial
port is 38400 but we will be
transmitting at 19200
•Works reliably with 5v
power supply
•Size 32X32mm
•Consumes between 80-100
mA of current
•Low-power and weight in an
equally small size
•Provides adequate resolution
and range
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Objective:
◦ Mylar Balloon
 Test benzoic acid inflations under different
temperature than the sublimating temperature
 Calculate the correct benzoic acid mass to inflate
the Mylar balloon within the vacuum chamber
 Record time for the benzoic acid to fully inflate
◦ Nitinol (SMA)
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Temperature for
benzoic acid inflation
◦ From Emerald Performance
Materials, estimated
sublimation temp is 12.5∘ C
◦ A thermistor will be use to
vary temperature when
testing benzoic acid inflation
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Mass of benzoic acid
◦ The required amount of
benzoic acid will be less
than 0.1 gram.
◦ The mass may vary to
increase the rate of
inflation
http://social.rollins.edu/wpsites/chm220th/file
s/2011/09/photo-4.jpg
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Time Limit
◦ Must inflate in under
300 seconds
◦ Goal of the
experiment is to have
the Mylar Balloon to
inflate in less than
200 seconds.
O-POD Design
David Warner
Cian Branco
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ODU Picosatellite Orbital Deployer
Bolted to Rocksat-X deck, “piggybacks” rocket
Directly connected to RS-X Power Interface (1 Ah)
Stores, imparts ejection velocity to CubeSat
 1.6 m/s from spring, lateral to deck
 Al-7075-T651 frame
 1.477 kg total mass
Materials
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7mm thick Al-7075 plates
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Holes can be cut for RS-X power
interface & instruments
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42 + 12 bolts (M4 x0.70 10mm)
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ASTM-A228 “Music Wire” Spring
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19.62cm length (entire)
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7 turns coil
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Held by crossbar on back plate
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Supports pusher-plate
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~1.5 kg total
Overall Dimensions
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12.7cm x 12.7 cm x 19.62 cm
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5 design iterations, still not space-rated
 Weak pusher-plate to spring connection
 Torsion in spring, friction issues on rails
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Quick Release Mechanism Options
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CubeSat mockup “f” varies w/ humidity (cardboard)
Aluminum mockup in the works
Lubrication?
Vectran Line Cutter (ODU built)
2 Linear Solenoids
Center-of-Mass
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Must be inside 2” square at center
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Further PATRAN & FEA analysis (vibrations
accountable)
Resume velocity measurements with new mockup
Choose quick release mechanism within budget
Design a mounting plate to connect O-POD to
RockSat-X
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Most of our time so far has been allocated to
gathering information, resources and
planning
We will apply that information to create
prototypes and perform the necessary
experimental tests for the successful mission
of our CubeSat
All tests and prototypes will be performed
and created to interface with RockSat-X, but
we will consider other options for test flights
as well.
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