Transcript Slide 1

Follow up Design Review
GoGreenSAT
The University of Northern Colorado
Jessica Gage, Max Woods, Brent Hill, Ryan Marshall, Zach Sears
Mar. 27 2009
Index
Section
Mission Overview
Mission Requirements
Fundimental Block Diagram
Concept of Operations
Structual Drawings
Structual Drawings
Structure**
Schematic*
Parts List*
Subsystem Overview*
Subsystems-Peltier Cooler**
Subsystems-Pendulum**
Test Plans
Cold Test Results**
Cold Test Results**
Cold Test Results**
Management
Conclusion
Appendix A-Calculations: Impact Test**
Appendix B-Weight Breakdown**
Appendix C-Box Dimensions**
*Change from original CDR, **New since original CDR
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Mission Overview
 The goal of GoGreen SAT is to observe the most
effective materials and conditions in which a payload
can generate energy to be used and stored.
 GoGreen SAT will determine the maximum energy
output of different onboard systems throughout the
flight.
 The three energy systems are:
 Pendulum: Capturing the swinging motion of the
flight line
 Solar Power: Capturing energy from the sun
 Peltier Cooler: Using the differences in temperature
inside and outside the box to produce energy
Mission Requirements
Requirement
Method
The payload must not exceed a weight of 1.5 kg.
Design, Test
The flight line should go through the payload's center of gravity.
Design, Analysis
The payload must be able to survive an impact of at least 16m/s.
Design, Test, Analysis
Components in payload must be able to survive a temperture of -80˚C. Design, Test
Payload must not "cut" through the flight line.
Design, Test
Payload must survive the "shaking" of balloon burst.
Design, Test
Green: Compliant, Yellow: Partially Compliant, Red: Not Compliant
Status
Fundamental Block Diagram
Concept of Operations
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Before the launch of the balloon, the payload will be activated via an
external switch to provide power to the Logmatic recording software.
During the ascent, the software will gather current readings from the solar
panels, the Peltier cooler, and the pendulum system. At a rate of 100 data
points per second.
The solar cells will gather light energy from the sun depending on the
payload’s orientation (an increase in altitude is expected to produce an
increase in energy output).
The Peltier cooler will produce a current as the outside of the payload is
cooled by decreasing atmospheric temperatures, and the inside of the
payload maintains a reasonably warmer climate.
The pendulum system is expected to produce a current as the turbulence of
the payload causes the pendulum to swing the attached magnet over a
series of six copper coils.
After payload recovery the SD card will be taken out of the data logger and
the flight data will be dumped into excel. The data will be calibrated.
Structural Drawings
Copper Coils on Board
Pendulum
Side View of Box, Solar Panels on Top
Structural Drawings
Side View of Box
Battery
Logomatic
Hot Hands
Peltier Cooler
Hobo, Barometer
Top View of Box
Copper Plate
Copper Coil
Pendulum
Back View of Box
Structure
 The box will be made out of ½ inch foam core
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board which will be cut to the correct
dimensions.
The box will be held together with hot glue.
The box will be reinforced with additional foam
core board inside.
The outside of the box will be painted black to
help absorb the heat from the sun.
PVC pipe will run through the middle of the box
for the flight line to go through.
The pipe will be attached to the box using ball
bearings.
SolarPa
1
*There will be resistors added to pull the created power
CurrentSensor
SolarPa
2
*The grounds will go to the
ground on the Logomatic
Barometer
Peltier
Cooler
CurrentSensor
Logomat
8 Data
7 Seq
D1
DIODE
CurrentSensor
6
5
4
3
2
1
CP1
CP2
StartSw
+ V1
7V
L1
100 coils
L2
100 coils
L3
100 coils
L4
100 coils
L5
100 coils
L6
100 coils
Schematic
Parts List
Parts
Company
Model
Solar Panels
Flex Solar Cells, OEM Components
RC 7.2-75
Peltier Cooler
Frozen CPU
437W
Magnet
K&J Magnetics, Inc.
DX0X0-N52
Low Current Sensor
Sparkfun Electronics
ACS712
Logomatic
Sparkfun Electronics
V1.0
Ball Bearings
McMaster-Carr
57155K356
Copper Sheet
Whimsie
21-gauge
Foam Core Board
Hobby Lobby
1/2"
SD Card
Lithium Battery
7V
Subsystem Overview
 Power for the payload will come from a 7V
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battery.
Data from the flight will be stored at a rate of
100 points per seconds in a SD card.
The payload will have two states, non-active and
active. A protected switch will be installed on the
outside of the box to activate the payload.
Peltier Cooler-there must be a temperature
difference between the two plates.
The inner components (Hobo, battery,
logomatic, and SD card) should not get below
negative 20˚C.
Pendulum-Must swing in only one dimension.
Subsystems-Peltier Cooler
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Peltier Cooler- If you apply a voltage
to a thermocouple it causes a
temperature difference between the
two plates.
The Seebeck Effect- If two different
metals are connected at two
different locations and there is a
temperature difference between the
two junctions a voltage will be
created.
The peltier cooler will be used to
create the Seebeck effect and
produce a voltage by creating a
temperature difference between the
plates.
The peltier cooler will be integrated
into the box so one side faces out of
the box and the other inside.
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There will be a copper sheet on the
outside of the box to cool that face
of the peltier cooler more
efficiently.
Hot Hands will be used to heat the
other side of the peltier more
efficiently inside the box.
*http://www.heatsink-guide.com/peltier.htm
Subsystems-Pendulum
 The pendulum system
will use magnetic
induction to create
power.
 A magnet will be placed
on the end of the
pendulum.
 The pendulum will swing
back and forth over six
copper coils.
 The swinging motion of
the balloon flight line will
drive the pendulum.
Test Plans
 Cold Test- Dry Ice/Liquid Nitrogen, Styrofoam
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cooler, four thermo probes, four multimeters,
timer
Impact Test- high place to drop box from
Shake Test- Line/string
Time Test- Timer
Flight Simulation Test- Time and Cold test
combined with all components
running/storing data
Cold GoGreenSAT:
Test Cold
Results
Test #1
20
Temperture(degrees C)
15
10
5
0
-5
0
5
10
15
20
25
30
35
40
45
Inside box Temp ˚C
Cooler Temp ˚C
-10
-15
-20
-25
Time (min)
GoGrennSAT: Cold Test #2
30
Temperture (degrees C)
25
20
15
10
5
Inside Inner box ˚C
0
-5 0
5
10
15
20
25
30
35
40
45
Cooler Temp ˚C
-10
-15
-20
-25
Time (min)
Cold Test #1 and #2: The box was suspendered inside a cooler where dry ice was placed. This test was done to see
how well a box inside the main box would insulate the electrical components. The dry ice did not cool the box
enough and an additional test had to be run.
Cold Test Results
Go Green SAT: Cold Test 3
40
20
0
Temperture (degrees C)
0
10
20
30
40
50
60
-20
Backhalf of Box ˚C
Fronthalf of Box ˚C
-40
Inner Box ˚C
Cooler Temp ˚C
-60
-80
-100
-120
Time (min)
Cold Test 3: The box was suspended inside a cooler with liquid nitrogen in the
bottom of it . The liquid nitrogen cooled the box past the predicted low
temperature of the flight. Another test will be run at a later date when all of the
components are working.
Cold Test Results
Peltier Cooler Cold Test #1
8
6
Voltage (mV)
4
2
Pelier (mV)
0
0
20
40
60
80
100
120
-2
-4
Temperature Difference (˚C)
Peltier Cooler Cold Test #1: This test was run during cold test #3. The results from
this test showed that there needed to be a way to stop the peltier cooler from
pulling voltage from the system.
Impact Test Results
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A test box was constructed of the same size and relatively the same
weight as the flight box to use for the impact test.
This was done as to not damage any actual flight components before
flight.
During actual flight impact the two pieces that need to survive are the
Logomatic and SD card.
The test box was dropped of a stair well at different heights.
The impact speed from past flights was calculated to be between
10mph-35mph (4.5m/s-15.5m/s).
Flight of Stairs
Impact speed(m/s)
Damage done to Box
1
7.7
none
2
10.8
none
3
13.3
slight dent
4
15.3
slight dent
5
17.1
slight dent
Management
 Program Manager-Jessica
 Project Members-Max, Brent, Ryan, Zach
 Faculty- Dr. Bob Walch
 Meetings, Tue. 6:00 p.m. and Thus. 7:00 p.m.
and scheduled as needed
 Budget-$800-$900
Conclusion
 Issues/Concerns:
 The magnet used in the pendulum system will
interfere with other components in the box.
 The current produced by the pendulum system will be
to little to measure at times.
 The temperature difference between the two plates of
the peltier cooler will “flip-flop” during the descent,
which will pull energy instead of produce it. This
problem could solved with a diode.
 The box will continue to swing in one direction for
extended amounts of time, causing the pendulum not
to move much.
This data from this payload should allow the efficiency of
each system to be analyzed during the different
sections of the flight.
Appendix A
Calculations: Impact Test
vf^2=vi^2+2gh
vf=sqrt(vi^2+2gh)
vf=2gh
vi=initial velocity=0 m/s
g=9.79m/s
vf=impact speed
h=drop height
Appendix B
Weight Breakdown
Item
Center Rod
Peltier Cooler
Copper Sheet
Box Frame
Magnet
Coils and Base
Pendulum
Solar Cells
Batteries
Inner Box
Ball Bearings
Hot Hand Pack
Bearings for Rod
Total Payload Weight
*Estimated Total Weight=1.4kg
Weight (kg)
.019
0.056
0.3
0.315
0.096
0.217
0.03
0.012
0.12
0.086
1.165
Appendix C
Box Dimensions
7”
10.6”
20.5”
20.5”
7”
14”
7”
14”
20.5”