Slide 1 - the Colorado Space Grant Consortium by shuifanglj

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									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                                                Slide Number
Mission Overview                                              3
Mission Requirements                                          4
Fundimental Block Diagram                                     5
Concept of Operations                                         6
Structual Drawings                                            7
Structual Drawings                                            8
Structure**                                                   9
Schematic*                                                   10
Parts List*                                                  11
Subsystem Overview*                                          12
Subsystems-Peltier Cooler**                                  13
Subsystems-Pendulum**                                        14
Test Plans                                                   15
Cold Test Results**                                          16
Cold Test Results**                                          17
Cold Test Results**                                          18
Management                                                   19
Conclusion                                                   20
Appendix A-Calculations: Impact Test**                       21
Appendix B-Weight Breakdown**                                22
Appendix C-Box Dimensions**                                  23

 *Change from original CDR, **New since original CDR
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                   Status


 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
Fundamental Block Diagram
Concept of Operations
   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
    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.
*There will be resistors added to pull the created power
             *The grounds will go to the
             ground on the Logomatic




                           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

SD Card

Logomatic            Sparkfun Electronics               V1.0

Ball Bearings        McMaster-Carr                      57155K356

Copper Sheet         Whimsie                            21-gauge

Foam Core Board      Hobby Lobby                        1/2"

Lithium Battery                                         7V
Subsystem Overview
 Power for the payload will come from a 7V
    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
   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                There will be a copper sheet on the
    produce a voltage by creating a               outside of the box to cool that face
    temperature difference between the            of the peltier cooler more
    plates.                                       efficiently.
   The peltier cooler will be integrated        Hot Hands will be used to heat the
    into the box so one side faces out of         other side of the peltier more
    the box and the other inside.                 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
    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
                                             Test Results
                                       Cold GoGreenSAT: Cold Test #1
                          20
                          15
                          10
 Temperture(degrees C)




                            5
                           0
                                                                                                      Inside box Temp ˚C
                           -5 0    5    10   15       20                25   30   35   40       45
                                                                                                      Cooler Temp ˚C
                          -10
                          -15
                          -20
                          -25
                                                           Time (min)

                                                  GoGrennSAT: Cold Test #2
                          30
                          25
                          20
 Temperture (degrees C)




                          15
                          10
                            5
                                                                                                       Inside Inner box ˚C
                           0
                                                                                                       Cooler Temp ˚C
                            -5 0   5    10   15       20                25   30   35   40        45
                          -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
                                0       10          20            30         40          50          60
Temperture (degrees C)




                          -20
                                                                                                          Backhalf of Box ˚C

                          -40                                                                             Fronthalf of Box ˚C
                                                                                                          Inner Box ˚C

                          -60                                                                             Cooler Temp ˚C



                          -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



               4
Voltage (mV)




               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
   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                           Weight (kg)
 Center Rod                       .019
 Peltier Cooler                   0.056
 Copper Sheet                       0.3
 Box Frame                        0.315
 Magnet                           0.096
 Coils and Base                   0.217
 Pendulum                          0.03
 Solar Cells                      0.012
 Batteries                         0.12
 Inner Box                        0.086
 Ball Bearings
 Hot Hand Pack
 Bearings for Rod
 Total Payload Weight             1.165

*Estimated Total Weight=1.4kg
       Appendix C
     Box Dimensions
                           7”




                   10.6”        20.5”

     20.5”     20.5”


7”

             14”



       7”

                   14”

								
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