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0363-EX-CN-2017 Text Documents

Georgia Institute of Technology

2017-05-16ELS_192084

   Experimental  Station  Frequency  Coordination  Request    —    Page   1     FREQUENCY  COORDINATION  REQUEST     ☐  Tick  here  if  this  space  station  is  also  planned  for  amateur-­satellite  service  operation.     Administrative  information:   0   DOCUMENT  CONTROL   0a   Date  submitted   14-­MAR-­17   0b   Document  version  number  (start  at   0   zero  and  increment  with  each   revised  request)       1   SPACECRAFT  (published)   1a   Name  before  launch   RECONSO   1b   Proposed  name  after  launch   RECONSO   1c   Country  of  license   USA   1d   Contact  individual  at  your  licensing   Douglas  Young   authority  and  contact  information   Federal  Communications  Commission   Experimental  Licensing  Branch   Phone:  (202)481-­2440   Fax:  (202)418-­1918   Email:  Douglas.Young@fcc.gov   1e   API/A  special  section  number   Will  forward  to  the  IARU  Satellite  Advisor  when   available.     2   SPACE  STATION  LICENSE  (published)   2a   Experimental  station  call  sign(s)   Will  furnish  when  issued.   2b   Licensee’s  name     2c   Representative’s  first  (given)  name   Francis   2d   Representative’s  last  (family)  name   Park   2e   Postal  address   Georgia  Institute  of  Technology   School  of  Aerospace  Engineering   270  Ferst  Drive  SE   Atlanta,  GA  30332-­0150   2f   Telephone  number  (including   +1-­973-­820-­3020   country  code)   2g   Representative  e-­mail  address:  our   Fpark8@gatech.edu  or  francis.park1@gmail.com   single  point  of  contact  who  will   receive  all  correspondence     2h   Skype  name  (if  available)   Francis_prk   2i   List  names  and  e-­mail  addresses   sterling.peet@gatech.edu   of  additional  people  (up  to  three)   who  should  receive  copies  of   correspondence   Rev.17      February  2015    

   Experimental  Station  Frequency  Coordination  Request    —    Page   2     Space  station  information:   3   SPACE  STATION  (published)   3a   Mission(s)   The  RECONSO  mission  is  designed  to  demonstrate   Describe  in  detail  what  the  space   visual  detection  and  tracking  of  space  debris  from  a   station  is  planned  to  do.    Use  as   small  Cubesat  platform.  The  spacecraft  has  been   much  space  as  you  need.   designed,  fabricated  and  tested  by  a  team  of  Georgia   Tech  undergraduate  and  graduate  students  who  will   also  be  responsible  for  mission  operations.   Photographs  of  the  sky  regions  of  interest  will  be   acquired  during  the  sunlight  portion  of  the  orbit.   Onboard  processing  will  occur  during  the  eclipse   periods.  Image  processing  will  detect  moving  objects   in  the  acquired  series  of  images  and  assign  orbital   parameters  to  the  detected  objects.  Downlinked  data   will  be  the  estimated  orbital  elements  for  the  debris,   not  raw  images.  RECONSO  contains  no  propulsion   system,  and  is  pointed  using  a  3-­axis  magnetorquer   system.   3b   Planned  launch  date   28-­APR-­2018   3c   Planned  mission  duration   ~  180  days   3d   Proposed  space  station  uplink     1 and  downlink  frequency  plan           Uplink/Downlink  Frequency:  437.325  MHz.     List  for  each  frequency  band:     Frequency  cannot  be  modified  in  flight  by     telecommand.   è frequency  band  (e.g.  435-­438   MHz)   Output  power:  1.5  W     è      indicate  if  operating  frequency   ITU  Emission  Designator:    12K5F2D can  be  changed  by  telecommand   and  frequencies  which  may  be   Common  Description:  9600,  19k2,  38k4  baud  packets,   used   G3RUH  FSK  Antenna  Gain  and  Pattern:  2.15  dBi,     Linear   è output  power     Attitude  Stabilization:  3-­axis  stabilized;;  antenna  in   è      ITU  emission  designator2,3     cross-­track  direction       è      common  description  of  the     emission  including  modulation  type     4 AND    data  rate                                                                                                                       1  Show  all  frequencies  numerically  in  MHz,  or  GHz.    Letter  band  designations  are  not  used.   2  ITU  emission  designators  are  defined  in  Appendix  I  to  the  radio  regulations.    Effect  of  Doppler  shift  is   NOT  included  when  determining  bandwidth.   3  If  using  a  frequency  changing  transponder,  indicate  the  transmitting  bandwidth.    Effect  of  Doppler  shift  is   NOT  included  when  determining  bandwidth.   4  Common  emission  description  means  terms  like  transponder,  NBFM,  PSK31,  1200  baud  packet  (AFSK   on  FM),  etc.   Rev.17      February  2015    

   Experimental  Station  Frequency  Coordination  Request    —    Page   3   è      antenna  gain  and  pattern5     è      attitude  stabilisation,  if  used6       4   INTERNATIONAL  (published)     Countries  with  international   NONE   arrangments  completed  or   anticipated.     5   TELECOMMAND    (NOT  published)   5a   Telecommand  frequency  plan.       Telecommand  Frequency:  437.325  MHz   List:     ITU  Emission  Designator:  11K4F2D Common   è      space  station  telecommand   Description:  1200  baud  packets,  AFSK     frequency  bands,       Link  Budget:   è      ITU  emission  designator(s)   Ground  Station  Transmitter  Power  Output:  35.0  W     Ground  Stn.  Total  Transmission  Line  Losses:  3.5  dB   è      common  description  of  the   Antenna  Gain:  18.9  dBi   emission  including  modulation  type   Ground  Station  EIRP:  30.8  dBW   AND    data  rate   Ground  Station  Antenna  Pointing  Loss:  1.7  dB     Gnd-­to-­S/C  Antenna  Polarization  Losses:  3.0  dB   è      link  power  budget(s)   Path  Loss:  151.5  dB     Atmospheric  Losses:  1.1  dB   è      a  very  general  description  of   Ionospheric  Losses:  0.4  dB   7 any  cipher  system   Rain  Losses:  0.0  dB     Isotropic  Signal  Level  at  Spacecraft:  -­126.8  dBW   Spacecraft  Antenna  Pointing  Loss:  0.4  dB   Spacecraft  Antenna  Gain:  2.2  dBi   Spacecraft  Total  Transmission  Line  Losses:  0.5  dB   Spacecraft  Effective  Noise  Temperature:888  K   Spacecraft  Figure  of  Merrit  (G/T):  -­27.8  dB/K   S/C  Signal-­to-­Noise  Power  Density  (S/No):  73.5  dBHz   System  Desired  Data  Rate:  9600  bps Command   System  Eb/No:  33.7  dB   Demodulation  Method  Selected:  AFSK/FM   Forward  Error  Correction  Coding  Used:  None   System  Allowed  or  Specified  Bit-­Error-­Rate:  1.0E-­05   Demodulator  Implementation  Loss:  1.0  dB   Telemetry  System  Required   Eb/No:  13.8  dB   Eb/No  Threshold:  14.8  dB   System  Link  Margin:  18.9  dB                                                                                                                     5  Common  patterns  include  omnidirectional,  unidirectional  (with  a  pattern).    Unstabilized  is  a  tumbler.    Stabilized  can  be  passive  magnetic,  spinner,  three  axis,  gravity  gradient,  etc.   6 7  Any  means  of  preventing  unauthorized  telecommand  of  the  space  station.    Recommended,  but  not   required.   Rev.17      February  2015    

   Experimental  Station  Frequency  Coordination  Request    —    Page   4     Encryption  Protocol:  AS256               5b   Positive  space  station  transmitter   The  transmitter  may  be  turned  off  via  telecommand.  If   control.   the  flight  computer  is  turned  off  or  fails,  transmission   Explain  how  telecommand  stations   will  cease.    The  RECONSO  mission  has  an  “End  of   will  turn  off  the  space  station   Life”  procedure,  where  all  systems  are  shut  down,   transmitter(s)  immediately,  even  in   including  the  transmitter.   the  presence  of  user  traffic  and/or   space  station  computer  failure.     NOTE:  Transmitter  turn  off  control     from  the  ground  is  absolutely   required.    Software  control  is   useful,  but  does  not  substitute  for   telecommand.   Good  engineering  practice  is  to   make  telecommand  independent   of  all  other  systems.     Be  sure  to  read  the  paper:   Controlling  Space  Station   Transmitters.   5c   Telecommand  stations.   Georgia  Institute  of  Technology   List  all  telecommand  stations.     Contact:  sterling.peet@gatech.edu   Sufficient  Earth  telecommand     stations  must  be  arranged  before   California  Polytechnic  State  University   launch  to  insure  that  can  be   Contact:  bellardo@calpoly.edu   terminated  immediately.    See  RR     22.1  and  #3  of  the  terms  and   conditions  above.     6   Launch  plans  (published)   6a   Launch  agency   Space  Test  Program-­2 6b   Launch  location   Kennedy  Space  Center   6c   Planned  orbit     Include         Apogee:  500  km   è      apogee     Perigee:  800  km   è      perigee   Inclination:  75  degrees   è      inclination   Period:  97.728  minutes è      period       Include  plans  for  orbit  changes.   6d   List  other  satellites  expected  to   LightSail  2,  Armadillo,  others  (not  publicly  available) share  the  same  launch.  Update   Rev.17      February  2015    

   Experimental  Station  Frequency  Coordination  Request    —    Page   5   when  more  information  becomes     available.     Rev.17      February  2015    

   Experimental  Station  Frequency  Coordination  Request    —    Page   6     Earth  station  information:   7   Typical  Earth  station  —  transmitting  (published)   7a   Describe  a  typical  telecommand   An  Earth  station  must  be  equipped  with  a  medium-­ station.   gain  antenna  with  a  method  of  pointing  and  an  FM   radio  with  a  broad  enough  filter  to  allow  for  9600  baud   data  rates. 7b   Link  power  budget.   Ground  Station  Transmitter  Power  Output:  35.0  W   Show  complete  link  budgets  for   Ground  Stn.  Total  Transmission  Line  Losses:  3.5  dB   each  Earth  station  transmitting   Antenna  Gain:  18.9  dBi   frequency  band.   Ground  Station  EIRP:  30.8  dBW   Ground  Station  Antenna  Pointing  Loss:  1.7  dB   Gnd-­to-­S/C  Antenna  Polarization  Losses:  3.0  dB   Path  Loss:  151.5  dB   Atmospheric  Losses:  1.1  dB   Ionospheric  Losses:  0.4  dB   Rain  Losses:  0.0  dB   Isotropic  Signal  Level  at  Spacecraft:  -­126.8  dBW   Spacecraft  Antenna  Pointing  Loss:  0.4  dB   Spacecraft  Antenna  Gain:  2.2  dBi   Spacecraft  Total  Transmission  Line  Losses:  0.5  dB   Spacecraft  Effective  Noise  Temperature:888  K   Spacecraft  Figure  of  Merrit  (G/T):  -­27.8  dB/K   S/C  Signal-­to-­Noise  Power  Density  (S/No):  73.5  dBHz   System  Desired  Data  Rate:  9600  bps Command   System  Eb/No:  33.7  dB   Demodulation  Method  Selected:  AFSK/FM   Forward  Error  Correction  Coding  Used:  None   System  Allowed  or  Specified  Bit-­Error-­Rate:  1.0E-­05   Demodulator  Implementation  Loss:  1.0  dB   Telemetry  System  Required   Eb/No:  13.8  dB   Eb/No  Threshold:  14.8  dB   System  Link  Margin:  18.9  dB     8   Typical  Earth  station  —  receiving  (published)   8a   Describe  a  typical  Earth  station  to   An  Earth  station  equipped  with  some  circularly   receive  signals  from  the  planned   polarized  UHF  Yagi  antennas  for  reception  on  a   satellite.   moveable  mount  for  pointing.   8b   Link  power  budget.   Space  Station  Transmitter  Power  Output:  1.5  W   Show  complete  link  budgets  for   Space  Stn.  Total  Transmission  Line  Losses:  0.3  dB   each  Earth  station  receiving   Antenna  Gain:  0.0  dBi   frequency  band.   Space  Station  EIRP:  1.4  dBW   Space  Station  Antenna  Pointing  Loss:  0.4  dB   S/C-­to-­Ground  Antenna  Polarization  Losses:  3.0  dB   Path  Loss:  151.5  dB   Atmospheric  Losses:  1.1  dB   Ionospheric  Losses:  0.4  dB   Rain  Losses:  0.0  dB   Isotropic  Signal  Level  at  Spacecraft:  -­155.0  dBW   Ground  Station  Antenna  Pointing  Loss:  1.7  dB   Rev.17      February  2015    

   Experimental  Station  Frequency  Coordination  Request    —    Page   7   Ground  Station  Antenna  Gain:  18.9  dBi   Ground  Stn  Total  Transmission  Line  Losses:  7.6  dB   Ground  Stn  Effective  Noise  Temperature:633  K   Ground  Stn  Figure  of  Merrit  (G/T):  -­16.7  dB/K   Signal-­to-­Noise  Power  Density  (S/No):  55.2  dBHz   System  Desired  Data  Rate:  9600  bps Command   System  Eb/No:  15.3  dB   Demodulation  Method  Selected:  GMSK   Forward  Error  Correction  Coding  Used:  None   System  Allowed  or  Specified  Bit-­Error-­Rate:  1.0E-­05   Demodulator  Implementation  Loss:  1.0  dB   Telemetry  System  Required  Eb/No:  13.8  dB   Eb/No  Threshold:  14.8  dB   System  Link  Margin:  1.8  dB       Additional  information:   Do  not  attach  large  files.  Indicate  the  URL  where  the  information  is  available.   9   The  space  station  telemetry  will  be  transmitted  for  1.0  sec  every  20  sec.               Signature:    Licensee  agrees  to  IARU  terms  and  conditions  for  coordination  and  represents   that  all  information  provided  is  true  and  correct.   10                                                                                                                                                                                                    14-­MAR-­2017   __________________________________                    ___________________________      Signature  of  licensee                                                                                          Date  submitted  for  coordination       Rev.17      February  2015    


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