FY  1976 «  197T  and  1977  RDT&E  DESCRTPTIVR  SUMMARY 
Program  Element  #  35158F  Title:  Satellite  Data  System 
Category  Intelligence  and  Communications    Budget  Activity  fh   -  Military  Astronautics  and  Related  Equipment 
BACKGROUND  AND  DESCRIPTION:  The  Satellite  Data  System  (SDS)  is  designed  to  provide  critical  transpolar,  two- 
way,  real-time  command,  control  and  communications  for  Strategic  Air  Command  Single  Integrated  Operational 
Plan  (SIOP)  forces.  Since  a  synchronous  equatorial  orbit  cannot  provide  communi cat ions  coverage  over  the 
polar  regions  above  70  degrees  North  Latitude,  etp&ighly  inclined  elliptica^orbit  was  selectedto  provide  ^ 
..  The  SDS  is  an  integral  part  of  the  Air  Force  Satellite  Communi- 
cations (AFSATCOM)  system  which  includes  the  Air  Force  Ultra  High  Frequency  (UHF)  communications  capability 
on  the  synchronous  equatorial  Fleet  Satellite  Communications  (FLTSATCOM)  program,  piggy-back  transponders  on 
selected  host  satellites,  and  airborne /ground  radio  terminals.  As  euch,  the  SDS  will  complement  the  FLTSATCOM 
program  by  providing  the  requisite  polar  UHF  capability.  Additionally,  the  SDS  will  support  the  Air  Force 
Satellite  Control  Facility  (AFSCF)  requirement  for  reliable  two-way  high  data  rate,  S-band  communications 
between  the  AFSCF  remote  tracking  station  at  Thule,  Greenland  and  the  CONUS. 
\ 
]  The  direct  benefits  derived  from  the  SDS  capabilities  will  be  the  reliable 
and  secure  direct  communications  linkage  over  the  polar  regions  to  provide  greatly  improved  command  and  control 
j>f  SIQP  forces,  eliminate  the  dependence  on  vulnerable  undersea  cables  to  the  Thule  station* 
RELATED  ACTIVITIES:  The  Space  segment  of  the  FLTSATCOM  will  be  developed,  procured  and  launched  under 
FLTSATCOM  Program  Element,  PE  33109N.  The  Air  Force  aircraft  and  ground  UHF  radio  terminals  required  for 
operation  with  the  FLTSATCOM  and  SDS  satellites  will  be  procured  within  the  AFSATCOM  Program  Element,  PE  336"01F. 
The  AFSCF  statins  are  funded  under  the  AFSCF  Program  Element,  PE  35H0F. 
WORK  PERFORMED  BY:  Headquarters,  Air  Force  Systems  Command,  Space  and  Missile  Systems  Organization  (SAMSO), 
Los  Angeles,  California,  is  responsible  for  the  Satellite  Data  System.  The  primary  contractor  is  Hughes 
Aircraft  Company,  El  Segundo,  California.  General  Systems  Engineering  and  Technical  Direction  (GSE/TD)  is 
performed  by  The  Aerospace  Corporation,  El  Segundo,  California. 
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Budget  Activity  f/U   -  Military  Astronautics  and  Related  Equipment 
Program  Element  #  35158F  Title:  Satellite  Data  System 
PROGRAM  ACCOMPLISHMENTS  AND  FUTURE  PROGRAMS: 
1.  FY  197k  and  Prior  Accomplishments:  The  technology  phase  of  the  program  was  completed  in  FY  1971.  This 
was  followed  by  a  contract  definition  phase  in  FY  1972  which  established  the  system  configuration.  The 
system  acquisition  contractor  was  selected  by  competitive  source  selection  and  a  system  development  contract 
was  awarded  in  June  1972.  The  system  critical  design  review  (CDR)  was  successfully  completed  in  March  of 
197?4  with  all  critical  specifications  being  met  or  exceeded.  The  structural  and  qualification  model  space- 
craft and  the  initial  flight  vehicle  (F-l)  are  being  procured  incrementnliv  vith  RDT&E  funds.  A  production 
option  to  the  development  contract  was  exercised  beginning  in  FY  1974.  This  option  provides  for  the 
fabrication,  assembly,  and  test  of  the  first  production  model  spacecraft  (F-2).  The  development  and  produc- 
tion schedules  are  phased  to  achieve  the  required  delivery,  launch  and  system  operational  dates.  The  key 
to  this  phased  schedule  is  that  subsystem  lead-time  is  essential  to  achieve  an  orderly  spacecraft  production 
flow.  Critical  development  and  qualification  activity  is  completed  before  subsystem/system  fabrication  and 
assembly  Is  begun  and  all  development  activity  is  completed  before  production  is  started  at  each  critical 
stage.  The  communications  subsystems  engineering  models  were  completed  by  November  1973.  Fabrication  of 
the  structural  model  spacecraft  was  completed  and  tests  were  begun  in  the  fourth  quarter  FY7^.  Fabrication 
and  assembly  of  the  qualification  model  spacecraft  was  started  during  FY  1971*. 
2.  FY  1975  Program:  Structural  model  testing  and  subsystem  level  qualification  testing  will  be  completed 
during  this  period.  Due  to  industry  wide  delays  in  delivery  of  high-reliability  electronic  piece  parts,  the 
qualification  model  and  development  spacecraft  (F-l)  assembly  and  test  schedules  have  been  altered.  System 
level  qualification  testing  is  now  scheduled  to  begin  during  the  third  quarter  FY75» 
"2   Production  of  the  back-up  flight  vehicle  (F-3) 
will  be  initiated  in  FY  1975.  Launch  vehicle  integration  and  spacecraft  software  development  will  be 
continued  during  this  fiscal  year. 
3.  Planned  Program  for  FY  1976  and  7T:  During  FY  1976,  system  level  qualification  will  be  completed*  / 
\   The  back-up  flight 
vehicle  (F-3)  will  be  delivered.  <& 
li.  Planned  Program  for  FY  1977:  Activities  planned  during  this  period  include  sustaining  engineering 
support,  Initiation  of  study  and  preliminary  design  to  improve  follow-on  satellites  for  survivability, 
reliability,  and  performance.  Design  work  to  convert  the  satellites  to  launch  on  the  space  shuttle  will 
also  be  Initiated. 
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Dudget  Activity  tik  -   Military  Aatronautlco  and  Related  Equipment 
Program  Element  #  3515QF  Title:  Satellite  Data  System 
5.  Program  to  Completion:   This  in  a  continuing^  program.  Ac  an  integral  part  of  the  AFSATCOM  System,  the 
program  will  continue  to  provide  critical  3 communications  coverage  and  be  totally 
compatible  with  the  AFSATCOM  aircraft  and  ground  radio  terminals.  Sustaining  engineering  support  will  be 
required  to  maintain  design  compatibility;  to  incorporate  improvements  for  survivability,  reliability  and 
capability  and  to  provide  additional  replenishment  spacecraft. 
Estimated  Cumulative  RDT&E  Cost  to 
6.  Milestones:  Date  Reach  Milestones  it   In  Millions) 
a.  System  PRD 
b.  System  CDR 
c.  First  Article  Config.  Insp. 
d.  Launch  First  Spacecraft 
e.  Launch  Second  Spacecraft 
f.  Full  Operational  Capability 
Mar 
_Mar 
1973 
197*U 
i 
i 
mf 
kg. 6 
_  96.6 
RESOURCES:   ($  In  Millions) 
FYJ1* 
FYT5  FYT6 
FY7T  FY77 
Additional  to 
Completion 
Total  Estimated 
Cost 
RDT&E:   Funds 
"Quantities 
Flight  Model  Spacecraft 
T-IIIB/Agena  Launch  Vehicles 
ill.  9 
36.5  30.2 
k.O    10. h 
continuing 
Not  applicable 
•These  quantities  will  be  procured  over  the  lifetime  of  the  program. 
39.6  U2.9       9'6    13.1*   9.6      continuing 
Missile  Procurement: 
Funds  (3020) 
Quantities 
Flight  Mnrfol  flpnrrcm.1t 
T-illl5/Ageiiu  Launch  VchlcLci! 
Not  applicable 
/ 
A 
*9The  Qualification  Spacecraft  will  be  refurbished  and  used  as  a  backup  flight  spare. 
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Budget  Activity:  0h   -  Military  Astronautics  and  Related  Equipment   
Program  Element:   35156F  -  Satellite  Data  System   
Test  and  Evaluation  Data 
1.  Development  Test  and  Evaluation:  The  development  contractor  for  the  Satellite  Data  System  (SDS) 
is  Hughes  Aircraft  Company,  El  Segundo,  California.  The  contractor  is  conducting  the  development 
program  in  support  of  satellite  launches  _   _ to  establish  the  initial  orbital 
deployment  and  achieve  an  Initial  Operational  Capability  _.  The  first  satellite  to  be 
launched  (P-l)  is  being  funded  entirely  within  the  development  program.  The  second  flight  spacecraft 
(F-2)  is  the  first  vehicle  being  funded  under  the  production  program.  The  development  hardware  includes 
engineering  models  of  the  communication  subsystems,  a  structural  model  spacecraft  (X-l)  and  a  full-up 
qualification  model  spacecraft  (Y-l).  Development  tests  of  the  communication  subsystems  engineering 
models  were  completed  In   November  1973  with  all  critical  performance  specifications  being  met  or  exceeded. 
The  X-l  spacecraft  has  been  fabricated,  assembled  and,  is  undergoing  testing 
System  level  qualification  is  designed  to  demonstrate  design  integrity  and  performance  to  specifi- 
cation via  a  series  of  tests  including  shock,  acoustic,  model  survey,  thermal,  electromagnetic  interference 
(EMI),  solar-thermal  vacuum,  and  integrated  system  test.  Subsystem  level  qualification  tests  are  in 
progress  and  will  be  completed  prior  to  initiation  of  system  level  qualification  testing.  Reliability 
(life)  tests  of  critical  components  will, continue  throughout  the  development  program ■,     The  F-l  spacecraft 
will  undergo  acceptance  test  during  the_ 
The  Y-l  spacecraft  is  a  full  configured  spacecraft  which  will 
be  refurbished,  as  required,  and  used  as  a  back-up  flight  vehicle  (F-h). 
2.  Operational  Test  and  Evaluation:  OTIfcE  is  accomplished  on  the  individual  systems  supported  by  this 
program  element,  such  as:  AFSATCOM,  PE  33601F  and  Satellite  Control  Facility,  PE  35HOF. 
3.  Systems  Characteristics: 
a.     UHF  mission  characteristics 
J?iiG-liOO  MHZ4 
13.2  -  5  KHz  channels,  75  BPS,  two-way  teletypgj^ 
Ant i- Jam  capability  - 
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Budget  Activity:  #U  -  Military  Astronautics  and  Related  Equipment 
Program  Element:  35158P  -  Satellite  Data  System 
f 
b.  AFSCF  Mission  Characteristics 
J(l.l6   -  2.jH$Hz   (3-Band) 
Data  pass  -$56   KBs,  32  KBs^)' 
c.  )pU°   elliptic  avU^rbit  JW2  hprperiod,  transpolar  coverage.  r 
d.  Orbital  life  Mean  Mission  Duration  (MMD)  -'  g 
Mission  characteristics  will  be  validated  during  DT&E,  Operational  characteristics  and 
orbit  performance  vill  be  demonstrated  during  OT&E. 
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