AC5 Peas Lifetime v2

0408-EX-ST-2013 Text Documents

Aerospace Corporation, THE

2013-04-29ELS_136316

 Distribution authorized to U.S. Government agencies and their contractors only;
 Administrative Use, 31 March 2013. Other requests for this document shall be
 referred to The Aerospace Corporation PICOSAT Program




 AeroCube 5/Peas
 Lifetime Analysis




John P. McVey
Glenn E. Peterson


January 11, 2013


                                          Distribution authorized to U.S. Government agencies and their contractors
John.P.McVey@aero.org                     only; Administrative Use, 31 March 2013. Other requests for this document
                                          shall be referred to The Aerospace Corporation PICOSAT Program
  © The Aerospace Corporation 2013


 Background

  •   AeroCube 5 will deploy small brass tubes called “Peas” from its pea placer device as
      part of the mission.
  •   At the request of David Hinkley (Mechanics Research Office)
                                                          Office), a long
                                                                     long-term
                                                                          term orbit
      evolution analysis was performed.
  •   The analysis provided in this report will determine the lifetime of these Pea tubes as
      ejected
       j      from AeroCube 5 and will determine compliance
                                                         p        with U.S. Debris Mitigation
                                                                                       g
      Standard Practice requirement of an on-orbit lifetime less than 25 years.




                              Distribution authorized to U.S. Government agencies and their contractors
John.P.McVey@aero.org         only; Administrative Use, 31 March 2013. Other requests for this document
                              shall be referred to The Aerospace Corporation PICOSAT Program


 Long-Term Orbit Propagation Tools
   •   Used precision integration code TRACE for orbit propagations
         – Developed by Aerospace (TRACE is used throughout the industry, but we used the most
           recent Aerospace version)
         – MSISE-86 atmosphere
                         p     model
         – 70 x 70 modified EGM-96 Earth gravity model
         – Sun and Moon gravity
         – Solar radiation pressure (assumed reflectivity coefficient = 1.3)


   •   The Pea tubes are assumed to be ejected soon after Aerocube 5 deployment from the
       launch vehicle.




                                 Distribution authorized to U.S. Government agencies and their contractors
John.P.McVey@aero.org            only; Administrative Use, 31 March 2013. Other requests for this document
                                 shall be referred to The Aerospace Corporation PICOSAT Program


 Peas Initial Conditions
   •   Area estimation:
        – Pea tube (assuming tumble) area = 1.007e-4 m2


   •   Mass estimate: 1.25 grams


   •   Atmospheric Assumption: Considered 5th, 50th, 95th percentile levels of solar flux
       (F10.7 ) and geomagnetic index (Ap)
        – Used NASA Marshall Space Flight Center monthly predictions (based on NOAA data) from
          January 2012 to 2030; for years after 2030, repeated last 11-years (2019-2030) of Marshall
          predicted data


   •   Initial orbit (p
                     (provided by
                                y David Hinkley)
                                              y)
                                                                   o
        – 469 x 972 km perigee/apogee altitude, 120 Inclination, Epoch: December 1, 2013


   •   Ejection velocity of the pea tubes at 1.2 m/s is considered negligible compared to the
       orbital velocity of spacecraft.
                           spacecraft




                                Distribution authorized to U.S. Government agencies and their contractors
John.P.McVey@aero.org           only; Administrative Use, 31 March 2013. Other requests for this document
                                shall be referred to The Aerospace Corporation PICOSAT Program


  Lifetime: Pea tube
   •   The 5th, 50th, 95th percentile atmospheric profiles were used to determine the orbit
       lifetime
   •   The pea tube “nominal” 50th percentile lifetime is ~3.1 years
        – This result is bounded by lifetimes of 1.2 and 8.6 years with high (95th) and low (5th)
          atmospheric profile assumptions.
   •   The pea tube de-orbited within 25 years after launch for all three solar cycle cases




                              Distribution authorized to U.S. Government agencies and their contractors
John.P.McVey@aero.org         only; Administrative Use, 31 March 2013. Other requests for this document
                              shall be referred to The Aerospace Corporation PICOSAT Program


  Conclusions
   •   The Peas tube that is ejected from the AeroCube 5 satellite has an orbital
       lifetime of ~3.1 years in a “nominal” 50th percentile atmosphere.
         – The bounding cases of 95th or 5th percentile atmospheric profiles produce
           lifetimes of ~1
                         1.2
                           2 and 8.6
                                 8 6 years.
                                     years


   •   All cases comply with U.S. Debris Mitigation Standard Practice requirement
       of an on-orbit lifetime less than 25 years
                                            y




                              Distribution authorized to U.S. Government agencies and their contractors
John.P.McVey@aero.org         only; Administrative Use, 31 March 2013. Other requests for this document
                              shall be referred to The Aerospace Corporation PICOSAT Program



Document Created: 2013-04-01 13:41:36
Document Modified: 2013-04-01 13:41:36

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