Revisiting the DSST Standalone Orbit Propagator

  1. Cefola, P.J. 46
  2. Folcik, Z. 15
  3. Di-Costanzo, R. 2
  4. Bernard, N. 2
  5. Setty, S. 7
  6. Juan, J.F.S. 3
  1. 1 53 Maynard Street, Arlington, MA, United States
  2. 2 CS Communications and Systemes, 5 rue Brindejonc des Moulinais, Toulouse Cedex 5, France
  3. 3 Universidad de La Rioja
    info

    Universidad de La Rioja

    Logroño, España

    ROR https://ror.org/0553yr311

  4. 4 University at Buffalo, State University of New York
    info

    University at Buffalo, State University of New York

    Búfalo, Estados Unidos

    ROR https://ror.org/01y64my43

  5. 5 MIT Lincoln Laboratory, United States
  6. 6 Spaceflight Mechanics, and Astrodynamics, Vineyard Haven, MA, United States
  7. 7 German Aerospace Center
    info

    German Aerospace Center

    Colonia, Alemania

    ROR https://ror.org/04bwf3e34

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Revista:
Advances in the Astronautical Sciences

ISSN: 0065-3438

Año de publicación: 2014

Volumen: 152

Páginas: 2891-2914

Tipo: Artículo

SCOPUS: 2-s2.0-84940745575 GOOGLE SCHOLAR

Otras publicaciones en: Advances in the Astronautical Sciences

Resumen

The goal of the Draper Semi-analytical Satellite Theory (DSST) Standalone Orbit Propagator is to provide the same algorithms as in the GTDS orbit determination system implementation of the DSST, without GTDS's overhead. However, this goal has not been achieved. The 1984 DSST Standalone included complete models for the mean element motion but truncated models for the short-periodic motion. The 1997 update included the short-periodic terms due to tesseral linear combinations and lunar-solar point masses, 50 x 50 geopotential, and J2000 coordinates. However, the 1997 version did not demonstrate the expected improved accuracy. Three projects undertaken by the authors since 2010 have led to the discovery of additional bugs in the DSST Standalone which are now resolved.