GRACE and GRACE-FO Related Publications (no abstracts)

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Lares Mission: Engineering Aspects

Paolozzi, A., Ciufolini, I., Gabrielli, A., Paris, C., and Sindoni, G., 2015. Lares Mission: Engineering Aspects. Aerotecnica Missili & Spazio, 94(1):23–30, doi:10.1007/BF03404685.

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@ARTICLE{2015AeMiS..94...23P,
       author = {{Paolozzi}, A. and {Ciufolini}, I. and {Gabrielli}, A. and {Paris}, C. and {Sindoni}, G.},
        title = "{Lares Mission: Engineering Aspects}",
      journal = {Aerotecnica Missili \& Spazio},
         year = 2015,
        month = jan,
       volume = {94},
       number = {1},
        pages = {23-30},
     abstract = "{LARES is a satellite of the Italian Space Agency, successfully launched
        with the new VEGA launcher in the occasion of its inaugural
        flight, VV01. It was put in a circular orbit at 1450 km
        altitude. This altitude was required to reduce atmospheric drag,
        whereas the satellite was designed to minimize the non-
        gravitational perturbations acting on the surface of the
        satellite. This was of paramount importance because the mission
        objective is to test Einstein general relativity, and any
        unmodeled effect could spoil the accuracy of the relativistic
        measurement. With the optimal design achieved, this non-
        gravitational unmodeled effects are maintained below 1\% of
        frame-dragging or Lense-Thirring effect. This effect is the
        orbital node shift induced by the Earth rotation as predicted by
        general relativity. To achieve the accuracy required for the
        test, it was conceived a constellation of three laser ranged
        satellites (LAGEOS 1, LAGEOS 2 and LARES) along with the latest
        determination of the Earth gravitational field by GRACE
        satellite. The satellite is a passive system and embedded with
        92 Cube Corner Reflectors that have the properties of reflecting
        back to the emitting ground station the laser pulses, thus
        allowing its precise orbital determination. In this paper
        engineering aspects of the mission will be addressed.}",
          doi = {10.1007/BF03404685},
       adsurl = {https://ui.adsabs.harvard.edu/abs/2015AeMiS..94...23P},
      adsnote = {Provided by the SAO/NASA Astrophysics Data System}
}

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