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HUYGENS PROBE (NAIF ID = -148) SPACECRAFT
CONFIGURATION TEXT KERNEL


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ID148_Spacecraft_Description = ( 'HUYGENS PROBE +'
                               'SPACECRAFT +'
                               'CONFIGURATION')

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Spacecraft Initial Mass [kg] for the four phases:

   1.- ENTRY PHASE FROM 1270 KM ALTITUDE UP TO MAIN CHUTE DEPLOYMENT
   2.- DESCENT PHASE WITH MAIN CHUTE AND FRSS
   3.- DESCENT PHASE WITH ONLY MAIN CHUTE (AFTER FRSS EJECTION)
   4.- DESCENT PHASE WITH STABILIZER


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ID148_Mass = (3.20D+02, 2.88677D+02, 2.0764D+02, 2.02423D+02)

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Spacecraft cross-sectional area [m**2] for the four phases:

   1.- ENTRY PHASE FROM 1270 KM ALTITUDE UP TO MAIN CHUTE DEPLOYMENT
   2.- DESCENT PHASE WITH MAIN CHUTE AND FRSS
   3.- DESCENT PHASE WITH ONLY MAIN CHUTE (AFTER FRSS EJECTION)
   4.- DESCENT PHASE WITH STABILIZER

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ID148_Area = (5.730D+00, 5.9830D+01, 5.544D+01, 8.570D+00)


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Sigma value for mass ablation effect [m**-2 s**2]
Sigma = 4.18E-10 corresponds to total entry phase
ablation mass loss of 9.7 kg.
Estimated by V. Gaborit [Ref. 1]

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ID148_Sigma=(4.180D-10)

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Initial guess for aerodynamic drag coefficient
for first iteration in the reconstruction of
atmospheric properties.

For Free Molecular Flow Regime and AOA=0 deg:
CA = CD = 2.09


AOA [DEG]   |    CA
------------------------
0           |  2.09

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 ID148_CD =(2.09)

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Spacecraft Diameter [m] (Frontshield)


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ID148_DIAMETER=(2.6937)


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 References:

 [Ref. 1] V. Gaborit, PhDThesis: " Modèles et méthodes
          expérimentales qui supportent une mission spatiale:
          reconstruction de la trajectoire d'une sonde dans
          une atmosphère planétaire