error occurs when running neptune-sa

[jnnccc]

• Reading planetary ephemerides data...
• Starting propagation...
  FATAL ERROR in subroutine getAtmosphericDensity:
  Object re-entered Earth's atmosphere.
  Error No. 1206 occurred. Propagation stopped.
  %------------------------------------------------------------------
  Error Message: Object re-entered Earth's atmosphere.
  Traceback:
  +-> neptune
  +-> integrateStep
  +-> varstormcow
  +-> deriv
  +-> getAtmosphereAcceleration
  +-> getAtmosphericDensity
  +++ Program terminated! +++

---

[ckebschull]

Hi @jnnccc and welcome!
Can you share you input files?

[jnnccc]

#-----<IRAS/NEPTUNE>-----------------------------------------------------------
#
#   NEPTUNE -- Input File
#   [v1.1.2-release]
#
#------------------------------------------------------------------------------
#
#   Overview
#
#   1)  General configuration
#   2)  Input
#   3)  Output
#   4)  File paths
#   5)  Numerical integration parameters
#
#==============================================================================
#
#   1) General configuration
#
#------------------------------------------------------------------------------
#
#   Run ID (max. 50 characters, no blanks)
#
    neptune
#
#   Switch for progress writing (1 or 0) - and file where it goes to
#
    1
    neptune.tmp
#
#==============================================================================
#
#   2) Input
#
#------------------------------------------------------------------------------
#
#   Input type (state vector)
#
#   1 = cartesian state vector      (GCRF)
#   2 = osculating kepler elements  (GCRF)
#   3 = cartesian state vector      (TEME)
#   4 = cartesian state vector      (ITRF-2000)
#   5 = cartesian state vector      (ITRF-2000 & TEME)
#
  1
#
#   Input type (covariance matrix)
#
#   1 = GCRF
#   2 = UVW frame
#
  2
#
#------------------------------------------------------------------------------
#
#   Propagation time span
#     - gregorian date: YYYY MM DD HH MM SS.SSS... (separated by blanks)
#     - julian day:     XXXXXXX.XX...              (no blanks)
#
  2016 07 20 00 31 50.00   2440980.0    Begin date
  2016 08 03 00 31 50.00   2441345.0    End date
#
#------------------------------------------------------------------------------
#
#   Cartesian state vector (if input type == 1)
#
     615.119526d0               radius   x-component (km)
   -7095.644839d0               radius   y-component (km)
    -678.668352d0               radius   z-component (km)
     0.390367d0                 velocity x-component (km/s)
     0.741902d0                 velocity y-component (km/s)
    -7.796980d0                 velocity z-component (km/s)
#
#   Osculating kepler elements (if input type == 2)
#
   7150.59176    semi-major axis (km)
   0.0012347     eccentricity
   98.4076293    inclination (deg)
   30.3309997    right ascension of ascending node (deg)
   68.5606724    argument of perigee (deg)
   291.5725696   true anomaly (deg)
#
#   Covariance matrix
#
  10.d-06       variance position x/u (km**2)
  100.d-06      variance position y/v (km**2)
  30.d-06       variance position z/w (km**2)
  2.d-10        variance velocity x/u (km**2/s**2)
  1.d-10        variance velocity y/v (km**2/s**2)
  1.d-10        variance velocity z/w (km**2/s**2)
#
  0.d0                      covariance matrix 2nd row (units see above..)
  0.d0 0.d0                 covariance matrix 3rd row
  0.d0 0.d0 0.d0            covariance matrix 4th row
  0.d0 0.d0 0.d0 0.d0       covariance matrix 5th row
  0.d0 0.d0 0.d0 0.d0 0.d0  covariance matrix 6th row
#
#------------------------------------------------------------------------------
#
#   Perturbations to be considered
#
#     1 = on
#     0 = off (special case Gravity potential:  0  = central body force
#                                              >0  = degree of gravity potential
#
  6   Geopotential
  1   Atmospheric drag    ! (0 = off, 1 = on, 2 = on+wind (HMW07))
  1   Sun gravity
  1   Moon gravity
  1   Solar radiation pressure
  1   Earth albedo
  0   Solid Earth tides
  1   Ocean tides
  0   Orbital maneuvers   ! specification to be provided in file as given below in section 'File paths'
#
#   Geopotential model to be used (if geopotential perturbation /= 0):
#     1 = EGM96
#     2 = EGM2008
#     3 = EIGEN-GL04C
#
  3
#
#   Atmosphere model to be used
#     1 = Exponential
#     2 = NRLMSISE-00
#     3 = JB2008
#     4 = NRLMSIS2.0
#
  2
#
#   Use only a subset of spherical harmonics of the geopotential
#     - First set switch to '1', then provide harmonics in the
#       subsequent line
#     - Blank separated codes for harmonics, e.g.: '20 30 22' translates to: '20' -> J2; '30' -> J3; '22' -> J22; etc.
#     - NOTE: only 255 characters in total can be used to define spherical harmonics
#
  0   ! on/off switch
  20 30
#
#   Shadow model options
#
  1   ! Shadow model switch (0 = no shadow, 1 = conical)
  0   ! Shadow boundary correction (Lundberg algorithm, 1 = on, 0 = off)
#
#   Covariance matrix propagation
#
  1     Propagation switch (1=on, 0=off)
  2     Degree of geopotential (0=two-body only, n=degree of geopotential, but smaller than or equal to degree in state vector propagation!)
  1     Atmospheric drag (variational equations)
  0     Sun  (variational equations)
  0     Moon (variational equations)
  0     Solar radiation pressure (variational equations)
#
#   Noise matrix computation
#
#     1 = on (only considered if covariance matrix propagation is on)
#     0 = off
#
  0
#
#------------------------------------------------------------------------------
#
#   Further options
#
#   a.1) Earth orientation parameters
#           1 = on
#           0 = off
  1
#
#   a.2) Precession-Nutation theory lookup tables
#           1 = on
#           0 = off
  1
#
#   b) Satellite characteristics settings
#       1 = constant (cannon-ball model), from this input file (see c))
#       2 = read from tabular data file
  1
#
#   c) Satellite characteristics
#
  1.3d0         Mass (kg)
  0.01d0        Cross-section (m**2)
  2.2d0         Drag coefficient
  1.3d0         Reflectivity coefficient
#
#   d) Solar and geomagnetic activity long-term forecast (used if no data is available)
#
  15            Geomagnetic activity Ap
  150.0         Solar activity (sfu)
#
#   e) Re-entry stop condition (min. altitude, km)
#
  50
#
#==============================================================================
#
#   3) Output
#
#------------------------------------------------------------------------------
#
#   Output time step (in seconds)
#
  60
#
#   Time step for ephemerides in internal array (available via 'getNeptuneData' API)
#   (in seconds - IF not '0' then output time step (above) will be overwritten by this
#   value!)
#
  0
#
#   Desired output (1 = on, 0 = off)
#
  1           cartesian state vector             vs. time
  1           osculating kepler elements         vs. time
  0           geodetic lat., lon. and altitude   vs. time
  0           total atmospheric density          vs. time
#
  0           variances (ECI, diagonal elements) vs. time
  1           variances (UVW, diagonal elements) vs. time
  0           covariances (ECI, non-diagonal)    vs. time
  1           covariances (UVW, non-diagonal)    vs. time
#
  1           total accelerations                vs. time
  0           acceleration due to geopotential   vs. time
  0           acceleration due to drag           vs. time
  0           acceleration due to Sun            vs. time
  0           acceleration due to Moon           vs. time
  0           acceleration due to SRP            vs. time
  0           acceleration due to Earth albedo   vs. time
  0           acceleration due to solid tides    vs. time
  0           acceleration due to ocean tides    vs. time
  0           acceleration due to orb. maneuvers vs. time
#
#==============================================================================
#
#   4) File paths
#
#------------------------------------------------------------------------------
#
  data              Data path (files which are not edited)
  input             Input path (files which are edited)
  output            Output path
#
  neptune.mnv       Orbital maneuvers input file
  neptune.srf       Oriented surfaces definition file
#
  fap_day.dat       Data file for daily solar and geomagnetic activity
  fap_mon.dat       Data file for monthly solar and geomagnetic activity (only used if ESA daily data file used)
  apexgrid.dat      Pre-computed interpolation grid for quasi-dipole coordinates (needed for HWM07)
  dwm07b_104i.dat   Disturbance winds data file (needed for HWM07)
  hwm071308e.dat    Horizontal Wind Model (HWM07) data file
  eop19620101.txt   Earth Orientation Parameters data file
#
#==============================================================================
#
#   5)  Numerical integration parameters
#
  1          Integrator to be used (1 = Variable-step Störmer-Cowell, 2 = Fixed-step Gauss-Jackson)
#
  1.d-10     Störmer-Cowell relative tolerance
  1.d-11     Störmer-Cowell absolute tolerance
#
  60.d0      Covariance matrix integration step size (sec) [multiple of output step, should not be greater than output step!!]
  3          Covariance matrix integration method: 1=taylor expansion, 2=RK4, 3=RK8
#
#   Integration logfile (stepsize, local error)
#     1 = on
#     0 = off
#
  0
#
#------------------------------------------------------------------------------

[jnnccc]

History version: ae01399 is OK

[ckebschull]

Thanks for sharing!
I just ran the configuration from the new develop branch. Can you check whether this issue persists on your side using this new branch?