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  1. GMAT
  2. GMT-4572

Validation not catching aligned outgoing asymptote vector in mission sequence

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      Description

      The following Keplerian elements generate an orbit with the outgoing hyperbolic asymptote vector aligned with the coordinate system z-axis, which is a singularity in outgoing hyperbolic asymptote state type:

      GMAT TestSat.SMA = -20000;
      GMAT TestSat.ECC = 2;
      GMAT TestSat.INC = 90;
      GMAT TestSat.RAAN = 0;
      GMAT TestSat.AOP = 330;
      GMAT TestSat.TA = 0;
      

      In the Spacecraft GUI, converting this state from Keplerian to OutgoingAsymptote causes the error:

      Utility Exception:  Error in Cart2OutgoingAsymptote: Cannot convert from  Cartestion to Outgoing Asymptote Elements because Outgoing Asymptote vector is aligned with z-direction.
      

      The same condition is not caught if the script is reporting OutgoingAsymptote parameters in the mission sequence.

      See attached scripts, which should all generate the same error.

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            jjkparker Joel Parker added a comment -

            Verified as fixed using GMAT R2014a.

            Show
            jjkparker Joel Parker added a comment - Verified as fixed using GMAT R2014a.
            Hide
            jjkparker Joel Parker added a comment -

            Already tested and documented. Closing.

            Show
            jjkparker Joel Parker added a comment - Already tested and documented. Closing.

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              • Assignee:
                jjkparker Joel Parker
                Reporter:
                jjkparker Joel Parker
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                • Created:
                  Updated:
                  Resolved: