This file contains examples of a clock calibration report and
an Attitude and Orbit State Report for the ACE mission. This is
the format in which ASC receives the data from GSFC. It is NOT
the format in which ASC delivers the data to investigators.

BEGIN_GROUP=HEADER;
        FILENAME=ACE_GMOC_CCR_1997-261T00-00-00Z_V01.DATA;
        CDH=A;
        DATE_CREATED=1997-262T21:47:55Z;
END_GROUP=HEADER;
BEGIN_GROUP=Daily_Clock_Calibration_Record;
/* Daily Linear Regression Equation relating spacecraft    */
/* counts to seconds from spacecraft epoch:                */ 
/*   T =  C * SLOPE + OFFSET                               */
/*   Where T = elapsed seconds from s/c epoch              */
/*           C = observed s/c time count                   */
/*           SLOPE = slope of regression line              */
/*           OFFSET = y intercept of regression line       */
/*   The regression solution is derived from s/c time      */
/*   count observations from DAY_OF_YEAR/PRODUCT_YEAR.     */
/*   This regression equation will be used by the ACE/IMOC */
/*   to process spacecraft telemetry data with a s/c time  */
/*   count between C_INITIAL and C_FINIAL corresponding    */
/*   to 00:00:00Z of DAY_OF_YEAR +1 to 23:59:59Z of        */
/*   DAY_OF_YEAR +1. THE spacecraft_EPOCH is the time      */
/*   when the ACE spacecraft clock was turned on.          */
     PRODUCT_YEAR=1997;
     DAY_OF_YEAR=261;
     C_INITIAL=2016694;
     C_FINAL=2103094;
     SLOPE-1=-5.65E-07;
     OFFSET=2.69E+00;
     SPACECRAFT_EPOCH=1997-237T15:48:24.604Z;
END_GROUP=Daily_Clock_Calibration_Record;






BEGIN_GROUP = HEADER;
   FILENAME = ACE_GMOC_AOR_2000-052T16-35-59Z_V01.DATA;
   DATE_CREATED = 2000-052T16:35:59.688Z;
END_GROUP = HEADER;
BEGIN_GROUP = Definitive_Attitude_State;
    Spacecraft Clock = 78626883;  /* counts */
    UTC_TIME = 2000-052T16:34:42.810Z;
    PB11 =   1.0000000000e+00;
    PB12 =   0.0000000000e+00;
    PB13 =   0.0000000000e+00;
    PB21 =   0.0000000000e+00;
    PB22 =   1.0000000000e+00;
    PB23 =   0.0000000000e+00;
    PB31 =   0.0000000000e+00;
    PB32 =   0.0000000000e+00;
    PB33 =   1.0000000000e+00;
    State_Status = BEG_PASS;
    J2000_X =   8.5626147609e-01; /* direction cosine */
    J2000_Y =  -5.0371549101e-01; /* direction cosine */
    J2000_Z =  -1.1439837708e-01; /* direction cosine */
    J2000_Spin_Rate_Vector = (  4.4703917019e-01,  -2.6298106525e-01,  -5.9725395794e-02);
    /* radians/sec */
    RTN_R =  -9.9390624897e-01; /* direction cosine */
    RTN_T =   5.6248807569e-02; /* direction cosine */
    RTN_N =   9.4796834842e-02; /* direction cosine */
    RTN_Spin_Rate_Vector = ( -5.1890110345e-01,   2.9366520580e-02,   4.9491772744e-02);
    /* radians/sec */
END_GROUP = Definitive_Attitude_State;
BEGIN_GROUP = Definitive_Orbit_State;
    Spacecraft Clock = 78626883; /* counts */ 
    UTC_TIME = 2000-052T16:34:42.810Z;
    S/C_POS_J2000_X =   1.2854241119e+06; /* km */ 
    S/C_POS_J2000_Y =  -8.2466580375e+05; /* km */ 
    S/C_POS_J2000_Z =  -1.9872274611e+05; /* km */ 
    S/C_VEL_J2000_X =   1.1490533751e-01; /* km/sec */  
    S/C_VEL_J2000_Y =   1.7793135596e-01; /* km/sec */ 
    S/C_VEL_J2000_Z =   5.5727068931e-02; /* km/sec */ 
    S/C_POS_GSE_X =   1.5264086320e+06; /* km */ 
    S/C_POS_GSE_Y =  -1.4396583343e+05; /* km */ 
    S/C_POS_GSE_Z =   1.4570549791e+05; /* km */  
    S/C_VEL_GSE_X =  -1.3516258209e-02; /* km/sec */ 
    S/C_VEL_GSE_Y =  -9.3002421493e-02; /* km/sec */ 
    S/C_VEL_GSE_Z =  -1.9648441077e-02; /* km/sec */ 
END_GROUP = Definitive_Orbit_State;
BEGIN_GROUP = Definitive_Attitude_State;
    Spacecraft Clock = 78627087;  /* counts */
    UTC_TIME = 2000-052T16:38:07.340Z;
    PB11 =   1.0000000000e+00;
    PB12 =   0.0000000000e+00;
    PB13 =   0.0000000000e+00;
    PB21 =   0.0000000000e+00;
    PB22 =   1.0000000000e+00;
    PB23 =   0.0000000000e+00;
    PB31 =   0.0000000000e+00;
    PB32 =   0.0000000000e+00;
    PB33 =   1.0000000000e+00;
    State_Status = END_PASS;
    J2000_X =   8.5626989027e-01; /* direction cosine */
    J2000_Y =  -5.0369903036e-01; /* direction cosine */
    J2000_Z =  -1.1440787484e-01; /* direction cosine */
    J2000_Spin_Rate_Vector = (  4.4713011711e-01,  -2.6302338666e-01,  -5.9741919055e-02);
    /* radians/sec */
    RTN_R =  -9.9390624897e-01; /* direction cosine */
    RTN_T =   5.6275420588e-02; /* direction cosine */
    RTN_N =   9.4781038645e-02; /* direction cosine */
    RTN_Spin_Rate_Vector = ( -5.1900157013e-01,   2.9386103241e-02,   4.9493106544e-02);
    /* radians/sec */
END_GROUP = Definitive_Attitude_State;
BEGIN_GROUP = Definitive_Orbit_State;
    Spacecraft Clock = 78627087; /* counts */ 
    UTC_TIME = 2000-052T16:38:07.340Z;
    S/C_POS_J2000_X =   1.2854476136e+06; /* km */ 
    S/C_POS_J2000_Y =  -8.2462941058e+05; /* km */ 
    S/C_POS_J2000_Z =  -1.9871134843e+05; /* km */ 
    S/C_VEL_J2000_X =   1.1490664080e-01; /* km/sec */  
    S/C_VEL_J2000_Y =   1.7794073282e-01; /* km/sec */ 
    S/C_VEL_J2000_Z =   5.5725635033e-02; /* km/sec */ 
    S/C_POS_GSE_X =   1.5264058678e+06; /* km */ 
    S/C_POS_GSE_Y =  -1.4398485436e+05; /* km */ 
    S/C_POS_GSE_Z =   1.4570147731e+05; /* km */  
    S/C_VEL_GSE_X =  -1.3513618885e-02; /* km/sec */ 
    S/C_VEL_GSE_Y =  -9.2994498541e-02; /* km/sec */ 
    S/C_VEL_GSE_Z =  -1.9653486577e-02; /* km/sec */ 
END_GROUP = Definitive_Orbit_State;