/// <summary>
/// This method is used to store in a list all TLE parameters for each epoch time
///
/// Each entry of the return list is a TLE_Sat variable with its parameters defined except for the name (which is not necessary as every entry is related to the same satellite)
/// </summary>
/// <param name="data_raw">List of array of bytes with every TLE (its two lines) for each entry</param>
/// <returns>List of TLE_Sat containing processed data</returns>
public static List <TLE_Sat> TLE_Lines_DataExtractor(List <byte[]> data_raw)
{
try
{
List <TLE_Sat> TLE_individualSat_List = new List <TLE_Sat>();
foreach (byte[] byte_arr in data_raw)
{
TLE_Sat _TLE_sat = new TLE_Sat();
DateTime epoch = new DateTime();
// First row
_TLE_sat.Sat_Number = Convert.ToUInt32((System.Text.Encoding.Default.GetString(byte_arr)).Substring(2, 5));
_TLE_sat.Sat_Classification = (System.Text.Encoding.Default.GetString(byte_arr)).Substring(7, 1);
_TLE_sat.Sat_IntDesignator = (System.Text.Encoding.Default.GetString(byte_arr)).Substring(9, 8);
_TLE_sat.Sat_ElementSetEpoch = (System.Text.Encoding.Default.GetString(byte_arr)).Substring(18, 14);
_TLE_sat.Sat_FirstMeanMotionDer = Convert.ToDouble((System.Text.Encoding.Default.GetString(byte_arr)).Substring(33, 10), System.Globalization.CultureInfo.InvariantCulture);
_TLE_sat.Sat_SecMeanMotionDer = TLE_Data_AuxMethods.GetDoubleFromScientificNotation((System.Text.Encoding.Default.GetString(byte_arr)).Substring(44, 8));
_TLE_sat.Sat_BSTARDrag = TLE_Data_AuxMethods.GetDoubleFromScientificNotation((System.Text.Encoding.Default.GetString(byte_arr)).Substring(53, 8));
_TLE_sat.Sat_SetType = (System.Text.Encoding.Default.GetString(byte_arr)).Substring(62, 1);
_TLE_sat.Sat_SetNumber = (System.Text.Encoding.Default.GetString(byte_arr)).Substring(64, 4);
_TLE_sat.Sat_LaunchYear = TLE_Data_AuxMethods.GetLaunchYearFromDesignator(_TLE_sat.Sat_IntDesignator);
_TLE_sat.Sat_LaunchNumber = TLE_Data_AuxMethods.GetLaunchNumberFromDesignator(_TLE_sat.Sat_IntDesignator);
_TLE_sat.Sat_LaunchPiece = TLE_Data_AuxMethods.GetLaunchPieceFromDesignator(_TLE_sat.Sat_IntDesignator);
_TLE_sat.Sat_EpochYear = TLE_Data_AuxMethods.GetYearFromEpoch(_TLE_sat.Sat_ElementSetEpoch);
_TLE_sat.Sat_EpochDay = TLE_Data_AuxMethods.GetDayFromEpoch(_TLE_sat.Sat_ElementSetEpoch);
if (TLE_Data_AuxMethods.GetDateTimeFromEpoch(_TLE_sat.Sat_ElementSetEpoch, out epoch))
{
_TLE_sat.Sat_EpochDateTime = epoch;
}
// Second row
_TLE_sat.Sat_Inclination = Convert.ToDouble((System.Text.Encoding.Default.GetString(byte_arr)).Substring(79, 8), System.Globalization.CultureInfo.InvariantCulture);
_TLE_sat.Sat_RightAscension = Convert.ToDouble((System.Text.Encoding.Default.GetString(byte_arr)).Substring(88, 8), System.Globalization.CultureInfo.InvariantCulture);
_TLE_sat.Sat_Eccentricity = Convert.ToDouble(("0." + (System.Text.Encoding.Default.GetString(byte_arr)).Substring(97, 7)), System.Globalization.CultureInfo.InvariantCulture);
_TLE_sat.Sat_ArgumentPerigee = Convert.ToDouble((System.Text.Encoding.Default.GetString(byte_arr)).Substring(105, 8), System.Globalization.CultureInfo.InvariantCulture);
_TLE_sat.Sat_MeanAnomaly = Convert.ToDouble((System.Text.Encoding.Default.GetString(byte_arr)).Substring(114, 8), System.Globalization.CultureInfo.InvariantCulture);
_TLE_sat.Sat_MeanMotion = Convert.ToDouble((System.Text.Encoding.Default.GetString(byte_arr)).Substring(123, 11), System.Globalization.CultureInfo.InvariantCulture);
_TLE_sat.Sat_RevNumber = Convert.ToUInt32((System.Text.Encoding.Default.GetString(byte_arr)).Substring(134, 5));
// Post-processed data
_TLE_sat.Sat_SemiAxis = TLE_Data_AuxMethods.GetSemiAxisFromPeriod(_TLE_sat.Sat_MeanMotion);
_TLE_sat.Sat_Perigee = TLE_Data_AuxMethods.GetPerigee(_TLE_sat.Sat_SemiAxis, _TLE_sat.Sat_Eccentricity);
_TLE_sat.Sat_Apogee = TLE_Data_AuxMethods.GetApogee(_TLE_sat.Sat_SemiAxis, _TLE_sat.Sat_Eccentricity);
TLE_individualSat_List.Add(_TLE_sat);
}
return(TLE_individualSat_List);
}
catch (Exception ex)
{
Debug.WriteLine(ex.ToString());
return(null);
}
}
public List <TLE_Sat> ParseTLEString(byte[] TLE_data)
{
try
{
// POR AHORA SE PIERDE EL ULTIMO SATELITE, POR COMO ESTA PENSADA LA RECUPERACION
int counter = 0;
int _internal_counter = 0;
TLE_Sat tle_sat = new TLE_Sat();
byte[] buffer = new byte[250];
DateTime epoch;
//List<TLE_Sat> final_list = new List<TLE_Sat>();
while (counter < (TLE_data.Length - 1))
{
if (TLE_data[counter] == 10 && TLE_data[counter + 1] == 49)
{
tle_sat.Sat_Name = System.Text.Encoding.Default.GetString(buffer).Substring(2, 24).Replace("\0", String.Empty).Replace("\r", String.Empty);
Array.Clear(buffer, 0, buffer.Length);
_internal_counter = 0;
}
else if (TLE_data[counter] == 10 && TLE_data[counter + 1] == 50)
{
tle_sat.Sat_Number = Convert.ToUInt32((System.Text.Encoding.Default.GetString(buffer)).Substring(2, 5));
tle_sat.Sat_Classification = (System.Text.Encoding.Default.GetString(buffer)).Substring(7, 1);
tle_sat.Sat_IntDesignator = (System.Text.Encoding.Default.GetString(buffer)).Substring(9, 8);
tle_sat.Sat_ElementSetEpoch = (System.Text.Encoding.Default.GetString(buffer)).Substring(18, 14);
tle_sat.Sat_FirstMeanMotionDer = Convert.ToDouble((System.Text.Encoding.Default.GetString(buffer)).Substring(33, 10), System.Globalization.CultureInfo.InvariantCulture);
tle_sat.Sat_SecMeanMotionDer = TLE_Data_AuxMethods.GetDoubleFromScientificNotation((System.Text.Encoding.Default.GetString(buffer)).Substring(44, 8));
tle_sat.Sat_BSTARDrag = TLE_Data_AuxMethods.GetDoubleFromScientificNotation((System.Text.Encoding.Default.GetString(buffer)).Substring(53, 8));
tle_sat.Sat_SetType = (System.Text.Encoding.Default.GetString(buffer)).Substring(62, 1);
tle_sat.Sat_SetNumber = (System.Text.Encoding.Default.GetString(buffer)).Substring(64, 4);
// Processed items
tle_sat.Sat_LaunchYear = TLE_Data_AuxMethods.GetLaunchYearFromDesignator(tle_sat.Sat_IntDesignator);
tle_sat.Sat_LaunchNumber = TLE_Data_AuxMethods.GetLaunchNumberFromDesignator(tle_sat.Sat_IntDesignator);
tle_sat.Sat_LaunchPiece = TLE_Data_AuxMethods.GetLaunchPieceFromDesignator(tle_sat.Sat_IntDesignator);
tle_sat.Sat_EpochYear = TLE_Data_AuxMethods.GetYearFromEpoch(tle_sat.Sat_ElementSetEpoch);
tle_sat.Sat_EpochDay = TLE_Data_AuxMethods.GetDayFromEpoch(tle_sat.Sat_ElementSetEpoch);
if (TLE_Data_AuxMethods.GetDateTimeFromEpoch(tle_sat.Sat_ElementSetEpoch, out epoch))
{
tle_sat.Sat_EpochDateTime = epoch;
}
Array.Clear(buffer, 0, buffer.Length);
_internal_counter = 0;
}
else if (TLE_data[counter] == 10 && TLE_data[counter + 1] == 48)
{
tle_sat.Sat_Inclination = Convert.ToDouble((System.Text.Encoding.Default.GetString(buffer)).Substring(8, 8), System.Globalization.CultureInfo.InvariantCulture);
tle_sat.Sat_RightAscension = Convert.ToDouble((System.Text.Encoding.Default.GetString(buffer)).Substring(17, 8), System.Globalization.CultureInfo.InvariantCulture);
tle_sat.Sat_Eccentricity = Convert.ToDouble(("0." + (System.Text.Encoding.Default.GetString(buffer)).Substring(26, 7)), System.Globalization.CultureInfo.InvariantCulture);
tle_sat.Sat_ArgumentPerigee = Convert.ToDouble((System.Text.Encoding.Default.GetString(buffer)).Substring(34, 8), System.Globalization.CultureInfo.InvariantCulture);
tle_sat.Sat_MeanAnomaly = Convert.ToDouble((System.Text.Encoding.Default.GetString(buffer)).Substring(43, 8), System.Globalization.CultureInfo.InvariantCulture);
tle_sat.Sat_MeanMotion = Convert.ToDouble((System.Text.Encoding.Default.GetString(buffer)).Substring(52, 11), System.Globalization.CultureInfo.InvariantCulture);
tle_sat.Sat_RevNumber = Convert.ToUInt32((System.Text.Encoding.Default.GetString(buffer)).Substring(63, 5));
Array.Clear(buffer, 0, buffer.Length);
_internal_counter = 0;
_TLE_Sat_List.Add(tle_sat);
tle_sat = new TLE_Sat();
}
else
{
buffer[_internal_counter] = TLE_data[counter];
_internal_counter++;
}
counter++;
}
// Parse ROWS
/*string[] raw_rows = TLE_data.Split('\n');
* List<string> final_rows = new List<string>();
* string _row = "";
*
* for (int i = 0; i < raw_rows.Count(); i++)
* {
* _row += " " + raw_rows[i];
* if ((i + 1) % 3 == 0)
* {
* final_rows.Add(_row);
* _row = "";
* }
* }
*
* // Parse COLUMNS
* List<string[]> final_list = new List<string[]>();
* char[] delimiters = new char[] { ' ', '\r' };
*
* foreach(var item in final_rows)
* {
* string[] raw_final_row = item.Split(delimiters, StringSplitOptions.RemoveEmptyEntries);
* final_list.Add(raw_final_row);
* //Debug.WriteLine("Count: " + final_list.Count + "; Elements: " + raw_final_row.Length);
* }*/
return(_TLE_Sat_List);
//return null;
}
catch (Exception ex)
{
Debug.WriteLine(ex.ToString());
return(null);
}
}
/// <summary>
/// This method is needed to promediate raw data
///
/// In case there is only one entry in the input list, it will not change data except datetime epoch
/// </summary>
/// <param name="TLE_buffer_list">Raw TLE list data input</param>
/// <returns>TLE instance with promediated data</returns>
private static TLE_Sat TLE_PromediateList_Processed(List <TLE_Sat> TLE_buffer_list)
{
try
{
TLE_Sat result = new TLE_Sat();
// Get datetime epoch. In this case hours, minutes and seconds will be 0. As it doesnt matter which entry is used, we get the first one
int day;
int month = TLE_Data_AuxMethods.GetMonthAndDayFromEpoch(TLE_buffer_list[0].Sat_ElementSetEpoch, out day);
DateTime _TLE_epochDatetime;
if (TLE_buffer_list.Count != 1)
{
_TLE_epochDatetime = new DateTime((int)TLE_buffer_list[0].Sat_EpochYear, month, day, 0, 0, 0);
}
else
{
_TLE_epochDatetime = TLE_buffer_list[0].Sat_EpochDateTime;
}
// Promediate certain parameters
double _Sat_ElementSetEpoch_double = 0;
double _Sat_FirstMeanMotionDer = 0;
double _Sat_SecMeanMotionDer = 0;
double _Sat_BSTARDrag = 0;
double _Sat_Inclination = 0;
double _Sat_RightAscension = 0;
double _Sat_Eccentricity = 0;
double _Sat_ArgumentPerigee = 0;
double _Sat_MeanAnomaly = 0;
double _Sat_MeanMotion = 0;
uint _Sat_RevNumber = 0;
double _Sat_Semiaxis = 0;
double _Sat_Perigee = 0;
double _Sat_Apogee = 0;
for (int i = 0; i < TLE_buffer_list.Count; i++)
{
_Sat_ElementSetEpoch_double += Convert.ToDouble(TLE_buffer_list[i].Sat_ElementSetEpoch, System.Globalization.CultureInfo.InvariantCulture);
_Sat_FirstMeanMotionDer += TLE_buffer_list[i].Sat_FirstMeanMotionDer;
_Sat_SecMeanMotionDer += TLE_buffer_list[i].Sat_SecMeanMotionDer;
_Sat_BSTARDrag += TLE_buffer_list[i].Sat_BSTARDrag;
_Sat_Inclination += TLE_buffer_list[i].Sat_Inclination;
_Sat_RightAscension += TLE_buffer_list[i].Sat_RightAscension;
_Sat_Eccentricity += TLE_buffer_list[i].Sat_Eccentricity;
_Sat_ArgumentPerigee += TLE_buffer_list[i].Sat_ArgumentPerigee;
_Sat_MeanAnomaly += TLE_buffer_list[i].Sat_MeanAnomaly;
_Sat_MeanMotion += TLE_buffer_list[i].Sat_MeanMotion;
_Sat_RevNumber += TLE_buffer_list[i].Sat_RevNumber;
_Sat_Semiaxis += TLE_buffer_list[i].Sat_SemiAxis;
_Sat_Perigee += TLE_buffer_list[i].Sat_Perigee;
_Sat_Apogee += TLE_buffer_list[i].Sat_Apogee;
}
_Sat_ElementSetEpoch_double = _Sat_ElementSetEpoch_double / TLE_buffer_list.Count;
_Sat_FirstMeanMotionDer = _Sat_FirstMeanMotionDer / TLE_buffer_list.Count;
_Sat_SecMeanMotionDer = _Sat_SecMeanMotionDer / TLE_buffer_list.Count;
_Sat_BSTARDrag = _Sat_BSTARDrag / TLE_buffer_list.Count;
_Sat_Inclination = _Sat_Inclination / TLE_buffer_list.Count;
_Sat_RightAscension = _Sat_RightAscension / TLE_buffer_list.Count;
_Sat_Eccentricity = _Sat_Eccentricity / TLE_buffer_list.Count;
_Sat_ArgumentPerigee = _Sat_ArgumentPerigee / TLE_buffer_list.Count;
_Sat_MeanAnomaly = _Sat_MeanAnomaly / TLE_buffer_list.Count;
_Sat_MeanMotion = _Sat_MeanMotion / TLE_buffer_list.Count;
_Sat_RevNumber = _Sat_RevNumber / (uint)TLE_buffer_list.Count;
_Sat_Semiaxis = _Sat_Semiaxis / TLE_buffer_list.Count;
_Sat_Perigee = _Sat_Perigee / TLE_buffer_list.Count;
_Sat_Apogee = _Sat_Apogee / TLE_buffer_list.Count;
// Fill all TLE_Sat output. All data not promediated will be the first entry
result.Sat_Number = TLE_buffer_list[0].Sat_Number;
result.Sat_Classification = TLE_buffer_list[0].Sat_Classification;
result.Sat_IntDesignator = TLE_buffer_list[0].Sat_IntDesignator;
result.Sat_ElementSetEpoch = string.Format("{0:0.00000000}", _Sat_ElementSetEpoch_double);
result.Sat_FirstMeanMotionDer = _Sat_FirstMeanMotionDer;
result.Sat_SecMeanMotionDer = _Sat_SecMeanMotionDer;
result.Sat_BSTARDrag = _Sat_BSTARDrag;
result.Sat_SetType = TLE_buffer_list[0].Sat_SetType;
result.Sat_SetNumber = TLE_buffer_list[0].Sat_SetNumber;
result.Sat_Inclination = _Sat_Inclination;
result.Sat_RightAscension = _Sat_RightAscension;
result.Sat_Eccentricity = _Sat_Eccentricity;
result.Sat_ArgumentPerigee = _Sat_ArgumentPerigee;
result.Sat_MeanAnomaly = _Sat_MeanAnomaly;
result.Sat_MeanMotion = _Sat_MeanMotion;
result.Sat_RevNumber = _Sat_RevNumber;
result.Sat_LaunchYear = TLE_Data_AuxMethods.GetLaunchYearFromDesignator(result.Sat_IntDesignator);
result.Sat_LaunchNumber = TLE_Data_AuxMethods.GetLaunchNumberFromDesignator(result.Sat_IntDesignator);
result.Sat_LaunchPiece = TLE_Data_AuxMethods.GetLaunchPieceFromDesignator(result.Sat_IntDesignator);
result.Sat_EpochYear = TLE_Data_AuxMethods.GetYearFromEpoch(result.Sat_ElementSetEpoch);
result.Sat_EpochDay = TLE_Data_AuxMethods.GetDayFromEpoch(result.Sat_ElementSetEpoch);
result.Sat_EpochDateTime = _TLE_epochDatetime;
result.Sat_SemiAxis = _Sat_Semiaxis;
result.Sat_Perigee = _Sat_Apogee;
result.Sat_Apogee = _Sat_Apogee;
return(result);
}
catch (Exception ex)
{
Debug.WriteLine(ex.ToString());
return(null);
}
}
