User manual - Astropedia
Contents
1. 24 PreviSat 3 4 Astropedia c 2005 2015 Location Paris 002720743 East 48975139 North Om Local time UTC offset UTC 01h00 Conditions of observations Maximal elevation of the Sun 6 Minimal elevation of the satellite 10 Range unit km Age of the most recent TLE 2 88 days at 2012 03 18 16 41 00 Age of oldest TLE 3 50 days Jur Date Hour Sat Azimuth Sat Elev RA Sat Decl Sat Cst Ang Mir Magn Alt Range Sun Azim Sun Elev Max Long Max Lat Range Max Magn 12 2012 03 18 205382520 T04q 46 58 50726247 TL0n32m45sS 28 l6 32 LMI 3 99 D 2 0 784 982 1 289 04 26 16 38 28 12 2012 03 18 20 98 51 492 108700739 49 35 10 T h28ms4s 26 1037 Leo 3 54 BD L 0 184 901 7 269 05 33 S16 3919 003 3625 E 48 7964 N 75 0 E 7 4 12 2012 09 18 20 39 02 I111 11 29 498 47 25 TOh24md8s 24 11 53 Leo 3 95 Dr 240 784 2 1002 2 289 06 37 16 40 08 T0 20127205719 05480020 200158441 597 058 53 T15n48m355 tl17 3320 Ser 3 02 G 32 0 783 SIT T5 TANGAN lt l 35047242 TO 2012 08 19 0574040325 1989 41 AS 5275851 L5h52ml3s 413 01400 Ser 0 14 Go w 7835 953 9 DTS LET ZO 1309 55 00243290 E 48 8380 N 2 8 W 6 9 10 2012 03 19 05 40 14 5 196 18 22 4907142 15h55m16s 08 59 S3 Ser 3 36 G 2 0 783 996 9 075 18 31 13 01 07 60 2012 03 19 143200 TL 43 216 0238 LL S4M0S 29h0959m0 75 lt 12 35100 meu 0y40 6 0 J8T 6 1666 9 206111137 ES 49 054 60 2012 03 19 142037 2T716 20 49 D Sya 22. By default and with each starting PreviSat is in the Real time mode that is to say that the display of the elements of the maps as well as the numeric data of the Main and Osculating elements tabs follow the system hour Various time steps ranging between 1 and 60 seconds can be selected in the drop down list for the update of the curves on the maps and the data on the tabs The Manual mode can be activated by several different manners By selecting the manual mode in the choice list By pressing the keys gt F10 jump between Real time and Manual mode and vice versa gt F11 move back in time by time step specified in the drop down list gt F12 move up in time by time step specified in the drop down list By double clicking the date in the Main or Osculating elements tab One can also use the manual mode by modifying the value s of the date of the Main tab or the Osculating elements tab month day year hour minutes or seconds When the manual mode is activated a toolbar appears on the Main tab making it possible to move automatically during time from any date Fa Radar The radar represents the sky of the observer projected on a plan North West East The external circle reproduces the ideal horizon of the observer and the center of the radar is the zenith of the place The other concentric circles are the circles of a height of 30 and 60 degrees The azimuths are graduated by steps of 30 degrees It i
3. a Widebsran w Tenk n i di Capella West 33 Annexes Annex 1 Designation Latin Englush French Ant Antlia Air Pump Machine Pneumatique Aql Aquila Eagle Aigle Agr Aquarius Water Bearer Verseau Ari Aries Ram B lier Aur Auriga Charioteer Cocher Cap Capricornus Sea Goat Capricorne Car Carina Keel Car ne Cha Chamaeleon Chameleon Cam l on CMa Canis Major Breat Dog Grand chien CMi Canis Minor Small Dog Petit Chien Col Columba Dove Colombe Com Coma Berenices Berenice s Hair Chevelure de B r nice CrB Corona Borealis Northern Crown Couronne Bor ale Cru Crux Southern Cross Croix du Sud Crv Corvus Crow Raven Corbeau Cyg Cygnus Swan Cygne Del Delphinus Dolphin Dauphin Dra Draco Dragon Dragon Eri Eridanus River Eridanus ridan For Fornax Furnace Fourneau Gru Grus Crane Grue Her Hercules Hercules Strong Man Hercule Hya Hydra Water Serpent Hydre Femelle Ind Indus Indian Indien Lac Lacerta Lizard L zard Leo Leo Lion Lion Lep Lepus Hare Li vre er oft constellations 35 Lib Libra Scales Balance Lyn Lynx Lynx Lynx Men Mensa Table Mountain Table Mic Microscopium Microscope Microscope Mus Musca Fly Mouche Oph Ophiuchus Serpent Bearer Ophiucus Peg Pegasus Winged Horse P gase Per Perseus Perseus Hero Pers e Phe Phoenix Phoenix Ph nix PsA Piscis Austrinus Southern Fish Poisson Austral Psc Pisces Fishes Poissons Ret Reticulum Net R ticule Sco Scorpius Scorpion Scorpion Ser Serpens Serpent Serpent Sex Sext
4. N INDO IRID ISRA ISS T ITSO JPN LUXE A E NATO NETH NICO NIG NKOR O 03B gt J UJ gt lt Z JJ PAKI O POR PRC D Signification Arab satellite communications organization Asiatsat corp Algeria Argentina Austria Australia Azerbaijan Belarus Brazil Canada Peoples republic of China Brazil Chile Commonwealth of independent states Columbia Czechoslovakia Denmark Ecuador Egypt European Space Agency European Space Research Organization Estonia European organization for the exploitation of meteorological satellites European telecommunications satellite organization EUTELSAT France Germany France Germany Globalstar Greece Hungary International maritime satellite organization INMARSAT India Indonesia Iran Iridium Israel International Space Station Italy International telecommunications satellite organization INTELSAT Japan Luxembourg Malaysia Mexico North Atlantic Treaty Organization NATO Netherlands New Ico Nigeria North Korea Norway O3B Networks Orbital telecommunications satellite GLOBALSTAR Pakistan Poland Portugal Peoples republic of China 17 R Republic of China Taiwan SEAL Sea Launch Demo RA Regional african satellite communications organization S Soci t europ enne des satellites SAUD Saudi Arabia USBZ United States Brazil VENZ Venezuela VTNM Vietnam SAFR South Africa Sc OC OM RP Republic of Philippines ES PN
5. Simplified model pp163 164 Simplified model pp337 342 Simplified model pp209 216 From the formula p88 Sun position Moon position Planets positions Sidereal time of Greenwich Osculating elements Atmospheric extinction Catalog of main stars Astronomical Algorithms 2 edition Meeus Fundamental of Astrodynamics and Vallado Application 2 edition Magnitude corrections for Green atmospheric extinction 1992 Bright Star Catalog 5 1991 Hoffleit Constant Symbol Value Gravitational geocentric constant GM 398 600 8 km s Second zonal harmonic Third zonal harmonic Fourth zonal harmonic Flatness of Earth globe Terrestrial equatorial radius Astronomical unit Solar equatorial radius Lunar equatorial radius Magnitude of solar disc center 0 001 082 6158 0 000 002 538 81 0 000 001 655 97 1 298 26 6378 135 km 149 597 870 km UAI 1976 696 000 km 1738 km 26 98 WGS 72 40 Annex 4 Thanks would like to thank T S Kelso for the information he communicated to me and numerous information available on his site www celestrak com David Vallado for the publication of corrected model SGP4 2006 and the calculation methods present in his Fundamental of Astrodynamics and Applications consult the site www celestrak com to buy it Jean Meeus where the Astronomical Algorithms supplied the essential astronomical calculations calculation of the julian day Sun s position sidereal time Michel
6. 00 2015 07 25 03 27 00 2015 07 25 05 00 00 2015 07 26 01 03 00 2015 07 26 02 35 00 Finish date 2015 07 21 05 14 00 2015 07 22 05 06 00 2015 07 23 04 57 00 2015 07 24 04 48 00 2015 07 25 04 39 00 2015 07 19 04 04 00 2015 07 20 03 10 00 2015 07 20 04 47 00 2015 07 21 02 17 00 2015 07 21 03 54 00 2015 07 21 05 29 00 2015 07 22 03 00 00 2015 07 22 04 37 00 2015 07 23 02 07 00 2015 07 23 03 43 00 2015 07 23 05 20 00 2015 07 24 01 13 00 2015 07 24 02 50 00 2015 07 24 04 27 00 2015 07 25 01 57 00 2015 07 25 03 33 00 2015 07 25 05 10 00 2015 07 26 01 03 00 2015 07 26 02 40 00 Max Elevation Max Magn D0 27 03 0120727 0124717 0125417 0271210 26 48 03 14 19 13 7491605 23 11 18 09 2 03 20 26 46 1411 56704 26 20 20 35 65 55 16 08255 23 6443647 4971530 0271627 3922739 4902455 16 18 48 6473341 5071218 02728 26 76 30 39 114 2 118 10 4 410 2 9 7 0 6 H0 7 4 6 1 7 1 8 0 0 2 1 1 97 2 2 1 6 5 87 1 4 1 7 HI 4 2 2 1 7 Sun Elevation 08702582 28715 46 2 10726 542 11 29 552 177374272 15 06 03 2 18 40 01 2 20 2708 2 16 1418 2 06 3647 2 19 29 59 2 12740052 20956572 17724372 08 09 48 2 2072806 2 2019242 14 00 25 2 21 2750 2 18 28 132 092414472 0370372 21 05 1272 East IMen PEEL d Capella Hirmhak Eomalhaut South West 22 WII Iridtum Flares tab The Iridium flares tab allows to carry out of I
7. 25 deso Mode Los ana consta NES node ironie Pak an na k k 40 ARTES A E PMR SA A A A AAA EA A AOS 41 Ta TEARS Kakak ay ak aia ET AEE AEE A E E 41 Z5 CADRE cons SR I ET NN EE 41 Bnnes ziv 2 COR DC S NE BO ST se uds telae tC bA ER MA RN e TRI NN IUS A KANAAN W WBA HA WA Se E EPUM UR MU AN 42 I Overview PreviSat is free open source software to track artificial satellites on a world map It is developed in C Qt and available on Windows GNU Linux and Mac OSX operating systems Its simple and intuitive interface is designed to meet both the needs of the neophyte to those of the casual observer PreviSat allows to know the position of the satellites in several coordinate systems cartesian equatorial horizontal To do this it uses the SGP4 orbital model revised in 2006 by David Vallado and orbital elements called TLE provided by Celestrak or the Space Track It also displays the position of the Sun and the Moon SGP4 model takes into account only the principal natural disturbances acting on the satellite first terms of the Earth potential irregularities simplified model of atmospheric drag lunisolar disturbances or resonance phenomena it is necessary to regularly reactualize the orbital elements of the satellites in order to guarantee an optimal precision on the position and the speed of the satellites in particular when there is an orbital correction manoeuvre The orbital elements placed at the disposal on the site www
8. AE K S Table 2 countries or organizations 18 VI Predictions tab The Predictions tab allows to make predictions of passes for one or more satellites above a given place of observation Oscilatng elements Satelite informations Predctons es Ontons Start date 07 19 2015 03 56 00 Erase hours ERBS ERS 1 Finish date 07 26 2015 03 56 00 ERS 2 GENESIS 1 Output 1 minute w tput step mnue GENESIS 2 Name of location Paris ho Illumination required H ga 1 2 P ee en 7 HST Sun elevation Civil twilight 6 Maximal magnitud evation twilight 67 iS FT IDEFIX amp ARIANE 42P R B INTERCOSMOS 24 INTERCOSMOS 25 ISIS 1 Default settings Show results Wl Iss Minimal elevation of satellite 0 U It is necessary to supply the initial and final dates and hours the calculation step as well as the place of location By default the initial date is the current date and the initial hour is the current hour truncated to the minute the date by default is initial date increased by 7 days The calculation step is initially fixed at one minute It is possible to take into account of the magnitude of the satellite by ticking the Maximal magnitude box and by indicating the desired magnitude This option will only apply to the satellites of which the standard magnitude
9. This tab contains a list of checkboxes allowing to display or not to display elements in the graphic interface Some checkboxes have 3 possible states Name of satellites box Checked the names of selected satellites are displayed Partially checked the display of the box varies with the system requirements the name of default satellite is displayed Unchecked the display of the names of satellites is disabled Foot print box Checked the foot prints of all selected satellites display Partially checked the foot print of the default satellite displays Unchecked the display of foot prints is disabled Radar box Checked the radar only displays if a satellite is present in the sky of the place of observation Partiellement coch the radar displays permanently Unchecked the display of the radar is disabled Name of locations box Checked the names of all places of observation are displayed Partially checked the name of the default location displays the other locations are represented by a white cross Unchecked the name of the default locationdisplays Display of constellations box Checked when the sky map is maximized the constellation lines and names of constallation are displayed Partially checked constellation lines are displayed Unchecked the display of constellation lines and names of constellations are disabled 28 A first choice list makes it pos
10. and represent the orbit that the satellite would follow if all the disturbances which the satellite undergoes disappeared suddenly We give first of all under the name of state vector the results provided by the SGP4 model namely the components of the positionvector and the velocity vector Then starting from thes components we calculate the following osculating elements e The semi major axis a of the ellipse characterizing the size of the orbit e The eccentricity e characterizing the shape of the ellipse e The inclination i of the orbit measured from the celestial equator always ranging between o and 180 The types of orbit according to the value of the inclination are the following The equatorial orbits have an inclination of o or 180 The direct orbits have an inclination ranging between o and 90 The retrograde orbits have an inclination ranging between 90 and 180 The polar orbits have an inclination of 90 e The right ascension of ascending node Q is the angle measured between the vernal point and the ascending node of the orbit point where the satellite crosses the celestial equator plane from the South to the North and counted along the celestial equator e The argument of perigee w is the angle counted along the orbital plane between the ascending node and the perigee point where the radius vector passes to a minimum e The mean anomaly M is the angle counted from the perigee to the
11. celestrak com and also on the site www space track org in the form of text files are presented in the following way ISS ZARYA 1 25544U 98067A 06283 55379626 000142097 UODUDU D 100095 4451 2 29944 021 0421 119 2529 0003075 219 0525 19279404 15 7 220127920 1472 PreviSat has 2 operating modes real time mode and manual mode The first mode allows to monitor in real time the evolution of the position of the satellites The second mode allows the satellites for dates other than the system date Osculating Elements tab contains instantaneous orbital parameters of the orbit of the selected satellite This allows in particular to estimate the size and shape of the satellite orbit Satellite Information tab details the various components of TLE and also provides information on the satellite itself dimensions maximum magnitude PreviSat calculates the satellite pass predictions for a given place of observation with the possibility of setting many parameters selection of the place of observation minimum height of the satellite height of the Sun PreviSat is able to determine quickly and accurately flares produced by the Iridium satellites which can reach a magnitude of 8 5 which is 30 40 times brighter than Venus Many display options to customize the GUI are available zone of visibility of satellites ground track Sun shadow of the Earth Moon The graphical interface allows easy management of places of observat
12. is known Then it is possible to regulate the minimal elevationwhich the satellite must have for the calculation of the predictions for example if the horizon of your place of observation is masked by a building a mountain or luminous urban pollution If you choose Other in the drop down list you are then invited to select a positive integer value in the adjacent text field In the same way you can parameterize the elevation of the Sun following the criteria below Horizon 0 Civil twilight 6 default value Nautical twilight 127 Astronomical twilight 187 Indifferent all passes will be displayed including those of day Other you are then invited to select an integer value ranging between 90 and 90 in the adjacent text field By default the list of satellites dedicated to predictions is filled by the satellites of the main list of satellites It is possible to add or to eliminate satellites By right clicking on the list we can check all the satellites or none Then just click on the Run button to run the search Once calculations are finished an explicit message appears in the task bar and the button Show results appears By clicking on this button one can display the results obtained and then have the possibility to save them in a text file In the first tab of result window the passes are written in the form of columns as shown in the following example 19 PreviSat 3 4 Astr
13. main window Minor correction in the prediction of passes Standization of source code for Windows Linux MacOS X platforms Version 3 1 revision 3 October 2012 July 2013 Correction for low resolution screens Modification of TLE files management in the user interface Night vision mode Calculation of adapted orbital parameters Online setup Bug fix in checking TLE validity Version 3 0 revision 5 July 2011 October 2012 C 0t development New implementations for predictions of passes Iridium flares orbital events and ISS transits Calculation of coordinates of the maximum for Iridium flares and ISS transits Modifications in the graphic user interface adding planets display of the SAA South Atlantic Anomaly 37 Version 2 3 revision 4 January October 2011 Many internal modifications Add the sky map with the constellations and the name of main stars Maximised display of world map or sky map Add the simulation mode Downloading of new locations and world maps management of TLE downloading Management of satellite names for TLE with 2 lines Version 2 2 revision 2 October 2009 November 2010 Sizeable main window Display of the Moon Management of several locations on the world map Calculation of ISS transits with the Sun and the Moon New display options Version 2 1 revision 8 April October 2009 SGP4 model with corrections from D Vallado use of oriented objec
14. to 360 And the maximum magnitude go The value 99 indicates that the magnitude is not a selection criteria 30 TLE File to read NORAD number Number of revolutions per day from 00 000000000 to 18 000000000 RA of ascending node From 0 to 360 Argument of perigee From 0 to 360 nclinalian iinterva from 0 ale w 180 E Name of personal file For example one wants to build a file containing the most luminous those of which the standard magnitude is known One can retain the following criteria NORAD number All Right ascension of the ascending node From o to 360 Eccentricity From o to 0 001 slightly eccentric one could tolerate satellites of which the orbit is more eccentric and to take from 0 to 0 2 Number of revolutions per day From 14 to 18 to keepthe satellites at low altitude potentially most luminous Inclination From 35 to 145 so as to be visible in temperate zones of the northern hemisphere of the Earth Argument of perigee From o to 360 Maximal magnitude 4 all the satellites where the minimal magnitude is lower than 4 will be kept E Orbital events tab Orbital events Start date 07 19 2015 03 56 00 v Fl ERS 2 GENESIS 1 MD H 2A RJB Events E H 2AR B Passes to nodes Passes to shadow penumbra light IDEFIX amp ARIANE 42P R B Passes to quadrangles Day night transitions E INTERCOSMOS 24 Passes to apogee perigee I
15. 3h02m345 12 12 06 Agr 04106 E 36 0 781 7 1654 4 206 17 55 7748914217 002 3055 E 48 8330 N 4 3 W 6 0 60 2012 03 19 L41920 16 0 216 39 33 22 09 41 23h02mOls 11 48 40 Aor 0440 C 94 0 181 17 1641 8 206 18 38 37 4834 Temps elapsed 0 11s The first column gives the number of the Iridium satellite responsible of the flare Then successively there is the date the hour the coordinates of the satellite and the constellation One then give the angle of reflection of the antenna as well as the concerned antenna F Front R Right L Left Next are specified the visual magnitude of the flare the altitude and the range to the satellite and the coordinates of the Sun Finally we give the terrestrial coordinates where the reflection angle reaches a minimum the distance at the East or at the West to the observer and its visual magnitude Note concerning the observation of Iridium satellites Calculation uses an internal file which provides the attitude state of the satellites to know if the satellite is operational spare or having lost its attitude In general the operational satellites produce flares such as they are envissaged by PreviSat However there can exist an angular offset between the true attitude of the satellite and the theorical attitude manceuvres for example which can result in a magnitude modification The result provided by PreviSat is thus an estimate of the magnitude of the flare in general represented
16. 502 1905 2314 O QO S HO OO QO rP W y OY IN HO 1 01 ds Sun Azim B26 39 55 348 12 46 SAS ATL 348 41 49 348 56 22 ASTON CLO C 20M OLLI 02 OLE 26 34 011 41 06 OIL 55737 OT2 TOO 0127241371 OL2 3950 6 QI 55M 033 00 47 033 13 Se 0997 7 03 033 4010 O33 5 LEN 0340 6 20 QS TD 31 094 92 26 0344512 qM 0847 582m O35 IA 265 Sun Elev 1938515951 18 28 06 18 30 09 18 32 02 D C oO Le 95 wig Le ape 16 SR 02 2 8 26520 18 24 16 ups p o M Le 2001 A n n 5 459 OO 21936537 i Mc HN aL sl 2943 12 204 12 14 42 1209 0057 xu Dots SLL oreo 2 SITENG We point out in the header of the results file the place of location the time zone as well as the conditions of observation here conditions by default We then display for each satellite the list of its passes here 4 passes separated one from another by a line jump Each pass is made up as we can see from date and hour followed by its characteristics First of all the azimuth and the elevation of the satellite then the right ascension the declination and the constellation If the standard magnitude of the satellite is known the visual is then calculated by means of the following formula 2 d m Msta 15 75 2 5 log 5 where d is the range to the observer and the illumination The magnitude is sometimes followed by an asterisk meaning that the satellite is in the p
17. 52 21 3 2015 07 21 23 52 49 7 2620217 6 3 157253172 Iridium 34 2015 07 22 00 01 37 3 2015 07 22 00 01 47 2 2124750 1 8 16 08 34 2 Iridium 41 2015 07 22 02 55 01 2 2015 07 22 02 55 09 4 5121755 1 9 199343472 Iridium 64 2015 07 22 04 25 42 9 2015 07 22 04 25 54 0 50 06 33 1 9 13154172 Iridium 70 2015 07 22 16 58 45 6 2015 07 22 16 58 48 2 4374821 6 5 43257 1272 Iridium 97 2015 07 22 23 46 14 1 2015 07 22 23 46 38 9 26748 14 0 6 15 0506 2 Iridium 5 2015 07 22 23 55 23 2 2015 07 22 23 55 48 8 27224542 0 4 15 51 08 2 Iridium 52 2015 07 23 01 12 40 3 2015 07 23 01 12 53 9 4273513 1 0 207155072 Iridium 11 2015 07 23 06 05 44 9 2015 07 23 06 05 46 9 74 26 56 4 8 01 40 19 0 Ji Toii PA ne r fo in 4 is Pi A A fi o a E 4 isle Adam SS a c 440 4 444 TEN mmt J A 20 km x 10 mi C rgy L m RR 9 faverny a gr P3 4 Sarcelles qmantesta Jone Andr sy DE oe en vyan d e Meaux Eol sy N Saint Denis e N me R Chelles A 140 IPA e di e fa ARIS y e Plaisir 74 IL ewampigir aucMsni Ozoir la Ferri re lap and Map OC nm lt Capella East Cou m West 26 VILL Options tab The Options tab allows to carry tou the adjustments of PreviSat place of observation display d bocati0n tab Satelite informations Location Category selection Locations in the category Selected locations My Favorites Paris A A Location Paris France Longi
18. 7 14231146 12H00ml6s 09 41130 Vir 0 7 274 33 19 2536509 12h14m41s 21 52 47 Com 0 5 294381411 46 48 58 I2n50m255 47 27 48 CVn 1 7 018 13 56 57 08 34 20hn22m37s 76 19 11 Cep 2 0 056171251 3215146 23h20mb52s5 45 17 49 And 0 9 065 34 18 18 09 00 23h45ml0s 29 32 52 Peg 0 4 069 36 03 10 09 22 23h57m15s 21 00 37 Peg 1 7 071 54 29 04 47 29 00h05m45s 15 27 26 Peg 3 7 O73 2655 00251147 00h12m22s ALI 27 EAU Psc 8 8 285 00 21 03205110 12h13m54s T12 09 39 Vir 49 287 27 45 072471221 12h19m58s LI IS Com Z3 291 28 58 14 25 19 12h27m17s 24 53 35 Com 0 9 299 31 38 2504125 12h37m47s 37 47 43 CVn 0 3 322 42 32 43 47 43 13h07m26s 64 01 42 Dra 1 4 033 08 11 51 12 19 23h40m31s 68 46 01 Cep 1 7 070591201 S9 44 55 00h22m16s H34 41 45 And 0 7 082 10 11 173889196 00h33m51s 18 16 41 Psc 065 087 10 57 09 54 19 0O0h41m36s 09 17 17 Psc 1 9 090 03 42 04 38 06 OOh48m02s 03 26 53 Psc 3 9 09158114 00 45 31 00h53m30s 00 43 30 Cet 49 3 m 417 417 418 418 418 417 418 418 418 418 419 419 419 419 418 418 418 419 419 419 419 419 418 418 418 Altitude 417 4 COM CO XO UI N N a OW oO OO On QI Jo O O NEMA OO SA Range 2347 TENE 1040 1409 1803 2208 1242 864 9995 492 TA 1092 1486 16 93 2303 2053 1647 1250 879 586 52 a 759 1112 1
19. Casabonne whose support and contributions helped to bring new features and significant improvements to PreviSat and people who helped me in the development of PreviSat for their advice and their software tests thanks Claudia Yannis R mi JB Benoit Maurice Jean Louis also address thanks to all the people who expressed to me their appreciations of the software 4 Translations English Mr O Donoghe Ea Graphics icons splashscreen Claudia Martinez 41 Annex 5 Contact License This software is under the GNU GPL license version 3 The numerical results can be distributed freely as well as predictions passes of the satellites and Iridium flares have no restrictions The lastest version of the software can be downloaded free at the site astropedia free fr Any non authorized commercial distribution is strictly prohibited For any information suggestion or in the event of a problem send an e mail to the author of the software at the following address astropedia Ofree fr 42
20. NTERCOSMOS 25 El 1518 1 Default settings Show results I55 The third tab allows to determine the orbital events of the selected satellites We can choose the events The passes of the satellite to ascending and descending nodes equatorial crosses The passes to quadrangles at position go and 270 that is to say the passes to the maximal latitudes The passes to shadow penumbra light The passes to apogee perigee And the day night transitions that is to say the passes of the satellite over the day night limit 31 4 Loo Transita tab man Osadatng elements Satelite informations Predcions iridium fares Options TLE update ISS transits Body Start date 07 19 2015 03 56 00 Erase hours Finish date 07 26 2015 03 56 00 Moon Name of location TLE file TE espe a DAN TLE maximal age 2 0 Maximal elongation with the body 5 0 The fourth tab allows calculating the conjunctions and the transits of the ISS with the Sun and or the Moon It is necessary to give the initial and final dates and hours the place of location and the TLE file containing the orbital elements of ISS You have to specify which bodies you want to calculate the transits Sun and or Moon the minimal elevation of satellite and the maximal elongation between ISS and the body The file containing the results shows in its header the conditions of obsevations he results are provided under the form of columns which co
21. ans Sextant Sextant Sgr Sagittarius Archer Sagittaire Tau Taurus Bull Taureau TrA Triangulum Australe Southern Triangle Triangle Austral Tuc Tucana Toucan Toucan UMa Ursa Major Great Bear Grande Ourse Vel Vela Sail Voiles Vir Virgo Maiden Vierge Vo Vul Volans Vulpecula Flying Fish FOX Poisson Volant Petit Renard 36 Annex 2 Version history Version 3 4 revision 5 October 2014 September 2015 Added the weather window for the observer location and for NASA bases Removing the obsolete video stream of ISS Live Changing the display of ISS Live for MacOS X platform Added the magnitude of the Moon Small improvements in source code Corrections for display Corrections in checking software update Corrections in TLE manager Version 3 3 revision 1 November 2013 September 2014 Added the ISS Live Added the Wall Command Center visualization Added the 12 clock 24 clock option Added the map for predictions results New calculation of satellite eclipses with atmospheric refraction Correction of local time offset in the calculations of predictions Correction in TLE updating Version 3 2 revision 1 July November 2013 Modification for checking updates Added more information on the satellites Conservation of the list of satellites for each file of the TLE directory Display of TLE age in ISS Transit tab Display of Iridium satellites status Calculation of Iridium magnitude in the
22. bital period is inferior to 225 minutes we precise NE Near earth on the contrary we indicate DS Deep Space The dimensions of the object and the radar cross section issued from an internal file The launch date The orbital category cf table 1 below The country or organization cf table 2 below It is possible to record in a text file the values provided in ths tab by clicking on the Save item in the main menu or with the shortcut Ctrl S D signation Signification P riode Inclinaison Excentricit P rig e Apog e h ji km km TAO Trans atmospheric 0 0 180 0 0 0 1 0 0 80 gt 80 Equatorial low orbit O 80 Intermediate Sun synchroneous Retrograde 104 0 180 0 Medium 0 0 180 0 80 34680 1682 Highly elliptique 0 0 180 0 0 92 80 14331 13000 Molniya 80 7294 19489 GEO Transfer Stationary geosynchr 35353 35795 35775 Inclined GEO 33667 35795 35775 Synchronous 0 0 180 0 80 35795 35775 Drift GEO 32628 37028 GEO ID Inclined drift GEO 25 00 0 0 20 0 32628 37028 34681 39198 GEO NS Near synchr 23 00 25 00 0 0 180 0 0 0 0 85 80 37028 34681 73976 Table 1 orbital categories http planet4589 org space log orbits html 16 D signation UJ gt LG ARGN ASRA AUS AZER BELA Uy gt N N gt CHBZ CHLE CIS O CZCH DEN ECU EGYP ESA ESRO ES EUME EUTE FGER C mU A e A E GLOB GREC U Z T
23. d UTC The pseudo ballistic coefficient caracterizes the atmospheric drag and its dimensionis given in reverse of the Earth radius SGP4 model uses this value to estimate the atmospheric drag The mean motion expressed in number of revolutions per day The first time derivative of mean motion divided by 2 expressed in revolutions per day squared represents the acceleration or the deceleration of the satellite It s generally a question of acceleration when the satellite descends to a slightly lower orbit a deceleration can occur at the moment of a satellite manoeuvre this parameter is not used in SGP4 The second time derivative of mean motion divided by 6 is expressed in revolutions per day cubed this parameter is not used in SGP4 The revolution number at epoch from the TLE The mean inclination The right ascension of the ascending node The mean eccentricity The mean argument of perigee 15 The mean mean anomaly The standard magnitude and the maximum magnitude The standard magnitude is issued from an internal file in PreviSat The letter which follows its value indicates how this latter has been determinate d it is calculated according to dimensions of the satellite v it is estimated according to visual observations The maximal magnitude is evaluated starting from the standard magnitude and semi major axis and eccentricity The propagation model used SGP4 For the satellites whose or
24. e has a positive elevation and is not eclipsed the magnitude and the illumination in 2 The magnitude value is followed by an asterisk when the satellite is in the penumbra of the Earth which supposes a weakening of the glare of the satellite The number of orbits carried out since the launch is displayed number increased each time the satellite passes to the ascending node Finally we show the next AOS date Acquisition of signal that is to say the next date when the selected satellite will be above the horizon of the location The next LOS Loss of signal is the time when the satellite passes below the horizon We also give the delay of the AOS resp LOS relative to the current date and the azimuth where the satellite will appear resp disappear We then give the coordinates of the Sun and the Moon in the following reference frames Elevation azimuth range Right ascension declination constellation The range given here is the range to the observer which is generally different from geocentric range We also give the informations about the Moon phase its illuminated fraction in and its magnitude It is possible to record in a text file the values provided in ths tab by clicking on the Save item in the main menu or with the shortcut Ctrl S The Sun and Moon positions are calculated from simplified models Astronomical Algorithms 2 edition by Jean Meeus there can thus be differences compared to precise e
25. e is above the horizon and negative when it is below the horizon The azimuth is the angle counted horizontally from North and increasing towards the East This angle ranging between o and 36o is that which one finds on compasses North o East 90 South 180 West 270 Finally we put the range between the satellite and the place of The elevation when it is positive is corrected by the atmospheric refraction by the formula given in the Astronomical Algorithms 2 edition by Jean Meeus p 106 10 observation taking into account of the flatness of the Earth Right ascension declination and constellation These coordinates are used to locate the satellite among stars The right ascension of which the origin is the vernal point located in the constellation of Fishes is counted by convention from o to 24h and increasing towards the east along the celestial equator The declination is the angle measured indegrees from one side of the celestial equator to the other from o to 90 in the boreal celestial hemisphere and from o to 90 in the southern celestial hemisphere Given next is various information concerning the motion of the satellite that is to say the direction of the satellite on its orbit ascending as it moves from South to North and descending in the contrary case the orbital velocity and the range rate negative if the satellite is approaching the observer One provides when the satellit
26. ements of the TLE Mame ISS 1 255440 380678 13242 51201987 00008300 OO000 0 15003 3 0 4526 2 25544 51 6456 100 0367 0004486 315 8748 60 8306 15 506087592846234 NORAD number 25544 Mean motion 15 5060879 rev day Launch date 11 20 1998 COSPAR Designation 980674 mp2 0 00008300 rev day Orbital category LEG Epoch UTC 08 30 2013 12 17 19 n 6 0 00000000 rev day Country Organization 155 Pseudo ballistic coef 0 00015003 1 Er Orbit at epoch 84623 Inclination 51 6496 Mean anomaly 60 8306 RA of ascending node 100 0367 Std Max magnitude 0 5v 2 4 Eccentricity 0 0004486 Propagation model SGP4 ME Argument of perigee 15 8748 Dimensions Section Cylindrical L 30 0 m R 220 0 m 304 00 m We point out first of all the name of the satellite and the lines composing the TLE We give successively The NORAD number identification number assigned sequentially by North American Aerospace Defense Command Each NORAD number refers to a single object satellite debris The COSPAR Designation COmmittee on SPAce Research provides the year of launching the number of the launch in the year as well as one to three letters indicating a piece of the launch The epoch of the TLE is given peculiar format the 2 first digits refers to the year the following digits are the number of days with decimals elapsed since January 1 The epoch is given in Universal Time Coordinate
27. enumbra of the Earth If standard magnitude is not known the magnitude column only contains question marks In the case that the satellite illumination is not required for the instants where the satellite is in the shadow of the Earth the magnitude column only contains dashes Next is given the altitude and the range to the satellite then horizontal coordinates of the Sun azimuth and elevation The nonvisible satellites for the search period are not mentionned in the result file Finally the time necessary to carry out the search is specified This time depends in particuliar on the machine and the availability of its resources as well as quality of search algorithm This time is lenghtened if one chooses a long time interval and or a short calculation step and or a great number of satellites In the second tab the table summarizes each satellite pass By clicking on a table row we display the corresponding passage in the sky map 21 Text file Predictions of passes Satellite HST HST HST HST HST Start date 2015 07 21 05 12 00 2015 07 22 05 03 00 2015 07 23 04 55 00 2015 07 24 04 47 00 2015 07 25 04 38 00 2015 07 19 03 58 00 2015 07 20 03 07 00 2015 07 20 04 40 00 2015 07 21 02 16 00 2015 07 21 03 48 00 2015 07 21 05 21 00 2015 07 22 02 57 00 2015 07 22 04 29 00 2015 07 23 02 05 00 2015 07 23 03 38 00 2015 07 23 05 10 00 2015 07 24 01 13 00 2015 07 24 02 46 00 2015 07 24 04 19 00 2015 07 25 01 54
28. f the future ground track of the satellite Add the satellite Informations Decompression of TLE files with gz format Version 1 0 revision 114 September 2005 February 2006 Developing the module calculating position and velocity with orbital models SGP4 SDP4 Numeric display of the position vectors position and velocity then in the various reference points Calculation of the predictions of a satellite Add the world map Add shortcut buttons on the graphic interface Add the Real time mode the status bar and of the calculation of osculating elements Prediction of several satellites Add the manual mode Save results in a text file Choice among several steps in manual mode Optimization of the calculation of the predictions 39 Annex 3 Technical features Li Development Software Version Comments PreviSat 3 4 5 15 27 000 lines of source code Qt Creator 3 4 2 IDE Qt Library 4 8 7 GUI Library CppCheck 1 69 Checking and analyzing of source code Inno Setup Compiler 5 5 6 a Installation setup for Windows Tortoise Hg 3 5 Version control software UPX 3 91 Executable file compression software zlib 1 2 8 File compression decompression library Za Used Models and constants Reference Author Comments SGP4 Spacetrack report n 3 Hoots Roehrich Revision of 2006 corrections Models for propagation of Vallado brought by Vallado NORAD Element Sets Component Propagation model
29. http astropediafree fr User manual PreviSat Satellite tracking for everyone Ts Bia nec RE PE D DE Sa deewasouacsnyisneseuteoni din ves seeutcsunsanstansetuieass dunia aa 3 iTe Graphical DICE LA aa kaa aaa ahan a aga aa OR Daya 4 1 YO DC TEL aa ay a nay ER BNN ER RE AN OR KRE KU NA N KEWE KEN GERD KUK WW VERA 9 K 4 25 Wald Comman o Conter Sa Sual AZ ae D OT k y iu MH MERE M 6 3 cu aya RO DT UN 7 4 Mode of use Peak ume Marisa MO ska i amm Re HERE ota 7 5 BNN A RO 8 6 Dele nc U E Si PMID T RT 9 Ta AM SED danana ee Seraya Ka be ra a a a dS Wan O A a a K We ERA XOR S kun KA a Ke W 10 pu OSCuU Labang Glemenbs Ta td 12 V Sl AS Ao ao Tack a 15 Vis MEL BA saga 19 LL Miedo tec A A A EE Xula ka ab aaa a 23 VELL pecu ser E et er D E E 27 Li VOC ae NOM E On Aya Sl 27 2x e BENG ES ebe e ai galak ahan adakan A dd 26 Ok Wall Command Center EO bans aa NN da 29 Xe ES ES qc n N GE aa aan aa baia 30 Ty TECE Upda ton TA Dira iS T A A A a A ev D V 20 n Mu R RN EE 30 ore PEE BE E ss aia 30 4 MO PR SAS Nee o NA N AD ND ee PUE MODA TIEN 31 ERN LESS LES DO NA MNA C AM DIVA MA AAA ia 32 Hewe oh ER Ss S COn SE lla CLOS a E IN N e yay 35 la lel PS OC Dn Ee Ley Ose AAA E a O 37 Ann rr 40 dia Dev LO DINGS Ear NS ROYE S VENAN KWE KRA E AO sound NAN K MEK RO WE A e EREN EREK DEWE V EKA Ned U VE W k EWE K WES R WE H WEN EW Kek 40
30. ile containing them amongst other Just like for the Predictions tab it is necessary to indicate the minimal elevation of the satellite by default 10 and the elevation of the Sun which will make possible to determine the day night transition By default the maximum magnitude for a night time flare is equal to 2 while for a day time flare it is 4 We can also take into account the maximum angle of reflexion of the antennas by default 4 Flares are calculated only for the operational satellites that is to say for which 3 axe stabilization is assured at least in theory Spare satellites placed on higher orbits and the satellites of which attitude monitoring is doubtful are not taken into account in the calculation To take into the spare satellites into account de select the box Only the operational satellites Satellites having completely lost their attitude monitoring are excluded from search We can choose to publish the results in the form of one line the moment when the magnitude value passes by a minimum or in three lines the moment of the minimum is surrounded by the dates corresponding to the limiting conditions imposed by the preceding maximum magnitudes or the angle of reflexion It is possible to classify the results either by satellites or by chronological order usual case In the first tab of result window the results are displayed in the form of columns as shown in the example below one day calculation only
31. ion A special category of places of observation called My Favorites allows you to group most used observation sites Two management utilities of TLE are available in the software TLE updating or creating a TLE file from an existing file There are also two features making prediction calculations e Calculation of orbital events determines the dates of shadow penumbra light transitions apogee perigee transits to nodes of the orbit etc e Calculation of the ISS transits to the Moon or the Sun PreviSat has a display Wall Command Center resembling as closely as possible to the ISS command control center of NASA This visualization allows particular view live streaming video of the ISS II Graphical interface Ds World map When displayed the world map is the main visual element of the graphic interface E ENVISAT 150 120 90 60 30 W 0 E 30 60 90 120 150 On this many elements appear of which most important are the places of location represented by a white cross and the satellites represented by a small coloured disc Labels are assigned respectively with these two elements The color of the disc representing the satellite varies according the illumination of the satellite the disc is yellow if the satellite is illuminated by the Sun the disc is green if the satellite is in the penumbra of the Earth the disc is red if the satellite is in the shadow of the Earth The white contour around the satellite represe
32. isplay of beta angle Set the color of ZOE Red Shchelokovo SHKR F Display of orbit number Set the font Ulan Ude ULDR Ussuriysk USKR Display of acquisition cirdes Kourou CSG Houston J5C Kennedy KSC IM Edwards EDW Display of SAA and ZOE 29 IX Tools Tab The Tools tab makes it possible to update TLE files and to create is own TLE files from other files Two other calculations are provided the calculation of orbital events and the transits of ISS with the Sun and the Moon Ls TLE update tab Osculating elements Satellite informations Predictions TLE update TLE file extraction 155 transits Sdentihc www celestrak com Allow TLE add remove Manual TLE update File science txt TLE of satellite IBEX 33401 not updated TLE file to update ocal Astropedia PreviSat te Visual txt TLE of satellite RBSP B 38753 not updated r TLE of satellite MMS 1 40482 not updated TLE File to read 63 TLE s on 66 updated File geodetic txt All TLE s updated file of 8 satellite s Eila amninasrina teta The first tab allows updating TLE files that PreviSat uses in order not to carry out handling manually of TLE files decompression All that is carried out by this fonctionality You may choose the category you want to update and click on the Update now button PreviSat download the TLE files of the category and merges the files When you launch the update a report is displayed on the
33. mean position of the satellite considering a mean circular orbit e The true anomaly v is the angle counted from the perigee to the true position of the satellite 3 The formulas used here are from Fundamental of Astrodynamics and Applications 2 edition by David Vallado 12 One deduces from the preceding osculating elements the perigee minimum of the radius vector the apogee maximum of the radius vector the orbital period as well as the field of view Nord terrestre 4 P rig e noeud descendant NS L L du p bite cor Jd nt E ums anm t RN NE nt d A De Ve eee lt ES M ENA A Apog e satellite Xx Other orbital elements are available for circular and or equatorial orbits For a circular orbit we define the following elements My gt My Q un ais named position on orbit 13 For an equatorial orbit we define 2 i ly tan sin 2 0 40 M amp is named longitude of perigee For a circular equatorial orbit we define a e e cos w J2 ey e sin w 2 i Lt Q Ly an cos scm L tan 2 sin l w N v lis named true longitude argument It is possible to record in a text file the values provided in ths tab by clicking on the Save item in the main menu or with the shortcut Ctrl S 14 Va Satellite informations tab The Satellite informations tab provides the mean orbital el
34. ntain the date and hour and then the coordinates of ISS azimuth elevation right ascension declination and constellation We then give the angular separation between ISS and the center of the considered body the phenomenon type C Conjunction T Transit the body S Sun M Moon and also the illumination of ISS III Illuminated Pen Penumbra Ecl Eclipsed We finally give the altitude and the range of the satellite and the topocentric coordinates of the Sun 32 Text file Ta ISS transits Satellite Start date Finish date Angle Type Body Sun Elevation ISS 2015 07 30 22 08 07 2 2015 07 30 22 08 29 1 4 06 M 0524504 ISS 2015 08 0105 15 47 9 2015 08 0105 16 11 4 1 13 09747 19 ISS 2015 08 02 04 23 02 7 2015 08 02 04 23 20 8 gsm 15 46 52 ISS 2015 08 14 19 53 10 4 2015 08 14 19 54 35 4 1 50 M 11 00 38 ISS 2015 08 14 19 53 54 8 2015 08 14 19 55 00 0 1 94 C S 10 55 16 ISS 2015 08 15 19 00 53 0 2015 08 15 19 01 39 0 1 88 C S 1972101 2 LUisie Adam 5 d ni JAN CL As 20 km Cergy L 1 10 mi lt N Taverny a 2 i as rcelles he datge Andr sys my PA gera en France o n ESA niis 3 Saints eh SE id 5 Plaisi ny sur Marne o Cou Cr teil E ALL ae AS A lenene Saint georges avigny sur Orge y _ Rambo ulllet O A N Moissy Cramayel A Arpajon X S Leaflet Data imagery and map information provided by E OpenStreetMap and Map CC BY SA East IBellat rix
35. nts described above except the default place of location can be made nondisplayable by de selecting the boxes of the Options Display tab It is possible to select the default satelliteby clicking on his disc on the maps or on the radar or by right clicking on the list of satellites s Wall Command Center visualization When the ISS Live box is checked the representation of the world map is changed LAT ALT LON INC 26 8 2 1 It is then possible to view the live video stream of the ISS by clicking on the NASA button Most of the time the camera on board the ISS is pointing towards the ground Sometimes it shows inside of the station and you may see the crew During a spacewalk EVA the camera is placed on the helmet of an astronaut You can double click on the video in order to display it in fullscreen or click on the button to have it in a separate window Note because there is some delay in the broadcast of Live ISS stream times of eclipses observed on the video are not simultaneous with values displayed by PreviSat The sky map represents the sky seen the place of observation selected at the given instant North Fast West Fomalhaut South On this image taken the July 19th 2015 we can see the satellite ISS near the South West horizon and it will across the sky Along the ecliptic in yellow we can see Neptun in the Water Bearer constellation Aqr and Uranus in the Fishes constellation Psc
36. nts the foot print so the satellite is visible of the assembly of points of the globle located at the interior of this zone In reality the shape of the foot print is always a circle abstraction made from the flatness of the terrestrial globe but the projection on the planisphere can produce various forms We also draw the ground track of the future orbits of the default satellite The color of this curve is clear blue when the satellite is illuminated by the Sun green when the satellite is in the shadow of the Earth and red when the satellite is in the shadow of the Earth The Sun is drawn by a yellow disc on the maps For a place of observation whose geographical coordinates merge with the center of the disc representing the Sun this latter is found at the zenith of the considered place of location The zone of shade is the area of the globe located during the night One can observe the evolution of the zone of shade during the day day night alternation and of its shape during the year seasons The Moon is also displayed on the maps and its phase is drawn as it appears in the sky of the observer It is important to note that the size of the elements Sun Moon or satellites is not representative of the reality Also displayed on the world ma pis the grid of the geographical coordinates graduated in steps of 30 degrees and also the tropics The meridian at the center of the world map is the meridian line of Greenwich All eleme
37. opedia c 2005 2015 Location Timezone Conditions Range unit Age of the ISS Date 2014 05 30 2014 05 31 2014 05 31 2014705781 2014905731 2014 05 31 2014 05 31 2014 05 31 2014 05 31 2014 05 31 2014 05 31 2014 05 31 2014 05 31 2014 05 31 2014 05 31 2014 05 31 2014 05 31 2014 05 31 2014 05 31 2014 05 31 2014 05 31 2014 09 31 2014 05 31 2014 05 31 2014 05 31 2014 05 31 of observations ILE Hour 27 23 Dd 01 01 0T ois 02 02 02 02 02 02 02 OZ Oe 04 04 04 04 04 04 04 04 04 04 04 Elapsed time 00 01 25 0 3 04 233 34 35 1362 Ts s 991 40 41 08 09 10 14 123 TO 00 15 16 TA 18 14 0 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 01s Calculation for ISS and only for one day Paris 002 20 55 East 48 51 12 North Local time Maximal elevation of the Sun 6 Minimal elevation of the satellite 0 km 0 13 days at 05 30 2014 08 03 00 Sat Azimuth Sat Elev RA Sat Decl Sat Const Magn 084 05 02 00 28 42 20h26m14s 04 14 59 Del 9 9 105 20 41 31 55 49 19h33m45s 14 30 24 Aql 1 0 086 22 39 19 31 45 2lh0lm43s 16 54 45 Del 0 1 0780233 11 23 20 21h50m24s 16 24 00 Peg 143 07339126 005 47 59 22n20m30s 415 07 51 Peg 43 1 070 52 48 01 39 27 22h41m05s 13 43 20 Peg 6 9 2680815
38. phemeris about thirty arcseconds for the Sun 11 IV Osculating elements tab The Osculating elements tab contains the data concerning the position and the velocity of the satellite Main Osculating elements Satellite informations Predictions Iridium flares Options Tools Date Sunday July 19 2015 03 56 00 UTC 02 00 Mame 155 1 255440 580674 15199 _ 127776912 QOOIIlT7ZzS goagogg u 17730 3 O 5992 z 5544 51 6458 269 5403 0001736 6 0975 179 6600 15 55172958952656 Vecteur d tat ECI m Osculating elements Keplerian parameters m X 4231 517 km Semi major axis 6779 1 km RA of ascending node 284 77949 y 3362 946 km Eccentricity 0 0008949 Argument of perigee 106 2648 zi 4086 001 km Indination 51 6421 Mean anomaly 304 08 70 vx 1 433958 km s True anomaly 304 00202 Apogee Altitude 6785 2 km 407 1 km vy 6 483828 km s Eccentric anomaly 304 0445 Perigee Altitude 6773 1km 394 9 km VEZ 3 841994 km s Field of view 19 91 Orbital period ih 32m 235 In this tab we recall the date which is identical to that of the Main tab then the name of the satellite and the 2 lines of the orbital elements of the TLE These orbital elements are known average that is to say they do not represent the real orbite at the instant of epoch The osculating elements true characteristics of the orbit at a given moment vary with time
39. rather well Thus one should not be surprised if a flare is lower than hoped or even did not take place Under the second tab the table summarizes each Iridium flare By clicking on a table row we display the corresponding passage in the sky map and a map centered on the place of observation showing where the maximum flare produces 25 Iridium flares ned atiloW3 O LN P Pr ereton b NN Villeneuve Saint Georges O Les Savigny sur Orge e Ramboulllet O Evry Q j Arpajon Leaflet Data imagery and map information prov nded by lap Quest C a Mpissy Cramayel bra at entree Text file Satellite Start date Finish date Max Elevation Max Magn Sun Elevation Tridum6 2015 07 19 09 24 04 4 2015 07 19 09 24 07 0 25 02 04 5 7 29748 24 0 Iridium 5 2015 07 19 23 55 09 2 2015 07 19 23 55 35 9 30 26 00 2 1 15 18 182 Iridium 6 2015 07 20 00 04 17 1 2015 07 20 00 04 34 4 2591727 1 3 16 00 20 2 Iridium 53 2015 07 20 01 21 49 4 2015 07 20 01 22 00 6 4724051 40 1 19257072 Iridium 40 2015 07 20 02 57 50 8 2015 07 20 02 58 14 2 50 15 32 1 0 19040672 Iridium 8 2015 07 20 23 49 17 6 2015 07 20 23 49 39 6 30 1111 40 4 14 5907 2 Iridium 77 eL 02 3l 37 1 2015 07 21 02 32 a z sakkal 1 2 19230 1472 Iridium 70 2015 07 21 2 00 9 5095027 47 tegir Iridium 34 2015 07 21 09 21 18 2 2015 07 21 09 21 20 3 29 07 47 5 5 2904060 Iridium 19 2015 07 21 23
40. ridium flares search including those of day Predictions Iri e Start date 07 19 2015 03 56 00 Output display Finish date 07 26 2015 03 56 00 C 1line 3 lines Sun elevation Civil twilight 6 kl Name of location RESe iridum txt M Minimal elevation of satellite Maximal magnitude night 2 0 Only operational satellites Maximal magnitude day 40 Tara aan sand ange lekan 40 E RE Initially satellites of the Iridium constellation were satellites dedicated to telecommunications They have 3 very reflective antennas Main Mission Antenna see diagram below which are at the origin of the flares The latter can reach magnitude 8 which is 30 to 40 times more luminous than Venus magnitude about 4 A flare can least from a few seconds to about thirty seconds Photo Daniel Deak tI 411111 SIRIA Panneaux Compartiment solaires 21 des batteries Structure du module de commande Photo Daniel Deak section communication Antennes principales 3 uu Main Mission Antenna Antennes de liaison entre lez satellites Antennes de liaison avec le zal 23 Flare of Iridium 37 satellite in the constellation of Queen on December 9 2014 at 17h34 UT in Toulouse France magnitude 6 8 It is necessary to give the initial and final dates and hours You have to specify the path of the file containing Iridium satellites it can be a file containing only the Iridium satellites or a f
41. right hand side of tab You can create or modify categories by clicking on the Settings button in the window displayed it is possible to select categories that you want to update automatically at the starting of PreviSat and define the expiry date If the TLE expiry date is checked the TLE updating is made automatically when the TLE are older than the value indicated If not the TLE updating is made every starting of PreviSat You can also update files individually by indicating the TLE file to read containing recent TLEs and TLE file to update The file to read can be in the gz format Important the automatic updating of files of tle directory of PreviSat is done from the site www celestrak com Only the TLE files with the same names are downloaded from celestrak com P TLE file extraction tab The second tab makes it possible to create its own TLE files according to various criteria It is necessary to indicate the name of the file to be read and the name of the personal file One can create a file according to the following criteria between square brackets entries by default wich are also the tolerated maximum values The NORAD number All The right ascension of the ascending node From o to 3607 The eccentricity From o to 1 value 1 is excluded The number of revolutions per day From o to 18 The inclination From o to 1807 it is possible to define 2 intervals The argument of perigee From o
42. s drawn on the radar when they are in the sky of the observer the Sun the Moon and the selected satellites The color of the radar is purely indicative and should not represent exactly the color of the sky 6 Key shortcuts Key Shortcuts Ctrl M Maximization Minimization of the map ELL Main tab The Main tab contains all necessary information to know the position of the satellite with regards to the place of observation Date Saturday August 31 2013 08 59 23 UTC 02 00 Mame of location Paris n Conditions Day Sun coordinates Longitude 002 20 43 East Latitude 48 51 39 North X Altitude 60m Elevation 17 47 42 Azimuth M 097 18 42 Name 155 Time elapsed since epoch 0 78 days Range 1 009 AU Longitude 131 18 35 East Elevation 34 24 447 Right ascension 16h 00m 37s Right ascension 10h 38m 41s Latitude 47 51 28 North Azimuth N 0327 55 34 Dedination 401 43 00 Decination 089 35 23 Altitude 420 1 km Range 7922 8 km Constellation Ser Constellation Leo Direction Descending Satellite not visible 26 Moon coordinates Orbital velocity 7 665km s Orbit 84635 Elevation 45753717 Range rate 44 722 km s Next AOS 08 31 2013 11 46 35 in 02h 47min Azimuth 198 30 Azimuth N 155 44 54 First of all the current date is indicated which can be that of the system or that chosen by the user It is possible to pass from the Real time mode to
43. sible to choose the units displayed in PreviSat For the satellites as well as the Moon the unit can be either kilometers or miles 1 mile 1 609344 km the altitude of the place of observation and dimensions of the satellite are then expressed respectively in meters or feet 1 foot 0 3048 m The distance from the Sun is always given in astronomical units 1 AU 149 597 870 km 92 955 807 miles Note After the entry of a new place of observation when the unit is the foot the displayed altitude can slightly differ compared to the entered value because PreviSat stores the altitude in meters and in a integer value That does not affect any the calculations carried out by PreviSat A second choice list makes it possible to select the Local time UTC offset one can changes the value of this offset The Auto checkbox when it is checked allows to determine automatically this offset e f the Auto checkbox is checked at the time of closing of PreviSat the offset will be given with the system value at the next starting of Previsat e f not the offset will be given by the value indicated in the field at the next starting of PreviSat 2a Wall Command Center tab This tab allows you to manage the display options when the Wall Command Center is activated when the ISS Live box is checked Wall Command Center Dzhusaly DJSR 7 Wall Command Center style Set the color of GMT Kolpashevo KLPR j N m Petropavlosk PPKR D
44. t programmation Multi satellite management calculation algorithms display New algorithm for Iridium flares TLE updating and the creation of personal TLE files Several modifications concerning display Many improvements of source code manual mode lridium flares Calculation of orbital events Screen shot of the main window at JPEG or BMP format Automatic download of orbital elements TLE Version 2 0 revision 8 January 2006 April 2009 New graphical interface with VB2005 simplification of its use Rewriting of all the procedures adaptation to the language VB2005 translation in C language of the procedures containing many mathematical operations New management of locations Significant optimization of predictions and Iridium flares New display options Display of the zone of shade Gradual variation of the radar coloured background according to the elevation of the Sun New calculation of the satellite foot print and the zone of shade 38 Version 1 2 revision 11 June December 2006 Modification of the layout of elements in the graphic interface Add the radar Creation of TLE personal files and their update Version 1 1 revision 15 December 2005 June 2006 Predictions of Iridium flares personal algorithm concerning the magnitude Add the sound notification and the satellite foot print Add the Sun the terminator and the list of satellites in the main window Display o
45. the Manual mode by double clicking on the label containing the date We then point out the coordinates of the default place of observation name longitude latitude altitude We also give the conditions of observation that is an indication about the Sun s elevation Day Hs gt o Civil twilight 6 lt Hs lt 0 Nautical twilight 12 lt Hs 6 Astronomical twilight 187 lt Hs lt 12 Night Hs lt 189 O O O O X We then give the name of the default satellite as well as the time elapsed since the epoch of the TLE The color assigned to the age of the TLE give an approximative indication about its accuracy the green color indicates a recent TLE instead of the red color indicates an old TLE Then we grouped the coordinates of the satellite in various reference frames Longitude latitude and altitude They are the terrestrial coordinates over flown by the satellite where the altitude is calculated compared to the sea level by taking into account the flatness of the terrestrial globe Longitude and latitude over flown are thus the point of the globe where the satellite passes to the zenith Elevation azimuth and range They are undoubtly the most useful coordinates for the observation since they are related to the place of observation The elevation also called site angle is the angle counted vertically between the horizon and the satellite This angle is between o and 90 when the satellit
46. tude Q02 20 55 East Monde Latitude 48 51 12 North Altitude 30 m The first list in the Location tab contains the various categories of places of observation initially France World and My Favorites e The category France comprises the main towns of Metropolitan France e The category World contains the coordinates of almost 1700 cities in the world While clicking on an element of this first list one reveals in the second list the names of the places of the category When a place of observation is selected its coordinates are displayed on the right hand side of the tab While clicking on the small arrows one can select the locations for the application By right clicking on an element in the Location in the category list one can choose to remove it or to add itin the My Favorites category For the manual addition of a place in a category it is necessary to seize the name of the place of observation its longitude and its latitutde given for example by a GPS device The altitude can be neglected if it is not known because its value has small effect on calculations It is possible to create or remove a category except the category My Favorites or to download new categories by right clicking on the list Selection of the category 27 Eu Settings tab settings Wall Command Center W Name of satellites Ground track 2 Pl Satellite icons Sky track Sound notification 4 Moon phase 1 nha
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