R1i3dZddlmZmZmZmZmZmZddlm Z m Z ddl m Z m Z mZmZddlmZmZmZmZmZmZddlmZmZddlmZdd lmZed ZGd d eZGd de Z!ddZ"edZ#edZ$edZ%dZ&ddZ'y)z>An interface between Skyfield and the Python ``sgp4`` library.)array concatenateidentitymultiply ones_likerepeat) SGP4_ERRORSSatrec)AU_KMDAY_ST0tau)_Tmxmmxvrot_xrot_yrot_z)_find_discrete find_maxima)compute_calendar_date)VectorFunctioncfeZdZdZdZdZd dZdZedZ dZ e dZ d Z d Zd Zdd Zy)EarthSatelliteu. An Earth satellite loaded from a TLE file and propagated with SGP4. An earth satellite object is a Skyfield vector function, so you can either call its ``at()`` method to generate its position in the sky or else use addition and subtraction to combine it with other vectors. Satellite parameters are generally only accurate for a week or two around the *epoch* of the parameters, the date for which they were generated, which is available as an attribute: ``epoch`` A Skyfield :class:`~skyfield.timelib.Time` giving the exact epoch moment for these satellite orbit parameters. ``name`` Satellite name When building a satellite, use the arguments ``line1`` and ``line2`` to provide the two data lines from a TLE file as separate strings. Optional ``name`` lets you give a name to the satellite, accessible later through the ``name`` attribute. ``ts`` is a :class:`~skyfield.timelib.Timescale` object, used to generate the ``epoch`` value; if it is not provided, the satellite will use a built in ``Timescale`` object. If you are interested in the catalog entry details, the SGP4 model parameters for a particular satellite can be accessed through its ``model`` attribute: ``model.satnum`` The unique satellite NORAD catalog number given in the TLE file. ``model.classification`` Satellite classification, or else ``'U'`` for “Unknown” ``model.intldesg`` International designator ``model.epochyr`` Full four-digit year of this element set's epoch moment. ``model.epochdays`` Fractional days into the year of the epoch moment. ``model.jdsatepoch`` Julian date of the epoch (computed from ``epochyr`` and ``epochdays``). ``model.ndot`` First time derivative of the mean motion (ignored by SGP4). ``model.nddot`` Second time derivative of the mean motion (ignored by SGP4). ``model.bstar`` Ballistic drag coefficient B* in inverse earth radii. ``model.ephtype`` Ephemeris type (ignored by SGP4 as determination now automatic) ``model.elnum`` Element number ``model.inclo`` Inclination in radians. ``model.nodeo`` Right ascension of ascending node in radians. ``model.ecco`` Eccentricity. ``model.argpo`` Argument of perigee in radians. ``model.mo`` Mean anomaly in radians. ``model.no_kozai`` Mean motion in radians per minute. ``model.revnum`` Revolution number at epoch [Revs] iNcp|/|j}|!ddlm}|jx}t_|dn|j |_tj||}||_ |j}|dkr|dz}n|dz}|j|d|j|_ |j|y)Nr )load9iil)tsapir timescalerstripnamer twoline2rvmodelepochyrutc epochdaysepoch_setup) selfline1line2r$r rsatrectwo_digit_yearyears T/home/cursorai/projects/iching/venv/lib/python3.12/site-packages/skyfield/sgp4lib.py__init__zEarthSatellite.__init__Xs :Bz%)-)99^& LDdjjl ""5%0  B !D(D!D(DVVD!V%5%56  Fc,d|jz |_y)Ni`y)satnumtarget)r,r/s r2r+zEarthSatellite._setupms  - r4c|j|}||_d|_t|jd\}}t |\}}}|dz }|j ||||z|jz|_|j||S)zBuild an EarthSatellite from a raw sgp4 Satrec object. This lets you provide raw numeric orbital elements instead of the text of a TLE set. See :ref:`from-satrec` for detais. N??) __new__r&r$divmod jdsatepochrr( jdsatepochFr*r+) clsr/r r,wholefractionr1monthdays r2 from_satreczEarthSatellite.from_satrects{{3  !!2!2C8x07eS s VVD%x&:L:L)LM  F r4c|jSN) target_namer,s r2__str__zEarthSatellite.__str__sr4cdj|jxsd|jrdnd|jj|jj S)Nz{0}{1}catalog #{2} epoch {3} )formatr$r&r6r* utc_strftimerHs r2rGzEarthSatellite.target_namesH-44 IIO99C" JJ   JJ # # %   r4c|j}|j}|j|jtz z }t |ddrI|j ||\}}}|Dcgc]}|r t|nd} }|j|j| fS|j||\}} } |r t|nd} t| t| | fScc}w)a!Return the raw true equator mean equinox (TEME) vectors from SGP4. Returns a tuple of NumPy arrays ``([x y z], [xdot ydot zdot])`` expressed in kilometers and kilometers per second. Note that we assume the TLE epoch to be a UTC date, per AIAA 2006-6753. shapeN) r&r@ tai_fraction _leap_secondsr getattr sgp4_arrayr Tsgp4r) r,tsatjdrAerverrormessagespositionvelocitymessages r2_position_and_velocity_TEME_kmz-EarthSatellite._position_and_velocity_TEME_kmsjj WW>>AOO$5$== 2w %nnR2GAq!KLM1%e E*=1HM33X% %(+X(> %E8X,1k%(tG?E(OW< < Ns$C c|j|\}}}|tz}|tz}|tz}t|j||dd|j \}}|||fS)8Deprecated: use the TEME and ITRS frame objects instead.)rbr r TEME_to_ITRFr@ ut1_fraction)r,rWrTEMEvTEMEr]rITRFvITRFs r2ITRF_position_velocity_errorz+EarthSatellite.ITRF_position_velocity_errorsf #AA!Due   #AGGUE3$%NN4 ueU""r4c|j|\}}}|tz}|tz}|tz}ttj |}t ||}t ||}||d|fS)z@Compute this satellite's GCRS position and velocity at time `t`.N)rbr r rTEME rotation_atr)r,rWr[r\r]Rs r2_atzEarthSatellite._atsm99!< 1e U  U  U  t" # 1I 1I!T5  r4c|j}||z jdtz }|jjt z }d|z}dt |dz } | dkDrd} dfd} | | _t||| |d\} } | s | t| fS| k\} | j| }t|d }fd }tt|jf||jffd }|d d |dd zdz }t|j|||d\}}t||jf}t||d zf}|j}|j||||fS)uReturn the times at which the satellite rises, culminates, and sets. Searches between ``t0`` and ``t1``, which should each be a Skyfield :class:`~skyfield.timelib.Time` object, for passes of this satellite above the location ``topos`` that reach at least ``altitude_degrees`` above the horizon. Returns a tuple ``(t, events)`` whose first element is a :class:`~skyfield.timelib.Time` array and whose second element is an array of events: * 0 — Satellite rose above ``altitude_degrees``. * 1 — Satellite culminated and started to descend again. * 2 — Satellite fell below ``altitude_degrees``. Note that multiple culminations in a row are possible when, without setting, the satellite reaches a second peak altitude after descending partway down the sky from the first one. r:ig?r9g?cP|jdz|_tx|_|_y)z8Avoid computing expensive values that cancel out anyway.reN)ttgast _identityMMT)rWs r2cheatz)EarthSatellite.find_events..cheatsTTCZAF" "AC!$r4cZ||jdjSNraltazdegrees)rWatrys r2 altitude_atz/EarthSatellite.find_events..altitude_ats% !Ha5;;=#++ +r4 uint8c`||jdjkSr{r|)rWaltitude_degreesrrys r2below_horizon_atz4EarthSatellite.find_events..below_horizon_ats+ !Ha5;;=#++.>> >r4Nr g@)r rr r&no_kozairmax step_daysrrrtrrrargsorttt_jd)r,topost0t1rr half_secondorbits_per_minuteorbits_per_dayrrtmaxaltitudekeepersjdmaxonesrdoubletsjdotrsrsrYr\irrys ` @@r2 find_eventszEarthSatellite.find_eventssv2UUUl  Ek  JJ//#5 #443~s33  t I #  ,!* $R[+rJh4( (.. (  ?+x&ABAF}x|+s2 -={ANR % ) rAv ' JJLxx1!$$r4)NNre)__name__ __module__ __qualname____doc__centerr r3r+ classmethodrDrIpropertyrGrbrlrqrr4r2rrsaBFF B*.,   =* # !U%r4rc eZdZdZedZy)rnuThe SGP4-specific True Equator Mean Equinox frame of reference. Described in AIAA 2006-6753 Appendix C. See :ref:`reference_frames` for a guide to using Skyfield reference frames like this one. ct|j|j\}}||jdz tzz }t t ||jS)Ng8@)theta_GMST1982r@rgrurrrrw)rWtheta theta_dotangles r2rozTEME.rotation_at#sG)!''1>>By ++5<%%r4N)rrrr staticmethodrorr4r2rnrns &&r4rnc|tz |zdz }dddd|zz|zz|zz}ddd|zz|zz}|dz|z|tz dzzdztz}d|tdzz ztz}||fS) aReturn the angle of Greenwich Mean Standard Time 1982 given the JD. This angle defines the difference between the idiosyncratic True Equator Mean Equinox (TEME) frame of reference used by SGP4 and the more standard Pseudo Earth Fixed (PEF) frame of reference. The UT1 time should be provided as a Julian date. Theta is returned in radians, and its velocity in radians per day of UT1 time. From AIAA 2006-6753 Appendix C. g@gmIn@gz`Agt շ?g3ھgt ?gZmDr9)rr r)jd_ut1 fraction_ut1rWgdgrrs r2rr-s "| #w.A~WM)AQ(FF!KKA >]a,??1D DB c\L (1u9s? :c AC GErUW_--4I ) r4)rereg)r rr)rrr cP|t|tz|t|tzz SrF) _cross120 _cross201)abs r2_crossrDs' Y>1e}1e}v&6== SyR3Y %<2YOOE"I &   %<r4Nr)rerere)(rnumpyrrrrrrsgp4.apir r constantsr r rr functionsrrrrrr searchlibrrtimelibr vectorlibrrvrobjectrnrrrrrrfrr4r2rsD),,882*% QK I%^I%V &6 &"&-. 'N 'N Er4