Package: asteRisk 1.4.3.9999

asteRisk: Computation of Satellite Position

Provides basic functionalities to calculate the position of satellites given a known state vector. The package includes implementations of the SGP4 and SDP4 simplified perturbation models to propagate orbital state vectors, as well as utilities to read TLE files and convert coordinates between different frames of reference. Several of the functionalities of the package (including the high-precision numerical orbit propagator) require the coefficients and data included in the 'asteRiskData' package, available in a 'drat' repository. To install this data package, run 'install.packages("asteRiskData", repos="https://rafael-ayala.github.io/drat/")'. Felix R. Hoots, Ronald L. Roehrich and T.S. Kelso (1988) <https://celestrak.org/NORAD/documentation/spacetrk.pdf>. David Vallado, Paul Crawford, Richard Hujsak and T.S. Kelso (2012) <doi:10.2514/6.2006-6753>. Felix R. Hoots, Paul W. Schumacher Jr. and Robert A. Glover (2014) <doi:10.2514/1.9161>.

Authors:Rafael Ayala [aut, cre], Daniel Ayala [aut], David Ruiz [aut], Lara Selles Vidal [aut]

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asteRisk.pdf |asteRisk.html✨
asteRisk/json (API)
NEWS

# Install 'asteRisk' in R:
install.packages('asteRisk', repos = c('https://rafael-ayala.r-universe.dev', 'https://cloud.r-project.org'))

Peer review:

Bug tracker:https://github.com/rafael-ayala/asterisk/issues

Uses libs:
  • c++– GNU Standard C++ Library v3

On CRAN:

4.84 score 6 stars 19 scripts 402 downloads 31 exports 35 dependencies

Last updated 6 months agofrom:b55072e968. Checks:OK: 1 NOTE: 8. Indexed: yes.

TargetResultDate
Doc / VignettesOKNov 11 2024
R-4.5-win-x86_64NOTENov 11 2024
R-4.5-linux-x86_64NOTENov 11 2024
R-4.4-win-x86_64NOTENov 11 2024
R-4.4-mac-x86_64NOTENov 11 2024
R-4.4-mac-aarch64NOTENov 11 2024
R-4.3-win-x86_64NOTENov 11 2024
R-4.3-mac-x86_64NOTENov 11 2024
R-4.3-mac-aarch64NOTENov 11 2024

Exports:calculateRazeldateTimeToMJDdeg2radECItoKOEevaluateSPKSegmentGCRFtoITRFGCRFtoLATLONgetLatestSpaceDatahpopITRFtoGCRFITRFtoLATLONJPLephemeridesKOEtoECIlambertLATLONtoGCRFLATLONtoITRFparseTLElinesrad2degreadBinDAFreadBinSPKreadGLONASSNavigationRINEXreadGPSNavigationRINEXreadOEMreadTLErevDay2radMinsdp4sgdp4sgp4TEMEtoGCRFTEMEtoITRFTEMEtoLATLON

Dependencies:askpassBHbitbit64curldeSolvedigestdisordRemulatorfreealggmpgslhttrjsonlitelatticemathjaxrMatrixmimemvtnormnanotimeonionopensslpartitionspolynomR6rbibutilsRcppRcppCCTZRcppDateRcppEigenRcppParallelRdpacksetssyszoo

asteRisk

Rendered fromasteRisk.Rmdusingknitr::rmarkdownon Nov 11 2024.

Last update: 2023-12-03
Started: 2021-03-21

Readme and manuals

Help Manual

Help pageTopics
Calculates azimuth, elevation and range of a given objectcalculateRazel
Calculate Modified Julian Date for a given date and timedateTimeToMJD
Converts an angle in degrees to radiansdeg2rad
Calculate ECI coordinates from Keplerian orbital elementsECItoKOE
Evaluate a given SPK segmentevaluateSPKSegment
Convert coordinates from GCRF to ITRFGCRFtoITRF
Convert coordinates from GCRF to geodetic latitude, longitude and altitudeGCRFtoLATLON
Retrieves the latest space datagetLatestSpaceData
High-precision numerical orbital propagatorhpop
Convert coordinates from ITRF to GCRFITRFtoGCRF
Convert coordinates from ITRF to geodetic latitude, longitude and altitudeITRFtoLATLON
Calculate JPL main celestial objects ephemerides for a given Modified Julian DateJPLephemerides
Calculate ECI coordinates from Keplerian orbital elementsKOEtoECI
Solve Lambert's problem to determine a transfer orbitlambert
Convert coordinates from geodetic latitude, longitude and altitude to GCRFLATLONtoGCRF
Convert coordinates from geodetic latitude, longitude and altitude to ITRFLATLONtoITRF
Parse the lines of a TLEparseTLElines
Converts an angle in radians to degreesrad2deg
Read a generic binary DAF filereadBinDAF
Read a binary SPK filereadBinSPK
Read a RINEX navigation file for GLONASS satellitesreadGLONASSNavigationRINEX
Read a RINEX navigation file for GPS satellitesreadGPSNavigationRINEX
Read an Orbital Ephemeris Message filereadOEM
Read a TLE filereadTLE
Converts revolutions per day to radians per minuterevDay2radMin
Propagate an orbital state vector with the SDP4 modelsdp4
Propagate an orbital state vector with the SGP4/SDP4 modelsgdp4
Propagate an orbital state vector with the SGP4 modelsgp4
Convert coordinates from TEME to GCRFTEMEtoGCRF
Convert coordinates from TEME to ITRFTEMEtoITRF
Convert coordinates from TEME to geodetic latitude, longitude and altitudeTEMEtoLATLON