References

The models, algorithms and constants in satkit are taken from the sources below. Pages on this site cite them as (Author Year, §section), linking to the entry here; each entry gives the section, equation or algorithm numbers the code follows where that is useful.

Books

- Vallado, D. A. (2013). Fundamentals of Astrodynamics and Applications, 4th ed. Microcosm Press, Hawthorne, CA. ISBN 978-1881883180. Companion software and errata: https://celestrak.org/software/vallado-sw.php. Used for: SGP4 reference implementation (the C++ code satkit's port follows), GMST (Algorithm 15, Eq. 3-45), IAU-76/FK5 reduction (§3.7, Eqs. 3-88 to 3-90), TEME (§3.7.3), RSW/NTW frames (§3.3, Eq. 3-31), Kepler's equation (Algorithm 2), Sun position (Algorithm 29, §5.1.1), sunrise/sunset (Algorithm 30, §5.3.1), Moon position (Algorithm 31, §5.2.3), Hohmann transfer (§6.3), Lambert background (Ch. 7), TDB−TT (Eq. 3-50).

- Montenbruck, O., & Gill, E. (2000). Satellite Orbits: Models, Methods, Applications. Springer, Berlin. https://doi.org/10.1007/978-3-642-58351-3. Used for: the force-model structure and the forces-vs-altitude figure (§3.1, Fig. 3.1), spherical-harmonic gravity (§3.2, Eqs. 3.28–3.33), third-body point-mass attraction (§3.3.1, Eq. 3.37), solar radiation pressure and the conical shadow model (§3.4, Eqs. 3.69–3.75, §3.4.2), atmospheric drag (§3.5), variational equations and the state transition matrix (§7.1–7.2, Eqs. 7.42, 7.75), covariance mapping (§8.1).

- Battin, R. H. (1999). An Introduction to the Mathematics and Methods of Astrodynamics, revised ed. AIAA Education Series. https://doi.org/10.2514/4.861543. Used for: the hypergeometric-series form of the Lambert time-of-flight equation near the parabolic boundary.

- Hairer, E., & Wanner, G. (1996). Solving Ordinary Differential Equations II: Stiff and Differential-Algebraic Problems, 2nd ed. Springer. https://doi.org/10.1007/978-3-642-05221-7. Used for: the RODAS4 Rosenbrock integrator (§IV.7).

- Tapley, B. D., Schutz, B. E., & Born, G. H. (2004). Statistical Orbit Determination. Elsevier Academic Press. https://doi.org/10.1016/B978-0-12-683630-1.X5019-X. Used for: batch least-squares orbit determination and covariance propagation in the tutorials (§4.2–4.3).

- Markley, F. L., & Crassidis, J. L. (2014). Fundamentals of Spacecraft Attitude Determination and Control. Springer. https://doi.org/10.1007/978-1-4939-0802-8. Used for: quaternion and local-vertical/local-horizontal frame conventions.

Standards and conventions

- Petit, G., & Luzum, B. (eds.) (2010). IERS Conventions (2010). IERS Technical Note No. 36, Verlag des Bundesamts für Kartographie und Geodäsie, Frankfurt am Main. ISBN 3-89888-989-6. https://iers-conventions.obspm.fr/content/tn36.pdf. Used for: the ITRF↔GCRF reduction (Ch. 5: polar motion Eq. 5.3, Earth rotation angle Eq. 5.15, CIP X/Y and CIO locator series Tables 5.2a/5.2b/5.2d, frame bias §5.5.4 and Eq. 5.36), solid Earth tides (§6.2.1 Step 1, Eqs. 6.6–6.7, Table 6.3 Love numbers; §6.2.2 Step 2), time scales (Ch. 10, §10.1 TDB−TT), and the relativistic acceleration (§10.3, Eq. 10.12).

- CCSDS (2023). Orbit Data Messages. Recommended Standard CCSDS 502.0-B-3 (Blue Book), Consultative Committee for Space Data Systems, April 2023. https://ccsds.org/Pubs/502x0b3e1.pdf. Used for: the Orbital Mean-Element Message (OMM) format and the RTN reference frame used for covariance and maneuver components.

- NGA (2014). Department of Defense World Geodetic System 1984: Its Definition and Relationships with Local Geodetic Systems, Version 1.0.0, NGA.STND.0036_1.0.0_WGS84, National Geospatial-Intelligence Agency. https://nsgreg.nga.mil/doc/view?i=4085. Used for: the WGS 84 ellipsoid and defining parameters (\(GM\), \(\omega_\oplus\), \(a\), \(f\)).

- ITU-R (2002). Standard-frequency and time-signal emissions, Recommendation ITU-R TF.460-6. https://www.itu.int/rec/R-REC-TF.460-6-200202-I/en. Used for: the definition of UTC and leap seconds.

- IERS Bulletin C — leap-second announcements (Earth Orientation Center, Observatoire de Paris). https://hpiers.obspm.fr/iers/bul/bulc/bulletinc.dat. Source of the TAI−UTC table compiled into satkit.

Papers and reports

- Hoots, F. R., & Roehrich, R. L. (1980). Models for Propagation of NORAD Element Sets. Spacetrack Report No. 3, Aerospace Defense Command (reprinted by T. S. Kelso, 1988). https://celestrak.org/NORAD/documentation/spacetrk.pdf. The original SGP4/SDP4 description.

- Vallado, D. A., Crawford, P., Hujsak, R., & Kelso, T. S. (2006). "Revisiting Spacetrack Report #3." AIAA 2006-6753, AIAA/AAS Astrodynamics Specialist Conference, Keystone, CO. https://doi.org/10.2514/6.2006-6753. https://celestrak.org/publications/AIAA/2006-6753/AIAA-2006-6753-Rev3.pdf. The modern SGP4 reference: the algorithm, the TEME frame, and the test vectors satkit's port is verified against.

- Vallado, D. A., & Crawford, P. (2008). "SGP4 Orbit Determination." AIAA 2008-6770, AIAA/AAS Astrodynamics Specialist Conference, Honolulu, HI. https://doi.org/10.2514/6.2008-6770. Used for: fitting TLEs to state vectors (TLE.fit_from_states).

- Picone, J. M., Hedin, A. E., Drob, D. P., & Aikin, A. C. (2002). "NRLMSISE-00 empirical model of the atmosphere: Statistical comparisons and scientific issues." Journal of Geophysical Research: Space Physics, 107(A12), 1468. https://doi.org/10.1029/2002JA009430. satkit's density model is a Rust port of Dominik Brodowski's C implementation of NRLMSISE-00.

- Park, R. S., Folkner, W. M., Williams, J. G., & Boggs, D. H. (2021). "The JPL Planetary and Lunar Ephemerides DE440 and DE441." The Astronomical Journal, 161(3), 105. https://doi.org/10.3847/1538-3881/abd414.

- Folkner, W. M., Williams, J. G., & Boggs, D. H. (2009). "The Planetary and Lunar Ephemeris DE 421." IPN Progress Report 42-178, Jet Propulsion Laboratory. https://ipnpr.jpl.nasa.gov/progress_report/42-178/178C.pdf.

- Lemoine, F. G., et al. (1998). The Development of the Joint NASA GSFC and the National Imagery and Mapping Agency (NIMA) Geopotential Model EGM96. NASA/TP-1998-206861. https://ntrs.nasa.gov/citations/19980218814.

- Tapley, B. D., et al. (1996). "The Joint Gravity Model 3." Journal of Geophysical Research: Solid Earth, 101(B12), 28029–28049. https://doi.org/10.1029/96JB01645.

- Nerem, R. S., et al. (1994). "Gravity model development for TOPEX/POSEIDON: Joint Gravity Models 1 and 2." Journal of Geophysical Research: Oceans, 99(C12), 24421–24447. https://doi.org/10.1029/94JC01376.

- Akyilmaz, O., et al. (2016). ITU_GRACE16: The global gravity field model including GRACE data up to degree and order 180 of ITU and other collaborating institutions. GFZ Data Services. https://doi.org/10.5880/icgem.2016.006.

- Ince, E. S., et al. (2019). "ICGEM – 15 years of successful collection and distribution of global gravitational models, associated services, and future plans." Earth System Science Data, 11, 647–674. https://doi.org/10.5194/essd-11-647-2019. The archive the gravity coefficient files are taken from: https://icgem.gfz.de/.

- Berry, M. M., & Healy, L. M. (2004). "Implementation of Gauss-Jackson Integration for Orbit Propagation." The Journal of the Astronautical Sciences, 52(3), 331–357. https://drum.lib.umd.edu/handle/1903/2202.

- Verner, J. H. (2010). "Numerically optimal Runge–Kutta pairs with interpolants." Numerical Algorithms, 53, 383–396. https://doi.org/10.1007/s11075-009-9290-3. Coefficient sets from https://www.sfu.ca/~jverner/: RKV98.IIa.Efficient, RKV87.IIa.Robust and RKV65.IIIXb.Efficient (via the numeris crate).

- Tsitouras, Ch. (2011). "Runge–Kutta pairs of order 5(4) satisfying only the first column simplifying assumption." Computers & Mathematics with Applications, 62(2), 770–775. https://doi.org/10.1016/j.camwa.2011.06.002.

- Izzo, D. (2015). "Revisiting Lambert's problem." Celestial Mechanics and Dynamical Astronomy, 121(1), 1–15. https://doi.org/10.1007/s10569-014-9587-y.

- Lancaster, E. R., & Blanchard, R. C. (1969). A Unified Form of Lambert's Theorem. NASA Technical Note D-5368. https://ntrs.nasa.gov/citations/19690027552.

- Vincenty, T. (1975). "Direct and Inverse Solutions of Geodesics on the Ellipsoid with Application of Nested Equations." Survey Review, 23(176), 88–93. https://doi.org/10.1179/sre.1975.23.176.88.

- Bowring, B. R. (1976). "Transformation from Spatial to Geographical Coordinates." Survey Review, 23(181), 323–327. https://doi.org/10.1179/sre.1976.23.181.323. Used for: the Cartesian → geodetic conversion.

- Shoemake, K. (1985). "Animating rotation with quaternion curves." SIGGRAPH '85, 245–254. https://doi.org/10.1145/325334.325242. Used for: spherical linear interpolation (SLERP).

- Clohessy, W. H., & Wiltshire, R. S. (1960). "Terminal Guidance System for Satellite Rendezvous." Journal of the Aerospace Sciences, 27(9), 653–658. https://doi.org/10.2514/8.8704. Origin of the RIC (radial / in-track / cross-track) relative-motion frame.

- Marquardt, D. W. (1963). "An Algorithm for Least-Squares Estimation of Nonlinear Parameters." Journal of the Society for Industrial and Applied Mathematics, 11(2), 431–441. https://doi.org/10.1137/0111030.

- Nelder, J. A., & Mead, R. (1965). "A Simplex Method for Function Minimization." The Computer Journal, 7(4), 308–313. https://doi.org/10.1093/comjnl/7.4.308.

- Danby, J. M. A. (1987). "The solution of Kepler's equation, III." Celestial Mechanics, 40, 303–312. https://doi.org/10.1007/BF01235847. Used for: the starting value of the Kepler-equation iteration.

- Wallace, P. T., & Capitaine, N. (2006). "Precession-nutation procedures consistent with IAU 2006 resolutions." Astronomy & Astrophysics, 459(3), 981–985. https://doi.org/10.1051/0004-6361:20065897.

- Mathews, P. M., Herring, T. A., & Buffett, B. A. (2002). "Modeling of nutation and precession: New nutation series for nonrigid Earth and insights into the Earth's interior." Journal of Geophysical Research: Solid Earth, 107(B4), 2068. https://doi.org/10.1029/2001JB000390. The IAU 2000A nutation model.

- Seidelmann, P. K. (1982). "1980 IAU Theory of Nutation: The final report of the IAU Working Group on Nutation." Celestial Mechanics, 27, 79–106. https://doi.org/10.1007/BF01228952. The nutation series used by the IAU-76/FK5 (_approx) reduction and by TEME.

- Charlot, P., et al. (2020). "The third realization of the International Celestial Reference Frame by very long baseline interferometry." Astronomy & Astrophysics, 644, A159. https://doi.org/10.1051/0004-6361/202038368.

- Altamimi, Z., Rebischung, P., Collilieux, X., Métivier, L., & Chanard, K. (2023). "ITRF2020: an augmented reference frame refining the modeling of nonlinear station motions." Journal of Geodesy, 97, 47. https://doi.org/10.1007/s00190-023-01738-w.

- Standish, E. M., & Williams, J. G. "Keplerian Elements for Approximate Positions of the Major Planets." JPL Solar System Dynamics. https://ssd.jpl.nasa.gov/planets/approx_pos.html. Used for: the low-precision planetary ephemerides (satkit.planets).

- NASA Goddard Space Flight Center. General Mission Analysis Tool (GMAT) Mathematical Specifications, distributed with GMAT (R2026A: docs/GMATMathSpec.pdf); an early draft is on NTRS at https://ntrs.nasa.gov/citations/20080031744. Used for: the GMAT configuration of the validation corpus (coordinate systems, §4.1.1 Table 4.1 and §4.2.6 relativistic terms).

- Hughes, S. P., Qureshi, R. H., Cooley, S. D., & Parker, J. J. (2014). "Verification and Validation of the General Mission Analysis Tool (GMAT)." AIAA 2014-4151, AIAA/AAS Astrodynamics Specialist Conference. https://doi.org/10.2514/6.2014-4151.

- Rodriguez-Solano, C. J., Hugentobler, U., & Steigenberger, P. (2012). "Adjustable box-wing model for solar radiation pressure impacting GPS satellites." Advances in Space Research, 49(7), 1113–1128. https://doi.org/10.1016/j.asr.2012.01.016. The box-wing SRP model referred to (but not implemented) in the force-model guide.

- Beutler, G., Brockmann, E., Gurtner, W., Hugentobler, U., Mervart, L., Rothacher, M., & Verdun, A. (1994). "Extended orbit modeling techniques at the CODE processing center of the International GPS Service for Geodynamics (IGS): theory and initial results." Manuscripta Geodaetica, 19, 367–386. The CODE empirical solar-radiation-pressure parameterization.

- Springer, T. A., Beutler, G., & Rothacher, M. (1999). "A new solar radiation pressure model for GPS satellites." GPS Solutions, 2(3), 50–62. https://doi.org/10.1007/PL00012757. The reduced 5-parameter ECOM.

- Arnold, D., Meindl, M., Beutler, G., Dach, R., Schaer, S., Lutz, S., Prange, L., Sośnica, K., Mervart, L., & Jäggi, A. (2015). "CODE's new solar radiation pressure model for GNSS orbit determination." Journal of Geodesy, 89(8), 775–791. https://doi.org/10.1007/s00190-015-0814-4. ECOM2 (even harmonics in Δu from orbit noon).

- Dach, R., Lutz, S., Walser, P., & Fridez, P. (eds.) (2015). Bernese GNSS Software Version 5.2. Astronomical Institute, University of Bern. https://www.bernese.unibe.ch/docs/DOCU52.pdf. §2.2.2.3 restates the ECOM equations and the shadow convention used by CODE.

- Duan, B., & Hugentobler, U. (2021). "Enhanced solar radiation pressure model for GPS satellites considering various physical effects." GPS Solutions, 25, 42. https://doi.org/10.1007/s10291-020-01073-z. 24-hour GPS prediction accuracy quoted on the ECOM page.

- Hilla, S. (2016). The Extended Standard Product 3 Orbit Format (SP3-d). International GNSS Service. https://files.igs.org/pub/data/format/sp3d.pdf. The precise-orbit file format read in the GPS tutorials and tests.

Data sources

- CelesTrak Space Data — https://celestrak.org/SpaceData/. Daily EOP-All.csv (Earth orientation parameters, from IERS Bulletin A / finals) and SW-All.csv (space weather: F10.7, Ap; from GFZ and NOAA). - NOAA/SWPC predicted solar cycle — https://services.swpc.noaa.gov/json/solar-cycle/predicted-solar-cycle.json, the F10.7 forecast used when propagating beyond the space-weather record. - NAIF generic kernels — https://naif.jpl.nasa.gov/pub/naif/generic_kernels/spk/planets/ (de440.bsp, used by GMAT in the validation corpus). satkit itself reads JPL's binary DE files (linux_p1550p2650.440, lnxp1900p2053.421). - ICGEM — https://icgem.gfz.de/ (Ince et al. 2019): source of the .gfc gravity-coefficient files. - NRLMSISE-00 at CCMC — https://ccmc.gsfc.nasa.gov/models/NRLMSIS~00/: reference implementation and documentation of the density model.

Verification

The Rust and Python test suites check the implementation against:

• SGP4 — the test vectors distributed with the reference C++ code of Vallado et al. (2006).
• JPL ephemerides — JPL's testpo Chebyshev-interpolation test vectors for DE440/DE441 (Park et al. 2021).
• Frame transforms and Keplerian elements — worked examples from Vallado (2013).
• Gravity — reference values from ICGEM.
• Numerical propagation — ESA/IGS precise GPS orbits in SP3-d format, and the NASA GMAT reference corpus described in Validation: GMAT Comparison.