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| template<class T > |
| T | physics::orbit::period (T a, T gm) |
| | Calculates the period of an elliptical orbit according to Kepler's third law. More...
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| template<class T > |
| T | physics::orbit::mean_motion (T a, T gm) |
| | Calculates the mean motion (n) of an orbit. More...
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| template<class T > |
| T | physics::orbit::mean_motion (T t) |
| | Calculates the mean motion (n) of an orbit. More...
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| template<class T > |
| T | physics::orbit::argument_periapsis (T om, T lp) |
| | Derives the argument of the periapsis (omega) of an orbit, given the longitude of periapsis (pomega) and longitude of the ascending node (OMEGA). More...
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| template<class T > |
| T | physics::orbit::longitude_periapsis (T om, T w) |
| | Derives the longitude of the periapsis (pomega) of an orbit, given the argument of periapsis (omega) and longitude of the ascending node (OMEGA). More...
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| template<class T > |
| T | physics::orbit::semiminor_axis (T a, T ec) |
| | Derives the semiminor axis (b) of an orbit, given the semimajor axis (a) and eccentricity (e). More...
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| template<class T > |
| T | physics::orbit::semilatus_rectum (T a, T ec) |
| | Derives the semi-latus rectum (l) of an orbit, given the semimajor axis (a) and eccentricity (e). More...
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