Russian version of the page | Description |
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Input data | The way of input | To take into account pertubations from the following planets: | |||||||||||||||||||||||||||||||
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Epoch (JD, TT) Initial motion parameters Mass of the object: Start ephemeris time (JD): Final ephemeris time (JD): Output step: | |||||||||||||||||||||||||||||||||

Elements must obey the following order: 1) perihelion distance q (AU) 2) eccentricity e 3) inclination i (deg.) 4) ascending node W (deg.) 5) argument of perihelion w (deg.) 6) mean anomaly M (deg.) When using rectangular coordinates | Ephemerides of planets and the Moon to compute the perturbations: | ||||||||||||||||||||||||||||||||

The basic plane: | Initial integration step (days): Order of the Everhart's method: | ||||||||||||||||||||||||||||||||

Parameters of nongravitational forces: A _{1}= _{2}= ^{2} | Floating-point numbers' bit capacity: | ||||||||||||||||||||||||||||||||

To compute approaches to the following planets: (at the right the maximal distance (in AU) to the planet's center should be input) |

What to output in the ephemeris | The way of output | Format of output | Number of decimal digits | |||||||||||||||
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and declination (delta) in the reference frame 2000.0 for which they are computed | ||||||||||||||||||

(heliocentric) | ||||||||||||||||||

Orbital elements (ecliptic 2000.0) | Linear elements: | |||||||||||||||||

Angular elements: | ||||||||||||||||||

Perihelion time: | ||||||||||||||||||

Distance (d_) to: | ||||||||||||||||||

Time moments (TT) |