Sun-Jupiter Integrator (3D)
HELP. Displays this help screen. To exit, click one of the Exit Help buttons located at the
top and bottom of this screen.
INTEGRATION TIME. Here you specify how long into the future
the orbit should be followed. Be careful in choosing this parameter as
it is directly correlated to how long you will wait before seeing a
plot! A good strategy is to try a short integration time first to get
an idea of how fast the program is.
Orbit of the Asteroid or Comet
SEMIMAJOR AXIS. The semimajor axis is half the long axis of the
initial elliptical orbit.
ECCENTRICITY. The eccentricity gives the shape of the third body's
elliptical orbit; it must be a value between 0 and 1.
An eccentricity of 0.0 will produce an initially circular orbit;
larger eccentricities correspond to narrower ellipses.
INCLINATION. The asteroid's inclination is measured relative to the
plane of the orbits of the other two bodies.
ARGUMENT OF PERICENTER (). The argument of pericenter is an angle measured in the
orbit plane between the ascending node and pericenter (P).
TRUE ANOMALY (). This
parameter specifies the angle between pericenter (P) and the
position of the asteroid along its orbit.
LONGITUDE OF THE ASCENDING NODE (). The Longitude of the Ascending Node is an angle
measured in the reference plane from a reference point () to the
Ascending Node. The Ascending Node is the position where the
plane of the orbit crosses the reference plane heading north.
SUBMIT FORM. Send the parameters that you have chosen to the
orbital integration program!
LOAD DEFAULTS. Set all parameters back to their default values.