| Default units to use on this page are Astronomical Units. |
|---|
| A beta version of a work in progress, hyperbolics need more work. |
| The Gravitational Constant is preset as 6.674080 X 10-11 Nm2kg-2. |
| Please choose Planets and input their desired Circular Orbital Altitude, velocities will be calculated. |
| Planet Choice | Orbit Altitude | Orbit Velocity | Escape Velocity | ||
|---|---|---|---|---|---|
| Start : | Km | m/s | m/s | ||
| Destination : | Km | m/s | m/s | ||
| Enter start position's 3D or 2D cartesian coordinates: | X: Y: Z: AU's | Enter destination position's 3D or 2D cartesian coordinates : |
| X: Y: Z: AU's | |
| Please enter required or observed time between chosen points. In Earth days : | |
| Magnitude of start pos' vector : Magnitude of end pos' vector: AU's |
| Departure phase angle : deg's (the angle between the current departure and future arrival points) |
| k parm : AU l parm : AU m parm : AU |
| p1 parm : AU p2 parm : AU start p parm : AU end p parm : AU |
| the a parm : AU the f parm : the g parm : the dot f parm : |
| The eccentric anomaly calculation values: ΔE : sin(ΔE) : cosh(ΔF) : rad's |
| Derived journey time: Iteration count : Diagnostic 1 : Diagnostic 2 : |
| dotg: v1x: v1y: v1z: v2x: v2y: v2z: |
| Magnitude of start velocity vector : m/s...... Magnitude of end velocity vector : m/s...... |