Aerobraking to Jupiter/Europa and Saturn/Titan
|
Dist |
Vcirc |
Mass |
Vesc |
Radius |
Moon |
Dist |
Vorb |
Launch |
Tranf. |
Aero |
radial |
Land |
|
AU |
km/s |
|
km/s |
Mm |
Dest. |
Mm |
km/s |
km/s |
years |
km/s |
gees |
km/s |
Earth |
1.00 |
29.78 |
1.0 |
11.2 |
6.38 |
Luna |
384 |
1.02 |
|||||
Jupiter |
5.20 |
13.07 |
317.8 |
59.5 |
71.49 |
Europa |
671 |
13.74 |
14.24 |
2.73 |
|||
Saturn |
9.55 |
9.69 |
95.2 |
35.5 |
60.27 |
Titan |
1221 |
5.57 |
15.21 |
6.01 |
Launch Velocity
\large \Delta v_p = v_{ce} { \Large \left( \sqrt{ { 2 r_a } \over { r_e + r_a } } - 1 \right) } ~ ~ ~ \Delta v_{launch} = \sqrt{ \Delta {v_p}^2 + {v_{esc} }^2 }
Transfer time ( Earth Years)
Years \large = \sqrt{ ( 1 + AU )^3 / 32 }
Apogee Delta V, Delta V to planet
\large \Delta v_a = v_{ce} { \Large \left( \sqrt{ { 2 r_a } \over { r_e + r_a } } - 1 \right) }
\Delta v_{planet} = \sqrt{ \Delta {v_a}^2 + {v_{esc} }^2 }
Moon transfer distance ratio b = r_{moon} / r_{planet}
Moon transfer perigee \large v_{mp} = v_{ma} { \Large \sqrt{ { 2 b^2 } \over { 1 + b } } }