Earth To Orbit
A table of launch information.
Destination |
Launch V |
2000km |
2000km |
10 gee |
10 gee |
transit |
Arrival |
altitude |
radius |
|
V m/s |
gees |
time s |
dist km |
time s |
hrs |
∆V m/s |
km |
km |
LEO |
7451 |
1.41 |
537 |
283 |
76 |
0.74 |
65 |
300 |
6678 |
m288 |
8586 |
1.88 |
466 |
376 |
88 |
1.30 |
1009 |
6411 |
12789 |
GEO |
9875 |
2.49 |
405 |
497 |
101 |
5.24 |
1490 |
35786 |
42164 |
Moon |
10547 |
2.84 |
379 |
567 |
108 |
119.42 |
833 |
378022 |
384400 |
Slingshot Moon to m288 |
10547 |
2.84 |
379 |
567 |
108 |
241.74 |
-2184 |
6411 |
12789 |
Slingshot Moon to GEO |
10547 |
2.84 |
379 |
567 |
108 |
255.56 |
-1053 |
35786 |
42164 |
Note that the slingshot orbits show negative arrival ∆V. With some kind of rotating or linear tether system at the arrival orbit, the positive ∆V from ground launch payloads and the negative ∆V from a slingshot payloads can be averaged. This greatly reduces the size of the orbital insertion kick motors needed to inject payloads into these orbits. By sending 30% of m288 payloads the long way around the moon, for example, the cost of delivering payloads to m288 could be halved.