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A table of 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.

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.

EarthToOrbit (last edited 2009-08-24 05:12:42 by KeithLofstrom)