Re: Ephemerides for Falcon Heavy hardware?

From: Marco Langbroek via Seesat-l <>
Date: Tue, 6 Feb 2018 15:00:15 +0100
Op 6-2-2018 om 14:47 schreef Matija Perne via Seesat-l:

> I believe one way of reaching an Apollo orbit like the one proposed is
> boosting the object in the direction of Earth's travel around the Sun.
> A GTO-like orbit that is reached through an insertion burn over Africa
> 00:28:52 after launch has its apogee in front of the Earth, generally
> speaking. Assuming the boost to heliocentric orbit is approximately
> parallel with the direction of travel, it would thus happen on the way
> towards the apogee of the GTO-like orbit. For the rocket to be there 6
> hours after launch, the GTO-like orbit could have its apogee higher
> than a GTO would, so it is not reached yet by then.

For a perigee boost in the second 200 x 20000 option, it would indeed be boosted
into a direction more or less parallel to earth movement.

For the first option with boost at apogee of a 200 x 36000 km GTO, it distinctly
would not, which is why that option appears illogical.

- Marco

Dr Marco Langbroek  -  SatTrackCam Leiden, the Netherlands.

Cospar 4353 (Leiden):     52.15412 N, 4.49081 E (WGS84), +0 m ASL
Cospar 4355 (Cronesteyn): 52.13878 N, 4.49937 E (WGS84), -2 m ASL
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Received on Tue Feb 06 2018 - 08:01:27 UTC

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