Agamemnon

now they supplied material to ptolemy and are measuring... that would mean that the whole science sequence was performed as planned (even if one of the experiments failed because of the shutter)

they are commanding philae to rotate to have more sunlight... plus it seems, acc. to twitter, that the drilling was successful and the drill went down as expected

they have signal to philae... currently transmitting telemetry and science data...

from emily lakdawalla https://twitter.com/elakdawalla/status/533371448979890176

iirc, as they are done with all science (and primary objectives) they can get (resp. they will be if the drill worked and they will get data in the evening in the next comm window)... they will risk it and try to change the lander position to get more sunlight

she wont stay one year on the iss... she just uses the fact that soyuz will be changed in the middle of the one year stay of kornienko/kelly for a new one and there will be one week window for a tourist (because of the direct handover)... and she pays 50 mil. for the week

usually no tourists because of indirect handovers (just in exception cases, like the one year stay in 2015... with sarah brightman as a tourist)

it is effiecient for a gas generator kerolox... not so much for a kerolox in general - eg. there is a staged combustion kerolox engine (routinely used today) optimised for high thrust (not for isp) and for use on first stages that has nearly the same isp as merlin 1d vac optimised for high isp (the engine is rd-180 with vac isp 338 s) there is an isp optimized kerolox engine used in soyuz 2-1b upper stage with isp 359 s (rd-0124)

the reason being that it uses quite crappy upper stage engine - quite low specific impulse for an upper stage - for m1d vac it is only 340 s... and the more energetic orbit (gto, geo, escape) you are targeting the better isp is required or you are getting quite harsh payload penalties... ariane 5 or atlas 5 uses hydrolox upper stage engines with specific impulse around 440-450 s (btw - russian staged combustion kerolox upper stage engines have isp close to 360 s) so... using better upper stage engine would help (eg. ariane, atlas, delta)... using 3rd stage would help too (eg. proton)

and actually... the harder part of an orbital spaceflight is not to get high enough, but to be fast enough

new image, from 1000 km http://blogs.esa.int/rosetta/2014/08/02/comet-at-1000-km/

net 29th july

actually, the launch is 25th July, 01:41:04 utc edit: forget that... seems to be delayed by several days due to an issue with the second stage

from what i seen, it is pushed to 27th; because of the recent death of v.popovkin (former roscosmos head)

what about sabre? atm the best shot, i guess