QUOTE (centsworth_II @ Sep 16 2014, 01:12 PM)
From the landing selection video after 1:09 there is this:
"To deliver the lander successfully, we have to fly relatively fast in front of the comet and this brings the spacecraft again on hyperbolic orbit so we are not bound any more to the gravity of the comet."
The quote you cite sounded to me like they were talking about the fly-away burn after deployment.
Again - refer to that drawing I grabbed from the conference - it's quite clear that they in essence do a pseudo 'deorbit' burn - separate the lander, and then do a divert burn to avoid following the lander into the comet.
Also from the press event.... "We are in orbit around the comet. We interrupt this orbit - we fly closer to the comet, we go downwards, we release the lander" and also "We phase the orbit of the spacecraft to meet the landing site"
Put it this way - let's conduct a thought experiment where they don't do a divert for the orbiter 30 mins after the separation.
The 18cm/sec separation speed, allowing for a 12:1 mass ratio between the 100kg lander and the approx 1200kg dry mass of Rosetta
This means Philae will be pushed forward at 16.6cm/sec and Rosetta pushed backwards at 1.4cm/sec ( roughly )
So after 7 hours, Rosetta will be 0.3km in one direction - the lander 4.1km in the other. The comet is approx 3 x 4km. If you had perfect navigation - and aimed such that the lander were aimed at the center of a 3.5km sphere..... the orbiter would swoop over the comet at an altitude of only 2.6km - way closer than they would normally fly the orbiter, especially given that in the conference they stated the difference in accuracy between orbit reconstruction and orbit prediction is about 1km.
So - is it an exact collision course? No. But it would be a damn close flyby if they didn't divert the orbiter 30 minutes after separation. DAMN close.