Can anyone explain why they placed the satellite in 295x80 000 km orbit? Is it especially hard to place satellites directly into geostationary orbit, or something else?
In order to get geostationary, you need to get to a circular orbit at an altitude of 35,786km above Earth's surface. Trying to do that all in one burn is, I guess, theoretically possible but is going to waste an absurd amount of fuel.
The reason for this is that changing altitude in orbit = changing your speed. Specifically, you have two points you care about: your apogee (highest altitude) and your perigee (lowest altitude). To raise your apogee in the most efficient manner, you accelerate prograde (in the direction of your orbit), at perigee. To raise perigee in the most efficient manner, you accelerate prograde at apogee. Or, more simply: what you do at a certain point in your orbit will end up affecting what happens at the point in your orbit that's precisely opposite the point where you did something.
So the most efficient way to get up there is to use a transfer orbit. First you get into a lower, "parking" orbit (which doesn't take as much fuel as going all the way up in one go). Then at perigee you burn to raise your apogee out to the altitude you want. Then you cruise to apogee, and burn again to raise your perigee, resulting in a circular orbit.
Here's a detailed article on that:
https://en.wikipedia.org/wiki/Hohmann_transfer_orbit
Except it never goes quite that simply in the real world, so you actually end up doing more than two engine burns, but under ideal theoretical circumstances, you'd do it in two.
I haven't read up on the burn plans, but it's possible that the mission is technically using a bi-elliptic transfer[1], rather than a straight hohmann transfer (warning: I learned my orbital mechanics from the Kerbal Space Academy).
Bi-elliptic transfer: (2.713240 + 0.908982 + 0.485255) = 4.107477 km/s Hohmann transfer: (2.335977 + 1.431307) = 3.7672853 km/s
This alone does not explain why they did so. But this is all assuming that the trajectory is planar. If there was a plane change coupled with the second burn at high apogee, it could explain it.
Secondly, there was never any stage where they circularized their orbit, as one would do with a Hohmann. Rather, they kept burning at perigee until they escaped earth. Picture a an ellipse growing more and more eccentric until it becomes open at one end.
Also note that they never burned at apogee. The point wasn't to raise apogee so they could escape at apogee, but to increase velocity at perigee until they could reach escape velocity with a 20 minute burn on their last orbit.
Also, inclination burns can be combined with raising periapsis, which allows you to save some fuel thanks to the way they are at a 90 degree angle.
Another advantage is that it provides an easy and cheap way to deliver the spacecraft into the correct position in the stationary orbit, by controlling the orbital period of the eccentric orbit so that the periapsis will be where you want it to be (possibly after several orbits).
Because of this, the best possible way to launch from far away from the equator to a geostationary orbit is to launch to a highly eccentric orbit, at apoapsis when you intersect the equator simultaneously raise your periapsis to geostationary and fix your inclination, and then circularize at periapsis.
If this is interesting, and you don't already own kerbal space program, head over to the steam store right now.
And if you like Kerbal Space Program, but you find it isn't quite sadistic enough, go download Orbiter.