Quote:
|
Originally Posted by Bob B.
All you have to do to perform a rendezvous is to get the two vehicles into the same orbital plane....
|
true, but the problem is that the orbital plane will happen only
30 (of 95) days and only for a few minutes (
36 minutes if the launch margin is +/-500km.) , then, will be sufficient that the CLV/SM/CEV will need time to change a defective (ECO-like) sensor, and...
Quote:
|
Originally Posted by Bob B.
If the LSAM/EDS is in an orbit with an inclination of 28.5 degrees, then there’ll be one launch window per day....
|
exact, the orbital inclination for a lunar mission will be 28.5, then,
one launch window per day, then
36 minutes (max) per day to launch the CLV/CEV, then
only 18 "HOURS" in TOTAL (inside the 95 days)
but we must consider that the LSAM/EDS will not wait in the Cape Canaveral's sky... it runs while the launch windows, then...
very very critical!
Quote:
|
Originally Posted by Bob B.
I don’t know how long each launch window will be, but I’m sure they’ll be pretty short. There isn’t much margin for error in getting the orbital planes to match....
|
I agree with you, this is (exactly) the problem of the one-and-half launch architecture
Quote:
|
Originally Posted by Bob B.
By carefully selecting the orbits and the timing, the two vehicles can be placed in orbit separated by a short distance.
|
true, but with so little and critic launch windows the risk to lose $6 billion of hardware is very high!
.