So, I was reading this memorandum to make some c# classes helping with keplerian/newtonian orbital simulations. Then, I found this weird piece for solving for $n$...
$n = (0, 0, 1)^T × h = (−h_y, h_x, 0)^T$
The paradox is, it doesn't mention any variable T beforehand. An answer that just solves the problem this part of the paper addresses (part c) works too.
In that case, we have the following given values:
The relative positional vector $r$
The velocity vector $r˙$
The standard gravitational parameter $µ$
The orbital momentum vector $h$
The eccentricity vector $ɛ$
and we want to find...
The vector $n$ pointing towards the ascending node
The true anomaly $v$
I saw this post, but it didn't explain everything for me.
Any help appreciated. Sorry for my slightly bizzare wording.
