# Trouble understanding the memorandum "Cartesian State Vectors → Keplerian Orbit Elements"

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.

That T is not a variable. It indicates that you should take the matrix transpose of those row vectors, making them into column vectors.

• Ah, weird formatting. Dec 28, 2021 at 5:10