Hi Brian. I would love to take a look at your HDD, but I assume that you live in the US?
If that's the case, it would be too expansive I guess, but if have a change to get it to The Netherlands, please let me know
Hello BrianJ, I apologize if I'm resulting irritating or onerous, but I have a question: I'm repairing an old addon of Alex, the Minotaur I ELV (you can see the early results in my profile photo and you can try the early beta in the post named Minotaur I can't see the rocket, if you want) I want to know if you contacted Alex for access of editing his addon (the H-IIA for the Hayabusa 2) freely.
Hello BrianJ, when I played the Halley Armada series (great addons) I thinked there's a 'honorary member' of the Halley Armada that faults. This member is the ISEE-3/ICE (International Cometary Explorer) Why do you don't make this addon?
Hi Brain, after trying out your great Falcon 9R addon I'd be very interesting to know what mathematics you used for calculating the required delta-v to get the first stage near its target upon re-entry. Did you use any differential equations or was it more a "back-of-the-envelope" type of calculation?
I have a few ideas about some addons I would like to do for Orbiter, but I don't really know how to use C++ that well yet. I was wondering if you would be willing to share your C++ source codes for the delta_missions_v1_100930. It would be a great help, and I would ensure that you get full credit for your work. Please e-mail me at [email protected] at your earliest convenience. Thank you in advance.
I am looking at doing a Asteroid Sample Return Mission video for a school project. I saw you did a Rosetta simulation. I was wondering if you had a tutorial or some information about doing mission to such small body? Do you know anyone who did a similar mission?
Please PM your VC++ code as you suggested : I can't program but I think I can read it at least, and can avoid misunderstanding so. Or use my e-mail address [email protected]
Also, for the equations, I assume your inputs from Orbiter are: R, Theta, Phi, dR/dt, dTheta/dt, dPhi/dt and you need dX/dt, dY/dt, dZ/dt in the same Reference, as you already have X, Y, Z converted (Phi is Longitude, Theta is Latitude, Z=South-to-North, [Z,X]= Null-Longitude, Y=Z^X). Let's try velocities first and the attitudes only later, ok?
If I'm wrong please specify your inputs and expected outputs.