Recent content by Pieter-S

is there anybody with some useful advice? regards, Pieter

Single-point Navigation Solution Giving the following satellites positions (coordinates are in meters and in Earth Centered Inertial Frame): r_(is,1)^i=[1.876371950559744e6 -10.6414313406656e6 24.2697646566144e6] r_(is,2)^i=[10.97666464137408e6 -13.08147952230029e6 20.35116937827073e6]...

Thanks ever so much sir, I am going to work on it, I will let you know if there still some uncertainties. have a good night:) Regards, Pieter

Yes, I did tried to implement those equation in simple m file, but it is not complete due initial conditions as this is unknown:(, I do appreciate your response and patience:). cheers, Pieter

Hi, Well I thought in the first place that I could solve this problem by following your recommendation, At least that is what I hoped. by looking further and reading some of those navigation books, the problem is complicated than it actually looks. so still I struggle to give a good go...

I am so sorry to say, but this sounds like an music to my ears:(

Thanks you for your prompt response , Hill–Clohessy–Wiltshire (HCW) describes two targets chasing each other. mine case is s simple mass point.

Well, I was ill during the lecture sessions, and I don't have contact with my study mates. I sent an email to lecturer though, but he said that I could google this out. King regards, Pieter

Dear :), could some one please guide me in the right direction to answer the following questions: 1) using MATLAB, implement the differential equations that describe the evolution with time of along-track , cross-track and vertical position. (Inertial Navigation System). and 2) for a...