Satellite orbital parameter problem

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Mohammed Magdy Sharara 2020-3-2

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https://ww2.mathworks.cn/matlabcentral/answers/508543-satellite-orbital-parameter-problem

评论： Thomas Giavasopoulos 2021-12-17

Hello,

I am doing a matlab project but i am facing a kind of a problem

I am trying to find the satellite height at the ascending node and the user is inputing the inclination ,the argument of perigee,semi major axis, eccentricity, satellite longitude and satellite latitude

I am trying to figure it out up to what formula but it seems i can't get a hold of it if anyone can help me out

Thanks in advance

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James Tursa 2020-3-2

What is the specific MATLAB question? I.e., what code do you have and/or what equations are you trying to code?

Marta Stanska 2020-11-13

Tou have to do an iteration to find Ek (anomaly), then

rk= a * (1- (e*cos(Ek)))

h=R-rk

(R- Earth Radius, a-semimajor axis, e-eccentricity)

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回答（1 个）

James Tursa 2020-3-2

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Use the orbital geometry to calculate the true anomaly at the ascending node, and then plug that value into the conic equation to get r. That can then be used to calculate height.

Are you familiar with the orbital mechanics equations to accomplish this? Has the instructor given you this?