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I am trying to convert orbital elements to the state vector in MATLAB. My orbital elements are as follows a = 6731; ecc = 0.01; inc = 142.461; raan = 155.9325; argp = 321.0439; f = 145.8291;   After transforming them I get : x = 3898.6; y = 3898.6; z = 3957; vx = 5.9771; vy = -4.5575; vz = -1.3245;   I am wondering if the transformation is done correctly. Because x, y, and z are defined from earth's radius to the spacecraft, right? If that is the case then x, y, and z should have values greater than the earth's radius. Is my assumption correct?

I am trying to convert orbital elements to the state vector in MATLAB. My orbital elements are as follows a = 6731; ecc = 0.01; inc = 142.461; raan = 155.9325; argp = 321.0439; f = 145.8291;   After transforming them I get : x = 3898.6; y = 3898.6; z = 3957; vx = 5.9771; vy = -4.5575; vz = -1.3245;   I am wondering if the transformation is done correctly. Because x, y, and z are defined from earth's radius to the spacecraft, right? If that is the case then x, y, and z should have values greater than the earth's radius. Is my assumption correct?

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)
Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)
8th Edition
ISBN:9781305387102
Author:Kreith, Frank; Manglik, Raj M.
Publisher:Kreith, Frank; Manglik, Raj M.
Chapter4: Numerical Analysis Of Heat Conduction
Section: Chapter Questions
Problem 4.6P
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I am trying to convert orbital elements to the state vector in MATLAB. My orbital elements are as follows

a = 6731;
ecc = 0.01;
inc = 142.461;
raan = 155.9325;
argp = 321.0439;
f = 145.8291;
 
After transforming them I get :
x = 3898.6;
y = 3898.6;
z = 3957;
vx = 5.9771;
vy = -4.5575;
vz = -1.3245;
 
I am wondering if the transformation is done correctly. Because x, y, and z are defined from earth's radius to the spacecraft, right? If that is the case then x, y, and z should have values greater than the earth's radius. Is my assumption correct?
 
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