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Convert Keplerian Orbital Elements to a State Vector

version 1.2 (4.03 KB) by

Convert orbital elements to a state vector, or a state vector back to orbital elements.



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Most readily available Keplerian orbital element conversion utilities do not address circular or parabolic orbits. This set of routines will address the complete spectrum of orbits from a circular equatorial orbit to a retrograde hyperbolic orbit without error. All functionality is vectorized for computational efficiency.

Example Function Call One:
>> [r_ECI v_ECEF] = orb2rv(p,e,i,O,o,nu);

p = semilatus rectum (km) [1 x N]
e = Eccentricity [1 x N]
i = Inclination (rad) [1 x N]
O = Right Ascension of the Ascending Node (rad) [1 x N]
o = Argument of Perigee (rad) [1 x N]
nu = True Anomaly (rad) [1 x N]

Example Function Call Two:
>>[a,e,i,O,o,nu] = rv2orb(r_ECI,v_ECI)

r = Position State Vector in km (ECI) [3 x N]
v = Velocity State Vector in km/s (ECI) [3 x N]

For those orbits which are equatorial or circular, the following full form function calls are necessary:

Convert state vector to full set of orbital elements:
>>[a,e,i,O,o,nu,truLon,argLat,lonPer,p] = rv2orb(r_ECI,v_ECI);

Convert full set of orbital elements back to a state vector:
>>[r_ECI,v_ECI] = orb2rv(p,e,i,O,o,nu,truLon,argLat,lonPer);

truLon = True Longitude (rad) [1 x N]
argLat = Argument of Latitude (rad) [1 x N]

Comments and Ratings (5)

Possibly mu is 3.986004418*10^14; Standard Gravitational Parameter for Earth
μ=3.986004418⋅10^14 m3/s2


Hayden (view profile)

Good, but getConst() is not a function in Octave, so have to replace it with the numerical value of mu.


vlas (view profile)

oops, forgot the comment, here it goes:
was about to write eci conversion functions myself, glad i've found these ones first!


vlas (view profile)



Updated outputs for orbital parameters when state vector is circular and equatorial.

MATLAB Release
MATLAB 7.11 (R2010b)

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