Examples
// Mean argument of latitude to true argument of latitude: ex = 0.1; ey = 0.2; psoM = [-0.1, 10.2]; // rad psov = CL_kp_anomConvertCir("M", "v", ex, ey, psoM) // Consistency test: psoM - CL_kp_anomConvertCir("v", "M", ex, ey, psov) // => 0 |  |  |
Conversion of anomaly (circular or equinoctical elements)
[pso2] = CL_kp_anomConvertCir(type_anom1, type_anom2, ex, ey, pso1)
Converts anomaly from one type to another, for circular or equinoctial orbital elements
The components of the eccentricity vector ex, ey are of the form:
ex = e*cos(A)
ey = e*sin(A)
Where:
A = w (argument of perigee) for circular orbital elements, or
A = W + w (RAAN + argument of perigee) for equinoctial orbital elements.
The "pso" quantity that can be converted is:
- pso = A + M if type_anom = "M"
- pso = A + v if type_anom = "v"
- pso = A + E if type_anom = "E"
Note:
- Only elliptical orbits are handled (eccentricity < 1)
(string) Type of input anomaly (1x1)
(string) Type of output anomaly (1x1)
x component of eccentricity vector (1xN or 1x1)
y component of eccentricity vector (1xN or 1x1)
Input anomaly (1xN or 1x1)
Output anomaly (1xN)
CNES - DCT/SB
// Mean argument of latitude to true argument of latitude: ex = 0.1; ey = 0.2; psoM = [-0.1, 10.2]; // rad psov = CL_kp_anomConvertCir("M", "v", ex, ey, psoM) // Consistency test: psoM - CL_kp_anomConvertCir("v", "M", ex, ey, psov) // => 0 | | |