Derivatives of eccentricity and argument of periapsis with respect to time
[deccdt, dpomdt] = CL_op_frozenOrbitDer(sma, ecc, inc, pom [[, er, mu, j1jn]])
Computes the time derivatives of eccentricity and argument of periapsis resulting from the gravitational effects due to J2 and J3.
The time derivative of the argument of periapsis is undefined (%nan) if the orbit is circular (ecc = 0) or equatorial (inc = 0 or pi).
(See the formulas, where: R = equatorial radius, n = keplerian mean motion)
Warning :
- The input argument "zonals" is deprecated as of CelestLab v3.0.0. It has been replaced by "j1jn".
Semi-major axis. [m] (1x1 or 1xN)
Eccentricity. [-] (1x1 or 1xN)
Inclination. [rad] (1x1 or 1xN)
Argument of pariapsis. [rad] (1x1 or 1xN)
(optional) Equatorial radius. Default: %CL_eqRad. [m] (1x1)
(optional) Gravitational constant. Default: %CL_mu. [m^3/s^2] (1x1)
(optional) Vector of zonal coefficients J1 to Jn, troncated to J3. Default: %CL_j1jn(1:3)). [-] (1xNz)
Time derivative of eccentricity. [s^-1] (1xN)
Time derivative of argument of periapsis. [rad/s] (1xN)
CNES - DCT/SB
1) "Frozen orbits in the J2+J3 problem", Krystyna Kiedron and Richard Cook, AAS 91-426.