Name

CL_op_frozenOrbit — Eccentricity and perigee argument for a frozen orbit

Calling Sequence

   [ecc,pom] = CL_op_frozenOrbit(sma,inc,[,er[,mu[,zonals]]])
   
   

Description

  • This function computes eccentricity allowing to "freeze an orbit". That is, the mean periapsis argument remains constant. Solution given with this function is not a solution correponding to critical inclination; it comes from the compensation of potential impacts (pair and impair terms) on the evolution of periapsis argument.

    Eccentricity and periapsis argument for a frozen orbit can be computed taking into account perturbations coming from terms J2 to Jn of gravitational potential.

    You can optionally give the zonals coefficients to be used : default is %CL_j1jn(1:3) (J1/J2/J3). (Please note that if you give %CL_j1jn with n =70, only the first 50 zonals terms will be used, due to algorithm validation).

  • Last update : 25/2/2008

Parameters

sma:

semi major axis [m] (1x1 : same semi major axis for all inclinations) or (1xM)

inc:

inclination [rad] (1x1 : same inclination for all semi major axes) or (1xM)

er:

(optional) equatorial radius [m] (default is %CL_eqRad)

mu:

(optional) geocentric gravitational constant [m^3/s^2] (default value is %CL_mu)

zonals:

(optional) vector of zonals coefficients J1 to Jn (troncated to J50) to be used (default is %CL_j1jn(1:3)) (1 x N)

ecc:

eccentricity (1xM)

pom:

argument of periapsis [rad] (1xM)

Authors

CNES - DCT/SB

Examples

sma = [%CL_eqRad+350.e3 %CL_eqRad+700.e3];
inc = CL_deg2rad([51.6 91.6]);
[ecc,pom] = CL_op_frozenOrbit(sma,inc)