<< CL_op_frozenOrbit Orbit properties CL_op_locTimeG50 >>

CelestLab >> Orbit properties > CL_op_frozenOrbitDer

CL_op_frozenOrbitDer

Derivatives of eccentricity and argument of periapsis with respect to time

Calling Sequence

[d_ecc_dt,d_pom_dt] = CL_op_frozenOrbitDer(sma,ecc,inc,pom, [er,mu,zonals])

Description

Parameters

sma:

Semi-major axis [m] (1x1 or 1xN)

ecc:

Eccentricity (1x1 or 1xN)

inc:

Inclination [rad] (1x1 or 1xN)

pom:

Argument of pariapsis [rad] (1x1 or 1xN)

er:

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

mu:

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

zonals:

(optional) Vector of zonal coefficients J1 to Jn, troncated to J3. Default is %CL_j1jn(1:3)). (1xNz)

d_ecc_dt:

Derivative of eccentricity [s^-1] (1xN)

d_pom_dt:

Derivative of argument of periapsis [rad/s] (1xN)

Authors

Bibliography

Examples

sma = [%CL_eqRad+350.e3 %CL_eqRad+700.e3];
inc = CL_deg2rad([51.6 91.6]);
[ecc,pom] = CL_op_frozenOrbit(sma,inc);
ecc = 0.999*ecc;
pom = 0.999*pom;
[d_ecc_dt,d_pom_dt] = CL_op_frozenOrbitDer(sma,ecc,inc,pom)
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