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celestlab >> Orbit properties > CL_op_frozenOrbitDerCir

CL_op_frozenOrbitDerCir

Derivatives of eccentricity vector (ex, ey) with respect to time

Calling Sequence

[exdot, eydot] = CL_op_frozenOrbitDerCir(sma, ex, ey, inc [[, er, mu, j1jn]])

Description

Parameters

sma:

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

ex:

Eccentricity vector "x" component. [-] (1x1 or 1xN)

ey:

Eccentricity vector "y" component. [-] (1x1 or 1xN)

inc:

Inclination. [rad] (1x1 or 1xN)

er:

(optional) Equatorial radius. Default: %CL_eqRad. [m] (1x1)

mu:

(optional) Gravitational constant. Default: %CL_mu. [m^3/s^2] (1x1)

j1jn:

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

exdot:

Time derivative of ex. [-/s] (1xN)

eydot:

Time derivative of ey. [-/s] (1xN)

Authors

Bibliography

See also

Examples

sma = 7000.e3;
ex = 1.e-4;
ey = 1.2e-3;
inc = CL_deg2rad(98.0);
[exdot, eydot] = CL_op_frozenOrbitDerCir(sma, ex, ey, inc);

// Check using CL_op_frozenOrbitDer
ecc = sqrt(ex^2 + ey^2);
pom = atan(ey, ex);
// Derivatives of ecc and pom:
[deccdt, dpomdt] = CL_op_frozenOrbitDer(sma, ecc, inc, pom);
exdot2 = deccdt * cos(pom) - ecc * sin(pom) * dpomdt;
eydot2 = deccdt * sin(pom) + ecc * cos(pom) * dpomdt;
exdot - exdot2 // => 0
eydot - eydot2 // => 0

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