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celestlab >> Orbit properties > CL_op_repeat2smaInc

CL_op_repeat2smaInc

Semi major axis and inclination corresponding to (N,P,Q)

Calling Sequence

[sma, inc] = CL_op_repeat2smaInc(N, P, Q, ecc, sso [[, incInput, er, mu, j2, rotr_pla, rotr_pla_sun]])

Description

Parameters

N:

Values of N. [-] (1x1 or 1xNt)

P:

Values of P. [-] (1x1 or 1xNt)

Q:

Values of Q. [-] (1x1 or 1xNt)

ecc:

Eccentricity. [-] (1x1 or 1xNt)

sso:

1 = sun synchronous orbits, 0 = fixed inclination. (1x1)

incInput:

(mandatory in case sso=0, unused otherwise) Inclinations. [rad] (1x1 or 1xNt)

er:

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

mu:

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

j2:

(optional) Second zonal harmonic (unnormalized). Default: %CL_j1jn(2). [-] (1x1)

rotr_pla:

(optional) Body rotation rate. Default: %CL_rotrBody. [rad/s] (1x1)

rotr_pla_sun:

(optional) Mean apparent rotation rate of the Sun around the body. Default: %CL_rotrBodySun. [rad/s] (1x1)

sma:

Semi-major axis. 'sma' is '%nan' if value cannot be computed. [m] (1xNt)

inc:

Inclination. 'inc' is '%nan' if value cannot be computed. [rad] (1xNt)

Authors

See also

Examples

N = 15;
P = 3;
Q = 16;
ecc = 0.01;
sso = 0;
incInput = CL_deg2rad(98);
[sma, inc] = CL_op_repeat2smaInc(N, P, Q, ecc, sso, incInput)

N = [15, 15];
P = [3, 5];
Q = [16, 6];
ecc = [0.01, 0.001];
sso = 1 ;
[sma,inc] = CL_op_repeat2smaInc(N, P, Q, ecc, sso)

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