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CL_ex_propagateMan

Orbit propagation with maneuvers (all analytical models)

Calling Sequence

[result1, result2] = CL_ex_propagateMan(mod, type_oe, t1, mean_oe_t1, t2, tman, dvman, dvframe, res [[, er, mu, j1jn]])

Description

Parameters

mod:

(string) Model name: "central", "j2sec", "lydsec", "lydlp", "eckhech". (1x1)

type_oe:

(string) Type of orbital elements used for input/output: "kep", "cir", "cireq" or "equin". (1x1)

t1:

Initial time. [days] (1x1)

mean_oe_t1:

Mean orbital elements at time t1. (6x1 or 6xN)

t2:

Final time. [days] (1xN)

tman:

Maneuver times. [days] (1xP)

dvman:

Delta-V with components in specified frame [dvx; dvy; dvz]. [m/s] (3xP)

dvframe:

(string) Frame for the DV components: any local orbital frame or "inertial". (1x1)

res:

(string) Type of output (mean or osculating): "m", "o", "mo", "om". (1x1)

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 harmonics coefficients. Default: %CL_j1jn. [-] (Nzx1)

result1, result2:

Mean or osculating orbital elements at t2. (6xN)

Authors

See also

Examples

// Initial state (mean keplerian elements)
t0 = 0; // days
kep0 = [8.e6; 0.2; CL_deg2rad(60); 0; 0; 0];
// Final times
t = t0 + (0 : 0.001 : 3.5); // days
// Maneuvers
tman = t0 + [1.5, 2.5]; // days
dvman = [[10; 0; 0], [0; 0; 150]];
dvframe = "tnw";

// Propagation including maneuver effects (result = osculating elements)
kep = CL_ex_propagateMan("lydsec", "kep", t0, kep0, t, tman, dvman, dvframe, "o");

// Plot semi-major axis (blue) and inclination (red)
scf();
plot(t, kep(1,:) / 1000, "b");
scf();
plot(t, kep(3,:) * (180/%pi), "r");

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