CL_ex_propagateMan

Description

• Propagates orbital elements using one analytical model while taking maneuvers (velocity increments) into account.

  The available propagation models are:

  "central": Central force (osculating elements = mean elements)

  "j2sec": Secular effects of J2 (osculating elements = mean elements by convention)

  "lydsec": Lyddane (mean elements include secular effects only)

  "lydlp": Lyddane (mean elements include secular and long period effects)

  "eckhech": Eckstein-Hechler (mean elements include secular and long period effects)

  Maneuvers are defined by:

  - tman: time of the maneuver.

  - dvman = [delta-Vx;delta-Vy;delta-Vz]: delta-V components in the chosen frame.

  - dvframe: name of the frame in which the components are given. The name can be any name compatible with CL_fr_locOrbMat, or "inertial".

• Notes:

  - If one maneuver occurs at one of the final times, the output orbital elements include the effect of the maneuver at that time.

  - The final times as well as the maneuver times should be sorted in increasing order.

  - t1 should be smaller than tman(k) for any k.

  - t1 should be smaller than t2(k) for any k.

• See Propagation models for more details.

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 [m] (default is %CL_eqRad)

mu:

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

j1jn:

(optional) Vector of zonal harmonics. Default is %CL_j1jn (Nz x 1)

result1, result2:

Mean or osculating orbital elements at t2 (6xN)

Authors

• CNES - DCT/SB

See also

• CL_ex_propagate

• CL_fr_locOrbMat

Examples

// Initial state (mean keplerian elements) t0 = 0; // days kep0 = [8.e6; 0.2; 60*(%pi/180); 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");