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celestlab >> Trajectory and maneuvers > CL_man_lowThrustApsKep

CL_man_lowThrustApsKep

Effect of continuous low thrust on the Keplerian orbital elements (elliptical orbits)

Calling Sequence

[result] = CL_man_lowThrustApsKep(kep, acc, acc_frame, alpha, apsis, res [[, opts, mu]])

Description

Parameters

kep :

Keplerian orbital elements [m, rad]. (6xN or 6x1)

acc :

Thust acceleration (in cartesian coordinates) in the specified frame [m/s^2]. (3xN or 3x1)

acc_frame :

(string) Frame in which the acceleration is defined : "qsw", "tnw" or "aps". (1x1)

alpha :

Angle (true anomaly) defining the thrust arc [rad]. (1xN or 1x1)

apsis :

(string) Center of thrust arc : "per" or "apo". (1xN or 1x1)

res :

(string) Computed result: "dkepdt" or "dkep". (1x1)

opts :

(structure, optional) Computation options (see above). Default: empty structure.

mu :

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

result :

Orbital elements time derivatives [m/s, rad/s] or increments [m, rad]. (6xN)

Authors

Bibliography

Examples

kep = [10000.e3; 0.2; 1; 0; 0; 0]; // m, rad
acc = [0; 1; 0] * 1.e-4; // m/s^2
acc_frame = "aps";
apsis = "per"; // around periapsis
alpha = %pi/4; // => between -alpha and alpha (true anomaly)
dkepdt = CL_man_lowThrustApsKep(kep, acc, acc_frame, alpha, apsis, "dkepdt")

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