CL_oe_convert

Description

• Converts orbital elements from a given type to orbital elements of another type.

  Available types of orbital elements are: "kep", "cir", "cireq", "equin" and "pv".

  Orbital elements of type "pv" are position and velocity in a 6xN vector ([pos;vel])

  See Orbital elements for more details on orbital elements.

• Notes:

  - mu is only needed when converting to or from "pv" orbital elements.

  - Only the conversions available in functions CL_oe_xxx are available. (i.e conversion to and from keplerian orbital element or cartesian orbital elements)

Parameters

type_oe1:

(string) Type of input orbital elements ("kep", "cir", "cireq", "equin" or "pv") (1x1)

type_oe2:

(string) Type of output orbital elements ("kep", "cir", "cireq", "equin" or "pv") (1x1)

oe1:

Input orbital elements (6xN)

oe2:

Output orbital elements (6xN)

mu:

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

jacob:

(optional) Transformation jacobian (See Orbital elements for more details) (6x6xN)

Authors

• CNES - DCT/SB

Examples

// Example 1 pos = [7000.e3;1000.e3;-500.e3]; vel = [1.e3;2.e3;7e3]; kep = CL_oe_convert("pv","kep",[pos;vel]); // Example 2 pos = [7000.e3;1000.e3;-500.e3]; vel = [1.e3;2.e3;7e3]; [kep,jacob1] = CL_oe_convert("pv","kep",[pos;vel]); [pv2,jacob2] = CL_oe_convert("kep","pv",kep); pv2 - [pos;vel] // zero jacob2 * jacob1 // identity