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celestlab >> Interplanetary > CL_ip_flybyOrbits

CL_ip_flybyOrbits

Arrival or departure orbits knowing inclination (hyperbolic orbits)

Calling Sequence

[result1, result2, ...] = CL_ip_flybyOrbits(vinf, rp, inc, branch [[, poldir, output, mu]])

Description

Parameters

vinf:

Arrival or departure excess velocity vector [m/s]. (3x1 or 3xN)

rp:

Radius at periapsis of hyperbolic orbit [m]. (1x1 or 1xN)

inc:

Inclination of hyperbolic orbit [rad]. (1x1 or 1xN)

branch:

(string) "a": arrival, "d": departure (1x1)

poldir:

(optional) Direction of polar axis. Default value is [0; 0; 1]. (3x1 or 3xN)

output:

(string, optional) Names of output arguments, see above for details. Default value is ["kep1", "kep2"]. (1x1)

mu:

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

result1, result2, ...:

Computed quantities [m, m/s, rad]. (6xN or 3xN depending on computed quantity)

Authors

See also

Examples

// Notes:
// - The planet is the Earth
// - The implicit frame is an equatorial frame
vinf = [-3000; 200; 500];
rp = 10000.e3;
inc = 60 * %pi / 180;
branch = "a"; // arrival

// Results
[kep1, kep2] = CL_ip_flybyOrbits(vinf, rp, inc, branch);

// Check results
kep1(1) * (kep1(2) - 1) - rp  // => 0
kep2(1) * (kep2(2) - 1) - rp  // => 0
kep1(3) - inc  // => 0
kep2(3) - inc  // => 0

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