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CelestLab >> Interplanetary > CL_ip_insertionDv

CL_ip_insertionDv

Delta-V needed for an insertion around a planet

Calling Sequence

[dv, ecc, tanoe] = CL_ip_insertionDv(vinf, rph, sma [, tanoh, mu])

Description

Parameters

vinf:

Velocity on hyperbolic orbit at infinity [m/s]. (1xN)

rph:

Periapsis radius of hyperbolic orbit [m]. (1xN)

sma:

Semi-major axis of target (elliptical) orbit [m]. (1xN)

tanoh:

(optional) True anomaly of the maneuvre (on the hyperbolic orbit) [rad]. Default value is 0. (1xN)

mu:

(optional) gravitational constant [m3/s2]. Default value is %CL_mu.

dv:

Norm of the delta-v. (1xN)

ecc:

Eccentricity of the final (elliptical) orbit. (1xN)

tanoe:

True anomaly on the elliptical orbit at the time of the maneuver [rad]. (1xN)

Authors

Examples

// Insertion around Earth:
vinf = [5 , 6] * 1.e3;
rph = [%CL_eqRad+250.e3 , %CL_eqRad+500.e3];
sma = [%CL_eqRad+350.e3 , %CL_eqRad+700.e3];
[dv, ecc, tanoe] = CL_ip_insertionDv(vinf,rph, sma)

// Insertion around Mars:
global %CL_planetC;
vinf = [5 , 6] * 1.e3;
eqrad_mars = %CL_planetC.mars.eqRad;
rph = [eqrad_mars+250.e3 , eqrad_mars+500.e3];
sma = [eqrad_mars+350.e3 , eqrad_mars+700.e3];
tanoh = [0, 0.1]; // radians
mu_mars = %CL_planetC.mars.mu;
[dv,ecc,tanoe] = CL_ip_insertionDv(vinf,rph,sma,tanoh,mu_mars)
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