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CelestLab >> Interplanetary > CL_ip_escapeDv

CL_ip_escapeDv

Delta-V needed to escape from a planet

Calling Sequence

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

Description

Parameters

sma:

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

ecc:

Eccentricity of initial orbit. (1xN)

vinf:

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

tanoe:

(optional) True anomaly of maneuver [rad]. Default value is 0. (1xN)

mu:

(optional) Gravitational constant of the planet considered [m3/s2]. Default value is %CL_mu.

dv:

Norm of the delta-v. (1xN)

rph:

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

tanoh:

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

Authors

Examples

// Escape a LEO (circular) orbit :
sma = [%CL_eqRad+350.e3 , %CL_eqRad+700.e3];
ecc = zeros(sma);
vinf = [5 , 6] * 1.e3;
[dv, rph, tanoh] = CL_ip_escapeDv(sma, ecc, vinf)

// Escape an orbit around Mars :
global %CL_planetC;
eqrad_mars = %CL_planetC.mars.eqRad;
sma = [eqrad_mars+350.e3 , eqrad_mars+700.e3];
ecc = [0.1 , 0.05];
vinf = [5 , 6] * 1.e3;
tanoe = [0, 0.1]; // radians
mu_mars = %CL_planetC.mars.mu;
[dv,rph,tanoh] = CL_ip_escapeDv(sma,ecc,vinf,tanoe,mu_mars)
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