Name

CL_man_sma — Delta V for an orbit shape modification (semi major axis)

Calling Sequence

   [dv,anv] = CL_man_sma(ai,ei,af[,posman[,mu]])
   
   

Description

  • This function computes delta-v requirement for an orbit shape modification. Maneuver consists to modify the periapsis or apoapsis radius without modification of its orientation. A modification of semi major axis and eccentricity is obtained; and the maneuver can be performed at periapsis or at apoapsis.

    Output dv is the impulsion required given in spheric coordinates in QSW frame: first parameter lambda is the in plane component (pi ~= towards planet and pi/2 = along velocity) second parameter phi is the out of plane component, positive towards the kinetic moment, third parameter is the norm

    anv is the true anomaly of maneuver execution point in radians.

  • Last update : 21/5/2008

Parameters

ai :

initial orbit semi major axis [m] (1xN)

ei:

initial orbit eccentricity (1xN)

af :

semi major axis of desired orbit [m] (1xN)

posman:

(optional) flag to indicate maneuver execution point (0->periapsis, 1->apoapsis; default is 0) (1xN)

mu :

(optionnal) geocentric gravitational constant. [m^3/s^2] (default value is %CL_mu)

dv :

delta_v required in spheric coordinates in QSW frame [lambda;phi;|dv|] [rad,rad,m/s] (3xN)

anv:

true anomaly of maneuver execution point [rad] (1xN)

Authors

CNES - DCT/SB

See also

CL_man_biElliptic, CL_man_hohmann, CL_man_hohmannG

Examples

ai = 7200.e3;
af = 7000.e3;
ei = 0.1;
[dv,anv] = CL_man_sma(ai,ei,af)
// Check results :
kep = [ai ; ei ; %pi/2 ; 0 ; 0 ; anv];
kep1 = CL_man_applyDv(kep,dv)