|
SUPPORT SITE |
|
|
|
SUPPORT SITE |
|
Path: Orbit/OrbitManeuver
% Compute the delta V required to change perigee
--------------------------------------------------------------------------
Form:
b = ChangePerigee( d )
--------------------------------------------------------------------------
------
Inputs
------
d (:) Input data structure
.a (1,1) Semi-major axis
.e (1,1) Eccentricity of initial orbit
.rP (1,:) New Perigee
.mu (1,1) Mu
-------
Outputs
-------
b (:) Output data structure
.dV (1,:) Datastructure
.e (1,:) New eccentricity
.a (1,:) New semi-major axis
.vA (1,:) Apogee velocity
--------------------------------------------------------------------------
Common: Graphics/Plot2D
Back to the Orbit Module page