Code covered by the BSD License
- befunc (x)
bi-elliptic radius objective function
astrodynamic and utility constants
- orb2eci(mu, oev)
convert classical orbital elements to eci state vector
- pvector (ri, vi, x)
primer vector and derivative magnitudes
- pviniz (tof, r1, v1, dv1,...primer vector initialization
- stm2 (mu, tau, ri, vi)
two body state transition matrix
- twobody2 (mu, tau, ri, vi)solve the two body initial value problem
View all files
Bi-elliptic Transfer Between Coplanar Circular Orbits
02 Nov 2012
(Updated 09 Jul 2013)
Bi-elliptic orbital transfer between two coplanar circular Earth orbits.
Watch this File
This is a MATLAB script that can be used to determine the characteristics of a three impulse bi-elliptic transfer between two coplanar circular orbits. The impulsive assumption means that the velocity, but not the position, of the space vehicle is changed instantaneously.
| Required Products
MATLAB 7.14 (R2012a)
|09 Jul 2013
Added three-dimensional trajectory graphics and a graphical primer vector analysis. Updated PDF document to reflect these new features.