Name

CL_ex_kepler — Keplerian orbit extrapolation

Calling Sequence

   [eph]=CL_ex_kepler(t1,kep,t2[,mu])
   
   

Description

  • Given a set of keplerian parameters (kep) at date t1, this function computes parameters at date t2. In fact, it calculates mean anomaly at dates t2 using orbit's mean motion. Other parameters are constant.

    Warning when using vectorized calculation: size of kep or size of t2 (M or N) must be 1.

  • Last update : 7/3/2008

Parameters

t1:

CNES julian day + ut/24 (ut in [h])

kep:

keplerian parameters at date t1 [a,e,i,pom,gom,M]' (6xN)

t2:

extrapolation date, CNES julian days + ut/24 (ut in [h]) (6xM)

mu :

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

eph:

extrapolated ephemerides, date + keplerian parameters [t,a,e,i,pom,gom,M]' (7 x max(N,M))

Authors

CNES - DCT/SB

Bibliography

Mecanique spatiale, CNES - Cepadues 1995, Tome I

See also

CL_ex_lyddane, CL_oe_kep2car, CL_kp_M2E, CL_kp_E2v

Examples

t1 = 21482.125
kep = [24464560,0.7311,0.122138,3.10686,1.00681,0.048363]'
T = CL_kp_orbitalPeriod(kep(1))  //orbital period in seconds
T = T/86400 //orbital period in days
eph = CL_ex_kepler(t1,kep,[t1 t1+T/4 t1+T/2 t1+T])