def Geodesic_script():
# setup the initial conditions
geo = Geodesic()
# assume initially a vertical launch from 5 degrees latitude
radiusE = geo.oblateRadius(5) * 1000
# launch vehicle
lv = LaunchVehicle()
# standard atmosphere (1976) data
atm = Atmosphere()
[altList, tempList, pressureList, densityList, asoundList] = atm.stdAtm()
Area = pow(lv.Rcross,2)*pi
k = 9.81*pow(geo.a * 1000,2)
# flight path angle (deg)
fp = pi/2
# velocity magnitude /speed (m/s)
vc = 0
# altitude above geodesic (m)
alt = 0
nu = 0
# speed of sound (m/s)
a = np.interp(alt,altList,asoundList)
# atmospheric density (kg/m^3)
rho = np.interp(alt,altList,densityList)
r = radiusE + alt
r2 = pow(r,2)
g = k/r2
m = 2300000
T = 34020000
Isp = 400
theta = 0
Mach = vc/a
D = 0.5 * lv.getCd(Mach) * Area * rho * pow(vc,2)
params = (k, radiusE, altList, asoundList, densityList, Area, lv, Isp, T, theta)
x0 = [r,m,nu,fp,vc]
return x0, params
