Find the position and velocity if the planet given orbit and elements.
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Given
k = .01720209895  gravity constant 
q = .4255 AU perihelion    
e = .2 eccentricity
t = 40 days past perihelion
i = 72 degrees inclination
w = 105 degrees argument of perigee
o = 293 degrees longitude of ascending node
ie = 23.441028 degrees tilt of earth

Use data from orbit-1
p = q*(1+e) =.5106
M = 1.77389155705 mean anomaly
EE=  1.95900897924 radians

The first derinitive of each is 
d(th)/dt = k*SQRT[p]/r^2 = dth =.037550416193 radians/day
dr/dr = k*e* Sin[th] /SQRT[p] = drt = 4.05910212681E-3 AU/day

r * Sin[th] = a * ( Cos[EE] - e )
r * Cos[th] = a * (SQRT[ 1 - e^2 ]) * Sin[EE]

r=.5721416260 AU and th=122.535231561 degrees.

U = th + w = 227.535231561 degrees

x1 = r * Cos[U] = -0.386273822557 AU
y  = r * Sin[U] = -0.422064656473 AU

dx1 = drt * Cos[U] - r * Sin[U] * dth AU/day
dy  = drt * Sin[U] + r * Cos[U] * dth AU/day

y1 = y * Cos[I] = -0.130425151575 AU
z2 = y * Sin[I] = -0.401407341836 AU

dz2 = dy * Sin[i] = -1.41790996032E-2 AU/day
dy1 = dy * Cos[i] = -5.40752314709E-3 AU/day

x3 = x1 * Cos[O] - y1 * Sin[O] = -0.27098619163 AU
y2 = y1 * Cos[O] + x1 * Sin[O] = 0.304605761767 AU


dx3 = dx1 * Cos[O] - dy1 * Sin[O] = 1.4415181119E-4 AU/day
dy2 = dy1 * Cos[O] + dx1 * Sin[O] = -1.41790996032E-2 AU/day


y3 = y2 * Cos[IE] - z2 * Sin[IE] =  -0.27098619163 AU
z3 = z2 * Cos[IE] + y2 * Sin[IE] =  -0.247105509699 AU

dy3 = dy2 * Cos[IE] - dz2 * Sin[IE] =  -6.38837169935E-3 AU/day
dz3 = dz2 * Cos[IE] + dy2 * Sin[IE] =  -2.09096438056E-3 AU/day