nplnt  = 1,...,30 with ncentr.lt.0  integrated body is a planet
or asteroid orbiting the sun
nplnt  =11,...,30 with ncentr.gt.0  integrated body is a natural
satellite
nplnt=31,32,...  integrated body is an artificial space probe
(this routine would only be called in one of these cases)

ncentr= planet number of central body
0=sun     1=mercury   2=venus
3=earth   4=mars      5=jupiter
6=saturn  7=uranus    8=neptune
9=pluto   10=moon     negative=sun

for i=1-6 we have in this routine
sbcor(i) =  coordinates of integrated body relative to central body
bcor(i)  =  coordinates of integrated body relative to the sun
ccor(i)  =  coordinates of central body relative to the sun
for i=1-3 we have
pccor(i,l)= coordinates of body l relative to central body for
kp(30+l).ge.0 and l.ne.ncentr and l.ne.nplnt (l=1,...,10)
pbcor(i,l)= coordinates of body l relative to integrated body for
kp(30+l).ge.0 and l.ne.ncentr and l.ne.nplnt (l=1,...,10)
l=3 denotes earth-moon barycenter if kp(40).lt.0 and ncentr.ne.10
l=3 denotes earth if kp(40).ge.0 or ncentr.eq.10
mass1(l) =  (mass of body l)/(mass of sun), l=1,...,10
mass(3)  =  (mass of earth+moon)/(mass of sun)
mass(10) =  (mass of moon)/(mass of earth+moon)
masse =     (mass of earth)/(mass of earth+moon)
massp =     (mass of integrated body)/(mass of central body)

rsb2 = sbcor(1)**2+sbcor(2)**2+sbcor(3)**2
rsb  = sqrt(rsb2)
rsb3 = rsb2*rsb
similar definitions for rb,rc,rpc(l),rpb(l) quantities
kpb  = logical flags to control whether pbcor,pccor are calculated