Repatch (from linux) of OSX IRAF

1 files changed, 168 insertions, 0 deletions

diff --git a/math/slalib/pv2ue.f b/math/slalib/pv2ue.f
new file mode 100644
index 00000000..a2a686ab
--- /dev/null
+++ b/math/slalib/pv2ue.f
@@ -0,0 +1,168 @@
+      SUBROUTINE slPVUE (PV, DATE, PMASS, U, JSTAT)
+*+
+*     - - - - - -
+*      P V U E
+*     - - - - - -
+*
+*  Construct a universal element set based on an instantaneous position
+*  and velocity.
+*
+*  Given:
+*     PV        d(6)   heliocentric x,y,z,xdot,ydot,zdot of date,
+*                      (AU,AU/s; Note 1)
+*     DATE      d      date (TT Modified Julian Date = JD-2400000.5)
+*     PMASS     d      mass of the planet (Sun=1; Note 2)
+*
+*  Returned:
+*     U         d(13)  universal orbital elements (Note 3)
+*
+*                 (1)  combined mass (M+m)
+*                 (2)  total energy of the orbit (alpha)
+*                 (3)  reference (osculating) epoch (t0)
+*               (4-6)  position at reference epoch (r0)
+*               (7-9)  velocity at reference epoch (v0)
+*                (10)  heliocentric distance at reference epoch
+*                (11)  r0.v0
+*                (12)  date (t)
+*                (13)  universal eccentric anomaly (psi) of date, approx
+*
+*     JSTAT     i      status:  0 = OK
+*                              -1 = illegal PMASS
+*                              -2 = too close to Sun
+*                              -3 = too slow
+*
+*  Notes
+*
+*  1  The PV 6-vector can be with respect to any chosen inertial frame,
+*     and the resulting universal-element set will be with respect to
+*     the same frame.  A common choice will be mean equator and ecliptic
+*     of epoch J2000.
+*
+*  2  The mass, PMASS, is important only for the larger planets.  For
+*     most purposes (e.g. asteroids) use 0D0.  Values less than zero
+*     are illegal.
+*
+*  3  The "universal" elements are those which define the orbit for the
+*     purposes of the method of universal variables (see reference).
+*     They consist of the combined mass of the two bodies, an epoch,
+*     and the position and velocity vectors (arbitrary reference frame)
+*     at that epoch.  The parameter set used here includes also various
+*     quantities that can, in fact, be derived from the other
+*     information.  This approach is taken to avoiding unnecessary
+*     computation and loss of accuracy.  The supplementary quantities
+*     are (i) alpha, which is proportional to the total energy of the
+*     orbit, (ii) the heliocentric distance at epoch, (iii) the
+*     outwards component of the velocity at the given epoch, (iv) an
+*     estimate of psi, the "universal eccentric anomaly" at a given
+*     date and (v) that date.
+*
+*  Reference:  Everhart, E. & Pitkin, E.T., Am.J.Phys. 51, 712, 1983.
+*
+*  P.T.Wallace   Starlink   18 March 1999
+*
+*  Copyright (C) 1999 Rutherford Appleton Laboratory
+*
+*  License:
+*    This program is free software; you can redistribute it and/or modify
+*    it under the terms of the GNU General Public License as published by
+*    the Free Software Foundation; either version 2 of the License, or
+*    (at your option) any later version.
+*
+*    This program is distributed in the hope that it will be useful,
+*    but WITHOUT ANY WARRANTY; without even the implied warranty of
+*    MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
+*    GNU General Public License for more details.
+*
+*    You should have received a copy of the GNU General Public License
+*    along with this program (see SLA_CONDITIONS); if not, write to the
+*    Free Software Foundation, Inc., 51 Franklin Street, Fifth Floor,
+*    Boston, MA  02110-1301  USA
+*
+*  Copyright (C) 1995 Association of Universities for Research in Astronomy Inc.
+*-
+
+      IMPLICIT NONE
+
+      DOUBLE PRECISION PV(6),DATE,PMASS,U(13)
+      INTEGER JSTAT
+
+*  Gaussian gravitational constant (exact)
+      DOUBLE PRECISION GCON
+      PARAMETER (GCON=0.01720209895D0)
+
+*  Canonical days to seconds
+      DOUBLE PRECISION CD2S
+      PARAMETER (CD2S=GCON/86400D0)
+
+*  Minimum allowed distance (AU) and speed (AU per canonical day)
+      DOUBLE PRECISION RMIN,VMIN
+      PARAMETER (RMIN=1D-3,VMIN=1D-3)
+
+      DOUBLE PRECISION T0,CM,X,Y,Z,XD,YD,ZD,R,V2,V,ALPHA,RDV
+
+
+*  Reference epoch.
+      T0 = DATE
+
+*  Combined mass (mu=M+m).
+      IF (PMASS.LT.0D0) GO TO 9010
+      CM = 1D0+PMASS
+
+*  Unpack the state vector, expressing velocity in AU per canonical day.
+      X = PV(1)
+      Y = PV(2)
+      Z = PV(3)
+      XD = PV(4)/CD2S
+      YD = PV(5)/CD2S
+      ZD = PV(6)/CD2S
+
+*  Heliocentric distance, and speed.
+      R = SQRT(X*X+Y*Y+Z*Z)
+      V2 = XD*XD+YD*YD+ZD*ZD
+      V = SQRT(V2)
+
+*  Reject unreasonably small values.
+      IF (R.LT.RMIN) GO TO 9020
+      IF (V.LT.VMIN) GO TO 9030
+
+*  Total energy of the orbit.
+      ALPHA = V2-2D0*CM/R
+
+*  Outward component of velocity.
+      RDV = X*XD+Y*YD+Z*ZD
+
+*  Construct the universal-element set.
+      U(1) = CM
+      U(2) = ALPHA
+      U(3) = T0
+      U(4) = X
+      U(5) = Y
+      U(6) = Z
+      U(7) = XD
+      U(8) = YD
+      U(9) = ZD
+      U(10) = R
+      U(11) = RDV
+      U(12) = T0
+      U(13) = 0D0
+
+*  Exit.
+      JSTAT = 0
+      GO TO 9999
+
+*  Negative PMASS.
+ 9010 CONTINUE
+      JSTAT = -1
+      GO TO 9999
+
+*  Too close.
+ 9020 CONTINUE
+      JSTAT = -2
+      GO TO 9999
+
+*  Too slow.
+ 9030 CONTINUE
+      JSTAT = -3
+
+ 9999 CONTINUE
+      END