Ephemerides improvement for the first 4 asteroids.
&NMLST1
EXTPRC= 0, $ Use hardware extended precision
ICT(1)= 10,
ICT(3)= 1,
ICT(4)= 1, $ Compute partial derivatives
ICT(5)= -1, $ Do not used saved normal equations
ICT(9)= 0,
ICT(10)= -2, ICT(11)= -2,
ICT(12)= 2, $ prediction or harmonic analysis
ICT(34)= 3,
ICT(39)= 1,
ICT(50)= 1, $ USE BROWN MEAN MOON IF NO IPERT
ICT(80)= 0,
JCT(13)= 1, $ Use J2000.0 coordinates.
JCT(33)= -1, $ Use USNO UT1 and wobble
JCT(27)= 1, $ Use * commands
JCT(28)= 7,
MASS(1)= 6023600.D0, $ Use DE200 masses for the planets
MASS(2)= 408523.5D0,
MASS(3)= 328900.550000000047D0,
MASS(4)= 3098710.D0,
MASS(5)= 1047.35001090551827D0,
MASS(6)= 3497.99999984177066D0,
MASS(7)= 22960.0000007059389D0,
MASS(8)= 19314.0002382557432D0,
MASS(9)= 130000000.238686755D0,
MASS(10)= 0.012150581D0,
MASS(11)= 2.239D9,
MASS(12)= 9.247D9,
MASS(13)= 8.7D10,
MASS(14)= 7.253D9,
MASS(17)= 1.849D11,
AULTSC= 499.0047837D0, $ AU in light seconds
ECINC= 23.439281083D0, $ Use DE118 Obliquity
PRMTER(47)= 0.0D0, $ RA OF ASC. NODE OF BELT
PRMTER(48)= 23.4433D0, $ INCLINATION OF BELT
PRMTER(49)= 2.9D0, $ DISTANCE OF BELT FROM SUN
PRMTER(50)= 8.773725302941010D-10, $ MASS OF BELT
PRMTER(81)= 0.0D0,
MDSTSC= 0., $ MOON TAPE DISTANCE UNIT IN AU
NBODY= 0, IPERT= 10,
NUMOBT= 1,
IOBS = 30,
IOBS1= 14, IOBS2= 15,
$ EPS(3)= 100,
$ EPS(4)= 100,
LPRM(1)= 11, LPRM(2)= 12, LPRM(3)= 14,
*OBJECT EARTH-ROTATION
CON(22)= 5029.0966,
CON(23)= 84381.4119,
*OBJECT 11
NAME= ' CERES ',
INCND= 0, ITAPE= 31, NCENTR= 0, JTYPE=6,
A=2.767121817D0, E=0.07749262D0, INC=27.116375D0,
ASC= 23.471566D0, PER= 133.40890D0, ANOM=2.08129D0,
JD1=2378801, JD2=2450001, JD0=2444801,
K(31)=1, K(32)=1, K(33)=1, K(34)=1, K(35)=1, K(36)=1, K(37)=1,
K(38)= 1, K(39)= 1, K(40)= 1, K(41)= 1, K(42)= 1,
K(43)= 1, K(44)= 1,
K(61)= 1 $ Include GR
K(87)= 2, INT= 2, $ INTERVALS
K(88)= 2, K(89)= 6, $ ADAMS-MOULTON, 7 TERMS
K(91)= -3, K(92)= -6, EPS(3)=1E-9 $ STARTING INTERVALS
K(98)= -500, K(99)= 0, K(100)= -1, $ PRINT + TAPE; ORDI-
NARY EQNS OF MOTION
KI= 1, 1, 1, 1, 1, 1, 1, 12, 13, 14,
L= 1, 1, 1, 1, 1, 1,
*OBJECT 12
NAME= ' PALLAS ',
INCND= 0, ITAPE= 32, NCENTR= 0, JTYPE=6,
A= 2.771672932D0, E= 0.23398027D0, INC= 11.809637D0,
ASC= 161.02570D0, PER= 322.78775D0, ANOM= 298.543057D0,
JD1= 2379251, JD2= 2450001, JD0= 2449601,
K(31)= 1, K(32)= 1, K(33)= 1, K(34)= 1, K(35)= 1,
K(36)= 1, K(37)= 1,
K(38)= 1, K(39)= 1, K(40)= 1, K(41)= 1, K(42)= 1,
K(43)= 1, K(44)= 1,
K(61)= 1, $ Include GR
K(87)= 2, INT= 2, $ INTERVALS
K(88)= 2, K(89)= 6, $ ADAMS-MOULTON, 7 TERMS
K(91)= -3, K(92)= -6, EPS(3)= 1E-9 $ STARTING INTERVALS
K(98)= -500, K(99)= 0, K(100)= -1, $ PRINT + TAPE; ORDI-
NARY EQNS OF MOTION
KI= 1, 1, 1, 1, 1, 1, 1, 11,
L= 1, 1, 1, 1, 1, 1,
*OBJECT 13
NAME= ' JUNO ',
INCND= 0, ITAPE= 33, NCENTR= 0, JTYPE= 6,
A= 2.670660949D0, E= .25626106D0, ANOM= 156.782239D0,
INC= 10.814499D0, PER= 46.75209D0, ASC= 11.27760D0,
JD1= 2380151, JD2= 2450001, JD0= 2444801,
K(31)= 1, K(32)= 1, K(33)= 1, K(34)= 1, K(35)= 1, K(36)= 1,
K(37)= 1,
K(38)= 1, K(39)= 1, K(40)= 1, K(41)= 1, K(42)= 1, K(43)= 1,
K(44)= 1,
K(61)= -1,
K(87)= 4, INT= 4, $ Intervals
K(88)= 2, K(89)= 6, $ Adams-Moulton integra-
tor, 7 terms
K(91)= -3, K(92)= -6, EPS(3)= 1E-9, $ Starting intervals
K(98)= -500, K(99)= 0, K(100)= -1, $ Print & tape, ordi-
nary eqs. of motion
KI= 1, 1, 1, 1, 1, 1, 1,
L= 1, 1, 1, 1, 1, 1,
*OBJECT 14
NAME= ' VESTA ',
INCND= 0, ITAPE= 34, NCENTR= 0, JTYPE= 6,
A= 2.362114063D0, E= 0.08961581D0, INC= 22.717580D0,
ASC= 18.187358D0, PER= 237.48420D0, ANOM= 308.51911D0,
JD1= 2381051, JD2= 2450001, JD0= 2444801,
K(31)= 1, K(32)= 1, K(33)= 1, K(34)= 1, K(35)= 1,
K(36)= 1, K(37)= 1,
K(38)= 1, K(39)= 1, K(40)= 1, K(41)= 1, K(42)= 1,
K(43)= 1, K(44)= 1,
K(61)= 1, $ Include General Relativity
K(87)= 2, INT= 2, $ INTERVALS
K(88)= 2, K(89)= 6, $ ADAMS-MOULTON METHOD, 7
TERMS
K(91)= -3, K(92)= -6, EPS(3)= 1E-9 $ STARTING INTERVALS
K(98)= -500, K(99)= 0, K(100)= -1, $ PRINT + TAPE; ORDI-
NARY EQNS OF MOTION
KI= 1, 1, 1, 1, 1, 1, 1, 11,
L= 1, 1, 1, 1, 1, 1,
*OBJECT 27
NAME= ' Arete ',
INCND= 0, ITAPE= 37, NCENTR= 0, JTYPE= 6,
A= 2.73942088D0, E= 0.1630220D0, INC= 26.08786D0,
ASC= 20.12111D0, PER= 310.03548D0, ANOM= 168.77030D0,
JD1= 2407351, JD2= 2450002, JD0= 2450001,
K(31)=1, K(32)=1, K(33)=1, K(34)=1, K(35)=1, K(36)=1,
K(37)=1,
K(38)= 1, K(39)= 1, K(40)= 1, K(41)= 1, K(42)= 1,
K(43)= 1, K(44)= 1,
K(61)= 1, $ Include GR
K(87)= 2, INT= 2, $ INTERVALS
K(88)= 2, K(89)= 6, $ ADAMS-MOULTON, 7 TERMS
K(91)= -3, K(92)= -6, EPS(3)= 1E-9 $ STARTING INTERVALS
K(98)= -500, K(99)= 0, K(100)= -1, $ PRINT + TAPE; ORDI-
NARY EQNS OF MOTION
KI= 1, 1, 1, 1, 1, 1, 1, 14,
L= 1, 1, 1, 1, 1, 1,
*SITES
APPENDIX: TYPICAL
PEP
INPUT
As an example of the old-style program interface, following is an excerpt
taken from a typical
PEP
input file. Compare to Figure 7. This particular
file (courtesy James Hilton) was used in the generation of ephemerides for
the four largest asteroids for use in the Astronomical Almanac for the year
2000.
which serves also to provide further insight into how a modern, high-
precision solar system ephemeris can be generated, as well an indication as
to some of the complexity of such an undertaking. It is relatively simple
and straightforward to write a program that makes low-precision predic-
tions. However, generation of a high-precision ephemeris is another mat-
ter altogether.
MURISON: MODELING PLANETARY MOTIONS
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