CCSD3ZF0000100000001CCSD3VS00002MRK**001
VOL_IDENT: USA_NASA_NSSD_P10Z_0002
VOL_CREATION_DATE: 1995-07-11
MEDIUM_DESCRIPTION: 1/2-inch, 9-track, 6250 bpi magnetic tape
TECHNICAL_CONTACT: David W. Lozier
NASA Ames Research Center (Mail Stop 244-14)
Moffett Field, CA 94035
Electronic Mail: David_Lozier@QMGATE.ARC.NASA.GOV
Telephone: 415-604-3147
PREV_VOLS: USA_NASA_NSSD_P10Z_0001
CCSD$$MARKERMRK**001CCSD3SS00002MRK**002
DATA_SET_NAME: PIONEER 10 TRAJECTORY EPHEMERIS ARCHIVE (Extension to
2000)
DATA_SOURCE: Pioneer 10 trajectory data were generated using the
Jet Propulsion Laboratory's (JPL) "Double Precision
Trajectory" (DPTRAJ) computer program, an element
of the JPL Navigation Software System, reference (A).
DPTRAJ creates a spacecraft ephemeris by integrating
the equations of motion for a full set of acceleration
models. For the Pioneer 10 trajectory ephemeris, DPTRAJ
integration was limited to the N-body gravitational
terms (planets, Sun and Moon) with Earth oblateness,
Jupiter oblateness (J2 and J4), and a simple solar
pressure model included.
Initial conditions for the DPTRAJ runs were obtained
from various Orbit Determination (OD) solutions
performed during the mission. A set of seven spacecraft
initial state vectors (position, velocity and epoch)
was compiled to cover all phases of the mission from
launch to 1 January 1990 (Volume
USA_NASA_NSSD_P10Z_0001).
(1) Launch to second midcourse maneuver
(2) Second midcourse maneuver to first "IO"
targeting maneuver
(3) First "IO" targeting maneuver to
second "IO" targeting maneuver
(4) Second "IO" targeting maneuver to
Jupiter phase
(5) Jupiter encounter OD
(6) Jupiter encounter to 1983 solar escape
(7) 1983 solar escape to 1 January 1990
A complete set of input for the seven DPTRAJ runs is
provided in reference (B).
This volume extends the Pioneer 10 trajectory from
1 January 1990 to 1 January 2000.
The DPTRAJ input for volume USA_NASA_NSSD_P10Z_0002 is
provided in reference (D).
SCIENTIFIC_CONTACT: none
SPACECRAFT_CHARACTERISTICS: Pioneer 10 is a 550 pound spin stabilized
spacecraft powered by four RTGs. Communications with
the Earth is provided by a 9 ft. diameter parabolic high
gain antenna located on the spin axis of the spacecraft.
Periodic precession maneuvers are performed to maintain
Earth pointing of the high gain antenna. The spacecraft
possesses a complete complement of particles and fields
instruments as well as a UV spectrometer, IR radiometer
and an imaging device (IPP). The primary mission
objective was the exploration of the plant Jupiter with
a secondary objective of exploring the interplanetary
environment between Earth and Jupiter and beyond
Jupiter. Pioneer 10 was launched on March 3, 1972 and
encountered Jupiter on December 4, 1973. After passing
Jupiter, Pioneer 10's trajectory became escape with
respect to the Sun and is moving away from the Sun at
about 2.4 AU per year.
INSTRUMENT_ATTRIBUTES: not applicable
DATA_SET_PARAMETERS: Following is a description of the seventy-seven
trajectory parameters found in each output record.
Julian Date of reference epoch = 2433282.5 (J1950.0)
Body-1 is JUPITER, Body-2 is SATURN
MNEMONIC DESCRIPTION
ETSPRF Time of record in Ephemeris Time (ET)
seconds past the reference epoch
JULDAT Julian date (days)
DOYDAT Days past the start of the year
TFLANC Time from launch (sec)
Launch time was 01:49:03.6 UTC
3 March 1972
TFINJE Time from injection (sec)
Injection epoch is 02:03:18 UTC
3 March 1972
ETMUTC ET - Universal Time Coordinated (UTC)
(sec)
DEVENT Flag which gives the type of event
which caused the record to be written:
= 0.D0 for an absolute or TDT save tape
event
= 1.D0 for some other type of TWIST
geometric event
The next 13 parameters are defined in a geocentric
space-fixed coordinate system referenced to Earth's true
equinox and equator plane of date. The X-axis is in
the direction of the Vernal Equinox, the Z-axis is
normal to the equatorial plane and the Y-axis lies in
the equatorial plane completing the right-handed
coordinate sytem.
RANGRP Range rate of spacecraft (rate of
change of REARPR below, km/sec)
MAGVEL Magnitude of spacecraft inertial
velocity vector (km/sec)
INPATH Inertial path angle (deg)
INAZIM Inertial azimuth angle (deg)
REARPR Earth-spacecraft range (km)
DECPRO Declination of spacecraft (deg)
RTASCP Right ascension of spacecraft (deg)
REARSU Earth-Sun range (km)
DECSUN Declination of Sun (deg)
RTASCS Right ascension of Sun (deg)
REARMO Earth-Moon range (km)
DECMOO Declination of Moon (deg)
RTASCM Right ascension of Moon (deg)
The next 7 parameters are defined in a heliocentric
space-fixed coordinate system referenced to Earth's true
equinox and orbit plane (Ecliptic) of date. The X-axis
is in the direction of the Vernal Equinox, the Z-axis
is normal to the orbit plane and the Y-axis lies in the
orbit plane completing the right-handed coordinate
system.
HRANGP Sun-spacecraft range (km)
HMAGVP Magnitude of spacecraft inertial
velocity vector (km/sec)
HINPTH Inertial path angle (deg)
CELLTP Celestial latitude of spacecraft
(deg)
CELLNP Celestial longitude of spacecraft
(deg)
CELLTE Celestial latitude of Earth (deg)
CELLNE Celestial longitude of Earth (deg)
The next 5 parameters are defined in a heliocentric
rotating coordinate system referenced to the direction
of Earth and Earth's true orbit of date. In the
Sun-Earth-line coordinate system the X-axis points to
the Earth, the Z-axis is normal to the Earth's orbit
plane (Ecliptic) and the Y-axis lies in the orbit plane
completing the right-handed coordinate sytem.
XSCSEL X-component of spacecraft position in
Sun-Earth-line coordinate system (km)
YSCSEL Y-component of spacecraft position in
Sun-Earth-line coordinate system (km)
ZSCSEL Z-component of spacecraft position in
Sun-Earth-line coordinate system (km)
SPSEXY Projection of Sun-spacecraft range
vector into the XY-plane of the
Sun-Earth-line coordinate system (km)
LNPSEL Longitude of spacecraft in
Sun-Earth-line coordinate system (deg)
ICBODY Integration central body number.
= 1 for SUN
= 3 for EARTH
= 5 for JUPITER
FERPFL FERP flag for equinox and reference
plane for the next 28 parameters:
= 12 is the Earth's mean equinox and
orbit of B1950.0
The next 28 parameters are defined in a space-fixed
coordinate system referenced to the equinox and plane
specified above in FERPFL. The X-axis is in the
direction of the mean 1950.0 Vernal Equinox, the Z-axis
is normal to the mean 1950.0 Earth's orbit plane
(Ecliptic) and the Y-axis lies in the orbit plane
completing the right-handed coordinate sytem.
XPGSFF X-component of geocentric spacecraft
position (km)
YPGSFF Y-component of geocentric spacecraft
position (km)
ZPGSFF Z-component of geocentric spacecraft
position (km)
DXPGSF X-component of geocentric spacecraft
velocity vector (km/sec)
DYPGSF Y-component of geocentric spacecraft
velocity vector (km/sec)
DZPGSF Z-component of geocentric spacecraft
velocity vector (km/sec)
XPHSFF X-component of heliocentric spacecraft
position (km)
YPHSFF Y-component of heliocentric spacecraft
position (km)
ZPHSFF Z-component of heliocentric spacecraft
position (km)
DXPHSF X-component of heliocentric spacecraft
velocity vector (km/sec)
DYPHSF Y-component of heliocentric spacecraft
velocity vector (km/sec)
DZPHSF Z-component of heliocentric spacecraft
velocity vector (km/sec)
XP1SFF X-component of Body-1 centered
spacecraft position (km)
YP1SFF Y-component of Body-1 centered
spacecraft position (km)
ZP1SFF Z-component of Body-1 centered
spacecraft position (km)
DXP1SF X-component of Body-1 centered
spacecraft velocity vector (km/sec)
DYP1SF Y-component of Body-1 centered
spacecraft velocity vector (km/sec)
DZP1SF Z-component of Body-1 centered
spacecraft velocity vector (km/sec)
XP2SFF X-component of Body-2 centered
spacecraft position (km)
YP2SFF Y-component of Body-2 centered
spacecraft position (km)
ZP2SFF Z-component of Body-2 centered
spacecraft position (km)
DXP2SF X-component of Body-2 centered
spacecraft velocity vector (km/sec)
DYP2SF Y-component of Body-2 centered
spacecraft velocity vector (km/sec)
DZP2SF Z-component of Body-2 centered
spacecraft velocity vector (km/sec)
B1MAGR Body-1 centered spacecraft range (km)
B1MAGV Body-1 centered magnitude of spacecraft
velocity vector (km/sec)
B2MAGR Body-2 centered spacecraft range (km)
B2MAGV Body-2 centered magnitude of spacecraft
velocity vector (km/sec)
The next 15 parameters are defined in a body centered,
body-fixed rotating coordinate system. The XY-plane is
the true-of-date equatorial plane of the body where the
X-axis points towards the prime meridian of the body,
the Z-axis is normal to the equatorial plane and the
Y-axis completes the right-handed coordinate system.
Definition of the direction to the north pole, the
prime meridian and the rotational rate is per
reference (C).
EALATP Earth centered latitude of spacecraft
(deg)
EALONP Earth centered longitude of spacecraft
(deg)
EAVELP Earth centered magnitude of spacecraft
velocity vector (km/sec)
EAPTHP Earth centered path angle (deg)
EAAZIP Earth centered azimuth angle (deg)
B1LATP Body-1 centered latitude of spacecraft
(deg)
B1LONP Body-1 centered longitude of spacecraft
(deg)
B1VELP Body-1 centered magnitude of spacecraft
velocity vector (km/sec)
B1PTHP Body-1 centered path angle (deg)
B1AZIP Body-1 centered azimuth angle (deg)
B2LATP Body-2 centered latitude of spacecraft
(deg)
B2LONP Body-2 centered longitude of spacecraft
(deg)
B2VELP Body-2 centered magnitude of spacecraft
velocity vector (km/sec)
B2PTHP Body-2 centered path angle (deg)
B2AZIP Body-2 centered azimuth (deg)
DATA_PROCESSING_OVERVIEW: not applicable
LIT_REFERENCE: (A) NOCC NAVIGATION SUBSYSTEM
Software Operators Manual - Vol. 1
Overview of DPTRAJ and ODP Software
Doc. No. SOM-NVI-5241-OP, Rev. D
18 April 1989 Jet Propulsion Laboratory
(B) Pioneer Project Technical Coordination
Memorandum,titled: DPTRAJ inputs for
the Pioneer 10/11 NSSDC Trajectory
Ephemeris Archive; 28 January 1992
NASA/ARC David W. Lozier.
(C) IAU "Report of the IAU Working Group on
Cartographic Coordinates and Rotational
Elements of the Planets and Satellites:
1982", M.E. Davies, et.al., published
in Celestial Mechanics vol. 29 (1983)
pp. 309-321.
(D) Pioneer Project Technical Coordination
Memorandum,titled: Extension of the Pioneer
10/11 NSSDC Trajectory Archive; 23 June 1995
NASA/ARC David W. Lozier.
CCSD$$MARKERMRK**002CCSD3KS00002MRK**003
VOL_TIME_COVERAGE: 1990-01-01 00:00:00.000 UTC to
2000-01-01 00:00:00.000 UTC
FILE_NAMING_CONVENTION: PIONEER 10 TRAJECTORY files are named according to each
data record contained on the tape as follows:
TRJP10YYA.DAT
TRJP10YYB.DAT
TRJ for TRAJECTORY.
P10 for PIONEER 10.
YY for year 90, 91, ... 99, 00.
A for 1st six months of the year.
B for 2nd six months of the year.
FILE_TIME_COVERAGE: TRJP1090A.DAT
TRJP1090B.DAT
TRJP1091A.DAT
TRJP1091B.DAT
TRJP1092A.DAT
TRJP1092B.DAT
(etc.)
TRJP1099A.DAT
TRJP1099B.DAT
TRJP1000A.DAT
CCSD$$MARKERMRK**003CCSD3RF0000300000001
REFERENCETYPE=$VMS;
LABEL=ATTACHED;
REFERENCE=FORMAT.SFD;
LABEL=NSSD3IF0006600000001;
REFERENCE=TRJP10*.*