***** File ICE.TXT
NOTE: This file was created by scanning the original hardcopy article
and only the Figure captions are included.
The International Cometary
Explorer (ICE) Mission to Comets
Giacobini-Zinner and Halley
J.C. Brandt
Laboratory for Astronomy and Solar Physics, NASA /Goddard Space
Flight Center, Greenbelt, Maryland, USA
1. History and scientific
mission objectives
The Third International Sun-Earth Explorer (ISEE-3) was launched on 12 August
1978 as one element of a three-spacecraft mission that began in 1977. The original
purpose was to study the solar-wind interaction with the Earth's magnetosphere. The
spacecraft was maintained in a 'halo orbit' about the libration point, L1, where it
monitored the solar-wind input. It completed four years of uninterrupted operation at
that location.
Several opportunities to use ISEE-3 in an extended mission phase were avallable.
Among the most attractive scientifically were exploration of the distant geotail and an
intercept of periodic Comet Giacobini-Zinner. Either or both of these options were
available. The comet option was constrained to an intercept of Giacobini-Zinner in
September 1985; specifically, an intercept of Comet Halley was not possible.
In order to explore the comet option, a subcommittee of the ISEE Science Working
Team (SWT) was formed at the request of the ISEE-3 Project Scientist, T. von Rosen-
vinge, and chaired by E. Smith. The subcommittee and the SWT as a whole found
the option to be of considerable scientific interest, and a report entitled 'Intercept of
Giacobini-Zinner by ISEE' was issued in June 1982, and revised in May 1983.
An ad hoc subcommittee of the Space Science Board recommended that NASA pro-
ceed with both the geotail option and the comet intercept. After an in-house review
and a review of the readiness of the spacecraft to perform the intercept by the Goddard
Space Flight Center, NASA approved the intercept with Comet Giacobini-Zinner.
The manoeuvres necessary to achieve the trajectory that would send the spacecraft
into the distant geomagnetic tail and to an intercept of Comet Giacobini-Zinner are
not simple. They are the brainchild of R. Farquhar, Flight Director for the Project.
Basically, five gravitational encounters with the Moon were required to change the
spacecraft's orbit (Fig. 1). The last encounter (also see Fig. 6) was on 22 December
1983 when the spacecraft made a close swingby, passing only 120 km above the lunar
surface. This manoeuvre effectively 'launched' the spacecraft from the Earth-Moon
system. At the same time, the spacecraft was renamed the Internationai Cometary Ex-
plorer (ICE) to correspond to its new mission.
Figure 1. A colour-coded schematic showing
the trajectory of the ISEE-3/ICE spacecraft.
ICE returns to the vicinity of Earth in the year
2013 and, if retrievable, might provide comet
dust for analysis
The first extensive survey of the distant geotail was accomplished by ISEE-3 in
1983. This survey achieved distances as great as 237 Earth radii in the tail. Aside from
the scientific significance of the results obtained, the study of particle, field, and wave
phenomena in the geotail provided an excellent rehearsal and scientific baseline for
experiment operations during the cometary encounter. Results from the geotail excur-
sion were presented in the October 1984 issue of Geophysical Research Letters (Vol.
11, No. 10).
The primary ICE scientific objective is to study the interaction between the solar
wind and a cometary atmosphere by passing through the plasma tail. This will be ac-
complished by the intercept with Comet Giacobini-Zinner on 11 September 1985.
Details of the targeting strategy are discussed below. Additional scientific objectives
following the tail intercept of Comet Giacobini-Zinner include the support of Comet
Halley studies through the measurement of solar-wind conditions upstream of
P/Halley. Such opportunities occur in October 1985 and March 1986.
2. Comet Giacobini-Zinner
(G/Z)
This short-period comet was discovered by M. Giacobini at Nice in 1900 and
rediscovered in 1913 by E. Zinner at Bamberg. The discovery and recovery history
of the comet is summarized in Table 1. The perihelion distance of 1.03 AU occurs
near the ecliptic plane, making G/Z well suited to spacecraft encounters during its in-
tervals of maximum nuclear and atmospheric activity. The orbital elements are listed
in Table 2.
Typically, the plasma tail of G/Z is observed to begin developing at a heliocentric
distance of about 1.7 AU. Conventional photographic observations at previous appari-
tions show that the plasma tail can exceed 500000 km in length. The coma, also
observed photographically, reaches a typical diameter of about 50000 km (Fig. 2).
G/Z is associated with the Draconid (Giacobinid) meteor showers. An analysis by
D.K. Yeomans indicates that there is a limited possibility that a Giacobinid shower
will occur on 8.5 October 1985, although it is unlikely to rival the great displays of
this shower in 1933 and 1946. Ground-based observers and interplanetary-dust-
particle experiments should attempt to observe this shower. Details are given in. the
Comet Giacobini-Zinner Handbook.
The early recovery of Comet G/Z by ground-based observers was of special interest
to the ICE-mission flight dynamicists. In the event that the observed orbit had differed
significantly from the expected orbit of Comet G/Z, early detection of Comet G/Z
would have been crucial to carefully schedule operation of the onboard propulsion
capability in order to effect the flyby successfully. Fortunately, the first recovery
photographs (Fig. 2) obtained on 3 April 1984, by S. Djorgovski, H. Spinrad, G.
Will, and M. Belton with the 4 m Mayall telescope at Kitt Peak National Observatory,
revealed that G/Z was within 4 arcsec of the anticipated position. Current projections
indicate that further use of the propulsion system involves changes well within the
available fuel capacity. The celestial mechanics of the encounter produces an intercept
with the spacecraft travelling from south to north in the rest frame of the comet.
Table 1. Discovery and recovery of periodic Comet Giacobini-Zinner
Approximate
Apparition Designation First observation Observer/Institution magnitude Reference
1 1900III (1900c) 20 Dec 1900 Giacobini/Observatoire de Nice 11 A.N. 154, 161
2 l913V (1913e) 23 Oct 1913 Zinner/Remeis-Sternwarte 9-10 A.N. 196, 167 & 353
3 1926VI (l926e) l6 Oct 1926 Schwassmann/Hamburger Sternwarte 14 A.N. 229, 122
4 1933III (l933c) 23 Apr 1933 Schorr/Hamburger Sternwarte 15 IAU Circ. 435
5 1940I (19391) 15 Oct 1939 Van Biesbroeck/Yerkes Observatory , 15 IAU Circ. 797
6 1946V (1946c) 29 May 1946 Jeffers/Lick Observatory 17 IAU Circ. 1046
7 1959VIII (1959b) 8 May 1959 Roemer/US Naval Observatory 20 IAU Circ. 1677
8 1966I (1965g) 17 Sept 1965 Roemer & Lloyd/US Naval Observatory 20 IAU Circ. 1923
9 l972VI (1972d) 11 Mar 1972 Roemer & McCallister/University of Arizona 19 IAU Circ. 2390
10 l979III (1978h) 30 Apr 1978 Shao & Schwartz/Harvard College Observatory 20-21 IAU Circ. 32l6
11 l985 (1984c) 03 Apr 1984 Djorgovski & Spinrad/Univ. Calif. Berkeley 23 IAU Circ. 3937
Will & Belton/Kitt Peak National Observatory
General references:
l. Baldet M F 1950, Liste Generale Des Cometes De L'Origine A l948
2. Marsden B G 1982, Catalogue of Cometary Orbits, 4th Edition, Smithsonian Astrophysical Observatory
Table 2. Orbit parameters for Comet
Giacobini-Zinner
q = perihelion distance 1 .03 AU
Q = aphelion distance 6.00 AU
e = eccentricity 0.708
i = inclination 31.9deg
OMEGA = longitude of ascending node 194.7deg
omega = argument of perihelion 172.5deg
P = period 6.5 y
T = time of perihelion 1985 Sept
5.25(ET)
Figure 2. Recovery photograph of Comet
Giacobini-Zinner obtained on 3 April 1984
with a charge-coupled device at the prime
focus of the 4 m telescope at the Kitt Peak
National Observatory. The observers were
S. Djorgovski and H. Spinrad of the
Astronomy Department, University of
California, Berkeley and G. Will and
M. Belton of the Kitt Peak National
Observatory
In order to develop the targeting strategy, a baseline tail model (Fig. 3) was
developed. The starting point was a gas production rate of 2.3 X 10**28 molecules/s at
perihelion (derived by N. Divine from the measured brightness of Comet G/Z during
previous apparitions). The model suggests a plasma tail width of about 5000 km from
the nucleus, consistent with the measured size on a photograph of Comet G/Z obtained
by E. Roemer on 26 October 1959 (Fig. 4). Features of the model include a bow
shock, a two-lobed magnetic tail, and neutral sheet separating the two magnetic lobes
in the tail. The model-dependent nature of these features should be kept in mind.
Figure 3. Schematic of the baseline plasma-
physics model for Comet Giacobini-Zinner
near perihelion
Figure 4. Photograph of Comet Giacobini-
Zinner, obtained by E. Roemer on 26 October
1959 (Official US Navy photograph). Linear
and angular scales have been added
The targeting strategy is based on the desire to penetrate the central, denser, fully-
formed plasma tail of Comet Giacobini-Zinner. Thus, the following elements must be
considered in the formulation of a targeting strategy:
1. the dust hazard
2. full formation of the tail; directly in the wake of the nucleus conditions may be
chaotic and it is thought that the tail may not be fully organized closer than a few
thousand kilometres to the nucleus
3. the cross-section of the plasma tails tends to increase or 'flare' with increasing
distance from the nucleus (Fig. 3)
4. the plasma tail tends to wag back and forth in response to variations in the solar-
wind velocity.
Elements 1 and 2 set a lower bound to the distance from the nucleus at which the in-
tercept occurs. Elements 3 and 4 conflict. The increasing cross-section 3 indicates that
targeting away from the nucleus increases the probability of intersection the tail for
a given targeting accuracy. The tail wagging 4 indicates that targeting away from the
nucleus decreases the probability of a successful tail intercept. A probabilistic model
has been developed for elements 3 and 4 and a solution sought for a 0.99 probability
of successful intercepts for a range of reasonable targeting accuracies. A solution con-
sistent with all presently available information and elements l through 4 indicates 3
tailward targeting distance of 10000 km from the nucleus.
The relative geometry of the intercept is shown in Figure 5. The spacecraft will pass
essentially south to north through the tail of the comet. Clearly, we expect to pass
through the bow shock, the contact surface separating the mixed solar-wind and com-
etary plasma, and the central plasma tail. As shown in Figure 5, the path of the ICE
spacecraft is nearly parallel to the expected orientation of the neutral sheet separating
the magnetic tail lobes. For the anticipated targeting accuracies, we cannot reasonably
expect to intersect the neutral sheet. However, we may be able to detect the neutral
sheet from the signatures of electromagnetic waves and plasma waves generated in the
neutral sheet and detected by ICE in the plasma tail.
Figure 5. The geometry of the cometary
encounter, as seen looking towards the Sun
Clearly, the maximum scientific return from the intercept depends on extensive,
supporting ground-based observations of the comet. The appropriate observations
have been requested through the International Halley Watch and a Comet Giacobini-
Zinner Handbook has been prepared (Yeomans & Brandt, 1985). Because the
'Giacobini-Zinner Watch', with a focus on the time period of September 1985, comes
before the time period of maximum effort for Halley, the Giacobini-Zinner Watch can
serve as a valuable dress rehearsal for Halley's Comet.
The coverage requested can be divided into four levels of activity:
1. Light coverage: This time period would be approximately one year centred on the
encounter date. The comet's development is to be monitored as it passes through
perihelion. Observations would emphasize astrometry and photometry.
2. Moderate coverage: This level has the goal of obtaining one good-quality observa-
tion per observer per day during the time periods 28 August to 4 September and
18 to 25 September 1985. These weeks, together with the periods of heavy and
intense coverage (see below), provide good coverage for one month or a full solar
rotation, which is important for establishing the comet's plasma environment. The
comet's heliocentric distance is almost constant (1.03 <r< 1.07 AU), and the
ecliptic latitude separation of the comet and the ICE spacecraft is less than 10deg
for this month. Thus, ICE can serve as an excellent upstream monitor during this
period, which is also one of excellent comet visibility from Earth. Therefore, we
expect the following International Halley Watch networks - Astrometry, Radio
Studies, Infrared Spectroscopy and Radiometry, Spectrophotometry and Spec-
troscopy, Photometry and Polarimetry, Near-Nuclear Studies, and Large-Scale
Phenomena - to be actively involved.
3. Heavy coverage: This level has the goal of obtaining at least two observations per
observer per day where appropriate, e.g. for time-sequence photographs. The
period covers 4 September to 18 September 1985, and the same networks as in
2 would be involved.
4. Intense coverage: This period covers the night of the encounter, which is schedul-
ed for 11.00 UT on ll September 1985. We have requested maximnm effort from
all observers during this night.
Comet Giacobini-Zinner is well situated for viewing during the month of September
1985 for Northern-Hemisphere observers. An abbreviated ephemeris is included as
Appendix 1. For a few days in September, Comets Giacobini-Zinner and Halley will
be close together in the morning sky; on 14 September, they will be separated by less
than 2deg. Comets Giacobini-Zinner and Halley should be roughly 8th and 12th
magnitude, respectively, and present a historic opportunity for wide-field celestial
photography.
For the possible Giacobini meteor shower on 8.5 October 1985, we will rely on the
newly-formed IHW network for Halley Meteor Studies for coverage.
3. The ICE instruments
The spacecraft supports 13 scientific investigations, which are listed in Table 3. The
line separates those experiments that will probably contribute useful measurements at
a comet and those that probably will not. The latter are principally experiments that
measure high-energy cosmic-ray nuclei and electrons. This division is, of course,
somewhat arbitrary. All experiments are candidates for operation during the cometary
encounter to the extent permitted by available spacecraft power and a suitable safety
margin.
l. Solar-Wind Plasma
The plasma electron analyzer is a 90deg, spherical-section electrostatic analyzer. Elec-
trons from secondary emitters are coupled into a discrete-dynode electron multiplier
to provide spatial resolution in polar and azimuth angles. Electrons having
5<E(e)< 1500 eV are analyzed in 16 steps. A complete two-dimensional distribution
is obtained in one spacecraft revolution and is read out every 24 s at 1024 bit/s.
_________________________________________________________________________________________________________________________________
Table 3. ICE experiments and status
Principal Experiment
Title Investigator Affiliation status
---------------------------------------------------------------------------------------------------------------------------------
1. Solar-Wind Plasma S. Bame Los Alamos Electrons only
National Laboratory (ion portion falled)
2. Plasma Composition K. Ogilvie NASA/Goddard Operational
Space Flight Center
3. Energetic Protons R. Hynds Imperial College Operational
London
4. X-Ray, Low- K. Anderson Unlversity of X-rays and E(e)>200 keV
Energy Electrons California, Berkeley (low-energy electron
portion failed)
5. Low-Energy D. Hovestadt Max-Planck- Partial failure
Cosmic Rays Institut fur Physik
und Astrophysik
6. Magnetometer E. Smith Jet Propulsion Operational
Laboratory
7. Plasma Waves F. Scarf TRW Systems Operational
8. Radio Waves J.-L. Steinberg Paris Observatory, Operational
Meudon
---------------------------------------------------------------------------------------------------------------------------------
9. Medium-Energy T. von Rosenvinge NASA/Goddard Operational
Cosmic Rays Space Flight Center
10. High-Energy E. Stone California Institute Partial failure
Cosmic Rays of Technology (isotope portion)
11. High-Energy M. Wiedenbeck Unlversity of Partial failure
Cosmic Rays Chicago (drift chamber)
12. Cosmic-Ray P. Meyer Ualversity of Operational
Electrons Chicago
13. Gamma-Ray Bursts B. Teegarden NASA/Goddard Partial failure
Space Flight Center (PHA memory)
_________________________________________________________________________________________________________________________________
2. Plasma Composition
The ion-composition experiment consists of a Wien filter, whose magnetic and elec-
tric fields provide velocity selection, followed by an electrostatic analyzer which
transmits ions based on the ratio of their energy to their charge. The range covered
by the dual analyzer is normally 470 to 10500 V. In the solar wind, the corresponding
mass/charge range extends from 1.0 to 5.6 AMU for singly ionized particles.
The mode of operation of the experiment is controlled by a microprocessor and will
be adjusted to optimize the experiment's performance for the comet flythrough. A
suitable measurement programme could cover the mass range from 4 to 50 in 25 steps
and a velocity range from 20 to 200 km/s in 25 steps. Normally, 20 min would be
required for each readout of this portion of parameter space.
The performance of this instrument may be seriously degraded due to aberration
caused by the encounter trajectory; for ion velocities believed to be reasonable, the
bulk flow is not in the acceptance cone of the instrument. Nevertheless, the
measurements are important and the microprocessor will be reprogrammed to an op-
timum cometary approach.
3. Energetic Protons
Energetic protons and heavy nucleons are detected by three identical charged-
particle telescopes aligned at different angles (30deg, 60deg and 135deg) to the spin axis.
Each telescope consists of a 1 cm**2 solid-state detector of 30 micro m thickness im-
mediately followed by a 2 cm**2 detector of 150 micro m thickness in anticoincidence.
Pulse-height analysis resolves the particle energies into eight channels between 35 keV
and 1.6 MeV. The count rate from each telescope and each channel is resolved into
eight sectors in the equatorial plane to measure the anisotropy of the particles.
Shielding, a mechanical collimator, and a magnetic broom prevent electrons from
entering the telescope. To sample the three telescopes, eight energies and eight sectors
requires 32 s at 1024 bit/s.
4. X-Rays, Low-Energy Electrons
Photons in the energy range 5-1250 keV are measured with a proportional counter
and a scintillation detector. A burst memory allows capture of fine timing detail both
for solar flares and for cosmic-gamma-ray bursts. Electrons with energies greater than
200 keV are also detectable by the scintillation detector.
5. Low-Energy Cosmic Rays
The instrument now consists of two different sensor systems: (i) an electrostatic
deflection analyzer system; and (ii) a thin-window flow-through proportional-
counter/solid-state-detector telescope. The combination measures the elemental abun-
dances, charge-state composition, energy spectra and angular distributions of ions
over parts of the range 2 keV/charge to 80 MeV/nucleon and of electrons between 75
and 1300 keV.
6. Magnetometer
The vector helium magnetometer is mounted on the end of a 3 m boom (Fig. 6) and
makes in-situ measurements of the ambient magnetic field vector in the frequency
range 0-3 Hz. The instrument automatically chooses one of eight ranges in which to
operate, the four lowest full-scale ranges being +/-4, +/- 14, +/-42, and +/- 146 nT. The
precision of measurement is 1/256 of the full-scale field values (0.016, 0.055 nT,
etc.). The absolute accuracy is limited by knowledge of the spacecraft magnetic field,
which is presently known to better than 0.1 nT. The time resolution corresponds to
three triaxial samples per second at 1024 bit/s . The magnetometer contains a three-
channel spectrum analyzer which is connected to the search-coil sensor of the plasma-
wave investigation (see No. 7).
Figure 6. The ISEE-3/ICI spacecraft
7. Plasma Waves
The plasma-wave investigation measures fluctuating electric and magnetic fields
associated with waves above the ion cyclotron frequency (1 - 100000 Hz). Spectral
analysis is performed on signals from three detectors: a pair of long electric-field
antennas, a short electric-field sensor and a search coil, both of which are mounted
on one of the experiment booms (Fig. 6). Electric-field fluctuations between 20 and
100000 Hz are measured in 16 frequency channels once per second at 1024 bit/s.
Cometary dust particles hitting the spacecraft or the electric antennas are expected
to cause detectable outputs similar to those detected when Voyager passed through
Saturn's ring-plane.
8. Radio Waves
Fluctuating electric fields are detected in three pairs of orthogonal antennas, one
aligned with the spacecraft spin axis and the other two in the equatorial plane (Fig.
6). The antenna voltages are preamplified and then analyzed by a radiometer con-
sisting of four superheterodyne receivers, which step through the frequency range
from 30 kHz to 2 MHz. Two channels are narrow-band with a filter bandwidth of
3 kHz, and two have a filter bandwidth of 10 kHz. The narrow-band filters sweep bet-
ween 30 kHz and 1 MHz in 12 steps, while the broadband filters cover frequencies
between 40 kHz and 2 MHz, also in 12 steps. The frequencies are scanned in a
nonlinear manner so that the highest frequencies are sampled 12 times as often as the
low frequencies. The complete scan sequence consists of 72 steps; 56 s are required
to read out all channels at 1024 bit/s.
9. Medium-Energy Cosmic Rays
The medium-energy cosmic-ray experiment measures the elemental composition of
nuclear energetic particles over wide ranges in energy (~ 1-500 MeV/nucleon) and
in charge (Z= 1-28). Electrons of ~0.2-10 MeV are measured as well. These
measurements are accomplished using all-solid-state detector telescopes with detectors
ranging in thickness from 15 to 3000 micro m. This experiment has been designed to study
solar-flare particles, galactic cosmic rays, and particles accelerated by the in-
terplanetary medium.
10. High-Energy Cosmic Rays
This experiment measures the isotopic composition of solar and galactic cosmic rays
with 5-250 MeV/nucleon and for all elements with charge Z<= 30. It consists of two
thin (50 micro m) solid-state detectors, which determine the entering particle trajectory,
followed by solid-state detectors that measure the particle energy.
11. High-Energy Cosmic Rays
Similar to the preceding experiment, this instrument is a telescope constructed from
trajectory-defining drift chambers, a large stack of solid-state detectors and a surround-
ing scintillator anti-coincidence detector. The experiment has been designed to
measure the isotopic abundances of galactic cosmic rays from ~ 20 to ~500
MeV/nucleon for isotopes with masses from A = 1 to 64.
12. Cosmic-Ray Electrons
Eight active detectors are used to determine the energy spectrum of electrons in the
range 5-400 MeV. The experiment also determines the energy spectrum and relative
abundances of nuclei from protons to the iron group in the range ~ 30 MeV/nucleon
to 15 GeV/nucleon. It may also be able to count cometary dust particles impinging
on the front detector.
13. Gamma-Ray Bursts
The gamma-ray-burst experiment is designed to detect cosmic gamma-ray bursts
with high spectral resolution (<3.5 keV at l MeV) and high temporal resolution (as
fast as 4 ms). The primary sensor, an intrinsic germanium solid-state detector cooled
to ~ l00 K by a two-stage radiative cooler, spans the energy range 0.05-6.5 MeV
Figure 7. The geometry of 'launch' and the
encounter on 11 September 1985. The range at
encounter is 0.47 AU and the Sun-Earth Comet angle
is 79.6deg.
Figure 8. ICE shortly before encountering
Comet Giocobini-Zinner in September 1985.
These experiments, in particular, experiments 1 through 8, although not chosen with
cometary research in mind, are well-suited for probing the plasma-tail environment.
The ICE spacecraft has no imaging capability nor any experiments designed to study
dust particles (but see descriptions for Nos. 7 and 12). For additional details of the
instruments as launched, see the July 1978 issue of IEEE Transactions of Geoscience
Electronics (Vol. GE-16, No. 3).
4. The spacecraft
The spacecraft (Fig. 6) is a developed version of the earlier Interplanetary Monitor-
ing Platform (IMP). Spacecraft weights are listed in Figure 6.
The spacecraft body is a 16-sided cylinder, 1.74 m in diameter and 1.6 m high.
Solar arrays mounted on the faces of the cylinder provide 160 W of primary power
at 28 V. A distinctive feature is a superstructure, or tower, which elevates the
telemetry antenna above the spacecraft body and provides a clear field of view for
several cosmic-ray detectors.
The spacecraft body supports a total of ten appendages. Two equatorial experiment
booms (3 m long) support the magnetometer and plasma-wave sensors. Four wire
antennas (each 49 m long) are deployed in the spin plane as part of the radio-wave
and plasma-wave investigations. Two axial antennas (7 m each) extend above and
below the spacecraft parallel to the spin axis to render the radio-wave measurements
three dimensional. Finally, two short inertial booms provide stability.
The radio system consists of two redundant S-band transponders operating at 2217
and 2270 MHz. There are two low-gain antennas and a telemetry antenna having
medium gain (7 dB) and a fan beam of +/-6deg. The radiated power is 5W. The standard
telemetry rate in halo orbit was 2048 and 512 bit/s.
The spacecraft is spin-stabilized at 19.75 rpm. Attitude information and control is
provided by two fine Sun sensors and a panoramic attitude sensor. The spin axis is
maintained perpendicular to the ecliptic plane to within <1deg.
Propulsion and attitude control use monopropellant hydrazine. The system contains
eight propellant tanks and 12 thrusters, including redundancy. A large amount of pro-
pellant was carried at launch (94 kg) as a safeguard against large errors associated with
the launch vehicle. As a result of a nominal launch, gas usage has been much lower
than anticipated, resulting in a substantial amount of excess gas still being available.
5. Mission description
The 'effective launch' of ICE took place on 22 December 1983. As the spacecraft
distance from Earth increased, tracking and data acquisition involved the NASA
Deep Space Network (DSN). The necessity for this involvement is apparent if one
considers that the ISEE-3 radio system was designed to transmit from the halo orbit
at a geocentric distance of 0.01 AU, whereas the distance to the spacecraft at cometary
encounter will be 0.47 AU. A major effort required for the ICE mission was the outfit-
ting of antennas in the DSN to operate at the ICE frequencies.
Current plans are to utilize the 64 m DSN (Goldstone, Madrid, Canberra) and the
300 m dish at Arecibo as the prime station. The anticipated data rate at encounter will
be 1024 bit/s, although 512 bit/s may be used at other times. The acceptable perfor-
mance is based on a bit error rate of 10**-4. There will be additional coverage by the
64 m station at Usuda, Japan. Operations outside the month centred on the encounter
date of 11 September 1985 are basically cruise-science measurements, which will be
discussed in the next section.
On 11 September 1985, Comet Giacobini-Zinner will be at the location shown in
Figure 7. The ICE spacecraft will be approaching the aim point on the main plasma
tail axis 10000 km from the nucleus, as shown schematically in Figure 8.
Some idea of the spatial scales associated with key instruments and their sampling
times is given in Table 4 for the expected data rate of 1024 bit/s. For the sampling
period indicated, the 'spatial resolution' is the distance travelled at the relative en-
counter speed of 20.7 km/s. These dimensions should be compared with the estimated
distance between bow-shock crossings of about 175 000 km and a measured main tail
diameter of 5000 km. Expressed in terms of time, we expect the spacecraft to be inside
the bow shock for about 2 h 20 min and in the maln plasma tail for about 4 min.
The magnetometer will produce many measurements during the encounter period
and we use it to illustrate possible scientific product. Current models of comets do not
indicate a major amplification of the cometary magnetic field over the solar-wind
value. However, major changes in field-line direction are expected. Well away from
the comet the magnetic field should, on average, show the Archimedian spiral angle
of 135deg or 315deg to the radial appropriate for normal solar-wind fiow. Interior to the
bow shock we expect a different, possibly somewhat chaotic, orientation tending to
the ordered two-lobed configuration along the axis of the plasma tail. If the neutral
sheet is encountered, a magnetic reversal should be recorded. The model-dependent
nature of this description must be stressed. For example, the bow shock may or may
not exist. We should know after 11 September 1985, and the model will be tested in
this and in other respects. Obviously, we need data from as many different ex-
periments as possible to complete our model testing.
To enhance the science return from the encounter, a Guest Investigator Program has
been established by NASA.
Table 4. Spatial resolution of the scientific meaurements (assuming 1024 bit/s)
Instrument Sampling period (s) Spatial resolution (km)
Magnetometer 1/3 7
Plasma Waves
16 channel E 1 21
8 channel E, B 16 330
Plasma Electrons
Two-dimensional distribution 24 500
Energetic Protons 32 660
Radio Waves 56 1200
Plasma Ions 1200 25000
6. ICE and Comet Halley
The ICE mission should be of direct benefit to the missions to explore Halley's
Comet in two general ways. The first is through the spin-off and synergism of the en-
counter, and the second is through the use of ICE as an upstream monitor of solar-
wind conditions.
The ICE experience at encounter will give the first indications of spacecraft pro-
blems in a cometary environment. For example, the dust emitted by Comet Giacobini-
Zinner is thought to be extremely fluffy and possibly one hundred times less dense
than the dust associated with Halley's Comet. Dust fluences from Comet Giacobini-
Zinner are estimated to be lower than for Halley's Comet. Thus, a relatively benign
dust environment is expected for the ICE encounter. If spacecraft problems are en-
countered and ascribed to dust, some revision of strategy for the Halley encounters
may be indicated.
On the scientific side, the Comet Giacobini-Zinner encounter is highly complemen-
tary to the Halley encounters. In-situ data will have been obtained for two comets
within a very short time, permitting intercomparisons. All the Halley probes are
targeted for the sunward side of the comet versus the tailward targeting for ICE. Both
data sets are probably necessary to sketch a moderately complete picture of a comet's
plasma and magnetic field.
Finally, experience with the 'Giacobini-Zinner Watch' carried out by the Interna-
tional Halley Watch in September 1985 could lead to more efficient coverage of
Halley's Comet in March of 1986. The opportunity to observe both comets
simultaneously around 14 September 1985 has already been mentioned.
The second role of ICE in Halley studies involves its use as an upstream monitor
of solar-wind conditions. In late March 1986, the ICE spacecraft can be considered
a 'fairly distant' probe to Halley's Comet (Table 5). A bipolar plot of the ICE trajec-
tory showing the alignments is given in Figure 9.
Two near-radial lineups are available, and relevant facts are assembled in Table 5.
Tracking of ICE at these times should not be a problem because the range from
Earth is approximately the same as the range at Comet Giacobini-Zinner encounter.
Furthermore, when ICE is in the cruise mode making solar-wind measurements, the
lower data rate of 512 bit/s would be acceptable.
Investigations of cometary phenomena utilizing input parameters from solar-wind
measurements have been carried out successfully for some years. However, we note
that three-dimensional plasma ion speeds have been quite important in these investiga-
tions. The challenge will be to fully exploit the ICE data.
With the caveat mentioned just above, ICE could provide important solar-wind data
during cruise-mode operations, which would include the 'week' of the five spacecraft
encounters with Halley's Comet in March 1986. The time delay between ICE and
Halley's Comet on 13/14 March 1986, calculated according to standard formulas, is
only two days, considered quite reasonable by scientists working in this field. If
suitable ion-velocity coverage is obtained from ICE or another spacecraft, solar-wind
data for the Halley encounters could be reasonably complete.
Finally, there is the near-radial alignment of ICE, Pioneer Venus Orbiter, Vega-1
and 2, and MS-T5 in the interval 15 May to 15 June 1985, which presents an oppor-
tunity for multispacecraft investigation of comet-like phenomena over large scale
lengths (described in Galeev & Scarf, 1985).
Table 5. Radial alignments with Comet Halley
Radial Angular Solar-wind
Date separation (AU) separation (deg) travel time (d) Range (AU)
31 October 1985 0.93 l 4 0.41
28 March 1986 0.21 6 1 0.56
Figure 9. A bipolar plot of the ICE trajectory
showing the radial alignments with Halley's
Comet
Appendix 1. Ephemeris for Comet Giacobini-Zinner
EXPLANATI0N OF EPHEMERIS ENTRIES *
J.D. = JULIAN DATE (TIMES IN THIS EPHEMERIS ARE EPHEMERIS TIMES)
R.A. 1950.0 DEC. = GEOCENTRIC RIGHT ASCENSION AND DECLINATION REFERRED TO
THE MEAN EQUATOR AND EQUINOX OF 1950.0 - LIGHT TIME CORRECTI0NS HAVE
BEEN APPLIED.
R.A. APPN DEC. = APPARENT RIGHT ASCENSION AND DECLINATION - LIGHT TIME,
ANNUAL ABERRATION, AND NUTATION CORRECTIONS HAVE BEEN APPLIED AND R.A.
AND DEC. HAVE BEEN PRECESSED TO THE EPHEMERIS DATE.
DELTA = GEOCENTRIC DISTANCE OF OBJECT IN AU.
DELDOT = GEOCENTRIC VELOCITY OF OBJECT IN KM/SEC.
R = HELIOCENTRIC DISTANCE OF OBJECT IN AU.
RDOT = HELIOCENTRIC VELOCITY OF OBJECT IN KM/SEC.
TMAG = TOTAL MAGNITUDE ESTIMATES AFTER THE ANALYSIS BY C.S. MORRIS.
PRE-PERIHELION
TMAG = 8.90 + 5*LOG(DELTA) + 11.00*LOG(R) FOR R > 1.3 AU
TMAG = 9.60 + 5*LOG(DELTA) + 4.73*LOG(R) FOR R = 1.3 TO 0.99 AU
POST-PERIHELION
TMAG = 9.65 + 5*LOG(DELTA) + 10.48*LOG(R) FOR R = 0.99 TO 1.71 AU
IN CASES WHERE TMAG IS NOT COMPUTED, IT IS SET EQUAL TO ZERO.
NMAG = NUCLEAR MAGNITUDE = 16.5 + 5*LOG(DELTA) + 5*LOG(R) + 0.03*BETA
THETA = SUN-EARTH-OBJECT ANGLE IN DEGREES.
BETA = SUN-OBJECT-EARTH ANGLE IN DEGREES.
MOON = OBJECT-EARTH-MOON ANGLE IN DEGREES.
THE FOLLOWING OSCULATING ORBITAL ELEMENTS ARE C0NSISTENT WITH THE EPHEMERIS:
EPOCH 2446320.5 1985 SEPT. 12.0 (E.T.)
PERIHELION PASSAGE 2446313.74907 1985 SEPT. 5.24907 (E.T.)
PERIHELION DISTANCE 1.0282614 AU
ECCENTRICITY 0.7075300
ARG. OF PERIHELION 172.48887
LONG. OF ASCENDING NODE 194.70595
INCLINATION 31.87829
IN THE ABOUE ORBITAL ELEMENTS, THE ANGLES ARE IN DEGREES AND REFERRED TO THE
ECLIPTIC AND EQUINOX OF 1950.0.
THE N0NGRAVITATIONAL PARAMETERS ARE AS FOLLOWS:
A1 = -0.0543
A2 = -0.0465
FOR THE DEFINITION OF A1 AND A2 SEE: MARSDEN ET AL, ASTRONOMICAL JOURNAL,
1973, VOL. 78, PP. 211-225.
COMPUTATIONS BY D.K. YEOMANS - JPL
* For an expanded ephemeris. see The Comet Giacobini-Zinner Handbook Yeomans & Brandt, 1985.
EPHEMERIS (WITH PERTURBATIONS) FOR P/GIACOBINI-ZINNER
YR MN DY HR J.D. R.A. 1950.0 DEC. R.A. APPN DEC. DELTA DELDOT R RDOT TMAG NMAG THETA BETA MOON
1985 3 15 .0 2446139.5 18 35.523 + 4 8.24 18 37.251 + 4 9.82 2.38 -32.19 2.34 -14.88 14.8 21.0 75.7 24.3 31
1985 3 25 .0 2446149.5 18 51.870 + 6 29.50 18 53.571 + 6 31.89 2.19 -31.48 2.25 -15.11 14.5 20.7 80.4 25.9 113
1985 4 4 .0 2446159.5 19 8.273 + 9 13.69 19 9.943 + 9 16.88 2.01 -30.40 2.16 -15.33 14.1 20.5 84.7 27.4 110
1985 4 14 .0 2446169.5 19 24.783 +12 22.08 19 26.417 +12 26.06 1.84 -29.04 2.08 -15.52 13.7 20.3 88.6 28.9 43
1985 4 24 .0 2446179.5 19 41.454 +15 55.70 19 43.050 +16 .47 1.68 -27.41 1.99 -15.69 13.3 20.0 91.9 30.4 121
1985 5 4 .0 2446189.5 19 58.413 +19 54.61 19 59.968 +20 .14 1.53 -25.56 1.89 -15.82 12.9 19.8 94.5 32.0 3
1985 5 14 .0 2446199.5 20 15.905 +24 18.27 20 17.416 +24 24.57 1.38 -23.61 1.80 -15.89 12.4 19.5 96.4 33.9 56
1985 5 24 .0 2446209.5 20 34.262 +29 4.80 20 35.729 +29 11.87 1.25 -21.60 1.71 -15.89 12.0 19.2 97.5 35.9 121
1985 6 3 .0 2446219.5 20 54.078 +34 10.19 20 55.504 +34 18.04 1.13 -19.66 1.62 -15.79 11.5 19.0 97.7 38.4 85
1985 6 13 .0 2446229.5 21 16.342 +39 29.04 21 17.734 +39 37.69 1.03 -17.88 1.53 -15.55 11.0 18.7 97.0 41.3 63
1985 6 23 .0 2446239.5 21 42.588 +44 52.86 21 43.966 +45 2.35 .93 -16.33 1.44 -15.12 10.5 18.5 95.5 44.6 116
1985 7 3 .0 2446249.5 22 15.443 +50 8.48 22 16.851 +50 18.84 .84 -15.03 1.35 -14.44 10.0 18.2 93.4 48.5 86
1985 7 13 .0 2446259.5 22 59.057 +54 55.08 23 .586 +55 6.24 .75 -13.95 1.27 -13.44 9.4 18.0 90.8 52.9 60
1985 7 18 .0 2446264.5 23 26.582 +56 56.06 23 28.231 +57 7.52 .71 -13.44 1.24 -12.79 9.3 17.9 89.4 55.3 85
1985 7 23 .0 2446269.5 23 58.803 +58 32.21 0 .620 +58 43.80 .68 -12.90 1.20 -12.03 9.1 17.8 88.0 57.8 9
1985 7 28 .0 2446274.5 0 35.984 +59 33.08 0 38.017 +59 44.53 .64 -12.30 1.17 -11.14 8.9 17.7 86.5 60.3 124
1985 8 2 .0 2446279.5 1 17.576 +59 46.31 1 19.847 +59 57.25 .60 -11.59 1.14 -10.12 8.8 17.6 85.1 62.9 89
1985 8 7 .0 2446284.5 2 1.895 +58 59.35 2 4.378 +59 9.34 .57 -10.71 1.11 - 8.97 8.6 17.5 83.7 65.4 51
1985 8 12 .0 2446289.5 2 46.356 +57 2.41 2 48.979 +57 11.07 .54 - 9.62 1.08 - 7.69 8.4 17.4 82.4 67.9 42
1985 8 17 .0 2446294.5 3 28.340 +53 51.22 3 31.006 +53 58.33 .52 - 8.24 1.06 - 6.27 8.3 17.3 81.2 70.1 84
1985 8 22 .0 2446299.5 4 6.077 +49 28.17 4 8.700 +49 33.70 .50 - 6.53 1.05 - 4.75 8.2 17.2 80.2 72.0 141
1985 8 27 .0 2446304.5 4 38.927 +44 1.87 4 41.454 +44 5.89 .48 - 4.52 1.04 - 3.13 8.1 17.2 79.5 73.4 140
1985 8 28 .0 2446305.5 4 44.918 +42 50.15 4 47.423 +42 53.89 .48 - 4.09 1.03 - 2.80 8.1 17.2 79.4 73.6 129
1985 8 29 .0 2446306.5 4 50.724 +41 36.57 4 53.205 +41 40.03 .47 - 3.65 1.03 - 2.47 8.1 17.2 79.3 73.8 118
1985 8 30 .0 2446307.5 4 56.349 +40 21.26 4 58.806 +40 24.45 .47 - 3.20 1.03 - 2.13 8.0 17.2 79.3 74.0 107
1985 8 31 .0 2446308.5 5 1.799 +39 4.35 5 4.231 +39 7.29 .47 - 2.74 1.03 - 1.79 8.0 17.2 79.2 74.1 95
1985 9 1 .0 2446309.5 5 7.078 +37 46.00 5 9.485 +37 48.68 .47 - 2.28 1.03 - 1.45 8.0 17.1 79.2 74.2 84
1985 9 2 .0 2446310.5 5 12.191 +36 26.35 5 14.573 +36 28.78 .47 - 1.81 1.03 - 1.11 8.0 17.1 79.1 74.3 73
1985 9 3 .0 2446311.5 5 17.144 +35 5.54 5 19.501 +35 7.73 .47 - 1.34 1.03 - .77 8.0 17.1 79.1 74.3 61
1985 9 4 .0 2446312.5 5 21.943 +33 43.73 5 24.274 +33 45.69 .47 - .87 1.03 - .43 8.0 17.1 79.1 74.4 50
1985 9 5 .0 2446313.5 5 26.591 +32 21.07 5 28.898 +32 22.80 .47 - .40 1.03 - .09 8.0 17.1 79.2 74.4 39
1985 9 6 .0 2446314.5 5 31.095 +30 57.70 5 33.377 +30 59.21 .47 .08 1.03 .26 8.1 17.1 79.2 74.3 28
1985 9 7 .0 2446315.5 5 35.460 +29 33.79 5 37.718 +29 35.08 .47 .55 1.03 .60 8.1 17.1 79.3 74.3 17
1985 9 8 .0 2446316.5 5 39.690 +28 9.46 5 41.924 +28 10.54 .47 1.02 1.03 .94 8.1 17.1 79.3 74.2 5
1985 9 9 .0 2446317.5 5 43.790 +26 44.88 5 46.000 +26 45.76 .47 1.49 1.03 1.28 8.1 17.1 79.4 74.1 5
1985 9 10 .0 2446318.5 5 47.765 +25 20.17 5 49.952 +25 20.85 .47 1.95 1.03 1.62 8.1 17.1 79.5 73.9 17
1985 9 11 .0 2446319.5 5 51.620 +23 55.48 5 53.783 +23 55.97 .47 2.40 1.03 1.96 8.2 17.1 79.6 73.7 29
1985 9 12 .0 2446320.5 5 55.357 +22 30.93 5 57.499 +22 31.24 .47 2.85 1.03 2.30 8.2 17.1 79.8 73.5 42
1985 9 13 .0 2446321.5 5 58.983 +21 6.66 6 1.102 +21 6.79 .47 3.29 1.03 2.64 8.2 17.1 79.9 73.3 55
1985 9 14 .0 2446322.5 6 2.499 +19 42.77 6 4.596 +19 42.74 .48 3.72 1.04 2.97 8.2 17.2 80.1 73.1 69
1985 9 15 .0 2446323.5 6 5.911 +18 19.39 6 7.987 +18 19.19 .48 4.14 1.04 3.30 8.2 17.2 80.2 72.8 82
1985 9 16 .0 2446324.5 6 9.221 +16 56.62 6 11.276 +16 56.26 .48 4.55 1.04 3.63 8.2 17.2 80.4 72.5 96
1985 9 17 .0 2446325.5 6 12.433 +15 34.56 6 14.468 +15 34.04 .48 4.95 1.04 3.95 8.3 17.2 80.6 72.2 110
1985 9 18 .0 2446326.5 6 15.551 +14 13.30 6 17.565 +14 12.62 .49 5.34 1.04 4.27 8.3 17.2 80.8 71.8 123
1985 9 19 .0 2446327.5 6 18.576 +12 52.91 6 20.571 +12 52.08 .49 5.71 1.05 4.59 8.3 17.2 81.1 71.4 136
1985 9 20 .0 2446328.5 6 21.513 +11 33.48 6 23.489 +11 32.51 .49 6.08 1.05 4.91 8.3 17.2 81.3 71.1 148
1985 9 21 .0 2446329.5 6 24.365 +10 15.07 6 26.322 +10 13.96 .50 6.42 1.05 5.22 8.4 17.2 81.5 70.7 157
1985 9 22 .0 2446330.5 6 27.133 + 8 57.74 6 29.072 + 8 56.49 .50 6.76 1.06 5.53 8.4 17.2 81.8 70.3 161
1985 9 23 .0 2446331.5 6 29.820 + 7 41.54 6 31.742 + 7 40.16 .50 7.08 1.06 5.83 8.4 17.2 82.1 69.8 157
1985 9 24 .0 2446332.5 6 32.429 + 6 26.51 6 34.334 + 6 25.01 .51 7.38 1.06 6.13 8.5 17.2 82.3 69.4 48
1985 9 25 .0 2446333.5 6 34.961 + 5 12.69 6 36.849 + 5 11.07 .51 7.67 1.07 6.42 8.5 17.3 82.6 68.9 138
1985 9 30 .0 2446338.5 6 46.544 - 0 37.46 6 48.354 - 0 39.64 .54 8.88 1.09 7.82 8.7 17.3 84.1 66.5 85
1985 10 5 .0 2446343.5 6 56.454 - 5 55.38 6 58.194 - 5 58.03 .56 9.74 1.11 9.09 8.9 17.4 85.8 63.9 42
1985 10 10 .0 2446348.5 7 4.808 -10 41.94 7 6.485 -10 44.98 .59 10.30 1.14 10.23 9.1 17.5 87.5 61.2 47
1985 10 15 .0 2446353.5 7 11.668 -14 59.21 7 13.289 -15 2.58 .62 10.61 1.17 11.23 9.3 17.6 89.4 58.5 98
1985 10 20 .0 2446358.5 7 17.073 -18 49.57 7 18.642 -18 53.20 .65 10.75 1.20 12.11 9.6 17.7 91.3 55.8 133
1985 10 25 .0 2446363.5 7 21.055 -22 15.35 7 22.578 -22 19.16 .68 10.76 1.24 12.86 9.8 17.7 93.3 53.2 112
EPHEMERIS (WITH PERTURBATIONS) FOR P/GIACOBINI-ZINNER
YR MN DY HR J.D. R.A. 1950.0 DEC. R.A. APPN DEC. DELTA DELDOT R ROOT TMAG NMAG THETA BETA MOON
1985 10 .0 2446368.5 7 23.635 -25 18.68 7 25.114 -25 22.61 .72 10.68 1.28 13.50 10.0 17.8 95.4 50.7 76
1985 11 .0 2446373.5 7 24.816 -28 1.26 7 26.225 -28 5.25 .75 10.55 1.32 14.04 10.3 17.9 97.6 48.3 55
1985 11 .0 2446378.5 7 24.599 -30 24.19 7 26.000 -30 28.17 .78 10.42 1.36 14.48 10.5 18.0 99.8 45.9 72
1985 11 .0 2446388.5 7 20.084 -34 12.51 7 21.419 -34 16.30 .84 10.30 1.44 15.15 10.9 18.2 104.4 41.5 116
1985 11 .0 2446398.5 7 10.764 -36 43.67 7 12.048 -36 47.04 .90 10.49 1.53 15.56 11.4 18.3 109.0 37.5 68
1985 12 .0 2446408.5 6 57.943 -37 56.51 6 59.196 -37 59.29 .96 11.11 1.62 15.80 11.8 18.5 113.4 33.8 95
1985 12 .0 2446418.5 6 43.530 -37 51.12 6 44.782 -37 53.24 1.03 12.26 1.72 15.89 12.2 18.6 117.2 30.7 97
1986 12 .0 2446428.5 6 29.752 -36 34.16 6 31.028 -36 35.64 1.10 13.88 1.81 15.89 12.6 18.8 120.2 28.1 65
1986 1 .0 2446438.5 6 18.353 -34 19.16 6 19.672 -34 20.10 1.19 15.92 1.90 15.81 12.9 19.0 121.8 26.1 116
1986 1 .0 2446448.5 6 10.369 -31 22.94 6 11.745 -31 23.52 1.29 18.26 1.99 15.68 13.3 19.3 122.0 24.8 76
1986 1 .0 2446458.5 6 6.128 -28 3.72 6 7.562 -28 4.12 1.40 20.72 2.08 15.51 13.7 19.5 120.6 24.0 74
1986 2 .0 2446468.5 6 5.389 -24 36.99 6 6.881 -24 37.37 1.52 23.20 2.17 15.32 14.1 19.8 117.9 23.7 124
1986 2 .0 2446478.5 6 7.733 -21 14.28 6 9.279 -21 14.80 1.67 25.54 2.26 15.10 14.5 20.1 114.1 23.6 55
1986 2 .0 2446488.5 6 12.653 -18 3.90 6 14.246 -18 4.68 1.82 27.64 2.34 14.87 14.8 20.4 109.5 23.5 94
1986 3 .0 2446498.5 6 19.638 -15 10.49 6 21.273 -15 11.64 1.98 29.46 2.43 14.63 15.2 20.6 104.3 23.3 115
1986 3 .0 2446508.5 6 28.283 -12 36.43 6 29.955 -12 38.02 2.16 30.93 2.51 14.39 15.5 20.9 98.8 23.1 41
Acknowledgement
I would like to thank Drs. T. von Rosenvinge and M. Niedner for their generous
assistance in preparing this paper.
References
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