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SPACECRAFT: VIKING ORBITER 1
Spacecraft Information
======================
Launch Date : 1975-08-20
Instrument Host Name : VIKING ORBITER 1
Instrument Host Type : SPACECRAFT
Mission Information
===================
Mission Start Date : 1968
Mission Stop Date : 1982
Mission Alias Name : VIKING75
Targets
=======
MARS
Instruments
===========
INFRARED THERMAL MAPPER
MARS ATMOSPHERIC WATER DETECTOR
VISUAL IMAGING SUBSYSTEM - CAMERA A
VISUAL IMAGING SUBSYSTEM - CAMERA B
Spacecraft Description
======================
The Viking spacecraft consisted of two orbiters, each with
a heat-sterilized lander within a capsule. Together with
fuel they each weighed 3530 kg just after launch. After
landing, their masses were about 900 kg for the orbiters
and 600 kg for each lander.
The orbiters, derived from earlier Mariner designs, were
powered by solar panels and were stabilized in three axes
by use of solar and star sensors in conjunction with
attitude control jets. Three remote sensing science
investigations resided on the two-axis scan platform: a
pair of high resolution slow scan televison framing cameras
(the Visual Imaging Subsystem, or VIS); a near-infrared
spectrometer for atmospheric water detection (the Mars
Atmosphere Water Detector, MAWD); and a visual and thermal
infrared radiometer system (Infrared Thermal Mapper, IRTM).
The landers each carried two facsimile cameras providing
stereo views of the surface; a boom-mounted set of
meteorology instruments; an X-ray fluorescence experiment
for inorganic chemical analysis of soil; a gas
chromatograph mass spectrometer to measure the soil and
atmosphere; three biology experiments: the pyrolytic
release, labeled release, and gas exchange systems; a
seismometer; a magnetic properties experiment. Soil
physical properties experiments were carried out using
several of the abovementioned systems. Upper atmosphere
measurements were performed using detectors on the landers
during entry through the atmosphere. Finally, radio science
was done using transmitters and receivers on both the
orbiters and landers. An extensible arm and scoop system on
each lander was programmable to acquire samples of soil and
rock for analysis on board the landers and to affect the
local environment for visual inspection.
Platform Descriptions
=====================
Platform SCAN PLATFORM
----------------------
The three Viking orbiter science instruments are mounted on
a scan platform that provides temperature control for them
and pointing in two axes: cone and clock. The platform can
be rotated in cone and/or clock at rates of 0.25 or 1.0
degree/sec. Subroutines stored in the memory of the
on-board computer can be called upon to move the platform
in specified patterns. The nominal range of motion possible
for the scan platform is from 45 to 175 degrees cone and 80
to 310 clock; however, there are mechanical constraints
that reduce this range. See reference.
Reference
=========
Journal: JOURNAL OF GEOPHYSICAL RESEARCH
Publication Date: 1977
Reference Key ID: SNYDER1977
Authors
-------
C. W. SNYDER
Citation
--------
'The Missions of the Viking Orbiters', C.W. Snyder, Journal
of Geophysical Research, vol. 82, p. 3971, 1977.
Reference
=========
Journal: JOURNAL OF GEOPHYSICAL RESEARCH
Publication Date: 1979
Reference Key ID: SNYDER1979
Authors
-------
C. W. SNYDER
Citation
--------
'The Extended Mission of Viking', C.W. Snyder, Journal of
Geophysical Research, vol. 84, p. 7917, 1979.
Reference
=========
Journal: JOURNAL OF GEOPHYSICAL RESEARCH
Publication Date: 1977
Reference Key ID: SOFFEN1977
Authors
-------
G. A. SOFFEN
Citation
--------
'The Viking Project', G. A. Soffen, Journal of Geophysical
Research, vol. 82, p. 3959, 1977.
__________________________________________________________________________
SPACECRAFT: VIKING LANDER 1
Spacecraft Information
======================
Launch Date : 1975-08-20
Instrument Host Name : VIKING LANDER 1
Instrument Host Type : SPACECRAFT
Mission Information
===================
Mission Start Date : 1968
Mission Stop Date : 1982
Mission Alias Name : VIKING75
Targets
=======
MARS
Instruments
===========
CAMERA 1
CAMERA 2
UNK
UNK
VIKING METEOROLOGY INSTRUMENT SYSTEM
Spacecraft Description
======================
The Viking spacecraft consisted of two orbiters, each with
a heat-sterilized lander within a capsule. Together with
fuel they each weighed 3530 kg just after launch. After
landing, their masses were about 900 kg for the orbiters
and 600 kg for each lander.
The orbiters, derived from earlier Mariner designs, were
powered by solar panels and were stabilized in three axes
by use of solar and star sensors in conjunction with
attitude control jets. Three remote sensing science
investigations resided on the two-axis scan platform: a
pair of high resolution slow scan televison framing cameras
(the Visual Imaging Subsystem, or VIS); a near-infrared
spectrometer for atmospheric water detection (the Mars
Atmosphere Water Detector, MAWD); and a visual and thermal
infrared radiometer system (Infrared Thermal Mapper, IRTM).
The landers each carried two facsimile cameras providing
stereo views of the surface; a boom-mounted set of
meteorology instruments; an X-ray fluorescence experiment
for inorganic chemical analysis of soil; a gas
chromatograph mass spectrometer to measure the soil and
atmosphere; three biology experiments: the pyrolytic
release, labeled release, and gas exchange systems; a
seismometer; a magnetic properties experiment. Soil
physical properties experiments were carried out using
several of the abovementioned systems. Upper atmosphere
measurements were performed using detectors on the landers
during entry through the atmosphere. Finally, radio science
was done using transmitters and receivers on both the
orbiters and landers. An extensible arm and scoop system on
each lander was programmable to acquire samples of soil and
rock for analysis on board the landers and to affect the
local environment for visual inspection.
Platform Descriptions
=====================
Platform METEOROLOGY BOOM ASSEMBLY
----------------------------------
The Meteorology Boom Assembly consist of a deployable
boom which supports the Meteorology Sensor Array in a
stowed position during the launch, cruise, and entry
portions of the mission. A short time after landing, a
pyrotechnic-activated pin releases the boom, which deploys
and latches it in the extended position. To prevent
entrainment of sand or dust in critical hinge areas, the
hinge and latch mechanisms are housed and sealed in a cover.
Platform SCAN PLATFORM
----------------------
The three Viking orbiter science instruments are mounted on
a scan platform that provides temperature control for them
and pointing in two axes: cone and clock. The platform can
be rotated in cone and/or clock at rates of 0.25 or 1.0
degree/sec. Subroutines stored in the memory of the
on-board computer can be called upon to move the platform
in specified patterns. The nominal range of motion possible
for the scan platform is from 45 to 175 degrees cone and 80
to 310 clock; however, there are mechanical constraints
that reduce this range. See reference.
Reference
=========
Journal: JOURNAL OF GEOPHYSICAL RESEARCH
Publication Date: 1977
Reference Key ID: SNYDER1977
Authors
-------
C. W. SNYDER
Citation
--------
'The Missions of the Viking Orbiters', C.W. Snyder, Journal
of Geophysical Research, vol. 82, p. 3971, 1977.
Reference
=========
Journal: JOURNAL OF GEOPHYSICAL RESEARCH
Publication Date: 1979
Reference Key ID: SNYDER1979
Authors
-------
C. W. SNYDER
Citation
--------
'The Extended Mission of Viking', C.W. Snyder, Journal of
Geophysical Research, vol. 84, p. 7917, 1979.
Reference
=========
Journal: JOURNAL OF GEOPHYSICAL RESEARCH
Publication Date: 1977
Reference Key ID: SOFFEN1977
Authors
-------
G. A. SOFFEN
Citation
--------
'The Viking Project', G. A. Soffen, Journal of Geophysical
Research, vol. 82, p. 3959, 1977.
__________________________________________________________________________