According to a November 18 Reuter's story on the HoustonChronicle.com, "Russia is likely to extend the life of its 12-year-old Mir space station until mid-2000," a year later than the Russians had previously pledged. The Russians had promised to bring down Mir next June in order to focus its limited financial resources on the new International Space Station.

The current crew (Mir 26) which arrived in August 1998, are Commander Gennady Padalka and Flight Engineer Sergei Avdeyev.

The (final?) Mir crew, Viktor Afanasyev and Sergei Treshchev, will replace Padalka and Avdeyev in February, 1999. Previously, the "final" Mir crew was expected to stay aboard Mir for a 5 month stay before deorbiting the Mir Space Station in July/August 1999.

Perhaps this legacy of human space flight is no longer destined to burn in the fire of re-entry into Earth's atmosphere within the next 2 years!

19981201-GS

Launch Date - Flight - Vehicle

20 NOV 1998 - 1A/R - Russian
03 DEC 1998 - 2A - US STS-88
MAY -- 1999 - 2A.1 - US STS-96
JULY -- 1999 - 1R - Russian
AUG -- 1999 - 2A.2 - US STS-101
OCT -- 1999 - 3A - US STS-92
DEC -- 1999 - 4A - US STS-97

After years of delays, hardware for a new space station is finally in orbit about the Earth. The first space station component, the Zarya Control Module, also known as the Functional Cargo Block and the Russian acronym FGB, was successfully launched by the Russians this week from the Baikonur Cosmodrome in Kazakhstan, not far from where Yuri Gagarin became the first human to be launched into space over 37 years ago. Zarya, the Russian word for sunrise, had a flawless liftoff into an overcast sky at 11:40 a.m. local (Kazakhstan) time, November 20, 1998, enclosed in the nose fairing of a Russian Proton rocket.

The first U.S.-built station component, the "Unity" connecting module, is targeted be launched aboard the Space Shuttle Endeavour on December 3, 1998. STS-88's six-person international crew will rendezvous with the Zarya Control Module and conduct three spacewalks to attach Unity to Zarya.

See the See the NASA SSHIO Flight 2A web page for more information about the Unity space station component.

19981201-GS

The Mars Climate Orbiter will be launched in December of 1998 on a Delta II rocket. It will be followed about 3 weeks later by the Mars Polar Lander, also launched by the same rocket system. The Jet Propulsion Laboratory will supervise both missions.

The Orbiter spacecraft will have a 10 month journey to the red planet. On about Sept. 23 1999, it will commence an aerobraking manuver to acheive Mars orbit insertion (MOI). This eliptical capture orbit will be incrementally reduced by successive passes through the thin upper atmosphere. After about 2 months the orbit will be circularized using onboard hydrazine thrusters into a circular polar mapping orbit (altitude ~ 400 km.)

The overall theme of the 2 part Mars Surveyor '98 mission is "volatiles and climate history". Once the Mars Climate Orbiter reaches its final orbit it will commence surface mapping, while another instrument package is analyzing the atmospheric composition and weather. The spacecraft will also act as a data link to relay information from its companion spacecraft (the Mars Polar Lander) back to Earth. The atmospheric sounding and imaging phase is scheduled to last for one Mars year (687 Earth days).

In its role as a data relay the Mars Climate Orbiter should be operational for at least 5 years. This will allow an encore data relay performance for the '01 Mars mission, arriving in January 2002.

JW

While the Mars Climate Orbiter surveys the planet from on high, the Mars Polar Lander will conduct its mission from the Martian surface.

The Mars Polar Lander must decellerate from 7 km/sec to 2.4 meters/sec for a safe Martian touchdown. This will be accomplished by aerobraking with an ablative heatshield, a parachute deployment and a final rocket propulsion firing for a soft landing. The destination is ~80 degrees S., the first lander in a polar region. This high latitude region has "layered terrain" which should have water ice near the surface and might show evidence of past climatic variations. Certainly new insights will be gained into the seasonal ice caps (CO2 ice) and polar weather. The lander will have a robotic arm for trenching, cameras, and atmospheric sensors. Its primary mission is 90 days.

JW

Piggybacked on the Mars Polar Lander spacecraft are 2 "microprobes". After 11 months in transit the microprobes will separate from the lander spacecraft for a passive atmospheric entry. These spacecraft are designed to survive an 80,000 G impact and be the first probes to gather subsurface data. Scientist hope these probes will help discover clues to Mars' past climate, including the apparent mystery of the "dissapeared" surface water. Does the water that may have caused the erosional features we can see today now exist as permafrost? If so, what implications would that have for possible life forms? Information on soil temperature, ices, air pressure, and solar measurements will all be relayed to the Orbiter, which will be overhead 10 times a day to relay the data back to Earth.

JW

The primary goal of the Stardust mission is to collect and comet dust and volatile samples of comet Wild 2, and samples of interstellar dust grains, and return the samples to Earth for analysis. The spacecraft will also send back images of the comet, counts of comet particles striking the spacecraft and conduct real-time analysis of the compositions of the particles and volatiles.

Stardust will use a unique substance called aerogel to capture and preserve the cometary and interstellar materials for return to Earth.

Stardust will be the first space mission ever to return extraterrestrial material from beyond the orbit of the Moon. Stardust is also the first U.S. mission dedicated solely to cometary research.

GS

Lunar-A's launch was originally scheduled for February or March of 1999. Due to problems with the penetrator batteries and an addition of an extra orbiter battery and removal of one of the three penetrators, the launch has been rescheduled for August or September, 1999.

19981202-GS

Lunar-A is a Japanese lunar orbiting mission. Lunar-A will carry a mapping camera and two 13kg surface penetrators. The surface penetrators are equipped with seismometers and devices to measure heat flow. The seismometers will monitor moonquake activity over the course of a year and this information will be used to learn about the structure of the Moon's interior and the size of the core. The heat flow measurements will provide information on the thermal state and evolution of the Moon. The penetrators will be individually released and impact the Moon at 250 to 300 m/s, burrowing 1 to 3 meters into the surface. Each penetrometer contains a two-component seismometer, a heat flow probe, a tiltmeter, an accelerometer, a radio transmitter and an antenna. The instruments are powered by Li-SOCL2 (super lithium) batteries with an expected lifetime of one year.

After deploying the penetrators, the orbiter will move up to a 200 to 300 km near circular mapping orbit. Data will be stored in memory in the penetrators and transmitted to the orbiter when it transits over each penetrator every 15 days.

A monochromatic mapping camera with a resolution of 30m will be used to take images near the terminator, where the lighting will enhance subtle topographic features.