(Sanitized)FLIGHT PATH

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP71B00185A000100060237-5
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 4
• Document Creation Date: December 12, 2016
• Document Release Date: May 7, 2002
• Sequence Number: 237
• Content Type: MISC

Approved For Release 2002/06/1471 B00185A000100060237-5
25X1A
FLIGHT PATH
During the Winter season and early Spring, the atmosphere
at 80-110,000 feet is dominated by 1 to 3 intense low cells which
surround the North Pole. At least one of these cells is usually
located over the northern portion of the USSR. The resultant flow,
which exists about 95% of the time is from northwest Europe or the
Mediterranean Sea area, over the site-of interest, thence to Mongolia.
About 90% of the time the winds flow from the west over the eastern
USSR to the Arctic Ocean and Alaska. About 10% of the time the
wind flow from Mongolia may be from the west, over Sakhalin to
the Sea of Skhotsh.
If the balloon is capable of descent to 50, 000 feet over
Mongolia/North China, the probability of a trajectory to the east,
toward Hokkaido, rather than northeast would increase to approximately
80%. The 10% to 80% change in probability is not a linear change
with altitude. The 10% probability remains constant from 100, 000
feet to 65, 000 feet followed by a rapid increase to near 80% at 50, 000
feet.
Approved For Release 2002/06-/14 CIA-RDP71 B00185A000100060237-5
 Approved For Release 2002/06/14: A- P71 B00185A000100060237-5
ALTITUDE PROFILE
In balloon flight profiles using a Super Pressure Vehicle with
adequate balance between payload and lift capability, the altitude
fluctuation is dependent mainly on pressure layers and diurnal
super heating effects. A maximum altitude variation of 5K ft. has
been estimated throughout a 6-day period after launch based on
permeability data and field tests performed with balloons.
Experience is limited on long, high altitude balloon flights
because prior programs were directed toward systems that could be
recovered after a short flight to altitude.
The attached chart is the predicted altitude profile that
can be achievable with the present materials and state of the art.
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 Approved For Release 2002/06/' M f DP71 B001854Q00100060237-5
DESTRUCT MECHANISM
Destruct system considerations:
Several methods to destruct the balloon-borne system
have been considered for the main purpose of preventing the real
mission of the unit from being divulged. The primary requirements
for a destruct system are:
1. The destruct function should not be accompanied
by open flames, blast, noise scattering of parts, corrosive liquids,
or any other mechanism which might be hazardous to personnel,
create fires, or initiate rumors that chemical or pyro warfare va s
being employed.
2. Destruction would be only limited to the electronic
circuits to prevent disclosure of its capability or application.
3. The system should not create a hazard when handled
during system processing and deployment.
The mechanism and philosophy proposed for develop-
ment of the destruct system include:
1. The electronic circuits will be etched on a pyro-
insulation board which can be "fired" electrically. This will cause the
circuits to melt and displacement of the components which are not
melted. This will make analysis of the circuits and deduction of
their functions difficult.
2. The "burning" will be continued within the electronic
housing which contains oxygen bearing chemicals to support high
level combustion.
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Destruction may occur under the following conditions:
1. Loss of altitude sensed at the deployment phase,
using an ascent rate sensor, and at descent from operational altitude.
2. A reduction in battery voltage.
signal.
3. On command through a radio link using a coded
4. A timer may be used to limit the maximum mission
time if desired.
Approved For Release 2002/06/14: CIA-RDP71 B00185A000100060237-5