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MARS BALLON FLOATAGING STATION. SCHEME OE.EXl'ERIMENT AND PROJECT-DYNAMIC PARAMETERS
R.S.Kremnev, G.N.Rogovsky, K.M.Pichkhadze, V.A.Vorontsov, V.Linkin J.Runavot, J.Blamont, C.Tarrieu
ABSTRACT
The planned Mars'94 soviet mission will include an aerostat as a vehicle to exploring the surface of the planet. This aerostate is to be designed and developed in the framework of the space cooperation between USSR and France. The mission of the ballon vehicle is to collect detailed information over various Mars surface sites. To meet this objective, the balloon flies daily using solar heating and moves to the next landing site pushed by the local winds. Therefore, the each day the aerostat will ivestigate a different place during its lifetime. The main challenge is to achieve a lightweight balloon, needed by the very low atmospheric density of Mars, able to provide a workable instrument platform. Several consepts have been considered, including a single gas balloon to dual balloon systems combining aerostatic gas and solar hot air effects. For all these consepts, the mechanical, thermooptical and leakage films properties have a major impact on the overall performance. Emphasis has been put on technological aspects as well as on the materials themselves and the envelopes manufacturing process.
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Sel f-contained smal l space tether systems Alpatov A.P., S.V.,
Be l onozhko P.A.,
:Khoroshilov V. S.,
( I nstitute of Sciences,
Dranovsky V.L.,
Grigor'yev
Pirozhenko A. V.
Technical
�chanics
of
Ukrainian
Academy
of
Design Bureau " Yuzhnoye", Dnepropetrovsk)
A creation of space tether systenB ( TS)
providing a great
deal of possibil ities in astronautics is connected to a number of qual itativel y
space TS movement theory mechanics, shown
as
that
well some
experimental considered to
A development of
new hard-solving probl enB. as
a
new
field
of
space
flight
as difficu lties arising TS depl oyment has problenB
studies. have
And
tether
of
space
if
main
length
TS
needs
space from
TS
tens
kil ometers then for treatment of depl oyment,
thorough
designs to
are
thousands
ways of placemant
and transportation the design of se l f-contained smal l space T S i s considered to be reasonable. km length and with tethered regarded
to
be
smal l
TS.
A tether system o f approx.
bodies
mass
of at1rospheric density,
measurements,
100
kg
is
e.g.
to study l atitude
to maintain exact base for
to create mul ti-el ement space systenB.
The studies
conducted
on design util ization of smal l T S
design incl ude anal ytical an d experimental TS deployment
to
This design utilization has both
scientific and practical appl ications, variation
up
1
dynamics,
investigations
of
defining of the main regul arities of
system motion in operational regims,
creating the patterns of
the units of system and experimental study of their operation. The paper
is
devoted
to
investigation procedures.
the
main
resul ts
of
study
and
Tbaes of
a
report
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Automatic dJnamlc test eomplex ol JDUltillUpport lnltaiow fre