Heavy mobile reusable space transportation system with the use of
surface-effect vehicle G.A.Dolgopolov, R.K.Ivanov,
M.M.Kovalevsky, V.P.Nikitsky, I.V.Yantchevsky Air Launch Aerospase Corporation 9, Druzhinnikovskaya Street, Moscow, 123242, Russia Tel: (495) 205 2733, fax: (495) 205 4979 The present paper shows the results of
preliminary design research on a heavy mobile reusable space transportation
system (H RSTS) for the realization of prospective space programs such as establishment
of permanent lunar bases for the use of lunar resources, deployment and
servicing of on-orbit solar power plants, establishment and support of space
industrial production, and other programs requiring a high payload delivery
rate. The suggested RSTS with horizontal takeoff and
landing is developed in a two-stage version with the use of a reusable
spaceplane (RSP) air-launched from a large-capacity surface-effect vehicle (SEV)
serving as the first stage. The takeoff from the water makes it possible to
develop a SEV with virtually any payload capacity without constructing
special-duty airfields, and the RSP improved energy performance due to the air
launch at an altitude of 8 - 9 km allows for the RSP developing on the basis of
conventional rocket technologies with the use of liquid OX/hydrogen propulsion
units. To achieve the RSTS maximum payload capacity and
to place payloads into orbits with any inclination, it is suggested to launch
RSTS from near-equatorial zones where, at the offshore refuelling complex, the
RSP is loaded with cryogenic propellant components and the SEV is refuelled. As a result of an integrated design research
carried out with due regard to the required ground launch preparation
facilities, the following technical and cost-performance characteristics have
been obtained: -
RSTS liftoff weight - 1,850-2,100 tons; -
Payload weight to equatorial baseline orbit of 200 km in altitude: -
with RSP orbiting 25-34 tons; -
without RSP orbiting - 50-60 tons; -
Development
costs - USD 12.5-14 Billion; -
Launch
cost - USD 30-40 Million; -
Project development stage - 8-10 years. The
comparison between the suggected H RSTS and expendable space launch vehicles of
a similar payload capacity, carried out for a payload delivery rate to
near-earth orbit of about 500 tons per year as applied to the US Moon
exploration program, has demonstrated a decided superiority of the H RSTS in
regard to the total development and operating costs. The suggested H RSTS can be built around available
Russian technologies of the development of heavy surface-effect vehicles. Gennady Aleksandrovitch Dolgopolov, S.P.Korolyov
"Energia" Space-Rocket Corporation, Chief expert. Corresponding Member of the
K.E.Tsiolkovsky Russian óosmonautics
Academy. Sphere of scientific interests: space aeromechanics. Robert Konstantinovitch Ivanov, "Air Launch
Aerospase" Corporation, Chief Designer. óandidate of Engineering Sciences, Full Member of the K.E.Tsiolkovsky
Russian óosmonautics Academy.
Sphere of scientific interests: design of aerospace systems and
rocket-and-space complexes. Mikhail Markovitch Kovalevsky, "Air Launch
Aerospase" Corporation, Chief manager. Sphere of scientific interests: design
of aerospace systems and rocket-and-space complexes. Vladimir Petrovitch Nikitsky, International Scientific-Technical Center of Spacecraft Payloads, Director-General. Doctor of
Engineering Sciences, professor, Full Member of the K.E.Tsiolkovsky Russian óosmonautics Academy. Sphere of scientific
interests: cosmonautics. Igor Vladimirovitch
Yantchevsky, PO "Computer Engineering and Computer-Aided Facilities",
Director-General. óandidate of
Engineering Sciences. Sphere of scientific interests: information technology
and computer engineering. |
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