Seventh International Aerospace Congress IAC'12
Dedicated to the 55th Anniversary of the launch of the First Artificial Satellite of the Earth
Section 5. PROPULSION SYSTEMS AND FUELS
DEVELOPMENT OF HYBRID ENGINES CONCEPTS FOR ADVANCED AIRLINERS
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"ELECTRIC" GASTIRBINE ENGINE SYSTEMS
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EVALUATING THE EFFECTIVENESS OF THE ENGINE BASED ON SOLID OXIDE FUEL CELLS FOR LONG-HAUL AIRCRAFT
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CONTROLLED HYDROGEN GENERATOR FOR INDEPENDENT POWER PLANTS BASED ON OXYGEN-HYDROGEN FUEL CELLS
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TRI-PROPELLANTDUAL-MODE SUSTAINER ROCKET ENGINE FOR AEROSPACE SYSTEMS AND LAUNCH VEHICLES (LVS) OF A NEW GENERATION”
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DEVELOPMENT OF THE MOST POWERFUL IN THE WORLD OF OXYGEN-KEROSENE LIQUID ROCKET ENGINE WITH A VACUUM THRUST AT 9.8 MN
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PULSE-PERIODIC GASDYNAMIC CONTROL OF COMBUSTION MODES IN SUPERSONIC FLOW
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Processes of mixing and burning In the compact combustor under the air stream swirling at the entrance
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INVESTIGATION OF WORKING PROCESS IN THE COMBUSTOR OF COMBINED RAMJET ENGINE WITH ASYMETRICAL AIR-INTAKE
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TOWARDS METHODOLOGY OF EFFECTIVE THRUST EXPERIMENTAL ASSESSMENT IN INTEGRATED HIGH-SPEED AIR-BREATHING VEHICLE.
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THE RESULTS OF EXPERIMENTAL STUDIES CONTROLLED PROJECTILE ELEMENT WITH AN IMPULSE JET ENGINE FUEL IN THE PASTE
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ON GENERATION OF THRUST BY ACCELERATION OF SOLID PROJECTILES
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WORKING OUT AND RESEARCH OF PERSPECTIVE SYSTEMS OF COOLING OF HEAT-STRESSED DESIGNS OF AVIATION ENGINES AND POWER INSTALLATIONS
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METHODOLOGY of DESIGNING of IMITATING TESTS of heat-stressed designs of aviation engines SAVING up the RESOURCE And POWER INSTALLATIONS AT LIFE CYCLE STAGES
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TECHNOLOGIES OF OPERATIONAL DEVELOPMENT OF HEAT-STRESSED DESIGNS OF AVIATION ENGINES AND POWER INSTALLATIONS AT THE STAGE OF KONSTRUKTORSKO-TECHNOLOGICAL WORKING OFF OF THE SKILLED PRODUCT
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TEST METHODS OF AVIATION ENGINE CASING CONTAINMENT WITH MODELING OF BLADE RELEASING
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TEST METHODS OF AVIATION GTE DISKS WITH MODELLING OF THE OPERATIONAL TEMPERATURE FIELDS
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REMARK TO SELECTING OF PARAMETERS OF LOAD REDUCTION DEVICE FOR STRENGTH ELEMENTS OF TURBOJET DOUBLE-CIRCUIT ENGINE (TDCE) AFTER FAN BLADE BREAKAGE
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TECHNIQUE OF SYNTHETIC LIQUID FUEL STRUCTURE OPTIMIZATION
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APPROACHES TO MATHEMATICAL MODELING of the POWER PLANT With dual-MODE SCramjet composed of hypersonic aircraft ON INITIAL design STAGE
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ROCKET LIQUID PROPELLANT COMPONENTS WITH HIGH–MOLECULAR ADDITIVES ARE THE REAL WAY TO EXPAND THE CAPABILITIES OF ROCKET AND SPACE COMPLEXES
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EXPERIENCE AND PROSPECT OF DOMESTIC ROCKET ENGINEERING BASED ON THE EXAMPLE OF OAO “NPO ENERGOMASH NAMED AFTER ACADEMICIAN V. P. GLUSHKO” |
Abstracts should
reach the Organizing Committee by May 15, 2012.
NEW Extended: June 1, 2012
Correspondence
Professor Mark Liberzon
IAC’12
Petrovka Str., 30/7, Bld. 1, off. 7, Moscow, 127006, Russia
Tel.: +7 (495) 694-2727
Fax: +7 (495) 650-6010
E-mail:
elena@fund.ru
www.fund.ru