; ; IR

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1 MS SATELLITE The MS satellite is designed for Earth Remote Sensing with the use of high resolution IR and multi-band imager. The satellite performs natural and man-caused disasters monitoring, reconnaissance, mapping and etc. Mass, kg ~ 200 Orbit: - altitude, km inclination, deg 98 Wavelengths for imaging modes, μm: - panchromatic multispectral ; ; IR Resolution in nadir, m 2.5 pan; 5 multi Swath width in nadir, km 15, for IR 55 Coverage area width, km ±420 Accuracy, deg Propulsion orbit support On-board memory, Gb 96 Transmission rate, Mbps 100 Frequency band for payload, MHz Frequency bands for radio-lines, MHz Lifetime, years

2 OPTOELECTRONIC OBSERVATION SATELLITE SICH-3-O The satellite is designed for optoelectronic observation of the Earth for mapping, land utilization, studies of meteorological processes, conditions of vegetation and soil cover, water resources as well as situations in emergency areas Mass, kg 1000 Wavelengths, μm: track and frame panchromatic imaging modes multispectral imaging mode ; ; Projection of pixel in nadir, m: panchromatic track/frame / imaging mode multispectral 1 2 / 2 3 track/stereoscopic imaging mode Imaged areas size, km: track panchromatic and multispectral imaging modes frame panchromatic imaging mode stereoscopic imaging mode 8 8 Lifetime, years 7 Off-track pointing distance, km: track mode ±500 frame mode ±80

3 RADAR OBSERVATION SATELLITE SICH-3-R Mass, kg 810 Payload synthesized aperture radar Wavelength, cm 3 Swath width, km 10 Ground resolution, m m 2 2 Minimum scattering cross-section for object detection, m 2 1 Off-track pointing distance, km ±500 The satellite is designed for radar observation of meteorological processes, monitoring of origination and behavior of cyclones, water resources, conditions of vegetation, intensity and amount of precipitation, and prediction of possible areas of disasters.

4 RADAR OBSERVATION SATELLITE SICH-3-RL The satellite is designed for radar observation of meteorological processes, monitoring of origination and behavior of cyclones, water resources, conditions of vegetation, intensity and amount of precipitation as well as prediction of possible areas of disasters Mass 900 Payload synthesized aperture radar Wavelength, cm 3 Coverage area width, km 450 or 700 (imaged area starts at a distance of 230 km to the right and left off-track) Resolution in coordinates, km in-track: 1.7 at the beginning of swath 2.5 (2.8) at the end of swath across track: 1.7 at the beginning of swath 1.3 (0.7) at the end of swath

5 LUNAR MISSION MULTI-PURPOSE SPACECRAFT LUNISAT WITH ELECTRIC-JET PROPULSION Mass at the Low Earth Parking Orbit, kg 450 Payload mass, kg 80 Altitude of Low Earth parking orbit, km 800 Duration of transfer to GEO, days near 210 Duration of transfer to the Earth escape trajectory, days near 150

6 COMPONENTS DEVELOPED BY YUZHNOYE

7 HEAT PIPES WITH CONSTANT THERMAL RESISTANCE FOR SPACE APPLICATION The heat pipes have characteristics that correspond to those of the best world pipes Material: aluminum alloy AD31-Т1, aluminum alloy 6060 Thermal resistance, K/W Pipe length, m up to 6 Density of the input flow, W/cm 2 up to 18 Working temperatures, K Heat carrier ammonia, propylene, methane, nitrogen, spirits, acetone, water

8 SATELLITE TRUSS MADE OF CARBON-REINFORCED REINFORCED PLASTICS Truss dimensions Truss mass mm 74 kg Truss elements made of carbonreinforced plastics by automated winding of plastics band

9 COMPONENTS Oxidizer Tank (Liquid Oxygen) Aft Bay Volume ~ l, Diameter 3900 mm, Length mm. Made of high-strength aluminum alloy. Waffle Structure. Mass ~800 kg, Diameter 3680 mm, Length 2325 mm. Made of aluminum alloy. Highly-efficient thermal protection is applied.

10 COMPONENTS Inter-stage Frame Fairing Mass ~700 kg, Diameter 3900 mm, Length 1500 mm. Made of high-strength steel, operating under cryogenic temperatures. Diameter 3900 mm, Length mm. Made of highly-strength aluminum alloy with highly efficient thermal protection, equipped with ventilating system.

11 COMPONENTS Dispenser Bellows Designed for installing 12 SC; Made of high-strength aluminum alloy; It is installed on the pipes with diameter of 400 mm. Equipped with ventilating and separation systems.

12 HONEYCOMB STUCTURES Element of a Fairing Heat shields of spacecraft Bases for solar panels Elements of heat insulation

13 UNITS MADE OF CARBON-CARBON MATERIALS Nozzle extension for Solid-propellant rocket engine Liquid-propellant rocket engine with uncooled nozzle extenstion made of carbon-carbon Elements of a nozzle unit

14 COMPONENTS AND ELEMENTS OF STRUCTURES MADE OF MULTI-LAYER LAYER METAL-COMPOSITES Steel-copper-brass composition Steel-aluminum bimetallic adapters Steel-aluminum composition Aluminum-copper compositions

15 UNITS MADE OF POLYMERIC COMPOSITE MATERIALS Aft bay Case of Solid Propellant Rocket Engine Metal-plastic ball gas container Coal-plastic truss for SC

16 PROJECTS PROPOSED FOR JOINT DEVELOPMENT

17 SPACE DISPOSAL OF HAZARDOUS WASTE The analysis of the ecological situation involving the increasing amount of waste of the atomic power stations shows that the issue of the waste isolating becomes extremely urgent for mankind. Isolation in space shall enable the globe to get rid of the long-lasting radioactive wastes forever unlike any other ways of burial on the planet.

18 At present there is a technical possibility to create a space rocket system for removing the highly radioactive waste into the remote space. weight of the annual radioactive waste of all the nuclear power stations of the country like e.g. Sweden or UK (10 GWatt), kg number of Zenit-3 LV launches for removing of such amount of radioactive waste the results of the project may serve a basis for launching a global program to remove the long-living radioactive waste from the Earth. - the cost of such a global program s implementation is estimated to be about 1 billion US dollars. - the expected profit is over 2 billion US dollars.

19 SOLAR KEY Space Solar Energy System The technology will be used for generating electric power from solar energy by application of special spacecraft and further energy transmission to users. At the areas of high sun light concentration there can be applied a number of reflecting spacecraft. The application of several spacecraft will make it possible to increase the power transmitted to the users. Re-reflecting spacecraft Re reflected energy ray Focal line Energy ray receiver Solar radiation density area Reflecting spacecraft Earth shadow Re-reflecting spacecraft 550 thousand km thousand km. Working part of concentration area

20 MICROSPACE Purpose of MICROSPACE is the injection of microsatellites into a wide orbit range using supersonic aircraft

21 LV MAIN SPECIFICATIONS Number of stages 3 Launch mass, kg 4945 Propellant mass, kg: I stage 3000 II stage 1070 III stage 120 Length, mm 8490 Diameter, mm 1090 Orbit injected SC mass, kg: H=500 km, i=97,4 deg 65 H=500 km, i=0 deg 107

22 REUSABLE SPACE TRANSPORTATION SYSTEM RASSVET LIQUID ENGINE RD-8 BASED DEMONSTRATOR OF RSTS TECHNOLOGIES Planer Fuel tank RD-8 engines Oxidizer tank Landing gear Booster

23 DEMONSTRATOR OF RSTS TECHNOLOGIES WITH RAMJET ENGINE View A

24 ALGORITHM OF RAMJET ENGINE DEVELOPMENT FOR REUSABLE FIRST STAGE OF RASSVET RSTS RD-8 Engine chamber Demonstrator of RSTS technologies Ramjet engine Multi-chamber module Suborbital airborne vehicle of the RSTS Ramjet engine 2G 0 =400т 1G 0 =200т

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28 Aerospace rocket complex Svityaz is determined for injection of different SC to the circular, elliptical and higher circular orbits including geostationary orbit. Aircraft An is developed by Aviation Science-Technical complex named after O. Antonov. It is the modification of serial aircraft An-225 Mriya. Svityaz LV is developed on the base of units, aggregates and systems of Zenit LV. It includes three stages and is working on nontoxic fuel components - liquid oxygen and kerosene.

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32 CONTACT DETAILS Stanislav Konyukhov General Designer- General Director Yuzhnoye SDO Alexander Degtyarev First Deputy General Designer- General Director Yuzhnoye SDO 3, Krivorozhskaya Street Dniepropetrovsk, UKRAINE, Phone: Fax: , Krivorozhskaya Street Dniepropetrovsk 49008, UKRAINE Phone: Fax: Oleg Ventskovsky Director European Representation Yuzhnoye SDO 20, rue Vautier, B-1050, Bruxelles, BELGIUM Phone/Fax +32 (2)