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Isc Kosmotras (International Space Company Kosmotras) ISC KOSMOTRAS (INTERNATIONAL SPACE COMPANY KOSMOTRAS) International Space Company (ISC) Kosmotras (a Joint Stock Company) was established in 1997 under the Russian law. The company’s principal office is located in Moscow, Russia. ISC Kosmotras core business activities are associated with implementation of the Russian Federation programs for elimination of the SS18 Intercontinental Ballistic Missiles (ICBMs) through their withdrawal from service and use in the Dnepr Space Launch System (SLS) for launching spacecraft into low earth orbits. ISC Kosmotras shareholders are a team of leading scientific research and manufacturing entities of Russia and Ukraine that built, under ISC Kosmotras supervision, the Dnepr SLS and today exercise the followon oversight of its operation. Since the inaugural Dnepr launch in April 1999, ISC Kosmotras has been actively present on the world launch services market. The launch service customers were space agencies and commercial companies from France, Germany, Italy, Japan, Saudi Arabia, South Korea, Thailand, UK, USA and other countries. ARCHITECTURE OF DNEPR PROGRAM OPERATIONS 4 5 The National Space 6 1 The Russian Federal The State Space Launch сustomers Agency Agency of the Republic Space Agency (FSA) of Ukraine (SSAU) of Kazakhstan 7 2 Central Research Institute Ministry of Defense of the ISC KOSMOTRAS of the Russian Federal Space Russian Federation 11 Agency (TsNIIMASh) 3 Central Research 10 9 8 Institute of the Russian Ukrainian Subcontractors in other Russian Ministry of subcontractors subcontractors countries Defense THE DNEPR PROGRAM (UTILIZATION OF SS-18 ICBMS FOR LAUNCHING SPACECRAFT ) The concept of ICBMs use as launch vehicles has been widely utilized since 1980s Availability of two launch sites: Baikonur Cosmodrome, Kazakhstan and Yasny (Dnepr and Rockot programs in Russia and Ukraine). Launch Base, Russia. High performance of baseline SS18 rocket. The SS18 ICBM is fully represented Availability of a backup rocket for each launch mission. in Dnepr LV, with its reliability level retained. Unique flight profile of LV Upper Stage up to spacecraft separation ensures SS18 ICBM upgrade for launching payloads into outer space does not involve any extremely high accuracy of insertion and orbit formation. This is confirmed by actual modification of baseline design of the original rocket. Thus, the high performance flight data gathered in the course of the Dnepr Program implementation. and reliability of the launch system are maintained. The team of Russian and Ukrainian companies that built and maintained operation of SS18 ICBM system is still in place for Dnepr Program. Use of underground silos protects the Launch Vehicle and Space Head Module (SHM) from exposure to adverse weather conditions, provides a capability for a long period of rocket standby in a readyforlaunch mode and enables to minimize acoustic impact on payloads. DNEPR LAUNCH CUSTOMERS Skybox Imaging Inc., USA CNES, France CalPoly Corporation, USA Space Flight Laboratory (SFL), Canada MegSat s.P.a Company, Italy INTA, Spain Innovative Space Logistics B.V. (ISL), Netherlands «La Sapienza» University of Rome, Italy SRI, Saudi Arabia The State Space Agency of Ukraine (SSAU) Bigelow Development Aerospace Division, LLC, USA ATSB Company, Malaysia Yuzhnoye State Design Office (YSDO), Ukraine SpaceQuest, USA TUBITAK UZAY, Turkey SSTL, UK TransOrbital, USA Japan Aerospace Exploration Agency, Japan Swedish Space Corporation, Sweden Deimos Imaging, Spain EIAST, UAE OHBSystem, Germany NPO Mashinostroeniya, Russia KARI, South Korea EADS Astrium, GmbH, Germany Academy of Sciences, Republic of Belarus 2 MAIN CHARACTERISTICS OF THE RS 20 MISSILE PAYLOAD FAIRING (PLF) DNEPR LAUNCH MAIN SPECIFICATIONS OF DNEPR LV Weight at Liftoff 210 tons GAS DYNAMIC SHIELD (GDS) VEHICLE Propellant Components UDMH + N O MAIN FEATURES 2 4 Number of stages 3 Orbit Injection Accuracy (H=300 km) 1st and 2nd LV stages are unmodified stages of the original SS18 ICBM. for altitude 4,0 km Upper Stage is an original SS18’s 3rd stage with modified control system flight software. for inclination 2,4 arc min ADAPTER WITH SC 3,0 arc min 36500 Space Head Module (SHM) design is based on the SS18 front section with several design for right ascension of the ascending node variations. Orbital inclination 98°, 64,5° UPPER STAGE During development and serial manufacture, the SS18 rocket underwent a large number of Flight Reliability 0,97 flight tests and today it is truly one of the most reliable launch vehicles on the launch services market. Flight Limit Loads : ND STAGE 2 longitudinal gload 7,5 lateral gload 0,8 integral acoustic pressure 135 dB 36500 PERFORMANCE TO CIRCULAR ORBITS 65° inclination orbit DNEPR LV 98° inclination orbit Standard Extended Standard Extended SHM SHM SHM SHM Launch site Orbit altitude (km) Payload mass, kg 1ST STAGE Yasny 1800 1650 3200 2950 300 Baikonur 1500 1450 — — Yasny 2000 1850 2950 2700 400 Baikonur 1700 1470 — — Yasny 2100 1850 2650 2400 500 Baikonur 1650 1450 — — Yasny 1700 1500 2000 1800 600 Baikonur 1350 1150 — — Yasny 1100 1000 1350 1200 700 CalPoly Corporation, USA Baikonur 800 750 — — INTA, Spain SRI, Saudi Arabia Yasny 600 450 700 600 ATSB Company, Malaysia 800 TUBITAK UZAY, Turkey Baikonur 450 350 — — Japan Aerospace Exploration Agency, Japan EIAST, UAE Ø3000 KARI, South Korea DNEPR SPACE HEAD MODULES AVAILABLE SHM CONFIGURATIONS Based on fl ight heritage and detailed market analysis, three types of Dnepr Space Head Modules were designed and are currently in production to maximize LV performance and use of payload envelope. Depending on specifi c launch mission re- quirements, ISC Kosmotras will offer an appropriate confi guration of the Dnepr Space Head Module (SHM), where cus- tomer’s satellite will be accommodated. SHM for a multiple small satellite mission (cluster SHM for midsize satel SHM for a largesize launch) lites satellite 4 DNEPR MISSION PROFILE Dnepr demonstrates outstanding accuracy of orbital insertion: DubaiSat2 (EIAST): semimajor axis – 3m, eccentricity – 0.00001 KompSat5 (KARI): semimajor axis – 550m, eccentricity – 0.0001 TanDEMX (DLR): semimajor axis – 220m, eccentricity – 0.000032 CryoSat2 (ESA): semimajor axis – 109m, eccentricity – 0.00015 YASNY LAUNCH BASE YASNY LAUNCH BASE IS LOCATED IN ORENBURG REGION, RUSSIA. The first Dnepr mission from Yasny Launch Base lifted off on June 12, 2006 successfully deploying Genesis1 satellite into its orbit. The Orsk international airport located in Orenburg Region, Russia, is capable of receiving any types of heavy aircraft. Spacecraft and their ground support equipment are transported from this airport to Yasny Launch Base. Assembly, Integration and Test Building (AITB) is furnished with the modern equipment and systems and meets the most stringent requirements to spacecraft prelaunch processing. The AITB has two clean rooms with cleanliness class of 30,000 (this parameter can be improved up to 10,000) and 100,000 respectively, and a fuelling station with a clean room of 30,000 cleanliness class appropriate for spacecraft loading with hydrazine and compressed gases. Yasny LB Baikonur YASNY LAUNCH BASE Cosmodrome Russian Federation MAIN ELEMENTS: Republic AITB, 3 clean rooms including of Kazakstan fueling station HotelAITB walkway Hotel complex Offices, recreation area, dining facilities and bar Green park area 6 LAUNCH PREPARATION ACTIVITIES 7. SHM loading into SHM 1. LV erected before installa transporteremplacer tion into launch silo 4. Autonomous space craft processing 5. Spacecraft fueling 8. SHM/LV mating 2. LV installation into launch silo 10. Dnepr liftoff 3. Spacecraft/GSE delivery to launch 6. SC/SHM integration 9. SHM integrated with LV site airport ISC KOSMOTRAS INTERNATIONAL SPACE COMPANY KOSMOTRAS MAIL ADDRESS: 7 Sergey Makeev Str., Bld. 2, Moscow, 123100, Russian Federation. PHONE: 7 (495) 745.72.61 FAX: 7 (495) 232.34.85 E-MAIL: [email protected] WEB: www.kosmotras.ru. 8.
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