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ISC «KOSMOTRAS» DNEPR PROGRAM ISC Kosmotras Proprietary Dnepr Program Background (use of SS-18 ICBM technologies for commercial spacecraft launch missions) • Concept of ICBM use as commercial launchers has been widely utilized since 1980s (in Russia and Ukraine, under the Dnepr, Rockot, Strela and Start programs). • Soviet-American treaties on strategic offensive arms provided for elimination of heavy SS-18 ICBMs. Currently, such obligations are no longer valid for Russia. • High performance of baseline SS-18 rocket. The SS-18 ICBM is fully represented in Dnepr SLS, with all its reliability features retained. • SS-18 ICBM upgrade for launching payloads into outer space does not involve any modification of baseline design of the original rocket. Thus, the high performance and reliability of the launch system are maintained • The team of companies that developed and maintained operation of SS- 18s is still in place for Dnepr SLS. ISC Kosmotras Proprietary 1 Specifics of Dnepr Program • Use of proven rocket technology and ground infrastructure. 16 successful launches were performed under the Dnepr program with the orbit injection of 64 spacecraft and payloads for the UK, Germany, France, USA, Japan, Italy, Egypt, Malaysia, and other countries. • Use of silos makes a launch possible under virtually any weather conditions and offers a long period of rocket standby in a ready-for-launch mode. • Steam ejection from silo minimizes acoustic impact on payload. • Availability of two launch bases: Baikonur Cosmodrome, Kazakhstan and Yasny Launch Base, Russia. • Availability of a back-up rocket for each launch. • Unique upper stage flight profile at spacecraft separation ensures extremely high accuracy of insertion and orbit formation. This was confirmed by actual flight data gathered in the course of the Dnepr Program implementation. ISC Kosmotras Proprietary 2 Typical Dnepr Mission Organization Launch Customer National Space Agency of Russian Federal State Space Agency Kazakhstan Space Agency Russian MoD of Ukraine (FSA) Central Research Russian MoD Institute of FSA ISC Kosmotras Central Research (TsNIIMASh) Institute Russian Ukrainian Subcontractors in other Subcontractors Subcontractors counties ISC Kosmotras Proprietary 3 Typical Dnepr Launch Mission Flow Pre-contract Launch contract Launch contract Mission & SC/ LV negotiations with launch negotiations signature customer compatibility analysis Critical Design Phase – Preliminary Design Phase PDR, signature of development of – development & release ICD (Ver.1). Release manufacturing of preliminary design of input data for Manufacture of ground documentation. CDR, documentation, manufacturing test and flight hardware signature of ICD (final including ICD documentation Ver.) and ‘go’ for HW manufacturing SC launch and provision of SC separation and SHM ground Delivery of LV, SHM, SC Launch campaign - LV, initial orbit parameters qualification test and GSE to launch site SHM and SC processing campaign (with SC for launch at launch site data to customer dummies) ISC Kosmotras Proprietary 4 Dnepr Launch Customers SSTL, UK • SRI, Saudi Arabia • Swedish Space Corporation • ATSB Company, Malaysia • OHB-System, Germany • SpaceQuest, USA • CNES, France • Trans Orbital, USA • Japan Aerospace Exploration Agency • Academy of Sciences of the • Bigelow Development Aerospace Republic of Belarus Division, LLC, USA • NPO Mashinostroeniya, Russia • EADS Astrium, GmbH • Yuzhnoye SDO, Ukraine • EAST, UAE • Cal Poly Corporation, USA • MegSat s.P.a Company, Italy • Deimos Imaging, Spain • “La Sapienza” • INTA, Spain University of Rome, Italy • TUBITAK UZAY, Turkey ISC Kosmotras Proprietary 5 The Dnepr Space Launch System consists of the following elements Launch Vehicle with Launch Complex with Launch Vehicle, Set of Telemetry, the Space Head the Launch Control Spacecraft and Data Collection and Module Center Space Head Module Processing means Processing Facilities ISC Kosmotras Proprietary 6 Main Specifications of Dnepr LV 1st and 2nd LV stages are unmodified standard SS-18 ICBM stages. 3rd stage is a standard SS-18’s 3rd stage with the modified control system flight software. Space Head Module design is based on the SS-18 front section with several design variations. At the stage of development and production-run manufacture SS-18 rocket underwent a great number of flight tests and today it is truly one of the most reliable LVs on the launch services market. Dnepr LV Basic Data Total launch mass 210 tons Propellant components for all stages UDMH + N2O4 Number of stages 3 Spacecraft injection accuracy •For altitude 4,0 km •For inclination 0,04 deg •For the right ascension of the ascending node 0,4 min Orbit inclination 98°, 64,5° Flight reliability 0,97 Loads affecting the spacecraft: •Maximum axial quasi-static g-loads 7,5 •Maximum lateral quasi-static g-loads 0,8 •Integral level of sound pressure 140 dB ISC Kosmotras Proprietary 7 Dnepr LV Performance Characteristics for Circular Orbits (kg) 98◦ Inclination 65◦ Inclination Launch Base Orbit Altitude, km Standard SHM Extended SHM Standard SHM Extended SHM Payload mass, kg Yasny 300 1800 1650 3200 2950 Baikonur 1500 1450 - - Yasny 400 2000 1850 2950 2700 Baikonur 1700 1470 - - Yasny 500 2100 1850 2650 2400 Baikonur 1650 1450 - - Yasny 600 1700 1500 2000 1800 Baikonur 1350 1150 - - Yasny 700 1100 1000 1350 1200 Baikonur 800 750 - - Yasny 800 600 450 700 600 Baikonur 450 350 - - ISC Kosmotras Proprietary 8 Dnepr Measured Injection Accuracy Cluster Launch, 2009 Demeter, Launched in 2004 Orbital Parameters Deviation Orbital Parameters Deviation Semi-major axis, km Eccentricity Inclination, deg SC Semi-major axis, km Eccentricity Inclination, deg Actual Actual Actual Actual Actual Actual ICD ICD ICD ICD ICD ICD Value Value Value Value Value Value ±3.0 -0,081 ≤0.001 0,00029 ±0,04 -0,0037 AprizeSat-3 ±4,0 -0,11 <0,0008 0,00001 ±0,04 -0,0033 NanoSat-1B ±3,0 0,04 <0,0007 0,00001 ±0,04 -0,0035 TerraSAR, Launched in 2007 AprizeSat-4 ±4,0 0,33 <0,0008 0,00003 ±0,04 -0,0030 Orbital Parameters Deviation DMC-2 ±4,0 0,60 <0,0008 0,00007 ±0,04 -0,0034 Semi-major axis, km Eccentricity Inclination, deg ± ± Deimos-1 4,0 0,65 <0,0008 0,00007 0,04 -0,0035 Actual DubaiSat-1 ±2,5 -0,02 <0,0005 0,00008 ±0,04 -0,0033 Actual ICD Actual ICD Value ICD Value Value RapidEye, Launched in 2008 ±2,000 0.100 <0,0004 0.0001 ±0,04 0.01 30 25 THEOS, Launched in 2008 20 Orbital Parameters Deviation 15 Semi-major axis, km Eccentricity Inclination, deg 10 Actual Actual Actual ICD ICD ICD 5 Value Value Value 0 ±2,0 -1,12 <0,0004 0,00017 ±0,035 0,021 5 -0.12 -0.09 -0.06 -0.03 0 0.03 0.06 0.09 0.12 -5 major axis, km -10 - PRISMA, Launched in 2010 -15 Semi Orbital Parameters Deviation -20 Semi-major axis, km Eccentricity Inclination, deg -25 Actual Actual Actual ICD ICD ICD -30 Value Value Value Inclination, deg ±3,0 0,278 <0,0004 0.0001 ±0,04 0,01 ISC Kosmotras Proprietary 9 Available Configurations of Dnepr Space Head Module (SHM) 7450 5250 5250 Extended SHM for a SHM for a multiple small satellite SHM for mid-size satellites large-size satellite mission (cluster launch) ISC Kosmotras Proprietary 10 • SC dummy/SHM fit-check • Vibration tests of assembled SHM • SCdummy/ SHM elements separation tests • Separation shock tests • SC adapter static tests • Test runs of LV control system and checkout equipment • Tests of SC electrical interface • Tests of mechanical ground support equipment (MGSE) ISC Kosmotras Proprietary 11 ISC Kosmotras Proprietary 12 Off-loading from Antonov-124 at Orsk Airport ORSK Yasny Off-loading at Yasny Launch Base Transportation to AITB, Yasny Launch Base ISC Kosmotras Proprietary 13 Autonomous SC processing SHM/SC integration ISC Kosmotras Proprietary 14 ISC Kosmotras Proprietary 15 ISC Kosmotras Proprietary 16 Dnepr Steam Ejection from Silo 1. Black powder gas generator activated 2. LV expelled from silo 3. Protective tray separated 4 4. Protective tray jettisoned 3 2 7 6 1 5 5. First stage motor ignited 6. Sealing rings dropped 7. LV powered flight started ISC Kosmotras Proprietary 17 Mission Profile Отделение Fairingобтекателя drop Разворот3rd stage 3-й “flipступени-over” 2Отделениеnd stageseparation 2-й ступени Работа2nd stage 2 -poweredй flight ступени Отделение1st stage separation 1-й ступени Работа1st stage 1 -poweredй flight ступени ОтделениеSC separation КА СтартLiftСтарт-off Separation of GDS/ SHMОтделение upper platform stackплатформы с ГДЭ rd 3Работа stageРабота 3 powered-й 3ступени--й ступени flight ISC Kosmotras Proprietary 18 Kosmotras Launch Bases and Dnepr LV Flight Routes 1st stage drop zone, incl. 64.5 deg 1st stage drop zone, SSO 1st stage drop zone, SSO ISC Kosmotras Proprietary 19 Two Launch Sites are Available: Baikonur Cosmodrome (Republic of Kazakhstan) and Yasny Launch Base (Russia) Baikonur Cosmodrome Yasny Launch Base 12 Dnepr launch missions performed from Baikonur 5 Dnepr launch missions flew from Yasny: in July 2006, Cosmodrome during 1999 - 2010. June 2007, October 2008, June 2010 and August 2011. Payload processing is performed in Assembly, Yasny launch base is located 110 km far from the airport Integration and Test Building (AITB) and offices of Orsk, Orenburg Region, Russia. available at Site 31 and launch pad (silo) at Site 109. Payload can be transported from Orsk airport to Yasny Distance from Town of Baikonur to AITB, Site 31 is 60 launch base either by road or by rail. km. SC fuelling is performed in a separate building, where the SC has to be transported. ISC Kosmotras Proprietary 20 YASNY LAUNCH BASE ISC Kosmotras Proprietary 21 Yasny Launch Base Infrastructure AITB with clean rooms and satellite fueling facility. Admin & Hotel Complex with accommodation rooms, dining facilities and offices. Launch pad (silo) with blockhouse that will host the satellite health status monitoring center (customer’s EGSE and personnel). Launch vehicle storage and processing facilities. Utilities and networks that support launch base functioning.
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