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Development of Propulsion Systems for Russia's Advanced Launch Vehicles

This article discusses the main lines of development of propulsion systems for Russia's advanced launch vehicles, including the use of reusable space rocket systems and the development of new engines.

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Development of Propulsion Systems for Russia's Advanced Launch Vehicles

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  1. FEDERAL SPACE AGENCY The main lines of development of propulsion systems for Russia advanced launch vehicles International conference “Europe space policy: ambitions 2015” Session 1. “General view on propulsion systems: LV of the future”

  2. PRESENT-DAY RUSSIAN LAUNCH VEHICLES

  3. DEVELOPMENT OF NEW RUSSIAN LAUNCH VEHICLES *- Reusable space rocket system for the first stage

  4. Engines РД-0124 РД-191 1 х РД-0124 Thrust: 30 tf Isp ~ 359 s Propellants: О2 + kerosene 5 х РД-191 Thrust: 5 х 196 tf Isp ~ 311 с Propellants: О2 + kerosene ENGINES OF “ANGARA-А5” LV «Angara-А5» LV

  5. OTV “Briz-M” is developedfor LV “Proton-M”. It isforeseen to use it jointlywith LV “Angara-A5” and“Angara-A3” Oxygen-hydrogen OTVis under development forLV “Proton-M”. On its basisKVRB for LV “Angara-A5”is under development Cryogenic upper stage 12KRBis developed for IndianLV GSLV OTV for LV “Angara-1.2”on the basis of central block of OTV“Briz-M” Multipurpose rocketmodule (URM-2) of the second and third stages of LV (new development) Second stage of LV “Angara-1.1” is under development on the basis of central block design for OTV “Briz-M” Engine RD-0124A is under development on the basis of engine RD-0124 for LV “Soyuz-2” Multipurpose rocketmodule (URM-2) of the first and second stages of LV (new development) Angara-1.2 Control system is unifiedfor all LV of the family.It is developed on the basisof CS for LV “Zenit” and “Proton-M” Angara-1.1 Angara-A3 Angara-A5 Engine RD-191 is under development on the basis of engines RD-170 for LV “Zenit” and RD-180 for LV Atlas • UNIFICATION OF LAUNCH VEHICLES OF “ANGARA” FAMILY.USE OF AVAILABLE SCIENTIFIC AND TECHNICAL WORKS AND TECHNOLOGIES

  6. MAIN TRENDS IN THE FIELD OF ROCKETAND SPACE ENGINE MANUFACTURING •  Increase of engine reliability (no less than 0.997 for sustainer LRE in LV). • Decrease of engine life cycle cost (development, manufacturing, operation). • Use of ecological propellant. • Increase of energy characteristics of engines. • Decrease of specific mass characteristics of engines.

  7. Launch vehicles evolution From multi-stage launch vehicles with vertical take-off, expendable LRE and SRM… 2030-2040 2025-2035 ...to single-stage launch vehicles with vertical or horizontal take-off, reusable ABE and LRE 2015-2020 1957-2000 Orbit insertion cost reduction 1 0,5 - 0,2 0,1 0,05 - 0,02

  8. THE FIRST PHASE OF DEVELOPMENT OF REUSABLE SPACE ROCKET SYSTEM RSRS-1 «RSRS-1» Takeoff mass – 935 t Payload mass in base line orbit Нcir = 200 km – 35 t(50 twhen using a solid booster) I stage propellants – oxygen and hydrocarbon fuel II stage propellants – oxygen and hydrogen Predicted reliability – 0.9995 Reusability of the first stage – 100return as an aircraft using supplementary turbojet engines Stage separation speed – 2500 m/s Payload Reusable stage Expandable II stage Booster The cost of SC injection is reduced by nearly half The mass of payload (delivered and returned) – 12 t

  9. Problems 1. Choice of propellants(oxygen + kerosene, oxygen + metane, oxygen + hydrogen) 2. Choice of engine cycle(generator gas exhaust cycle, staged combustion cycle, withadditional coolant-propellant) 3. Provision of strength and life characteristics(reusability of engine prior to overhaul 25) 4. Minimization of the cost of between – flight servicing 5. Metodology of test development 6. Ensuring reliability of multi-propulsion systems not less 0.999 7. Development of an effective system of diagnostics and emergency protection of engine and propulsion system as a whole REUSABLE LIQUID-PROPELLANT ENGINES

  10. ReusableLaunch Vehicle Europe-Russia cooperation Reusable Liquid Rocket Engines Propellant LOX-METHANE Vacuum Thrust, tf 200 - 400 Vacuum Specific Impulse, s 360 Mixture Ratio 3.5 Dry Engine Mass, kg 5000 Reusability 25 The Launch Vehicle with the winged reusable liquid-propellant booster and a expandable cryogenic stage

  11. To provide development of the oxygen - methane engine, the following scientific and technical problems are solved: • fuel-rich gas generation; • atomizing process (efficiency of working process in a combustion chamber c= 0.98); • chamber cooling (high cooling properties of methane and its thermal stability) • reliable ignition system • Available base • Experience in cycle-design study on Propulsion System • Tests of model engines on methane fuel

  12. cocoon(organic plastic) tetra(carbon phenolic material) Introduction of composites to use them in PS with LRE

  13. SOLAR THERMAL PS (SPPS)

  14. THERMAL ACCUMULATOR • TWO-MODE SOLAR THERMAL ENGINE • mode 1 – hot hydrogen • mode 2 – hot hydrogen + o2 SPPS LOCATION ON BOARD the LV

  15. SOLAR POWER PROPULSION SYSTEMFOR ORBITAL TRANSFER STAGES (OTS) OTS with SPPS OTS with conventional LRE SC mass in GEO, kg Sojuz-2fromKouru Angara-A3fromPlesetsk OnegafromPlesetsk OTS Briz-MKVRB Proton-M from Baykonur H-2AJapan CZ-3B China

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