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Access to Space in Europe: Current situation and perspectives ECSITE Toulouse, May 31 st, 2012

Access to Space in Europe: Current situation and perspectives ECSITE Toulouse, May 31 st, 2012 Christophe BONNAL Senior Expert – Technical Directorate CNES Launcher Directorate Christophe.bonnal@cnes.fr. Access to Space.  High altitude – High velocity :. Drawing from Newton 1687.

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Access to Space in Europe: Current situation and perspectives ECSITE Toulouse, May 31 st, 2012

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  1. Access to Space in Europe: Current situation and perspectives ECSITE Toulouse, May 31 st, 2012 Christophe BONNAL Senior Expert – Technical Directorate CNES Launcher Directorate Christophe.bonnal@cnes.fr

  2. Access to Space  High altitude – High velocity: Drawing from Newton 1687 ( 1687 ! ) This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  3. Access to Space  Launch into orbit: a never ending fall  High altitude – High velocity: An object released from a height of 4.9 m falls in 1 second, whatever its initial horizontal velocity Released with a horizontal velocity of x m/s, the object covers x m before impacting ground But Earth is spherical: over 7.900 m, ground “lowers” by 4.9 m Therefore, an object launched with a horizontal velocity of 7.900 m/s falls without ever hitting ground; it is orbited This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  4. Access to Space Mars This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  5. Access to Space  Little mission problem: • Given a large ATV satellite ATV, 20 tons, on ground  Altitude = 0, Velocity = 0 • How to send it towards International Space Station  Altitude 350 km, Velocity 7.7 km/s ? • Required energy: 33 MJ/kg Variant • Given a large GEO satellite, 8 tons, on ground  Altitude = 0, Velocity = 0 • How to send it towards the other 360 active satellites on the GEO ring  Altitude 35800 km, Velocity 3.1 km/s ? • Required energy: 58 MJ/kg This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  6. Propulsion  Rocket propulsion: Principle of Action & Reaction: “ Ejection of a mass in one direction leads to a reaction in the opposite direction”  Principle known since Antiquity: . Eolipyle (Heron of Alexandria, 2nd century BC) . Chinese rockets, fireworks . Propulsion of small chariots (XVIIème)  Konstantin Tsiolkovski proposes in 1883 to use this principle to “cross the limits of atmosphere and to conquer space around the Sun” This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  7. Propulsion  Rocket propulsion: Fundamental equation of Rocket Propulsion: mass m ejected at velocity w  mass M aquires a velocity V in the opposite direction  Conservation of the quantity of movement (product of mass and velocity): m.w = M.V  Derival versus time (= variation over infinitely small durations): F = M. = q.wwith q mass flow (kg/s), w ejection velocity (m/s), M rocket mass,  acceleration (m/s²)  A rocket engine only aims at ejecting as much mass as possible, as quickly as possible ! w Experience of Tsiolkovski V m M This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  8. Propulsion  Rocket propulsion: In 1 second: m = 1 kg w = 10 m/s • M = 740 t • V = 16 m/s •  = 16 m/s² m = 4300 kg w = 2800 m/s • M = 150 kg • V = 0,07 m/s •  = 0.07 m/s² This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  9. Access to Space This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  10. European launchers  Ariane 5: Fairing • Ariane 5: heavy lift launcher • 9.5 t GTO in ECA version • 20 t LEO-ISS (GS-ATV) • Ariane 5 lift off mass  766 t • 1 % corresponds to the mass of the satellite, • 9 % to the structure • 90 % to propellants • Its height is 50 m • (A building 20 stories high) • Power at lift-off  17 GW • Mean power (ATV launch)  1 GW • During 15 minutes Upper part payloads compartments Dual payload structure (SYLDA) Upper cryotechnic stage H14 (ESCA) Main cryotechnic stage H155 (EPC) Solid Rocket Booster P230 (EAP) VULCAIN 2 engine This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  11. European launchers  Ariane 5: Solid Rocket Booster EAP • 240 tons Solid Propellant • 36.5 tons structure: • Metallic cylinder made by fluo-spining • Maximal thrust 7000 kN each • Combustion time 130 sec • Interfaces with EPC: • 3 struts at the rear • Ball-bearing and elastomer device at the front, carrying all the thrust • Steerable nozzle: max 8° in any direction • Hydraulic control with lost oil This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  12. European launchers  Ariane 5: Main cryotechnic stage EPC • 174 tons cryotechnic propellants: • Liquid Oxygen: 149 tons; -183°C • Liquid Hydrogen: 25 tons; -250°C • Ø5.4 m; L 24 m; mean thickness 3mm; mini 1.5 mm • Dry mass with engine: 14.2 tons • Hydraulic flight control with lost oil • Maximal engine tilting: 8° Vulcain 2 Engine • Vacuum thrust  1350 kN • Gas temperature: 3200 °C • Chamber pressure: 11 MPa • LH2 turbopump: • Power 13 MW  2 TGV • Flow 6000 l/s This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  13. European launchers  Ariane 5: Main cryotechnic engine Vulcain Chamber pressure: 110 bar Gaz temperature: 3200 °C VULCAIN 1 Thrust  115T VULCAIN 2 • Hydrogen turbo pump : • Power 13 MW  2 TGV • Volumic flow 6000 l/s Thrust  135T This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  14. European launchers  Ariane 5: The upper stages EPS and ESC-A • EPS: storable propellants • Dry mass: 1290 kg • Structure made of Carbon-Alu honeycomb sandwich and tanks in Light alloy • Propellant mass: 10000 kg MMH & N2O4 in 4 tanks • Combustion time: 1100 s • Pressure: 1.1 MPa • Thrust: 29.5 kN • ESCA: cryotechnic propellants • Dry mass: 4600 kg • Propellant mass LOx, LH2: 14700 kg • Combustion time: 940 s • Thrust: 63 kN This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  15. European launchers  Soyuz in French Guiana: Soyuz = more than 1750 launches to date ! • Architecture: • 4 boosters = 1st stage 40 tons LOX-Kerosene • 2nd stage 94 tons LOX- Kerosene • 3rd stage improved wrt basic launcher, 23 tons LOX- Kerosene • 4th stage Fregat 5 tons UDMH-N2O4 • Fairing wide diameter  4.1m • Digital flight control • Performances from Guiana: • 5.6 t on 700 x 700 x 52° • 4.5 t on SSO • 3 t on GTO 5° • 1.2 t on GEO • 2 flights already done in 2011 This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  16. European launchers  Soyuz in Guiana: Fregat upper stage 1. S5.92 engine 2. Fuel tank (UDMH) 3. ACS tank (hydrazine) 4. ACS engines 5. Oxidizer tank (NTO) 6. Telemetry system antenna 7. Control system 8. Equipment bay cover-radiator 9. Telemetry and tracking system 10. Helium tanks 11. Chemical battery This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  17. European launchers  Vega: • High level requirements: • Small satellites market (< 1500 kg): 1.5 to 2 per year • Reference mission: 1500 kg on a polar 700 km / 700 km / 90° • Maximal launch rate  4 flights per year • Capable of a wide range of missions, including multiple payload launch • 1st flight in February 2012 • General description: • 3 stages with solid propulsions + 4th bi-liquid stage • Total length  30 m • Lift-off mass 137 t This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  18. European launchers  Vega: • 1st stage: 88 tons solid  3 m, L 10.5 m • 2nd stage: 24 tons solid  1.9 m, L 7.6 m • 3rd stage: 9 tons  1.9 m, L 3.6 m • 4th stage: 500 kg UDMH-N2O4 P/L adapter Interstage 3 / AVUM Interstage 1 / 2 Interstage 0 / 1 Interstage 2 / 3 P/L Fairing AVUM APM-AAM SRM Z9 SRM Z23 SRMP80FW This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  19. European launchers  Vega 1st stage: technological innovations: • Length: 10.5 m • Diameter: 3 m • Maximal Pressure: 95 bar • Combustion time: 107 s • Propellant mass: 88 t HTPB propellant with lower binder quantity Low cost, low density thermal protection Igniter simplified architecture Low torque, self protected, flexible bearing Cast carters Carbon filament-wound casing Low cost material (NAXECO) Mechanical shear ring Electrical actuation Simplified external thermal protection This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  20. Guiana Space Center Solid Boosters Integration Building Launcher Integration Building Final Assembly Building Launch Zone BIP BIL BAF ZL This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  21. CSG Launcher Integration Building This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  22. Guiana Space Center Transfer to Final Assembly Building and Payload Integration This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  23. CSG : Launch Zone This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  24. French Guiana: Soyuz Launch Zone This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  25. French Guiana: Soyuz Launch Zone This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  26. French Guiana: Soyuz Launch Zone This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  27. French Guiana: Soyuz Launch Zone This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  28. French Guiana: Soyuz Launch Zone This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  29. Guiana: Soyuz Launch Zone This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  30. CSG: Vega Launch Zone This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  31. CSG: Vega Launch Zone This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  32. CSG: Vega Launch Zone This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  33. CSG: Vega Launch Zone This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  34. CSG: Vega Launch Zone This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  35. Future European Launchers  Ariane 5 ME: Mid-Life Evolution: Very Long Faring Height: 20m (+ 3 m w.r.t. Current long fairing) Very long SYLDA (+3.1 m) Electrical System Adapted to new missions and new functional needs Synergies with A5ECA for obsolescence treatment EPC: Cryogenic Main Stage Stage mostly unchanged Reinforced JAVE New Cryogenic Upper Stage Propellant: 28t LH2/LOX Common bulkhead EAP: Solid Propellant Boosters Unchanged Propellant: 240 t Metallic case with Welded joints Engine: Vinci bi-thrust 180 kN – 130 kN Expander cycle Deployable nozzle Launch Base Reused ELA3 ground Infrastructure This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  36. Future European Launchers  Ariane 6 – Next Generation Launcher: • Wide range of missions • High modularity • On-going trade-off • Numerous possibilities ! This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

  37. Thank you for your attention Christophe.bonnal@cnes.fr This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA

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