Iranzo Ariane5 Lofa Rworkshop

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Iranzo Ariane5 Lofa Rworkshop

  1. 1. Ariane 5 – A European Launcher for Space Exploration Towards a European Infrastructure for Lunar Observatories - Workshop David Iranzo-Greus Head of Advanced Studies Launchers, Propulsion and Defence EADS SPACE Transporation Bremen, March 23 rd , 2005
  2. 2. Ariane 5
  3. 3. Ariane 5
  4. 4. Ariane 5 Flight
  5. 5. Ariane 5 is already a launcher for exploration SMART-1 – Ariane 516 Sept. 27th, 2003 Rosetta – Ariane 518 March 2nd, 2004
  6. 7. Ariane 5 options <ul><li>Reference Ariane 5 </li></ul><ul><li>Robotic exploration missions </li></ul><ul><li>Possible participation to assembly of infrastructure in conjunction with other heavy-lift launchers (international mission ) </li></ul><ul><li>Minor adjustments of Ariane 5 </li></ul><ul><li>Limited gain in performance </li></ul><ul><li>Heavy Lift Ariane </li></ul><ul><li>Ariane 5 technology Heavy Lift Launcher </li></ul>
  7. 8. Ariane 5 and LEO launch (1) L10 EPS H173 EPC Vulcain 2 P240 EAP Performance of Ariane 5 with EPS Performance : payload + adapter Ariane 5 ES : Performance : 20.9 t (200 km x 200 km / 51.6° ) 20.7 t (300 km x 200 km / 51.6° )  EPC falldown constraint taken into account (margin with respect to European coast) Ariane 5 ESv (versatile) : Performance : 21.3 t (200 km x 200 km) 21.1 t (300 km x 200 km)  “natural” EPC falldown in the Atlantic Ocean  ballistic phase (< 2 h) before EPS re-ignition
  8. 9. Ariane 5 and LEO launch (2) Performance of Ariane 5 with ESC-A Ariane 5 ECA : Performance : 20.7 t (200 km x 200 km / 51.6° ) 20.6 t (300 km x 200 km / 51.6° )  “ natural” EPC falldown in the Atlantic Ocean  no performance gain with respect to Ariane 5 ES and Ariane 5 ESv due to - non optimal staging for LEO - ESC-A non reignitable H14.4 ESC-A + HM7B P240 EAP ) H173 EPC Vulcain 2
  9. 10. Ariane 5 and LEO launch (3) Performance of Ariane 5 with ESC-B Ariane 5 ECB : Performance : 23 t (300 km x 300 km / 51.6° )  de-loading of ECB (17.5 t of propellant)  EPC falldown constraint taken into account  ballistic phase (3000 s) before ESC-B re-ignition P240 EAP H173 EPC Vulcain 2 H28 ESC-B + Vinci
  10. 11. Lunar Mission Example (1) LEO parking orbit LTO (Lunar Transfer Orbit) circularisation boost de-orbitation boost capture boost mid-course correction <ul><li>Mission profile : </li></ul><ul><li> V needs: </li></ul>
  11. 12. Lunar Mission Example (2) <ul><li>Hypotheses : </li></ul><ul><li>- Storable propellant stage for LTO i njection (13% structural coefficient used: idem EPS) - Storable propellant stage for mid-course correction, circularisation, descent and lunar landing (18% structural coefficient used) - Isp : 324 s (idem EPS) </li></ul><ul><li>Performance (simplified  V approach) : </li></ul>
  12. 13. Ariane 5 and direct LTO injection <ul><li>Hypotheses : </li></ul><ul><li>- LTO performance assumed equal to the performance into a parabolic scape trajectory (C3=0 / sizing hypothesis) - Storable propellant stage for mid-course correction, circularisation, descent and lunar landing (18% structural coefficient used) - Isp : 324 s (idem EPS) </li></ul><ul><li>Performance (simplified  V approach) : </li></ul>
  13. 14. Synthesis about Ariane 5 and Exploration <ul><li>Ariane 5: between 20 t and 23 t into LEO </li></ul><ul><li>Ariane 5 in the same performance range as: </li></ul><ul><ul><li>Atlas 552 – 19 tons </li></ul></ul><ul><ul><li>Delta IV Heavy – 23 tons </li></ul></ul><ul><li>Ariane 5 ECB provides a substantial gain for direct LTO injection </li></ul>
  14. 15. Adaptation of the Ariane 5 concept (1) <ul><li>Objective : </li></ul><ul><li>Maximize Ariane 5 performance without major architecture modifications </li></ul><ul><li>Approach :  increase of Vinci thrust level (ESCB) : 200 kN instead of 180 kN.  Composite casing for the EAP : 248 t of propellant for 27 t of dry mass (versus 240 t / 38,6 t for the current configuration)  Vulcain Mark III : evolutions with respect to Vulcain II + 13.3 s on the Isp (446.8 s) + 350 kN on thrust (1700 kN vac.) </li></ul>
  15. 16. Adaptation of Ariane 5 concept (2) <ul><li>LEO performance: 27 tons </li></ul><ul><li>Identified critical points </li></ul><ul><ul><li>high dynamic pressure level (> 48 000 Pa ) (+30% with respect to the Ariane 5 ECB reference version) </li></ul></ul><ul><ul><li>considering a dynamic pressure constraint on the trajectory optimization process would cancel the performance gain </li></ul></ul><ul><ul><li>important effect on the launcher aerodynamic loads </li></ul></ul><ul><ul><li>launcher ascent controlability to be verified </li></ul></ul>
  16. 17. Ariane 5 Heavy Lift Derivatives H70 H620 4 P230 Lift-off mass : 1874 t 5 Vulcain II Payload : 35 t (LTO injection ) 1 Vulcain II Height 74 m VEB <ul><li>Context : </li></ul><ul><ul><li>study initiated by CNES in 1991 </li></ul></ul><ul><ul><li>reference mission : human flight to the Moon (Apollo-like) </li></ul></ul><ul><ul><li>launcher performance > 32 t in LTO </li></ul></ul><ul><li>“ Ariane Super Lourd” / ASL : - 4 EAP (P230) - cryogenic lower stage : H620 / 8.2 m diameter 5 Vulcain II - cryogenic upper stage : H70 / 5.4 m diameter Vulcain at 700 kN (re-ignitable?) 90 tons in LEO 100 km x 200 km/23° 35 tons in LTO/23° </li></ul>
  17. 18. Synthesis <ul><li>Ariane 5 performance is interesting mainly for robotic exploration missions (21 to 23 tons in LEO) </li></ul><ul><li>Maximum performance increase to 27 tons in LEO while keeping the general Ariane 5 architecture </li></ul><ul><li>Ariane 5 heavy-lift derivatives could be considered but high development costs to be expected even with proven technologies </li></ul><ul><li>Ariane 5 elements could be used through an international cooperation aiming at developing an upper stage based on EPC and Vulcain technologies </li></ul>

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