• Share
  • Email
  • Embed
  • Like
  • Save
  • Private Content
Iranzo Ariane5 Lofa Rworkshop
 

Iranzo Ariane5 Lofa Rworkshop

on

  • 791 views

 

Statistics

Views

Total Views
791
Views on SlideShare
784
Embed Views
7

Actions

Likes
0
Downloads
3
Comments
0

2 Embeds 7

http://www.student.kuleuven.be 5
http://student.kuleuven.be 2

Accessibility

Categories

Upload Details

Uploaded via as Microsoft PowerPoint

Usage Rights

© All Rights Reserved

Report content

Flagged as inappropriate Flag as inappropriate
Flag as inappropriate

Select your reason for flagging this presentation as inappropriate.

Cancel
  • Full Name Full Name Comment goes here.
    Are you sure you want to
    Your message goes here
    Processing…
Post Comment
Edit your comment

    Iranzo Ariane5 Lofa Rworkshop Iranzo Ariane5 Lofa Rworkshop Presentation Transcript

    • 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
    • Ariane 5
    • Ariane 5
    • Ariane 5 Flight
    • Ariane 5 is already a launcher for exploration SMART-1 – Ariane 516 Sept. 27th, 2003 Rosetta – Ariane 518 March 2nd, 2004
    •  
    • Ariane 5 options
      • Reference Ariane 5
      • Robotic exploration missions
      • Possible participation to assembly of infrastructure in conjunction with other heavy-lift launchers (international mission )
      • Minor adjustments of Ariane 5
      • Limited gain in performance
      • Heavy Lift Ariane
      • Ariane 5 technology Heavy Lift Launcher
    • 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
    • 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
    • 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
    • Lunar Mission Example (1) LEO parking orbit LTO (Lunar Transfer Orbit) circularisation boost de-orbitation boost capture boost mid-course correction
      • Mission profile :
      •  V needs:
    • Lunar Mission Example (2)
      • Hypotheses :
      • - 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)
      • Performance (simplified  V approach) :
    • Ariane 5 and direct LTO injection
      • Hypotheses :
      • - 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)
      • Performance (simplified  V approach) :
    • Synthesis about Ariane 5 and Exploration
      • Ariane 5: between 20 t and 23 t into LEO
      • Ariane 5 in the same performance range as:
        • Atlas 552 – 19 tons
        • Delta IV Heavy – 23 tons
      • Ariane 5 ECB provides a substantial gain for direct LTO injection
    • Adaptation of the Ariane 5 concept (1)
      • Objective :
      • Maximize Ariane 5 performance without major architecture modifications
      • 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.)
    • Adaptation of Ariane 5 concept (2)
      • LEO performance: 27 tons
      • Identified critical points
        • high dynamic pressure level (> 48 000 Pa ) (+30% with respect to the Ariane 5 ECB reference version)
        • considering a dynamic pressure constraint on the trajectory optimization process would cancel the performance gain
        • important effect on the launcher aerodynamic loads
        • launcher ascent controlability to be verified
    • 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
      • Context :
        • study initiated by CNES in 1991
        • reference mission : human flight to the Moon (Apollo-like)
        • launcher performance > 32 t in LTO
      • “ 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°
    • Synthesis
      • Ariane 5 performance is interesting mainly for robotic exploration missions (21 to 23 tons in LEO)
      • Maximum performance increase to 27 tons in LEO while keeping the general Ariane 5 architecture
      • Ariane 5 heavy-lift derivatives could be considered but high development costs to be expected even with proven technologies
      • Ariane 5 elements could be used through an international cooperation aiming at developing an upper stage based on EPC and Vulcain technologies