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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 23rd, 2005
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Ariane 5
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Ariane 5
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Ariane 5 Flight
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Ariane 5 is already a launcher for exploration
Rosetta – Ariane 518
March 2nd, 2004
SMART-1 – Ariane 516
Sept. 27th, 2003
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Ariane 5 options
Reference Ariane 5
•Robotic exploration missions
•Possible participation to assembly of
infrastructure in conjunction with other heavylift launchers (international mission )
Minor adjustments of Ariane 5
•Limited gain in performance
Heavy Lift Ariane
•Ariane 5 technology Heavy Lift Launcher
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Ariane 5 and LEO launch (1)
Performance of Ariane 5 with EPS
L10 EPS
P240 EAP
H173 EPC
Vulcain 2
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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
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Ariane 5 and LEO launch (2)
Performance of Ariane 5 with ESC-A
H14.4 ESC-A
+ HM7B
P240 EAP)
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
H173 EPC
Vulcain 2
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Ariane 5 and LEO launch (3)
Performance of Ariane 5 with ESC-B
H28 ESC-B
+ Vinci
P240 EAP
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
H173 EPC
Vulcain 2
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Lunar Mission Example (1)
• Mission profile :
LEO parking orbit
de-orbitation
boost
capture
boost
mid-course correction
LTO
(Lunar Transfer Orbit)
• DV needs:
Phase
LTO injection
3131 m/s
Mid-course correction
30 m/s
LOI
780 m/s
Descent
1760 m/s
Moon landing
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DV
60 m/s
circularisation
boost
Notes
Duration ~140 hours
Altitude = 100 km
Preliminary estimate
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Lunar Mission Example (2)
• Hypotheses :
- Storable propellant stage for LTO injection
(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 DV approach) :
A5ES
A5ESv
A5ECA
A5ECB
20.5 t
20.9 t
20.3 t
22.6 t
6t
6.1 t
5.9 t
6.6 t
Mass on the Moon
2.6 t
2.7 t
2.6 t
2.9 t
P/L on the Moon (*)
2t
2t
1.9 t
2.2 t
Mass in LEO
Mass in LLO (**)
(*) = mass on the Moon – dry mass of propulsive stage
(**) Low Lunar Orbit
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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 DV approach) :
Mass in LTO
Mass on the Moon
P/L on the Moon
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A5ECA
A5ECB
6.8 t
10.8 t
3t
4.7 t
2.2 t
3.5 t
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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
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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.)
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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
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Ariane 5 Heavy Lift Derivatives
• Context :
•study initiated by CNES in 1991
Payload :
35 t (LTO injection )
•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°
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Height
74 m
VEB
H70
1 Vulcain II
H620
4 P230
5 Vulcain II
Lift-off mass :
1874 t
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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
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