iranzo ariane5 lofa rworkshop

This document is the property of EADS SPACE Transportation and shall not be communicated to third parties and/or reproduced without prior written agreement.Its contents shall not be disclosed. © - EADS SPACE Transportation - 2005

Ariane 5 – A European Launcher for Space Exploration

Towards a European Infrastructure for Lunar Observatories - Workshop

David Iranzo-GreusHead of Advanced Studies Launchers, Propulsion and DefenceEADS SPACE TransporationBremen, March 23rd, 2005


Ariane 5


Ariane 5 Flight


Ariane 5 is already a launcher for exploration

SMART-1 – Ariane 516Sept. 27th, 2003

Rosetta – Ariane 518March 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 EPCVulcain 2

P240 EAP

Performance of Ariane 5 with EPS

Performance : payload + adapterAriane 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



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 EPCVulcain 2



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 EPCVulcain 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:Phase V Notes

LTO injection 3131 m/s Duration ~140 hours

Mid-course correction 30 m/s

LOI 780 m/s Altitude = 100 km

Descent 1760 m/s

Moon landing 60 m/s Preliminary estimate


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 V approach) :

A5ES A5ESv A5ECA A5ECB

Mass in LEO 20.5 t 20.9 t 20.3 t 22.6 t

Mass in LLO (**) 6 t 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 (*) 2 t 2 t 1.9 t 2.2 t

(*) = mass on the Moon – dry mass of propulsive stage (**) Low Lunar Orbit


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) :

A5ECA A5ECB

Mass in LTO 6.8 t 10.8 t

Mass on the Moon 3 t 4.7 t

P/L on the Moon 2.2 t 3.5 t


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 IIHeight74 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 diameter5 Vulcain II

- cryogenic upper stage :H70 / 5.4 m diameterVulcain 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

iranzo ariane5 lofa rworkshop

Technology

leo ariane

tons ariane

exploration ariane

architecture ariane

synthesis ariane

adaptation of ariane

adapter ariane

general ariane