Introduction to the Ariane launchers family Ing. Luca del Monte ESA-HQ, Paris Corso di Propulsione Aerospaziale Universitadi Roma La Sapienza A.A. 2004-05.

Introduction to the Ariane launchers family

Ing. Luca del MonteESA-HQ, Paris

Corso di Propulsione Aerospaziale

Universita’di Roma “La Sapienza”A.A. 2004-05

2Corso di Propulsione Aerospaziale

A.A. 2004-05

A launcher is defined by:

• Its payload mass performance in a specified orbit• The available volume to hoist the payload• The environmental conditions supported by the

payload:thermal, electromagnetic, mechanical


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The Payload Orbits are classified by:

• Their plane angle compared to the Equatorial plane.

• Their altitude.


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Orbit Altitudes


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Orbit Inclination


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Low Earth Orbit

• Altitude between 100Km and 500Km• Polar or with dedicated inclination.• Used for Science, Observation, Telecom,

Navigation (Constellations).


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Sun Synchronous Orbits (S.S.O.)

• Polar Orbit• Altitude such that the satellite fly over a given part

of the earth at the same local hour.• Mainly 800 Km


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Geo Stationary Transfer Orbit

• Equatorial Orbit• Perigee: around 250 Km• Apogee: 36 000 Km• Circularisation at 36 000 Km made by the satellite

itself, or the launcher, depending on its architecture and the specific impulse of its last stage. Performance optimisation for the satellite.

• Telecom, TV, Meteorology, etc.


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Ariane 5 : Performance growth potential is one of the keys to success

1999 2000 2001 2002 2003 2004 2005 2006 2007 2008 2009 20104 t

5 t

6 t

7 t

8 t

9 t

10 t

11 t

12 t

Ariane 5G

Ariane 5 ECA

Ariane 5 ES

Ariane 5 ECB

GTO PERFORMANCE


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Advantages of an Equatorial Launching Base

• Trajectories to reach the final Orbit are simplified.• The performance Gain is significant• Kourou is an example.


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Launcher Design (1)

• From one to four stages, usually three• Expendables and Recoverable• Staging optimisation.


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Stage Propulsion

• Solid propulsion• Liquid propulsion ( storable propellant, Cryogenic

propellant)


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Launcher Design Disciplines

• Aerodynamics• Structures• Guidance and Control• Propulsion


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From Ariane 1 to Ariane 5: 162 launches

11

Ariane 1

6

Ariane 2

11

Ariane 3

118

Ariane 4

15

Ariane 5

208 satellites + 39 auxiliary payloadssuccessfully injected into orbit

First flight:24/12/79






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19801981

19821983

19841985

19861987

19881989

19901991

19921993

19941995

19961997

19981999

2000500

1,000

1,500

2,000

2,500

3,000

3,500

1/2 ARIANE Perfo

Satellites annual average massAriane 1

Ariane 3Ariane 4

Ariane 5


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Ariane 1 Objectives

• Free Access to Space.

• European Programme with French Space Agency as Prime Contractor.

• Already qualified technologies.

• Comparable performance with American launchers.


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Ariane 1 Design Choices (1)

• Technology proven structures:• metallic tanks already ground qualified.

• Classical aeronautical technologies for inter stages and fairing.• Two main engines:• Viking for the storable propellant stage,

• HM7 for the cryogenic stage, already ground tested.


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Ariane 1, L140

• 140 tons propellant UDMH-N2O4

• 19m high, 3.8m broad

• 2485kN Thrust

• 247.4s Specific Impulse

• ΔV=1800m/s


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Viking V

• Design coming from the French “Diamant” launcher.

• 621kN Thrust on ground

• Single shaft turbo pump

• Water cooled


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HM7

• Predevelopment in the 60’s in France

• 61.8kN Thrust

• 440.6s Specific impulse

• Turbo pump with gear box


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Ariane 1 Upper composite

• VEB with European electronic box (Ferranti inertial platform)

• Sylda in carbon fiber for double launches

• Standard adaptors


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Ariane 1 Fairing

• Classical Aeronautical structure.

• Parallel jettisoning

• Carbon Fibre sandwich for the rear part.


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Ariane 3 Objectives

• To launch 2 standard telecom satellites (average mass 1350kg) in GTO

• To reduce the recurring price


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Ariane 3 Design Choices

• To use strap on solid boosters• To increase the reliability of Viking propulsion by

using a propellant less sensitive to High Frequency phenomena

• To increase slightly the HM7 performance by increasing the chamber pressure.


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A3 Strap On Boosters

• 7.3 tons solid propellant

• Immerged and canted nozzle

• Subsonic jettisoning

• Mechanical ejection springs


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A3 H10

• Propellant mass increase from 8 to 10 tons

• Hm7 engine chamber pressure increase from 30 to 35 bars

• Hm7 Thrust increase to 64.8 tons

• Weight savings


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A3 Fairing

• Double canted nose cone to allow a standard volume for two 1350kg satellites


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Ariane 4 Objectives

• To offer a payload volume of 3.6m in diameter.

• To launch 2 satellites of 1800kg

• To be commercially competitive, using double launches.


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• Increase the solid booster performance.• Design liquid propellant boosters using the Viking

engine.• Use the already qualified carbon fibre technology

for upper part structures.


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A4 L220

• Liquid propellant mass increase from 140 to 220 tons

• Adaptation of the thrust frame to fit with ELA2 launch pad

• Adaptation of the structures for booster fittings.

• Integration of a new water tank


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A4 Liquid Propellant Booster

• 2 or 4 boosters.

• Liquid propellant UDMH-N2O4 (39tons each)

• Fixed canted engine Viking

• Supersonic jettison

• Water need fed by L220


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A4 Solid Propellant Booster

• 2 or 4 boosters

• Propellant mass increased from 7.3 to 9.5 tons

• Length adaptation to fit with the L220 attachments

• Burning time decreased from 10.3 to 7.3 mm/s

• Subsonic jettison


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A4 H10

• Replacement of the metallic rear skirt by a carbon fibre one

• Adaptation of the structures to the increased mechanical loads due to the new upper structure.


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A4 VEB

• Redesign of the structure due the fairing diameter increase from 3.2 to 4m

• Updating of the electronic equipment, particularly the computer and inertial platform


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A4 Fairing and Speltra

• Increased diameter to 4m.

• Two lengths configurations.

• Carbon fibre technology

• Parallel jettisoning with clean pyro-cutting


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Ariane 5 Objectives

• To launch the Hermes Vehicle

• To launch heavy commercial satellites

• To launch constellation satellites in batches

• To low down the launching services price


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• Man rated for Hermes.

• Less numerous, but more powerful and reliable Engines

• Re ignitable upper stage

• Double launch

• 20% less expensive than Ariane 4


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A5 Solid Propellant Stage

• 230 solid propellant engine, casted in a dedicated plant in near the launch pad.

• Flexible joint movable nozzle.

• Stage recovery for expertise.


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A5 Cryotechnic stage

• 5.4 m diameter.

• 158 ton of propellant LOX/LH2.

• 1145kN Thrust

• Sub orbital stage.

• The solid propellant stages thrust is transmitted to the upper composite via the EPC front skirt.


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A5 Vulcain Engine

• Thrust: 1145kN.

• Mixture ratio: 5.35.

• Mass: 1740kg.

• Gas generator fed with independent flow

• Specific Impulse:431s.


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A5 Vehicle Equipment Bay

• Hoist the Storable propellant stage.

• Includes an active attitude control system using small Hydrazine engines (400N)

• Redundant electrical equipments.

• Digital Bus for the whole launcher.


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A5 storable propellant stage

• Pressure fed Aestus Engine

• Storable propellant

• Two tanks with a flow combiner for each propellant

• Re ignitable


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A5 Fairing

• Adaptable length for single or double launch

• Acoustic internal protection for Satellite comfort!

• Parallel jettison using gas proof pyro devices.


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A5 payload volume


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A5 Speltra

• Adaptable length

• Used for launching two heavy satellites

• Carbon fibre technology


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ARIANE 1 – 5 LAUNCHES

(1 April 2004)

Launches Failures Period Success rate

Ariane 1 11 (2) 1979/1986 0.82

Ariane 2-3 17 (2) 1984/1989 0.88

Ariane 4 116 (3) 1988/2002 0.97

Ariane 5G 17 (2) 1996/2004 0.88

Ariane 5 ECA 1 (1) 2002 N.A.

Introduction to the Ariane launchers family Ing. Luca del Monte ESA-HQ, Paris Corso di Propulsione Aerospaziale Universitadi Roma La Sapienza A.A. 2004-05.

Documents

t ariane

mechanical slide

paris corso

ms slide

orbit inclination slide

cryogenic propellant

control propulsion slide

es ariane