introduction to the ariane launchers family ing. luca del monte esa-hq, paris corso di propulsione...
TRANSCRIPT
![Page 1: 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](https://reader035.vdocument.in/reader035/viewer/2022062318/55161ca1550346d46f8b6740/html5/thumbnails/1.jpg)
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
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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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3Corso di Propulsione Aerospaziale
A.A. 2004-05
The Payload Orbits are classified by:
• Their plane angle compared to the Equatorial plane.
• Their altitude.
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4Corso di Propulsione Aerospaziale
A.A. 2004-05
Orbit Altitudes
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5Corso di Propulsione Aerospaziale
A.A. 2004-05
Orbit Inclination
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6Corso di Propulsione Aerospaziale
A.A. 2004-05
Low Earth Orbit
• Altitude between 100Km and 500Km• Polar or with dedicated inclination.• Used for Science, Observation, Telecom,
Navigation (Constellations).
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7Corso di Propulsione Aerospaziale
A.A. 2004-05
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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8Corso di Propulsione Aerospaziale
A.A. 2004-05
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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9Corso di Propulsione Aerospaziale
A.A. 2004-05
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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10Corso di Propulsione Aerospaziale
A.A. 2004-05
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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11Corso di Propulsione Aerospaziale
A.A. 2004-05
Launcher Design (1)
• From one to four stages, usually three• Expendables and Recoverable• Staging optimisation.
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12Corso di Propulsione Aerospaziale
A.A. 2004-05
Stage Propulsion
• Solid propulsion• Liquid propulsion ( storable propellant, Cryogenic
propellant)
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13Corso di Propulsione Aerospaziale
A.A. 2004-05
Launcher Design Disciplines
• Aerodynamics• Structures• Guidance and Control• Propulsion
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14Corso di Propulsione Aerospaziale
A.A. 2004-05
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
First flight:31/05/86
First flight:04/08/84
First flight:15/06/88
First flight:04/06/96
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15Corso di Propulsione Aerospaziale
A.A. 2004-05
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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16Corso di Propulsione Aerospaziale
A.A. 2004-05
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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17Corso di Propulsione Aerospaziale
A.A. 2004-05
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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18Corso di Propulsione Aerospaziale
A.A. 2004-05
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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19Corso di Propulsione Aerospaziale
A.A. 2004-05
Viking V
• Design coming from the French “Diamant” launcher.
• 621kN Thrust on ground
• Single shaft turbo pump
• Water cooled
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20Corso di Propulsione Aerospaziale
A.A. 2004-05
HM7
• Predevelopment in the 60’s in France
• 61.8kN Thrust
• 440.6s Specific impulse
• Turbo pump with gear box
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21Corso di Propulsione Aerospaziale
A.A. 2004-05
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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22Corso di Propulsione Aerospaziale
A.A. 2004-05
Ariane 1 Fairing
• Classical Aeronautical structure.
• Parallel jettisoning
• Carbon Fibre sandwich for the rear part.
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23Corso di Propulsione Aerospaziale
A.A. 2004-05
Ariane 3 Objectives
• To launch 2 standard telecom satellites (average mass 1350kg) in GTO
• To reduce the recurring price
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24Corso di Propulsione Aerospaziale
A.A. 2004-05
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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25Corso di Propulsione Aerospaziale
A.A. 2004-05
A3 Strap On Boosters
• 7.3 tons solid propellant
• Immerged and canted nozzle
• Subsonic jettisoning
• Mechanical ejection springs
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26Corso di Propulsione Aerospaziale
A.A. 2004-05
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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27Corso di Propulsione Aerospaziale
A.A. 2004-05
A3 Fairing
• Double canted nose cone to allow a standard volume for two 1350kg satellites
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28Corso di Propulsione Aerospaziale
A.A. 2004-05
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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29Corso di Propulsione Aerospaziale
A.A. 2004-05
Ariane 4 Design Choices
• 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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30Corso di Propulsione Aerospaziale
A.A. 2004-05
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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31Corso di Propulsione Aerospaziale
A.A. 2004-05
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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32Corso di Propulsione Aerospaziale
A.A. 2004-05
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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33Corso di Propulsione Aerospaziale
A.A. 2004-05
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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34Corso di Propulsione Aerospaziale
A.A. 2004-05
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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35Corso di Propulsione Aerospaziale
A.A. 2004-05
A4 Fairing and Speltra
• Increased diameter to 4m.
• Two lengths configurations.
• Carbon fibre technology
• Parallel jettisoning with clean pyro-cutting
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36Corso di Propulsione Aerospaziale
A.A. 2004-05
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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37Corso di Propulsione Aerospaziale
A.A. 2004-05
Ariane 5 Design Choices
• 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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38Corso di Propulsione Aerospaziale
A.A. 2004-05
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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39Corso di Propulsione Aerospaziale
A.A. 2004-05
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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40Corso di Propulsione Aerospaziale
A.A. 2004-05
A5 Vulcain Engine
• Thrust: 1145kN.
• Mixture ratio: 5.35.
• Mass: 1740kg.
• Gas generator fed with independent flow
• Specific Impulse:431s.
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41Corso di Propulsione Aerospaziale
A.A. 2004-05
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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42Corso di Propulsione Aerospaziale
A.A. 2004-05
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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43Corso di Propulsione Aerospaziale
A.A. 2004-05
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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44Corso di Propulsione Aerospaziale
A.A. 2004-05
A5 payload volume
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45Corso di Propulsione Aerospaziale
A.A. 2004-05
A5 Speltra
• Adaptable length
• Used for launching two heavy satellites
• Carbon fibre technology
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46Corso di Propulsione Aerospaziale
A.A. 2004-05
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.