This document is the property of EADS SPACE and shall not be communicated to third parties and/or...

This document is the property of EADS SPACE and shall not be communicated to third parties and/or reproduced without prior written agreement. Its contents shall not be disclosed. - EADS SPACE - 2006

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Expandable launchersExpandable launchersExample of Ariane 5, European workhorseExample of Ariane 5, European workhorse

May 2006 H. LAPORTE - WEYWADA

Rocket Propulsion courseRoyal Institute of Technology, Stockholm


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1.1. Introduction to Space transportation activityIntroduction to Space transportation activity

2.2. Main driver for launcher conceptionMain driver for launcher conception

3.3. Ariane 5 Launch System descriptionAriane 5 Launch System description

Photos : ESA, CNES, Arinanespace, EADS, SNECMA


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Satellites : missions, configuration, orbits

Market

World-wide competition

Budget overview

• Introduction to Space Transportation activity

• Main driver for launcher conception

• Ariane 5 Launch System description


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SPACE MISSIONS OVERVIEWSPACE MISSIONS OVERVIEW

“Prestige” missions, manned flights

Scientific interplanetary missions ( a few % of automatic flights )

Scientific mission in earth orbit (astronomy,…)

Operational missions :

telecommunication (most important, the only one being

truly commercial )

meteorology

navigation

Earth observation

micro-gravity research activity


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Examples of satellitesExamples of satellites

ERS :

Radar earth observation in Sun Synchronous orbit

Atlantic Bird :

Telecom


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Integral :

Astronomy

Sonde Galileo :

Solar system exploration


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Meteosat :

Meteorology

ISS and ATV :

Manned flight, research


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CLASSICAL ORBITSCLASSICAL ORBITS

Orbits are defined by their altitude (min, max) and angles defining their position in space (inclination, perigee argument, ascending node longitude)


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CLASSICAL ORBITSCLASSICAL ORBITS

Classical orbits are

GEO : geostationary earth orbit, reached through GTO, geostationary transfer orbit

LEO : Low Earth Orbit < 1 500 km altitude

MEO : Medium Earth Orbit (6 000 to 20 000 km altitude)

SSO : Sun Synchronous Orbit

PEO : Polar Earth Orbit

HEO : Highly Elliptical earth Orbit


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OrbitsOrbits


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OrbitsOrbits

Orbit of Ulysse, solar poles exploration probe


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Market


Budget overview





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25-30

45-50

Institutional market

- Mainly USA & Russia- Europe : 1 to 2 launches per year

Commercial market

Satellites launches(yearly average, 2001)

WORLD WIDE LAUNCH MARKETWORLD WIDE LAUNCH MARKET


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Satellites launches

0

5

10

15

20

25

30

35

40

1995 1996 1997 1998 1999 2000 2001 2002 2003 2004 2005 2006 2007

MaximumMaximum

NominalNominal

COMMERCIALCOMMERCIAL MARKET MARKET

(2001)


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Num

ber o

f sat

ellit

es

Satellites needed to meet the C & Ku-band transponder demand model

0

5

10

15

20

25

30

1967 1970 1973 1976 1979 1982 1985 1988 1991 1994 1997 2000 2003 2006 2009

Mobile communication satellites

Digital audio broadcasting satellites

35

ForecastCompleted

All commercial GEO satellites*

70’s average: 4 /year

80’s average: 13 /year

90’s: 22 /year

00’s: 19 /year (21 with ICO)

ICO

Fixed service satellites

without

Market study result (e.g. Euroconsult)


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0%

10%

20%

30%

40%

50%

60%

70%

80%

90%

100%

1994 1995 1996 1997 1998 1999 2000 2001 2002 2003 2004 2005 2006 2007

<2400 Kg<2400 Kg

2400-3000 Kg2400-3000 Kg

3000-4000 Kg3000-4000 Kg

4000-5000 Kg4000-5000 Kg

>5000 Kg>5000 Kg

GTO SATELLITES MASS FORECAST GTO SATELLITES MASS FORECAST

(2001)


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LAUNCH MARKET

• Governmental market :

– Very important in USA (NASA + DoD : 20 à 25 launches per year)

– Very weak in Europe: scientific payloads (Envisat, Herschel Planck..), ATV,

military activities (com, elint, observation…). Average 1 per year.

• Commercial market:

– GEO : important, relatively stable (15 to 20 satellites per year)

major part = telecom

– Stabilization of satellite mass, maximum mass around 6 tonnes


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MISSIONS vs ORBITS

Mission Market type Orbit satellite mass

Telecoms commercial Mainly GEO LEO / MEO constellations

2.5 to 5 T in GTO some 100 kg to 4 T

Navigation governmental MEO 1 to 2 T

Weather forecast governmental GEO SSO, Low Polar (800km)

Earth observation mainly governmental

LEO, mainly SSO or polar

some 100 kg to 1 T

Manned flight governmental LEO (500 km, 63 °) 6 to 20 T

Sciences governmental From LEO to escape 100 kg to 2 T


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Market


Budget overview





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LAUNCHER CATEGORIESLAUNCHER CATEGORIES

Heavy and Super heavy launchers :

Able to lift to all orbits, including GTO and escape, masses of more than 3

tonnes en GTO( heavy ) or more than 10 tonnes en GTO (super-heavy )

Medium Launchers :

But not adapted to GTO orbit (around 1 tonne)

Able to lift more than 3 tonnes in LEO

Small launchers :

Limited to 1 to 1,5 tonne in LEO

Micro launchers :

limited to a few hundreds of kg in LEO


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new Delta 4 family, mainly to capture government orders

marketing of the Zenit, through Sea Launch

Launcher Delta 2 Delta 3 Delta 4 Medium Delta 4 Heavy SealaunchGTO performances 1.7 tons 3.4 tons 3.7 to 5.7 tons 12 tons 5.5 to 6 tons1st commercial launch 2001 2003/2004 >2004 ? 1999Price 70 to 85 M$ 130 M$ 65 M$ (to 85 M$)

Delta 2 Delta 3 Delta 4Sea Launch

*Équivalent Kourou

EELV

*

Boeing range of launcher


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Atlas 2 Atlas 5 ProtonAtlas 3

new Atlas 5 family : proven Atlas 3 technology and Russian RD180 engine

marketing of the Proton M through ILS

Launcher Atlas 2 AS Atlas 3 Atlas 5-400 Atlas 5-500 Proton Breeze MGTO performances 3.3 tons 3.6 to 4 tons 3.8 to 7.9 tons 4.1 to 8.2 tons 5.5 (up to 6.8) tons1st commercial launch end prod. 2000 2003/2004 ? Not in development 1999Price 65 to 90 M$ 85 to 110 M$ 75 M$

EELV

*

*Équivalent Kourou

Lockheed Martin range of launcher


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Launcher Soyouz-ST Rockot VegaES ECA ECB

GTO performances (7.5 tonnes) 10 tonnes (12 tonnes) 1.4 tonnes (Baïkonur)2.8 tonnes (Kourou.)

1st comm. launchqualif not yet

decided 2005dvp not yet

decided 2006

LEO performances 20 tonnes 5 tonnes 1.5 tonne 1,5 tonne1st comm. launch 2007 1999 ->2008-2010 > 2008

Ariane 5

Ariane 5(Arianespace)

Soyouz(Starsem)

Rockot(Eurockot)

Vega(Arianespace)

European range of launchers


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• Space Shuttle used only for US governmental mission, in particular access to International Space Station. Next flight(2nd after Columbia accident in 2004) is scheduled for July 2006.

OTHER LAUNCHERS IN THE WORLDOTHER LAUNCHERS IN THE WORLD


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• Other operational launchers :

– USA : small launchers Taurus XL, Pegasus XL (air launched)

– Japan : H2A (heavy launcher), M5 (medium launcher)

– China : Long March family, medium to heavy launcher

– India : PSLV, GSLV (medium launchers)

– Israel : Shavit, (small launcher)

– Russia / Ukraine : Proton, Soyuz, Cyclone, Zenith 2, Cosmos, Dniepr, Volna, Rockot

• Launcher in development :

– Brazil

– South Korea

– Russia : Angara

– Israel : Next

– Several US private initiatives (Falcon,…)

OTHER LAUNCHERS IN THE WORLDOTHER LAUNCHERS IN THE WORLD


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SMALL LAUNCHERS (1/2)


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Market


Budget overview





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SPACE BUDGETS IN THE WORLD

• USA predominance in the world

• France, Germany, Italy major contributors in Europe Others

13%Italy11%UK

10%Belgium

4%

Germany20%

France49%

BUDGET SPLIT IN EUROPE (Civilian + Military, 1999)

SPACE BUDGETS 1997

0

5

10

15

20

25

USA Europe Japan Russia

Md

€ Civilian Military


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SPLIT OF BUDGET PER CIVILIAN APPLICATION

ESA BUDGET 20023 Md€

Science14%

Manned Flight13%

Launchers12%

Others36%

Earth Observation

8%

Telecom.9%

Microgravity2%

General6%


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2.2. Main drivers for launcher conceptionMain drivers for launcher conception

Launcher mission and specification

Typical configuration of a launcher


• Main drivers for launcher conception



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• Launcher mission consists in giving to the satellite the speed (8 to 10 km/s) and the altitude (200 to 1000 km) needed to reach the intended orbit (injection orbit). This orbit can be the final one, or an intermediate orbit (transfer orbit)

• Once needed altitude and speed obtained (i.e. once injection orbit reached), the launcher provides adequate orientation and spin

• Then satellites are separated from the launcher.

LAUNCHER MISSIONLAUNCHER MISSION


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in orbit

launch Orbital manoeuvre(circularisation)

LAUNCH OF A GEOSTATIONNARY SATELLITELAUNCH OF A GEOSTATIONNARY SATELLITE


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After satellite release, the satellite control centre takes the satellite in charge and controls all operations ( solar panel opening, antennas deployment, checks,…) and manoeuvres (orientations, orbit change,…) needed to begin operational mission.

BEGINNING OF SATELLITE LIFEBEGINNING OF SATELLITE LIFE


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• Launch phase induces severe constraints on the satellite, driving its design :

– Severe mechanical environment (acoustic noise, vibrations, static acceleration, thermal fluxes during count down and during flight)

– In orbit injection inaccuracy (scattered speed and position leading to a slightly different orbit than the one targeted), which must be corrected by the satellite manoeuvre)

– Injection attitude inaccuracy (impacting satellite navigation system and thermal control)

– « Narrow » volume under the fairing, leading to folding / unfolding mechanisms for antennas, solar panels, etc..

CONSTRAINTS COMING FROM LAUNCH PHASE ON THE SATELLITECONSTRAINTS COMING FROM LAUNCH PHASE ON THE SATELLITE


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• Launcher specification gathers all satellite customer’s requirements from the launcher :

- Performance, targeted orbits

- Satellite orientation at injection

- Injection accuracy, attitude accuracy

- Flight environment- Mechanical

- Acoustic

- Thermal

- EMC

- Pollution

- Available Volume under fairing

- Services given to the satellite- Electrical orders,

- radio transparent windows under fairing,

- …

- Constraints during launch campaign

CONSEQUENCES ON LAUNCHER SPECIFICATIONCONSEQUENCES ON LAUNCHER SPECIFICATION


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2.2. Main drivers for launcher conceptionMain drivers for launcher conception

Launcher mission and specification

Typical configuration of a launcher


• Main drivers for launcher conception



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• A launcher is made of several “stages”– Each stage delivers part of speed needed for in orbit injection.

– Once empty, stage is jettisoned, following one is ignited.

• Each stage is made around a propulsive system more or less autonomous, comprising :

– Engines, delivering thrust

– Tanks, feed system (feeding the engines with propellant), and pressurisation system

– Connecting structures with other stages

• Avionic, including software, ensuring following functions :– « Guidance/Navigation/Control » (ensure flight control and trajectory optimisation)

– « Telemetry » (allows post flight check of the correct behaviour of launcher’s subsystems)

– « Safeguard » (allows protection of goods and people on earth, through ranging of launcher during flight to check trajectory, and potential destruction if it becomes dangerous).

• Upper Part– accommodates the Payloads and protects them from atmosphere

• Launch Range/Launch Pad– Provides facilities for satellite final assembly and tests, before integration atop of the

launcher

– Allows Launcher final assembly and tests, Launcher flight preparation (filling, final checks, take off)

– Provides Radar ranging and Telemetry acquisition during the whole flight

EXPANDABLE LAUNCH SYSTEM TYPICAL CONFIGURATIONEXPANDABLE LAUNCH SYSTEM TYPICAL CONFIGURATION


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Why several stages on a launcher ?

Isp (s)

0

500

1000

1500

2000

2500

3000

3,0% 5,0% 7,0% 9,0% 11,0%

Mass ratio

M e

rgol

(T)

450 350

To inject 1T in LEO (i.e. 7800 m/s + losses =10000m/s)ΔV = go Isp Log (1+k)/k

Single stage to orbit : today a dream

Conclusions : With today’s technology: Storable propulsion : k = 10% cryo propulsion : k = 10 à 15%

Needed mass ratio for SSTO is not realistic

•In addition, high risk in case of drift of mass during project development…


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SOLID PROPULSION TECHNOLOGIESSOLID PROPULSION TECHNOLOGIES

Solid propellants :

Isp 260 to 300s

Delivers very high thrust (take off)

High density, => compact stages

Easy / simple ignition

Thrust law (vs time) is frozen once for ever,

according to geometry of propellant block

Stop of thrust can not (or hardly) be

commanded in real time


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LIQUID PROPULSION TECHNOLOGIESLIQUID PROPULSION TECHNOLOGIES

Liquid propellants :

storable : Isp 260 to 330s

UDMH or MMH + Nitrogen peroxide : most frequent

semi-cryogenic : Isp 300 to 350s

LOX + kerosene, LOX + CH4

Cryogenic : Isp 425 to 455s

LOX + LH2 very efficient, but complex, and with low propellant density (LH2 70 Kg/m3)

Vacuum thrust quasi constant, or varies slightly with launcher acceleration (variation of pumps inlet pressures).

Engine are hardly throttable

Engine cut-off can be commanded in real time


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OTHER TECHNOLOGIESOTHER TECHNOLOGIES

Structures : search for low masses

Light/ strong aluminium alloys

Composites : high pressure filament wound envelopes, NIDA sandwich wrapped shells

Thermal protections

“Hot" : to protect from aerothermodynamics fluxes

“Cold" : for cryogenic propellant tanks

Hydraulic systems

Engine orientation : actuators, hydraulic fluid, electrical pumps or blow down pressure

Pyrotechnic systems

Used for stage separation

Classical pyrotechnic devices, high energy, optopyro transmission

Avionics : use of technology developed for other applications (aeronautics, military)

Hardening to resist to radiations

Software : real time, fault tolerant


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LAUNCHERS ARCHITECTURELAUNCHERS ARCHITECTURE

Number of propulsive stages :

2 stages for low energy orbit injection (LEO), sometime 3 (Single Stage

To Orbit not feasible)

1 additional stage to reach more energetic orbits

« linear » launchers, or « parallel » launchers (with strap on boosters or

stages)

linear : stages assembled one atop of the other, working one after the

other

Lateral stages : lowers launcher height (lowering loads on launcher

structure), allows simultaneous burning of stage

Air launched launcher (from a plane) : limited to small or micro launchers


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LAUNCHER ARCHITECTURELAUNCHER ARCHITECTURE

Upper part architecture :

Satellite interface : circular flanges on all launchers, except lateral

trunions on Space Shuttle bay

Satellite separation : clamp band or pyro bolts + springs

Avionic lay out :

Gathered in an Avionic bay, or distributed in all stages

Upper stage architecture :

Under fairing (lowers loads and thermal constraints on orbital stage,

but more complex fairing)

Or external (simpler, but heavier upper stage)


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LAUNCH FACILITIESLAUNCH FACILITIES

Constraint applying on Launch Range :

- safety during launcher trajectory (=> next to a sea or an unpopulated

area)

- Wide area needed for launch facility

- Proximity to equator (GTO launch)

- Access from production facility

Interest of Launch Range allowing to reach orbits of various inclination

Example : KOUROU, ALCANTARA

(need of CCAS and VAB in US for GTO and polar launches)

Interest of maritime platforms questionable (SAN MARCO - SEA LAUNCH)

Launch Ranges are very expansive assets, investment has to be backed by

highest launch cadence possible.


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Cost reduction (market price : low demand, increased offer)

New injection strategies (direct GEO injection, super synchronous orbits)

Transition to fully or partly reusable launchers (in a longer term) : several issues not

yet solved :

Technical feasibility Reusable high performance propulsion

Reusable structure (+ thermal protection), reusable systems (e.g. actuators)

Need of a low number of stages

Operational constraints Need of a higher reliability (e.g. fault tolerant systems, engine failure)

Overhaul cycle has to be quite shorter than today’s launch operations

Need of a high launch cadence

Otherwise expandable launcher remains cheaper

Trend for future

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