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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
KTH 05/2006
Page 1
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
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
KTH 05/2006
Page 2
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
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
KTH 05/2006
Page 3
1.1. Introduction to Space transportation activityIntroduction to Space transportation activity
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
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
KTH 05/2006
Page 4
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
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
KTH 05/2006
Page 5
Examples of satellitesExamples of satellites
ERS :
Radar earth observation in Sun Synchronous orbit
Atlantic Bird :
Telecom
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
KTH 05/2006
Page 6
Examples of satellitesExamples of satellites
Integral :
Astronomy
Sonde Galileo :
Solar system exploration
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
KTH 05/2006
Page 7
Examples of satellitesExamples of satellites
Meteosat :
Meteorology
ISS and ATV :
Manned flight, research
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
KTH 05/2006
Page 8
CLASSICAL ORBITSCLASSICAL ORBITS
Orbits are defined by their altitude (min, max) and angles defining their position in space (inclination, perigee argument, ascending node longitude)
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
KTH 05/2006
Page 9
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
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
KTH 05/2006
Page 10
OrbitsOrbits
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
KTH 05/2006
Page 11
OrbitsOrbits
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
KTH 05/2006
Page 12
OrbitsOrbits
Orbit of Ulysse, solar poles exploration probe
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
KTH 05/2006
Page 13
1.1. Introduction to Space transportation activityIntroduction to Space transportation activity
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
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
KTH 05/2006
Page 14
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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KTH 05/2006
Page 15
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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KTH 05/2006
Page 16
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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KTH 05/2006
Page 17
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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KTH 05/2006
Page 18LAUNCH 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
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
KTH 05/2006
Page 19MISSIONS 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
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
KTH 05/2006
Page 20
1.1. Introduction to Space transportation activityIntroduction to Space transportation activity
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
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
KTH 05/2006
Page 21
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
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
KTH 05/2006
Page 22
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$)
Delta 2 Delta 3 Delta 4Sea Launch
*Équivalent Kourou
EELV
*
Boeing range of launcher
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KTH 05/2006
Page 23
Atlas 2 Atlas 5 ProtonAtlas 3
new Atlas 5 family : proven Atlas 3 technology and Russian RD180 engine
marketing of the Proton M through ILS
Launcher Atlas 2 AS Atlas 3 Atlas 5-400 Atlas 5-500 Proton Breeze MGTO performances 3.3 tons 3.6 to 4 tons 3.8 to 7.9 tons 4.1 to 8.2 tons 5.5 (up to 6.8) tons1st commercial launch end prod. 2000 2003/2004 ? Not in development 1999Price 65 to 90 M$ 85 to 110 M$ 75 M$
EELV
*
*Équivalent Kourou
Lockheed Martin range of launcher
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KTH 05/2006
Page 24
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
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
KTH 05/2006
Page 25
• 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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KTH 05/2006
Page 26
• 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
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
KTH 05/2006
Page 27SMALL LAUNCHERS (1/2)
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
KTH 05/2006
Page 28
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
KTH 05/2006
Page 29
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
KTH 05/2006
Page 30
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
KTH 05/2006
Page 31
1.1. Introduction to Space transportation activityIntroduction to Space transportation activity
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
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
KTH 05/2006
Page 32
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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KTH 05/2006
Page 33
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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KTH 05/2006
Page 34
2.2. Main drivers for launcher conceptionMain drivers for launcher conception
Launcher mission and specification
Typical configuration of a launcher
• Introduction to Space Transportation activity
• Main drivers for launcher conception
• Ariane 5 Launch System description
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
KTH 05/2006
Page 35
• 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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KTH 05/2006
Page 36
in orbit
launch Orbital manoeuvre(circularisation)
LAUNCH OF A GEOSTATIONNARY SATELLITELAUNCH OF A GEOSTATIONNARY SATELLITE
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KTH 05/2006
Page 37
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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Page 38
• 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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KTH 05/2006
Page 39
• 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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Page 40
2.2. Main drivers for launcher conceptionMain drivers for launcher conception
Launcher mission and specification
Typical configuration of a launcher
• Introduction to Space Transportation activity
• Main drivers for launcher conception
• Ariane 5 Launch System description
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
KTH 05/2006
Page 41
• 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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Page 42
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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Page 43
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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Page 44
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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Page 45
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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Page 46
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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Page 47
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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Page 48
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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Page 49
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