Space Transportation Systems System Concepts

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DGLR / CEAS European Air and Space Conference 2007

DGLR Fachausschuss Raumtransportsysteme S4.1 / om-Raumtransportsysteme-Markt-Bedarf-V9 / 27.6.07

Space Transportation SystemsSpace Transportation Systems

System ConceptsSystem Concepts

Status of DiscussionDGLR-Fachausschuss S4.1

J. Kauffmann

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DGLR Fachausschuss Raumtransportsysteme S4.1 System Concepts

Outline

•• Europe's family of LaunchersEurope's family of Launchers–– Ariane 5Ariane 5–– VegaVega–– Soyuz CSGSoyuz CSG–– EvolutionsEvolutions

•• Future LaunchersFuture Launchers–– Long TermLong Term–– Short TermShort Term

•• SynthesisSynthesis

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FamilyFamily

Europe's access to space is build on a family of Launchers:

• Ariane 5– Ariane 5 ECA– Ariane 5 GS– Ariane 5 ES/ATV

• VEGA• Soyuz

Europe's family of launchers

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FamilyFamily

Ariane 5• Ariane 5 is since 1997 the main element of

European space transportation• Currently three different versions exist:

– Ariane 5 ECA– Ariane 5 GS– Ariane 5 ES ATV

• The current workhorse is the ECA version:– Perfo: 9.6 Mg GTO, – Double launch capacity

• => optimized for commercial missions to GTO• Whereas the ES/ATV version allows access to the

ISS • Limited reignition capability exists via the ES

version

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FamilyFamily

•• Vega will complete the Vega will complete the performance range on performance range on the lower end beingthe lower end being

•• tailored for small to tailored for small to medium sized satellite medium sized satellite payloads on missions to payloads on missions to LEO and SSOLEO and SSO

•• FourFour--stage design using stage design using solid propellant motorssolid propellant motors

•• Payload capacity of 1.5 Payload capacity of 1.5 Mg into a 700 km circular Mg into a 700 km circular polar orbitpolar orbit

•• First Flight : end of 2008First Flight : end of 2008

Vega

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FamilyFamily

Soyuz CSG

•• Ariane 5 will be Ariane 5 will be complemented in CSG complemented in CSG with the Russian Soyuz with the Russian Soyuz 22--11--a Launch Vehiclea Launch Vehicle

•• versatile launcher, versatile launcher, allowing for medium GTO allowing for medium GTO payloads (3 Mg), MEO, payloads (3 Mg), MEO, LEO and SSO satellites, LEO and SSO satellites, as well as Earth escape as well as Earth escape missionsmissions

•• First flight from CSG First flight from CSG foreseen foreseen beginning of beginning of 20092009

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FamilyFamily

Evolutions of current family of Launchers• are restricted to the European launch systems

Ariane and Vega• are mainly driven by the interest to

– Increase the performance– Increase versatility– Maintenance of industrial competences– Cost reduction

• For Ariane :– SRB overloading + more powerful, reignitable cryo

upper stage; perfo GTO +2 Mg• For Vega:

– Increase of performance of all three SRB and/or reignitable upper stage, Perfo 2 Mg 700km polar, 1 Mg MEO direct

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ESA Future LaunchersESA Future Launchers

Future Launch Systems

which are currently being considered are which are currently being considered are characterised by two distinct features:characterised by two distinct features:

•• The scenario The scenario w.r.tw.r.t. the initial operational . the initial operational capability capability

•• For the long term beyond 2020; the Next Generation For the long term beyond 2020; the Next Generation Launcher (NGL)Launcher (NGL)

•• For the short term around 2015; the For the short term around 2015; the ““Building BlockBuilding Block””LauncherLauncher

•• the priority to the fulfil the European the priority to the fulfil the European institutional needs, with the potential to institutional needs, with the potential to address the commercial market as an address the commercial market as an opportunity to support a cost efficient opportunity to support a cost efficient exploitation, which drives their conception exploitation, which drives their conception

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Mission Requirements The reference mission for both scenarios is to address The reference mission for both scenarios is to address European institutional needs, for LEO, MEO and GTO European institutional needs, for LEO, MEO and GTO missionsmissions

• Single launch

• Reference performance : 5 Mg in GTO (performance equivalent) institutional

• Enhanced performance for commercial missions: 8 Mg in GTO for a single pay-load

• Versatility through upper stage restart capability

• Performance modulation preferably through the lower composite architecture (use of different combinations of strap-on boosters)

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• Lower Composite– P240/P240-FW + P80 + strap-on boosters– 1 Vulcain2 + strap-on boosters– 2 Vulcain2 + strap-on boosters

The design of the LV concepts shall be based as far as possible on elements (Building Blocks) existing in Europe:

Building Block Launcher

• Upper Composite− Cryogenic restartable (based on

Vinci)− Storable restartable (based on Aestus

/ Aestus-2)− Cryogenic + storable kick-stage− Methane restartable (based on e.g.

MIRA)

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Next Generation Launcher (Expendable)

The design of the LV concepts rely on new elements:

•• Lower Composite LH2 options:Lower Composite LH2 options:–– LOX/LH2 with gas generator cycle, performance LOX/LH2 with gas generator cycle, performance

optimized engineoptimized engine–– LOX/LH2 with gas generator, lowLOX/LH2 with gas generator, low--cost enginecost engine–– LOX/LH2 with staged combustion engineLOX/LH2 with staged combustion engine

• Lower Composite– Solid propellant + solid Boosters – LOX/Methane propellant + solid Boosters – LOX/LH2 propellant + solid Boosters

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Next Generation Launcher (Expendable) The design of the NGL upper composite shall rely on the activities for the Building Block concepts but with relaxed TRL requirement (IOC 2020+):• Upper Composite

– Cryogenic restartable (based on Vinci)– Storable restartable (based on Aestus /

Aestus-2)– Cryogenic + storable kick-stage– Methane restartable (based on e.g.

MIRA)

• Innovative low thrust upper stage concepts:– Low thrust pressure-fed upper stage– Cryogenic orbital propulsion (use of fuel

cells)– Solar thermal with solar concentrators or

solar arrays– Electric propulsion

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• Sub-orbital Hopper-class

• Reusable First and Booster stages-class

FSSC-1 FSSC-3 FSSC-4 FSSC-5 FSSC-9 FSSC-12 FSSC-15 FSSC-16 SR FSSC-16 FR

ASSC-1 (Sub Orbital Hopper DLR)

ASSC-2 (LFBB - DLR)

Reusable First Stage (CNES) EVEREST (CNES)

VEHRA (DASSAULT)

Kistler K-1 Roton AirLaunch X-34 ROLV MAKS (Cargo) ANGARA\Baikal

Interim HOTOL (BAE - TsAGI)

BOOMERANG (EADS-Khrunichev)ASTRAL

(DLR-Khrunichev)

BARGOUZIN (CNES-Tsniimash)

Lockheed Martin /EADS-ST Liquid First Stage

RLV concepts studied in the frame of the previous ESA FESTIP program

RLVs studied in national programs in Europe

RLV concepts studied in USA and in Russia

European-Russian cooperations European-U.S.A cooperations

FSSC-1 FSSC-3 FSSC-4 FSSC-5 FSSC-9 FSSC-12 FSSC-15 FSSC-16 SR FSSC-16 FR

ASSC-1 (Sub Orbital Hopper DLR)

ASSC-2 (LFBB - DLR)

Reusable First Stage (CNES) EVEREST (CNES)

VEHRA (DASSAULT)

Kistler K-1 Roton AirLaunch X-34 ROLV MAKS (Cargo) ANGARA\Baikal

Interim HOTOL (BAE - TsAGI)

BOOMERANG (EADS-Khrunichev)ASTRAL

(DLR-Khrunichev)

BARGOUZIN (CNES-Tsniimash)

Lockheed Martin /EADS-ST Liquid First Stage

RLV concepts studied in the frame of the previous ESA FESTIP program

RLVs studied in national programs in Europe

RLV concepts studied in USA and in Russia

European-Russian cooperations European-U.S.A cooperations

• Sub-orbital Hopper-class

• TSTO-class

• Reusable First and Booster stages-class

• Parachute-retrievedclass

• Air-launched

Initial concept candidates Current conceptsNext Generation Launcher (Reusable)

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SynthesisSynthesis

•• Europe has with Ariane, Vega and Soyuz a LV family Europe has with Ariane, Vega and Soyuz a LV family covering a broad range of different missions and covering a broad range of different missions and performances, especially for the current commercial and performances, especially for the current commercial and institutional market institutional market

•• Some flexibility maybe added Some flexibility maybe added w.r.tw.r.t missions requiring remissions requiring re--ignition capability ( e.g. direct MEO and GEO)ignition capability ( e.g. direct MEO and GEO)

•• Interest in RLV as a means to reduce recurring cost for Interest in RLV as a means to reduce recurring cost for classical unmanned space transportation missions is classical unmanned space transportation missions is decliningdeclining–– Interest in reusability technology Interest in reusability technology maybemaybe revived by nonrevived by non--

classical approaches such as space tourismclassical approaches such as space tourism•• A Next Generation Launcher will not be operational before A Next Generation Launcher will not be operational before

the 2020 the 2020 –– 2025 timeframe => key industrial competences 2025 timeframe => key industrial competences need to maintainedneed to maintained

•• Space Exploration may become a strong driver for design Space Exploration may become a strong driver for design requirements on future launchersrequirements on future launchers

Space Transportation Systems System Concepts

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