Space Transportation Systems System Concepts Status of Discussion DGLR-Fachausschuss S4.1 J. Kauffmann DGLR Fachausschuss Raumtransportsysteme S4.1 / om-raumtransportsysteme-markt-bedarf-v9 / 27.6.07 1
Outline Europe's family of Launchers Ariane 5 Vega Soyuz CSG Evolutions Future Launchers Long Term Short Term Synthesis 2
Family 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 3
Family 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 4
Vega Vega will complete the performance range on the lower end being tailored for small to medium sized satellite payloads on missions to LEO and SSO Four-stage design using solid propellant motors Payload capacity of 1.5 Mg into a 700 km circular polar orbit First Flight : end of 2008 Family 5
Soyuz CSG Ariane 5 will be complemented in CSG with the Russian Soyuz 2-1-a a Launch Vehicle versatile launcher, allowing for medium GTO payloads (3 Mg), MEO, LEO and SSO satellites, as well as Earth escape missions First flight from CSG foreseen beginning of 2009 Family 6
Evolutions of current family of Launchers Family 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 7
ESA Future Launchers Future Launch Systems which are currently being considered are characterised by two distinct features: The scenario w.r.t.. the initial operational capability For the long term beyond 2020; the Next Generation Launcher (NGL) For the short term around 2015; the Building Block Launcher the priority to the fulfil the European institutional needs, with the potential to address the commercial market as an opportunity to support a cost efficient exploitation, which drives their conception 8
ESA Future Launchers Mission Requirements The reference mission for both scenarios is to address European institutional needs, for LEO, MEO and GTO missions 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) 9
ESA Future Launchers Building Block Launcher The design of the LV concepts shall be based as far as possible on elements (Building Blocks) existing in Europe: Lower Composite P240/P240-FW + P80 + strap-on boosters 1 Vulcain2 + strap-on boosters 2 Vulcain2 + strap-on boosters 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) 10
ESA Future Launchers Next Generation Launcher (Expendable) The design of the LV concepts rely on new elements: Lower Composite Solid propellant + solid Boosters LOX/Methane propellant + solid Boosters LOX/LH2 propellant + solid Boosters Lower Composite LH2 options: LOX/LH2 with gas generator cycle, performance optimized engine LOX/LH2 with gas generator, low-cost engine LOX/LH2 with staged combustion engine 11
ESA Future Launchers 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 12
ESA Future Launchers Next Generation Launcher (Reusable) Initial concept candidates Current concepts RLV concepts studied in the frame of the previous ESA FESTIP program Sub-orbital Hopper-class FSSC-1 FSSC-3 FSSC-4 FSSC-5 FSSC-9 FSSC-12 FSSC-15 FSSC-16 SR FSSC-16 FR RLVs studied in national programs in Europe ASSC-2 (LFBB - DLR) VEHRA (DASSAULT) ASSC-1 (Sub Orbital Hopper DLR) Reusable First Stage (CNES) RLV concepts studied in USA and in Russia EVEREST (CNES) Kistler K-1 Roton AirLaunch X-34 ROLV MAKS (Cargo) ANGARA\Baikal European-Russian cooperations European-U.S.A cooperations BOOMERANG ASTRAL (EADS-Khrunichev) Lockheed Martin /EADS-ST (DLR-Khrunichev) Liquid First Stage Reusable First and Booster stages-class Interim HOTOL (BAE - TsAGI) Sub-orbital Hopper-class TSTO-class Reusable First and Booster stages-class BARGOUZIN (CNES-Tsniimash) Parachute-retrieved class Air-launched 13
Synthesis Europe has with Ariane, Vega and Soyuz a LV family covering a broad range of different missions and performances, especially for the current commercial and institutional market Some flexibility maybe added w.r.t missions requiring re- ignition capability ( e.g. direct MEO and GEO) Interest in RLV as a means to reduce recurring cost for classical unmanned space transportation missions is declining Interest in reusability technology maybe revived by non- classical approaches such as space tourism A Next Generation Launcher will not be operational before the 2020 2025 timeframe => key industrial competences need to maintained Space Exploration may become a strong driver for design requirements on future launchers 14