Le transport spatial européen : hier, aujourd hui, demain. J. Berenbach, CNES/DLA

Transcription

1 Le transport spatial européen : hier, aujourd hui, demain J. Berenbach, CNES/DLA

2 SUMMARY Les lanceurs européens : petit historique Les lancements à venir depuis la Guyane Les lanceurs futurs européens Les concepts futuristes This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 2

3 Glossary Sigle Libellé A5 Ariane 5 BCER CSG Centre Spatial Guyanais CUST Cryogenic Upper Stage DTL-X Ultra-Light Thermostuctural Nozzle EAP Etages d accélération à poudre ELV Expandable Launcher Vehicle EPC Etage principal cryotechnique ESC Etage supérieur cryotechnique FLPP Future Launchers Preparatory Programme GEO Orbite Géostationnaire GG Gaz Generator GLOW Gross Lift-Off Weight GTO Geo Transit Orbit H/W HardWare HEDM High Energy Density Materials/Matter HTE High Thrust Engine H-X ISP ISS International Space Station IXV Intermediate experimental Vehicle (IXV) LCH4 Méthane liquide LEO Low Earth Orbit Sigle Libellé LH2 Hydrogène liquide LHC LOX Oxygène liquide LV Launch Vehicle MLA Micro Launcher Airborne MLAL Micro Launcher AirLauncher MLR Micro or Mini Launcher Reusable MPS Moteur propulsion solide NGL Next Generation of Launchers ODP Oscillations de pression OTV Orbital Transfer Vehicle P/L PayLoad PET PRE-X European gliding reentry demonstrator R&T Research & Technologies RLV Reusable Launcher Vehicle SNE S Nozzle? SPS Snecma Propulsion Solide SSO Sun Synchronous Orbit TP TurboPump TRL Technology Readiness Level UDMH Unsymmetrical Dimethylhydrazine UOHB This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 3

4 Les lanceurs européens : petit historique

5 DIAMANT Performances : 200 km cir. / 5 : 220 kg 1000 km cir. / 5 : 40 kg Base : Kourou 2 N Fairing : Ø 1,23 Cost unknown S17 P4 P0,68 1er 2è 3è 4è Programme partners DIAMANT A : DIAMANT BP 4 : 4 flights in 1975 Total : 14 satellites launched This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 5

6 Precious stones programme /11/65 06/02/ Sounding rockets Launchers This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 6

7 BLACK ARROW Base : Woomera Performances : 220 km / 30,9 : 135 kg 500 km / 30,9 : 102 kg 30,9 N Fairing : Ø 1,37 m (ext.) Cost unknown K H2O2 N2O4 UDMH P 1er 2è 3è 4è Programme partners 3 failures (2 in 1969, 1 in1970) 1 success in 1971 ROYAL AIRCRAFT ESTABLISHMENT SAUNDERS ROE This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 7

8 EUROPA I & II Performances : 200 kg GTO > 1 T LEO Bases : Kourou & Woomera 2 N 30,9 N Fairing : Ø 2 m (ext.) Cost unknown LOX RP-1 N2O4 UDMH N2O4 Az50 P 1er 2è 3è 4è Programme partners 5 ballistic tests ( ) 6 launch attempts ( ) This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 8

9 ARIANE 1-4 Family ARIANE 4 GTO Performances : A42-P : 3063 kg A44P : 3577 kg A42-L : 3572 kg A44-LP : 4330 kg A44-L : 4947 kg Base : Kourou 2 N Fairing : Ø 4 m (ext.) Prce : 100 M$ (ARIANE 44L) 0/2/4P9 0/2/4L39 N2O4 UDMH N2O4 UDMH H10 1er 2è 3è 4è Programme partners Commercial launcher A1 A4 : This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 9

10 ARIANE 1 4 development timeline ARIANE 1 ARIANE 2 ARIANE 3 ARIANE This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 10

11 ARIANE 4 versions GTO performances A40 A42-P A44P A42-L A44-LP A44-L 2000 kg 3063 kg 3577 kg 3572 kg 4330 kg 4947 kg This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 11

12 Les lancements à venir depuis la Guyane

13 Current launchers for Europe and possible future A5 evolutions for Current launchers: Opérational: For 2011: Ariane 5 /GS, /ES, /ECA 10t GTO, 10t SSO 20t ISS Soyuz /CSG 3t GTO, 4t SSO Vega 1.5 t LEO Possible future A5 A5 evolutions: A5 ME ESCB + Vinci - P 250? ~11 t GTO ~21 t ISS --- A5 F -> not planned -ESCB + Vinci -MPS 2? -VulcainHTE? t GTO 27 t ISS This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 13

14 Europe : ARIANE 5-ME for 2017 Performance Base : Kourou 11 T GTO Programme partners Family : heavy launcher Operator : ARIANESPACE Versions : G (1996), ECA (2002), GS (2004), ME (proposée pour 2017) Missions : ISS, SSO, MEO, GTO, EXPL Take-off weight 790 T (A5-ME) Maiden flight 2017 Stages : (1) 2 X P240 (2) 1 X VULCAIN 2 LOX/LH2 (3) 1 X VINCI LOX/LH2 This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 14

15 Europe : VEGA Evolution (for ?) Performance Base : Kourou 2 T SSO (?) Programme partners Family : light launcher Operator : ARIANESPACE Versions : Vega, Vega+ (étude) Missions : LEO, SSO Maiden flight 2017? Take-off weight 135 / 140 T Stages : (1) P80 or P100 (2) Z 23 or Z 40 (3)? (4)? This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 15

16 Les lancements futurs européens

17 Launchers for micro to heavy satellites 500 kg 3T Perfo GTO 100 kg 250 kg 800 kg Micro Sats Mini-Micro Mini Sats Small Sats 1.5T 4,5T Perfo LEO Micro LV classical or airborne 5-10 T GLOW Mini LV classical or airborne T GLOW Vega - Mini LV classical T GLOW Vega - Vega T GLOW Soyuz - NGL T GLOW Ariane 5 - NGL T GLOW This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 17

18 Future Launchers Preparation Major objectives: To adapt the current launchers to the needs for : Identify the future needs missions, payload mass, orbits Adaptation to new missions reignition capability Introduce cost reduction improvements Increased availability and flexibility To prepare the new generation launchers (NGL) for ARIANE 6 To prepare technologies evolutions for for NGL A6 To prepare the long future after 2030 This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 18

19 Open possibilities for future heavy ELV for 2025 in Europe and associated Demonstrators Preparatory Phase Decision Development Phase Decision First flight A5 ECA in operation A5 Mid Life evolution studies and development Demonstrators: H-X, CUST, ODP-X ARIANE 5 Mid Life Evolution in operation (new H-Vinci, etc ) New New generation generation ELV ELV studies studies Demonstrators Demonstrators :: P80, P80, Vinci, Vinci, Vulcain-X, Vulcain-X, H-X, H-X, CUST, CUST, HTE HTE demo, demo, Lox/Methane Lox/Methane demos, demos, ODP-X ODP-X New Generation Launcher Ariane 6 This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 19

20 Possible future heavy launchers for Europe in 2025 : New Generation Launcher NGL Two Two or or three stages+ boosters ELV /8 2-6/8 t t GTO GTO t t LEO LEO LEO LEO + orbital transfer OTV Heavy LEO Hydrogene, methane or kerozene, solid propellants Low Low cost cost engines :: Solid propellant Liquid propellant This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 20

21 CNES Future Launchers Preparatory Activities for NGL Ariane 6, in multilateral cooperation Techno Demonstrators for The future : -Avionics -System Ariane 6 concept Studies Objectives : Low cost and low weight cryo upper stage Cryo Demonstrators H-X Techno demos (CNES) for future cryo upper stage (CNES, DLR, CDTI,. ESA, ASI??) Solid propulsion demo: - small scale - Large scale (CNES, +.?) Low cost cryo main stage or Low cost solid propellant booster Low cost High Thrust Engine Air Liquide Vulcain-X Low cost S/Syst. Démos (CNES, SNSB, Belgium Coopé.) P180 EUP, SPS, SME ODP-X Pressure Oscillations Demo (ESA-CNES Coope.) PPH configuration HH Configuration HTE Studies High Thrust Engine NE-X Nozzle Extension TP-X GG-X VGC-X Snecma, Volvo, TA Volvo This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 21

22 Possible future complementary boosters for 2025 for Europe Flexibility with versatile number of boosters Low cost new technologies derived from P80 demonstrator : C fiber casing, new nozzle Fixed nozzle to reduce cost SPS courtesy This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 22

23 Technologies Axis for Future NGL for Europe for First Stage: high thrust cryogenic engine LH2/LO2 at low cost, or solid propulsion at low cost and low thrust oscillations best choice of the two types of propulsion Upper stage: LH2/L02 at high ISP -> VINCI expander engine re-ignition capability for versatile missions -> VINCI engine mastering of long ballistic phases This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 23

24 Possible future small launchers for Europe for ? VEGA possible evolutions : - Upper stages: Ly/Aestus 1 or 2, or Cy/Myra methane, - First stages: P100-Z23, P100-Z40, or P100 alone. -> perfo increased from 1,5 T LEO to 2-3 T depending from configuration Lyra : Véga with C10 upper stage ( Myra engine, Isp 360 s) instead of Z9 and Avum Lyra enhanced : Lyra with 2 xz23 added boosters LYRA VEGA Mini Véga* kg SSO ELV This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 24

25 Possible future mini and micro launchers? Launched from from ground :: Airborne :: MLC Micro or Mini Launcher Classical kg SSO 3 stages- 150 kg P10- P10- P2 P13- P5- L1 2 stages- 150 kg P19- C5 C18- C2 For 300 kg P20- P20- L4 MLA Micro Launcher Airborne kg SSO Py- (2Px)- Lz - MLAL Mini Launcher Airlaunched kg SSO Px- Py- Lz - MLR Micro or Mini launcher reusable This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 25

26 Possible future nano launchers? PERSEUS: a nano launcher developed by students for 10 kg at 250 km orbit Solid, liquid or hybrid propulsion- GLOW 5-10 T This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 26

27 Possible future nano launchers for Europe PERSEUS project Airborne launcher for nano-sat: DEDALUS (CNES + ONERA) 10 kg at 250 km Increasable up to 50 kg 3 stages solid propellant launcher, ~ 3,1 T, L=6 m carrier : 19 m span, 11 m length, ~ 2,6 T loaded weight This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 27

28 Possible future nano launchers PERSEUS project Hybrid propulsion (liquid+solid) N2O + PET or LOX+ Wax mean ISP about 250s or more High thrust possible Onera H/W and test This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 28

29 Possible new future Missions Orbital Station From the Earth to the Moon, Mars or another Star Lander Orbital Station Return Capsule Exolauncher Base Launcher Manned Vehicle Orbital Transfer Vehicle (OTV) Or Earth Departure Stage (EDS) Terre Reentry Vehicle Circularisation Vehicle This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 29

30 Active Debris Removal Concepts BOEING Adaptation of a solar electric tug to pull & deorbit debris CNES Debris hunter with arm & multiple deorbitation kits DLR Robotic arm variant (DEOS) DLR Net capture (ROGER concept) SSTL Solar sail for slow deorbitation of debris This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 30

31 Les concepts futuristes

32 Possible future Reusable Launch Vehicles RLV or semi-rlv and corresponding propulsion for 2030 and after This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 32

33 Possible Heavy RLV for long term (2030+) Some possible concepts (Astrium, CNES) BARGUZIN ARIANE 5 central stages Reusable liquid boosters for GTO or LEO satellites Vulcain 2 engines EVEREST LOx/LH2 reusable booster LOx/LH2 reusable orbiter for GTO or LEO satellites VEDA SC engine, 170 TF AMAZONE LOx/LH2 or LCH4 reusable booster & orbiter siamese and modular For GTO or LEO satellites VEDA orvolga CH4-230 T This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 33

34 Possible Heavy RLV for long term (2030+) opposite engine emergency cut-off one engine failure Barguzin (Astrium+ Tsniimash + Molnya) Vulcain 2 engines This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 34

35 Possible Heavy RLV for long term (2030+) Everest (Astrium+ Dassault) 170 T SC LH2 VEDA engines (Snecma) Booster H432 Minert= 108,5 k= 25,11 Orbiter H196 Minert=49,4 k=25,15 EUS K12,3 Minert=1,95 k=15,85 LEO P/L= GTO P/L= 7500 GLOW= 810 This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 35

36 Various types of RLV or semi-rlv projects (FESTIP) Semi-reusable suborbital Semi-reusable suborbital Semi-reusable with two stages (VTHL) Semi-reusable airborne (HTHL) Reusable first stage (VTVL) This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 36

37 European projects of suborbital vehicles ASTRIUM Apogee > 100 km Autonomous System Capacity : 4 pax + 1 pilot «safety first» Motorisation LOX/LCH4 Max speed Mach 3,5 DASSAULT «VSH» Apogee > 100 km Airborne system Capacity : 4 pax + 1 pilot «safety first» Motorisation: RD-0110 Max speed: Mach 3,5 This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 37

38 Future Launchers Preparation The Advanced Concepts and corresponding propulsion This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 38

39 The advanced concepts Orbital Transfer Vehicles (OTV) at low thrust heliothermal + LH2: ISP =800 s T= 10 to 500 N cryotechnical: ISP 430 s T= 0,1 to 100 kn This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 39

40 Picture of a heliothermal «Orbital Transfer Vehicle» This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 40

41 The advanced concepts Nuclear Orbital Transfer Vehicles Nucleo-thermal propulsion + LH2 ISP = 850 s, Thrust up to 390 kn (ex: Nerva project, USA) Nucleo-electrical propulsion: ISP > 2000 s, Thrust < 100 N This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 41

42 Nucleo-Thermal Propulsion PRINCIPAL : Acceleration of a fluid by heating Tested/qualified (1960) High Isp: s Thrust 89 T Problem: radioactivity APPLICATION NERVA 1969 (upper stage on SATURN V-25) Mass stage/struct.: 245/41 T Duration: 1500 Sec Isp: 825 Sec F: 89 T Thrust This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 42

43 A picture of a nucleo-thermal «Orbital Transfer Vehicle» This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 43

44 Nucleo-electrical propulsion Production of electrical power by a nuclear reactor Use of this electrical power by an electrical thruster for propulsion This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 44

45 Electrical Propulsion Thruster IONIC: ionisation of a gas thruster accelerated by an electrical field high Isp (> 2000 Sec), but low thrust : some N high specifical mass (5 kg/kw) low acceleration PLASMIC: ionisation of a gas thruster accelerated by an electromagnetic field high Isp (> 2000 Sec) low thrust : some N high specifical mass (5 kg/kw) low acceleration This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 45

46 Picture of a nucleo-electrical «Orbital Transfer Vehicle» This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 46

47 Future Launchers Preparation CONCLUSION Targets for the future : Lower cost, higher performance (as usual), simple operations Simplified systems, evolved propulsion and enhanced systems Partial reusability for the long future? New concepts can emerge for mini launchers for micro sat or nano sat Search for low cost (problem for this size) Towards airborne or semi-reusable concepts? THANK YOU FOR YOUR ATTENTION This document is CNES property. It shall not be communicated or copied without written authorization from CNES-DLA 47