ATV
HOTOL SAENGER Ariane 5 + HERMES
ARD
European Space Transportation System Projects since 1998
Crew Transport Studies Jürgen Herholz Mars Society Deutschland www.marssociety.de
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 1 Situation in Europe in 1985 Upcoming European Participation in Space Station No European Capacity for Man and Heavy Load Transportation Full Dependency on Shuttle Existing European Tradition in Winged Vehicle Studies (Eugen Saenger)
Space Transportation System Development Guidelines Limitation of manned Missions to Crew Transport plus minor Payload Transport of Satellites and heavy Payloads with unmanned Launch Systems Automatic Docking to ISS rather than man-tended Reduce Operations Cost by ¾ “Maintenance Friendly” Design (few Elements, few replaceable parts) ¾ „Airport Like“ Operations (SAENGER, HOTOL) ¾ Use of existing Facilities wherever possible
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 2 Winged Space Transportation Programs studied in Europe
HOTOL - UK Single Stage
All three Programs abandoned 1992
HERMES - ESA
Launched on Top of Ariane 5
Two Stage
Saenger - Germany
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 3 HOTOL- UK
Manned and Unmanned Versions Horizontal Takeoff and Landing Fully Reusable Stopped 1988, Antonov-carried Version stopped 1991 Pre-Design, no Proof of Concept
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 4 HOTOL Characteristics
Length 63 m, 7 m Diameter, 7 t Payload H/O Rocket Engine Rolls-Royce RB545 ¾ Utilisation of liquefied Oxygen up to Mach 7 and 32 km Altitude Problem Areas ¾ Heavy Engine, Problems to match CoG and CoP ¾ Oxygen Collection and Liquefaction difficult ¾ Structure and Thermal Protection ¾ Long cruising Phase at Mach 2 decreases System Efficiency ¾ Political Environment not favourable (as for Saenger)
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 5 Hermes System
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 6 The HERMES Carrier - Ariane 5
21 t to ISS, 4,5 m Payload Diameter similar to Shuttle Launch Cost 25% below Ariane for 2 GTO Satellites Launch Success Probability higher than Ar4 (0.99 instead 0.92) ¾ Limits Launch Cost (Insurance) ¾ Important for manned Application Limit Design / Operations Risks / Cost ¾ 1.Stage: cheap and reliable Solid Boosters ¾ 2.Stage: 1 cryogenic H/O Engine with moderately advanced Technology, now improved ¾ 3.Stage: conventional Technology, now modified Cryogenic Stage of Ariane 4 ¾ Less Elements than Ariane 4 ¾ Use / Continuation of Ariane 4 Design (tanks, launcher control, mission control)
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 7 Ariane 5 Versions
Payload Mass [t] Key Difference AR5 Liftoff Version Mass GTO SSO LEO Generic 746,00 6,00 9,50 (23) Foreseen for HERMES Evolution 6,15 More propellant Cryogenic Upper Stage, improved ECA 780,00 9,60 Vulcain 2 1st Stage Re-ignitable 2nd Stage, improved GS 750,00 6,70 Solid Boosters
ES ATV 21,00 Reinforced Vehicle Equipment Bay
GTO=Geostationary (Elliptic) Orbit
SSO= Sun Synchronous Orbit
LEO=Low Earth Orbit
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 8 Ariane 5 / HERMES Composite
Top mounted HERMES allows use of single Launcher for automatic and manned Payloads ¾ Better Rescue Potential than Side mounted Max HERMES Launch Mass 23 t (no AR Equipment Bay) No Damage of HMS at Launch possible as for STS Aerodynamic Force limits HERMES Wing Surface to 85m2 Crew Survival Requirement (0.999) requires Crew Rescue Capabilities ¾ Launch Phase: Ejection Seats up to Mach 2 ¾ Entry/Landing: similar to Shuttle Control of the AR5/HMS Composite by HERMES ¾ Common use of HMS Flight Computers ¾ HMS Flight Computer System is more reliable
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 9 Evolution of the HERMES Space Vehicle Configuration 1990-92 1985-Free Flyer (8R2)
Space Plane (SP) Resource Module (RM) •separates prior Entry 1987-Space Station•burns Servicing up ISS Waste 1983-Free Flyer
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 10 Evolution of the Space Vehicle Performance
80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 5M1 8R2 Primary Mission Autonomous Space Station Supply Crew 4 3 Payload 4 t 3 (HMS 1,5 RM 1,5) Docking Capability No Yes EVA (Extra-Vehicular Activities) No Yes Resource Module (RM) No Yes Program Duration 8 Years 12 Years
• Funding Problems • Program Extension NOT Cost optimised
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 11 HERMES Characteristics -8R2 Version 1992-
Servicing of Space Station and Free-Flying Module (MTFF) ¾ 3 Crew Transport (up and down) ¾ 3 t Payload up, 1.5 t down Landing and Refurbishment in Europe 2 Missions / Year 15 Missions Lifetime without Replacement of Thermal Protection Up to 30 Days Stay Time in Orbit Docking and EVA Capability Crew Survival Probability 0,999 ¾ requires Crew Rescue System ISS Proximity Operations, Docking requires Failsafe Design
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 12 Resource Module Benefits
Reduces Entry and Landing Mass of the Space Plane ¾ Allows smaller Wings (85 m2 Limitation) ¾ Improves CoG / CoP Relation in all Flight Domains Allows Docking to ISS Standards (Docking Port Diameter) Allows EVA
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 13 Evolution of Mass und Program Cost
Free-Flyer Mission MTFF/ISS Servicing Mission
80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 French National Feasibility & Concept Studies 5L3 5M1 5M2 8M1 8P9 8R1 8R2 HERMES Versions
Mass Evolution [t] Mass Prediction [%] 24 100 23 85% 22 Confirmation 21 by industrial 20 43% Estimates 19 18 23% 17 5...15% 0
Cost Evolution [B!] 7 •2 B! 66,7 •unmanned •Full-size HERMES System 5 Munich •Technology 4 Demonstrator 34,4 Spaceplane only 2 2 The Hague 2X-2000 1 Rome Granada
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 14 HERMES Program History 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 Ariane 5 Development Decision French national Program HMS Prep.Prog. Predevelopment (C1 / C2.1 / C2.2) Technology (MSTP)
CNES / Aerospatiale / Dassault + Europe ESA / CNES / Industry ESA / Industry
French Vehicle Feasibility & Concept Studies 5L3 5M1 5M2 8M1 8P9 8R1 8R2 HERMES Versions X-2000 SCR PDR
French National Funding ESA Funding 350 M! 270 M!
Industrial Consortium Eurohermespace EHS
Ministerial Conferences German X-2000 Proposal Rome The Hague Unification Munich Granada HERMES Program Program Decision Program Demonstrator abandoned (Studies) Decision X-2000 for 2 B! MTFF cancelled (Predevelop ment Phase) MSTP,ARD,ATV,CTV MSTP-Manned Space Transportation Program Studies COL-Columbus Mission: MTFF-Man-Tended Free Flyer Space ESA Program PDR-Preliminary Design Review Station Proposal ARD-Ariane Re-entry Demonstrator Servicing COLUMBUS ATV-Ariane Transport Vehicle ATV CTV-Crew Transport Vehicle
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 15 HERMES Program – Industrial Organisation
In 1992 HERMES occupied approx. 2000 Engineers throughout Europe
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 16 HERMES Program Schedule 1992 Ministerial Conference in Granada
Ariane 5
Hermes Unmanned Automatic Mission Flight Model
Flight Test Model
Structural/Thermal Model
Integration Model
Functional Model
Ground System
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 17 HERMES Launch Facilities in French Guyana Mission Scenario
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 18 HERMES – Docking Manoeuvre
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 19 HERMES – Crew Rescue Principle
•Crew protected by IVA Suit •Up to Mach 3
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 20 HERMES Configuration 8R2 - 1992 HERMES Space Plane Resource Module
12m69 5m61
Crew: 3
5m40
2m96 Launch Mass: 23 t
Mass 15.000 kg Mass 8.000 kg Landing Mass 15.000 kg Payload Mass 1.500 kg Payload in Orbit (28°,400 km) 1.500 kg „controlled Entry and Burn-up“ Payload Landing Mass 1.500 kg
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 21 HERMES Configuration 8R2 - 1992
76 °
9m01
11 ° 2m74
Thermal Protection
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 22 HERMES Configuration 8R2
3 Ejection Seats Payload EVA Suits and IVA* * Intra-vehicular Activities (Extravehicular Activities) Fuel Cells
Personal Galley Accommodation
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 23 1-Fuel Cell HERMES Configuration 2-Star Sensor 3-Inertial Navigation System 4-Control Nozzles 5-Control Nozzles 6-Lithium Batteries 7-Electrical Distribution System 8-Water Vaporiser 9-Landing Gear 10-Control Surface 11-Crew Access Port 12-Ejection Seats 13-Privacy Area 14-Crew Quarters 15-Payload (RM Part) 16-Crew Access Tunnel Sealing 17-Oxygen Tank 18-Water Tank 19-Separation Device 20-Separation Device 21-Waste Container 22-LiOH Cartridge 23-Fuel Tank 24-Docking Interface 25-EVA Exit Port The 9th International Mars SocietyItems Conference located in Washington in DC,the 3-6 RM Aug 2006 26-Deployable Freon24 Radiator Major Technologies Heritage (in Parentheses: Previous Applications)
Thermal Protection for up to 1700 °C (Missile) Life Support System (Spacelab) EVA and IVA Suit (Spacelab, Aircraft) Manipulator Arm (ISS-ERA) Fuel Cell (Submarine, Other) Navigation and Flight Control (Aircraft, Satellites, Eureca) Failsafe Computer System (ESA Technology, Ariane) Super- and Hypersonic Research and Facilities (G, F, I) Ejection Seats (Aircraft)
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 25 HERMES – Aero-Thermodynamic Analysis Temperature Distribution at Entry
1700 °C
600 °C
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 26 HERMES – Aero-Thermodynamic Test Model for Tests up to Mach 9 (DLR-Germany)
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 27 Development Status at Program Termination 1992
HERMES Feasibility confirmed by independent Experts (PDR in 1991) ¾ Space Plane and Resource Module Design to Equipment Level ¾ Validity of Ariane 5 / HERMES Composite ¾ Avionics System ¾ Product Assurance and Safety ¾ Mission and Operations Analysis and Design ¾ Aerodynamic and –Thermodynamics Design ¾ Orbit Dynamics, Entry and Landing ¾ Industrial Mass Estimates with Confidence in Feasibility ¾ Test of critical Hot Structure Samples ¾ Failsafe Computer Breadboard
>> Documentation of Results on 65 CD‘s in 1996
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 28 Conclusions
Budget Constraints were the main Reason for Program Termination
Priority on Ariane 5 and ISS Participation (COLUMBUS, ATV, Utilisation)
HERMES was not accepted as Part of the ISS Scenario
Additional Budget Constraints following the German Unification
Reluctance of the scientific Community towards manned Projects
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 29 SAENGER System
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 30 Saenger Predecessor
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 31 Saenger Design Objective: Reduce Launch Cost by using a single fully reusable multi-Purpose Launch System and Separation of manned and unmanned Mission Types -Single Launch Cost Projection -
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 32 Baseline Mission Model
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 33 Concepts Evaluated
B ASingle-Stage air breathing horizontal Launch (HOTOL) BTwo-Stage air breathing horizontal Launch (Saenger) CSingle-Stage Rocket propelled, vertical Launch DTwo-Stage Rocket propelled, vertical Launch
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 34 Principle Concept Selection Criteria
Selection Criteria Concept A B C D HERMES
Direct Orbit Access from Europe -+-- -+(Landing) Hypersonic Passenger Transport -+-- - Airport Launch / Landing Capability ++- - - Proven Propulsion Concept -+ + + Payload Performance Risk (Sensitivity) -+-+ - Launch Cost Reduction ++++ +
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 35 Saenger Configuration
1. 1st Stage EHTV (European Hypersonic Transport Vehicle) ¾ Space Booster for HORUS and CARGUS ¾ Hypersonic Transport of 225 Passengers or Cargo over 16000 km at Mach 4+ 2. 2nd Stage HORUS ¾ Space Station Support: 2-12 Persons + 2-4 t Payload ¾ Based on HERMES 3. Or: 2nd Stage CARGUS ¾ Up to 14 t and 4.5 m Diameter LEO Payloads ¾ Satellites of 3.8 tons into GTO
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 36 Comparison EHTV – Boeing 747
B 747 EHTV
Launch Mass 370 t 265 t Propellant Mass 120 t 120 t Passenger + Payload Mass 63 t 25-35 t Vehicle Length 70.5 m 93 m
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 37 Saenger Design Characteristics
Final Altitude 200-450 km (Space Station, Parking Orbit) Cross Range of 2500 km to reach Europe from 18.5 ° Orbit Cruising Altitude 36-39 km 1st Stage with Air breathing Turbo-Ramjet Propulsion 2nd Stage HORUS (manned) ¾ 2 Rocket Engines ATC-700 (LH2/LOX) 2nd Stage CARGUS (unmanned) derived from Ariane 5 Up to Mach 6.6 at Time of Separation Mach 5 needed to reach 28.5 ° Latitude at Separation
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 38 Mass Budget [tons]
Total Vehicle Launch Mass 220-339 First Stage EHTV * 165-265 * European Hypersonic Transport Vehicle -Propellant 60-150 -Landing Mass 110-175 Second Stage HORUS 74 -Propellant Mass 55 - Payload Mass 2-4 t -Landing Mass 12-16 -Passengers 2-12 Second Stage CARGUS 55 -Propellant Mass 50 -Payload 6-14
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 39 Saenger Mission Profile for GTO Payload
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 40 Saenger Mission Profile
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 41 Saenger Mission Profile
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 42 EHTV Configurations
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 43 EHTV Basic Data
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 44 EHTV Passenger Cabin
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 45 HORUS
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 46 HORUS
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 47 Comparison HERMES-HORUS-Shuttle
Hermes
Horus
Shuttle Orbiter
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 48 Comparison HERMES-HORUS-Shuttle
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 49 2nd Stage CARGUS Launch of conventional Payloads of up to 14 t in LEO or 3.8 t in GTO • Spacecraft • Platforms • Pressurised Modules
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 50 Saenger Technologies
Turbo-Ramjet Engine ¾ Air breathing up to 40 Km Altitude and Mach 6,6 ¾ Engine Technology-Pre-Development, 12.5 KN Thrust, 60s Rocket Engine MBB ATC-700 (LH2/LOX) ¾ High Specific Impulse 470 s ¾ Feasibility Tests performed at MBB Lightweight Structure High Temperature resistant Thermal Protection
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 51 Comparison Shuttle-Ariane 5-HORUS
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 52 2nd Stage CARGUS Derived from Ariane 5 H.140 Stage
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 53 Saenger Development Schedule
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 54 Saenger Development Cost
Cost in ’87 PB Man-years Remark [B!] EHTV 64,000 7,300
EHTV Engine 12,000 1,400 Use of HERMES HORUS 30,000 2,800 Technology HORUS ATC-700 8,000 0.750 Engine
Total 120,000 12.250
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 55 Saenger - Reasons for Project Termination 1992
Focus on Space Station and Ariane 5 Uncertainty on Long-term Space Program Objectives ¾Saenger Efficiency highly dependant on Mission Model Development / Cost Risks ¾ Turbo-Ramjet Engine ¾ External Heating at Mach 4-7 Multi-Wall thermal Protection Materials Thermal Protection ¾ Aerodynamics and Aero Thermodynamics ¾ Stage Separation Dynamics ¾ Lightweight Structures
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 56 HERMES Follow-On Programs after 1995
ATV - ESA Launch 2007
ARD - ESA
launched 1998
Crew Transport Studies
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 57 ATV- Automatic Transfer Vehicle
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 58 ATV - Automatic Transfer Vehicle
ISS Servicing, Launch 2007 by Ariane Indispensable ISS Part only after 1992 Carries Supplies for the ISS, the Crew and Experiments to the ISS Up to 8 t Cargo total, pressurised up to 5.5 t, Fuel up to 4.7 t Re-Lifts the ISS to a higher Orbit Burns ISS Waste at controlled Entry Up to 2 Missions / per Year Fully automatic Meeting ISS Failsafe Requirements Length 9.8 m, Diameter: 4.5 m Solar Panels: 22.3 m Launch Mass 20.7 t
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 59 ATV- Automatic Transfer Vehicle
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 60 ATV- Automatic Transfer Vehicle
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 61 ARD - Ariane Re-Entry Demonstrator
Configuration Experimental Entry Vehicle 70% Apollo Type Capsule Drop Test from Balloon in Sicily 1996 Launched 1998 with Ariane 5 2,80 m Diameter, 2,04 m high, 2,8 t Mass Existing Technology from Ariane Use of HERMES Aero thermodynamics and During Integration Material Development Proof of Concept for ¾ Attitude Control and Navigation ¾ Thermal Protection ¾ Data Transmission and Evaluation ¾ Orbit Calculation ¾ Tracking, Entry, Recovery on Sea ¾ Parachute System
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 62 ARD – Mating with Ariane 5
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 63 ARD – Mission Scenario Flight Time: 101 min
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 64 ARD – Sea Recovery and Postflight Inspection
Sea Recovery Heat shield after the Mission
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 65 CTV Studies Clipper with Russia
X-38 with NASA
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 66 Conclusion - Outlook
US STS Concept originally similar to SAENGER ¾ Present Concept selected for Cost / Risk Schedule Reasons 30 Years later: SAENGER Concept more feasible than original US STS due to Technology Progress since 1975? ¾ Experience with Manned Systems ¾ Turbo ramjet / Scramjet Engine Research ¾ Lightweight heat resistant Materials ¾ Experience with Shuttle, Concorde >> Long-term Objectives? Missions? International Cooperation? Hypersonic Passenger Transport? >>
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 67 ATV
HOTOL SAENGER Ariane 5 + HERMES
ARD
European Space Transportation System Projects since 1985
Jürgen Herholz Thank You for Your Attention Mars Society Deutschland www.marssociety.de
The 9th International Mars Society Conference in Washington DC, 3-6 Aug 2006 68