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Astrium Space Transportation TMI Dr. Stephan Walther

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1 Astrium Space Transportation TMI Dr. Stephan Walther
Experiences with performed and expectations on future ISTC projects ISTC / STCU Conference Ljubljana, Slovenia March 10-12, 2008 Astrium Space Transportation TMI Dr. Stephan Walther

2 Contents Overview to ISTC / STCU projects: Performed: Inflatable Reentry and Descent Technology Performed: Reusable Multi-layer Thermal Protection Systems Current: In-orbit Demonstration of a Gossamer Structure Current: EXPERT Ongoing: Robotics for Security Experiences / Lessons learnt “Environmental” changes Expectations on the future ISTC / STCU projects

3 IRDT Technology and History
3800 Height : 2037 IRDT Technology and History Lightweight inflatable system combining heatshield, parachute & landing system developed by LA/ Babakin Space Center for Mars 96 mission Adaptable for reentry and landing on Earth 1st IRDT test flight in Feb confirmed basic technology feasibility 2nd test flight with enhanced system design under orbital entry conditions launched July 2002: no activation IRDT-2 reflight performed on ; non-nominal landing site, reception of TM data for trajectory reconstruction

4 Lavochkin/EADS Astrium
Application Opportunities based on IRDT Roskosmos Lavochkin ESA European Development Mars Cooperation Lavochkin/EADS Astrium IRT-System Study (1)ESA IRT-Technology Study (2) ESA ESA Mars Mission Preparation Studies IRDT-1: ESA, ISTC 2000 IRDT-2: ESA, ISTC 2002 IRDT-2R: ESA, ISTC 2005

5 IRDT-2R - A Reflight Reflight of IRDT-2 with the goal to validate the performance and functionality of the Russian Inflatable Technology: IRDT-2R total Mass at landing 140 kg Reduced Sensor Package, data on-board storage for data retrieval Design Re-entry conditions at 100 km altitude for the Demonstrator (7000 m/sec; -6° entry angle) Design Reentry Environment: Dynamic Pressure >5000 Pa; Peak Heatflux at the surface of the inflatable envelope > 400 kW/m2; total heat input > 13 MJ/m2 Transfer of data to ground before landing, that are necessary for reconstruction of trajectory Stored measurement data shall be recoverable after landing Operational lifetime of Recovery Equipment of the Demonstrator shall include recovery activities up to 48 hours

6 IRDT-2R Major Changes to Precursor Flights
Responsibility of Launcher Payload Compartment (PC) design and D-2R Launcher Interface moved to Makeev Complete new design of the D-2R to Volna launcher mounting I/F Launcher Separation Mechanism Redesign Protective Cover Compartment redesign New design of Avionics compartment Implementation of Telemetry (TM) Function to receive data on ground before landing for the reconstruction of the trajectory TM: new antenna design inside a rigid TPS nose cone Autonomous Radio Telemetry System (ARTS): Data Memory and dump required Avionic SW: Updates for the System SW required GS additional equipment for quicklook flight data processing to support search activities New beacon antenna designs to support the search operations Implementation of Glonass / GPS System

7 IRDT-2R Programmatics Major Project Milestones RR/PDR 1.-4. April 2003
CDR / Expert Working Groups QFAR Final Inspection and FRR (Murmansk) Initial LRR (Murmansk / Kluchi, Kamtchatka) Launch date Industrial Consortium: EADS-Astrium ST prime Lavochkin Sub Makeev Sub/sub

8 IRDT Configuration (stowed)
Equipment Container IBU Envelope (stowed) Science Package IBU Filling System Equipment Container Shock-absorber (non-cocked) Housekeeping Equipment Aerodynamic Shield

9 IRDT-2R Configuration (deployed)
IBU Additional Part IBU Main Part Thermal Protection Blanket Aerodynamic Shield Equipment Container Shock-absorber (cocked)

10 IRDT-2R Mission Profile
1 – Take off of «Volna» LV, Barentz Sea 9 – Spin-up of D-2R 2 – Separation of 1-st stage 10 – Arming of the EC, platform separation 3 – Ignition of PS of 2-nd stage 11 – Beginning of inflation of D-2R MIBD 4 – Separation of 2-nd stage 12 – Re-entry, (100 km) 5 – Ignition of PS of 3-rd stage 13 – Aerobraking 6 – Venting of pressure from the PC 14 – Deployment of D-2R AIBD (13 km) 7 – Separation of PC cover 15 – Landing of the D-2R, Kamtchatka 8 – Separation of D-2R

11 IRDT-2R - Conclusion Major achievements: Successful launch with Volna
Due to the major design modifications and related extensive additional qualification work and a launcher failure of the Volna launcher the launch date had to be shifted to end of 2005 Major achievements: Successful launch with Volna Correct separation from Volna -> newly designed launcher I/F worked properly Reception of TM data before and after black out phase From TM data a proper inflation of the MIBD can be expected From the trajectory reconstruction it can be expected that the maximum heat flux was reached, but on the way to the point of maximum deceleration a non-nominal behavior of the inflatable occured

12 Project: Gossamer Structures IN-ORBIT DEMONSTRATION EXPERIMENT WITH INFLATABLE AND RIGIDIZABLE STRUCTURES Cooperation between EADS Astrium ST and Lavochkin Association Project #2835 => technology development; funded by Astrium-ST Project #2836 => flight test ; funded by ISTC Timeframe:

13 Tests of panel in the VC-48 Technical Requirements
Project #2835 => technology development Funded by Astrium-ST => completed in July 2006 Deployment & rigidization tests performed in Lavockin vacuum chamber ( Deployment control system to be improved ) Tests of panel in the VC-48 Name of Parameters Technical Requirements Actual argument Eigenfrequency of the structure The first mode of the IRIS shall be at a frequency higher than 0.5 Hz 0,625 Hz Maximal deviation from the theoretical panel plane The sag of any point of the deployed IRIS shall be lower than 150mm relatively to the theoretical plane 27mm Presence of folds No slack area in the membrane No folds

14 Project #2836 => flight test
LAVOCHKIN ASSOCIATION Flight test mission profile

15 Flight testing of generic demonstrator
Project #2836 => flight test LAVOCHKIN ASSOCIATION Flight testing of generic demonstrator (deployment & rigidization in space) Flight funded by ISTC 2 generic demonstrators (compatible with ULS “IOE” specifications – ESA funded TRP project ) funded by ISTC using the solvant evaporation rigidization technique => designed & manufactured by Lavochkin

16 flight test preparation final selection of flight test configuration
Project #2836 flight test preparation final selection of flight test configuration passenger on Soyuz Fregat launch in 2008 TASK 5 In-orbit experiments (measurements, ground control & support) CDR2 TASK 4 In launcher accommodation & insertion into the orbit CDR TASK 3 Manufacturing & testing of flight models TASK 2 PDR Demonstrator models ground tests TASK 1 Designing of the flight Demonstrator 2004 2005 2006 2007 2008

17 Project: Reusable Multi-layer Thermal Protection Systems
Cooperation between EADS Astrium ST/NGL, ESA and Yuzhnoye Project #3567 (STCU) Objective:Yuzhnoye SDO develops a metal multi-layer thermal protection system (TPS) for reusable spacecraft to protect the spacecraft surfaces when heated to not more than 1100ºC Timeframe: Resumee: Good results by analysis and investigations by Yuzhnoye; further activities should become part of the joint activities towards future reusable launcher systems

18 Project: Robotics for Security
ISTC Project # 3711 Russian State Scientific Center for Robotics and Technical Cybernetics, St.Petersburg Collaborators: EADS Astrium ST LAAS, France Joint Research Centre; Italy Sapienza. S.L.,Spain Objective: There is a significant demand to improve the available security equipment by high levels of autonomy, robustness and dependability, adaptability, modularity, application of microsystems, and user friendliness Proceeding: The environment and security range of concerns will be discussed with the relevant institutions and in close contact/cooperation with the user the selection of needed equipment with the respectively requirements have to be defined commonly to agree on the specifications for the developments Schedule: Status: First progress meeting took place in Germany in Nov 2007 Promising activities

19 Lessons learnt & recommendation (1 / Gossamer)
Lessons learnt /experience : Interesting technical achievements concerning materials & technologies developments Test means available at Lavochkin Association allow to perform the whole range of tests in view of a flight test preparation Positive support from Roscosmos in view of the flight test preparation Recommendations Need for regular progress meetings ( quarterly ) to check work progress and update the work plan when needed, depending on results achieved The experience achieved for the ISTC funded flight test preparation is a good background in view of the flight testing of technologies developed by Astrium-ST (both under internal fundings and on ESA fundings – TRP Program ) A common meeting ESA / Roscosmos / Astrium-ST / Lavochkin after ISTC flight completion would be a good opportunity to prepare further cooperation

20 Lessons learnt & recommendations (2 /IRDT)
Close monitoring of activities necessary, involves also higher resources for this purpose Direct access to sub-cos important, key players should be directly contracted (e.g. Makeev as launcher provider and operations responsible in case of IRDT-2R) Reviews/Meetings take longer, expectations have to be clearly communicated in advance and the common understanding has to be ensured It has to be acknowledged that the Russian standard approach for projects differs from the ESA environment (reviews not necessarily known to Russian industry as usually hold within ESA projects) The will to learn from each other and the standard practices has to be there on both sides, adaptation towards compromises to fit within both environments ESA/ Russian industry have to be taken. This can also be a very fruitful experience. Emphasis has to be put on testing, as analysis documentation is not that easy achievable and in Russian industry not necessarily the standard way forward as used to in an ESA environment

21 Lessons learnt & recommendations (3 / IRDT / general)
A lot of know how in research and development in technologies like materials and processes is available in Russia from the past The development approach differs from western approach drastically; Russia prefers more test activities than analyses It has to be clearly agreed on contractually which information, data and results will be accessible for the western European partners Uncertainties in handling of IPR Intellectual Property Rights on both sides with the tendency of more restricted Some Russian space industries were and are not interested in ISTC projects

22 What has changed in the meantime?
Political and economical self-confidence strongly increasing in Russia Political situation/trend not predictable Russian GDP Gross Domestic Product is growing at 6-7 % per year The Federal Space Budget has been increased and has been doubled in the last three years (FSA budget in 2007 is about 800 mEUR / ESA 3 bnEUR / NASA 14 bn$) Half of the money to the Russian space industry by space commercial activities Russia actively explores new markets in China, India, South Korea and Brazil Restructuring of the Russian industry in various clusters of companies is at various stages; privatization is envisaged to be finished in 2010 Ground infrastructure / facilities has to be improved significantly Demand for young engineers in the Russian space industry Harmonization of international management style and project performance

23 Expectations on future ISTC/STCU projects
Adaptation of the ISTC/STCU rules to current environment/trends Implementation of single ISTC/STCU projects into long term programs and perspectives in the relevant agencies planning From European financing/investment into industrial/institutional partnership; ROI; to establish “win-win situations” Future joint projects by clear commitments of all parties/partners

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