Transcript ST Roadshow 2007

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
Astrium Space Transportation
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
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3800
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. 2000
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 07.10.2005;
non-nominal landing site, reception of TM
data for trajectory reconstruction
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Height : 2037
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Application Opportunities based on IRDT
Roskosmos
Lavochkin
ESA
European
Development
Mars
Cooperation
Lavochkin/EADS Astrium
IRT-System Study
(1)ESA 2002-2004
IRT-Technology Study (2)
ESA 2003-2004
IRDT-1: ESA, ISTC 2000
IRDT-2: ESA, ISTC 2002
IRDT-2R: ESA, ISTC 2005
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ESA Mars Mission
Preparation Studies
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IRDT-2R - A Reflight
Reflight of IRDT-2 with the goal to validate the performance and functionality
of the Russian Inflatable Technology:
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IRDT-2R total Mass at landing 140 kg
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Reduced Sensor Package, data on-board storage for data retrieval
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Design Re-entry conditions at 100 km altitude for the Demonstrator (7000
m/sec; -6° entry angle)
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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
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Transfer of data to ground before landing, that are necessary for
reconstruction of trajectory
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Stored measurement data shall be recoverable after landing
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Operational lifetime of Recovery Equipment of the Demonstrator shall
include recovery activities up to 48 hours
Astrium Space Transportation
IRDT-2R Major Changes to Precursor Flights
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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
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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
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IRDT-2R Programmatics
Major Project Milestones
• RR/PDR 1.-4. April 2003
• CDR / Expert Working Groups 24.-31.03.2004
• QFAR 10.-13.05.2005
• Final Inspection and FRR 08.-12.09.2005 (Murmansk)
• Initial LRR 24.09.2005 (Murmansk / Kluchi, Kamtchatka)
• Launch date 07.10.2005
Industrial Consortium:
• EADS-Astrium ST prime
• Lavochkin Sub
• Makeev Sub/sub
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IRDT Configuration (stowed)
Equipment Container
IBU
Envelope
(stowed)
Science
Package
IBU Filling
System
Equipment Container
Shock-absorber
Housekeeping Equipment
(non-cocked)
Aerodynamic Shield
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+Z
+X
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IRDT-2R Configuration (deployed)
IBU Additional Part
IBU Main Part
Equipment Container
Shock-absorber (cocked)
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Thermal Protection Blanket
Aerodynamic Shield
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IRDT-2R Mission Profile
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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 D2R AIBD (13 km)
7 – Separation of PC
cover
15 – Landing of the D2R, Kamtchatka
8 – Separation of D-2R
Astrium Space Transportation
IRDT-2R - Conclusion
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:
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Successful launch with Volna
•
Correct separation from Volna -> newly designed launcher I/F worked
properly
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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 nonnominal behavior of the inflatable occured
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Project: Gossamer Structures
IN-ORBIT DEMONSTRATION EXPERIMENT
WITH INFLATABLE AND RIGIDIZABLE STRUCTURES
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Cooperation between EADS Astrium ST and Lavochkin Association
Project #2835 => technology development; funded by Astrium-ST
Project #2836 => flight test ; funded by ISTC
Timeframe: 2004-2008
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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
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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
Presence of folds
No slack area in the membrane
27mm
No folds
Astrium Space Transportation
Project #2836 => flight test
LAVOCHKIN
ASSOCIATION
Flight test
mission profile
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Project #2836 => flight test
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
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LAVOCHKIN
ASSOCIATION
Astrium Space Transportation
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)
TASK 4
In launcher accommodation &
insertion into the orbit
CDR2
CDR
TASK 3
Manufacturing &
testing of flight
models
TASK 2
Demonstrator models ground tests
PDR
TASK 1
Designing of the flight
Demonstrator
2004
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2005
2006
2007
2008
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Project: Reusable Multi-layer Thermal Protection Systems
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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: 2005-2006
Resumee:
• Good results by analysis and investigations by Yuzhnoye;
• further activities should become part of the joint activities towards
future reusable launcher systems
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Project: Robotics for Security
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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: 2008-2011
Status:
• First progress meeting took place in Germany in Nov 2007
• Promising activities
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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
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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
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Lessons learnt & recommendations (3 / IRDT / general)
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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
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What has changed in the meantime?
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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
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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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