Facility Description Large Space Simulator LSS

Document reference: ETS/THER/LSS/315, Issue Draft last updated: September 5, 2005

Table of Contents

1 Foreword 2 Acronyms 3 Introduction 4 Estec Test Centre 5 Purpose 6 General description 7 Detailed information7.1 LSS chamber7.2 Vacuum pumping system7.3 Shroud and Nitrogen Supply Equipment7.4 Sun Simulator7.5 Motion System7.6 Levelling System7.7 LSS mass spectrometer 7.8 Scaffolding7.9 Specimen Access Device7.10 Extra cooling subsystems7.11 Interfaces with test object7.12 Test data output7.13 Infrastructure7.14 Safety 8 AnnexesAnnex 1: Large Space SimulatorAnnex 2: Section through building Fg & LSS/EastAnnex 3: Section through building Fg & LSS/NorthAnnex 4: Top lid floor building FgAnnex 5: Plan view of the chamber & the test hallAnnex 6: LSS principal dimensionsAnnex 7: LSS Pump-down curveAnnex 8: LSS repressurisation curveAnnex 9: LSS shrouds cool-down & warming-up curvesAnnex 10: LSS shroud sectionsAnnex 11: LSS SUSI ray-trace schematicAnnex 12: Light intensity distribution in centre plane at 1378 W/m² Annex 13: SUSI spectrumAnnex 14: Motion System in Yoke configurationAnnex 15: Motion System in Gimbal stand configurationAnnex 16: Motion System - Spin Box I/FAnnex 17: Seismic tableAnnex 18: Main Chamber port locationsAnnex 19: Scaffolding configurationsAnnex 20: Scaffolding in bridge configurationAnnex 21: Specimen Access DeviceAnnex 22: ESTEC Test Centre location

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1 Foreword All intellectual property rights related to information provided in this document including but not limited to copyrights, are exclusively belonging to the European Space Agency. The Information is intended for use by a test customer exclusively and may not be multiplied, disclosed or otherwise brought to the notice of third parties without prior written consent of the European Space Agency. Inquiries concerning clarification or interpretation of this manual should be directed to: European Space Agency ESTEC TEC-TCP Mr. A. Popovitch Keplerlaan 1 – P.O. Box 299 2200 AG Noordwijk – The Netherlands Tel: (31) 71 565 3321 – Fax: (31) 71 565 6541 E-mail: alexandre.popovitch@esa.int On behalf of ESA, the ESTEC Test Centre is operated by European Test Services (ETS) B.V. Information on the facilities and on the utilization of the Test Centre can be obtained from: European Test Services (ETS) B.V. Mr. R. Effenberger Keplerlaan 1 2201 AZ Noordwijk – The Netherlands Tel: (31) 71 565 42 90 – Fax: (31) 71 565 5659 E-mail: ralf.effenberger@esa.int

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2 Acronyms AcronymsDescription AMU Atomic Mass Unit C1 Main LSS chamber C2 Auxiliary LSS chamber CPS Central Pumping Station ECSS European Cooperation for Space Standardization ESA European Space Agency ESD Emergency Shut Down ESTEC European Space Technology and Research Centre ETS European Test Centre B.V. GN2 Gaseous Nitrogen GS Gimbal Stand HVP High Vacuum Pumping System LHe Liquid Helium LN2 Liquid Nitrogen PFO Particle Fall Out LSS Large Space Simulator MS Motion Simulator PLC Programmable Logic Controller QCM Quartz Crystal Microbalance SAD System Access Device SB Spin Box SNSE Shroud & Nitrogen Supply Equipment SUSI Sun Simulator TDH Thermal Data-Handling TM Turbo Molecular UPS Uninterruptable Power Supply

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3 Introduction The ESTEC Test Centre of ESA includes the largest European test facilities such as the Large Space Simulator (LSS), the Large European Acoustic Facility (LEAF), the multi-axis hydraulic vibration facility (HYDRA) and the large electromagnetic compatibility facility (MAXWELL). This makes it a centre unique in Europe. This test centre is focused but not limited to perform environmental tests of satellites at system level. The management and operation of this test centre is entrusted to European Test Services (ETS) B.V. This is implemented according to customer quality demands and to space test standards like ECSS. European Test Services (ETS) B.V. is also certified according to EN ISO 9001: 2000. European Test Services (ETS) B.V. is working in close co-operation with ESA to ensure the optimal realisation of the customers test requirements. This document describes the test facility mentioned in the title, including auxiliary support equipment, relevant building infrastructures and interfaces to the test object (specimen) in the standard configuration. On request of ESA or the test customer configuration changes can be implemented through modifications and/or adaptations of the facility. This document is one out of a series of documents presenting the following test facilities of the ESTEC Test Centre:

Test FacilitiesDescription Thermal facilities LSS Large Space Simulator HBF 3 Heat Balance & Temperature Cycling Facility VTC 1.5 Vacuum Temperature Cycling Facility ATC 2 Accelerated Temperature Cycling Facility Mechanical facilities VIB 80 80 kN Shaker Vibration System VIB 160 – VIB 320 Multi Shaker Vibration System HYDRA Hydraulic Vibration System LEAF Large European Acoustic Facility WM 50/6 Combined Centre of Gravity & Moment of Inertia Machine E5 Dynamic Balancing Machine E6 Dynamic Balancing Machine M1 Moment of Inertia, Oscillating Table M2 Moment of Inertia, Oscillating Table WR 12 Centre of Gravity Machine EMC facilities MAXWELL Electromagnetic Compatibility & Electrostatic Discharge Chamber CPTR Compact Payload Test Range Data handling MDH Mechanical Data Handling TDH Thermal Data Handling Infrastructure Infrastructure ESTEC Test Centre infrastructure

This document is for information only and is subjected to periodical revision. Comments and suggestions on all aspects of this document are encouraged and will be appreciated.

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4 Estec Test Centre ESTEC Test Centre

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5 Purpose During the in-orbit life time, satellites are exposed to severe and extreme environmental space conditions like high vacuum and high/low temperatures. The temperatures of the surfaces of the satellite facing the sun can rise to nearly +100 ºC, while for other surfaces facing deep space it can drop below -100 ºC. The solar radiation, the thermal cycling and the vacuum conditions may have a severe impact on the lifetime of the spacecraft. The main objective of a thermal vacuum test facility is to simulate the extreme in-orbit environmental conditions in order to: • verify the thermal control of the satellite • verify the correct operation of all units of the satellite (hardware and software) • validate the thermal model of the satellite Although the facility is mostly used for testing of space hardware, it can also be made available to accommodate other equipment (e.g. from the aerospace and automotive industry).

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6 General description The Large Space Simulator is well suited to conduct thermal balance and/or thermal vacuum tests on large test objects, because of its exceptional large test volume, solar beam (6 m diameter), infrared radiation sources and temperature controlled shrouds. The facility simulates a space environment for deployment of large structures and deformation measurements using videogrammetry. LSS comprises the following 5 major subsystems: • Vacuum vessel including the main vertical cylindrical chamber • Vacuum pumping systems (CPS & HVP) with 4 turbomolecular pumps, two 20K cryopumps and one 4 K liquid helium cryopump • Shrouds and Nitrogen Supply Equipment (SNSE) including 615 m² of black painted shrouds, temperature controlled by gaseous or liquid nitrogen • SUn SImulator (SUSI) providing a horizontal homogeneous and parallel light beam • Motion Simulator (MS) to simulate the motion of the satellite in space along two-axis (spin and attitude) w.r.t. the solar beam The specific design features and excellent performance characteristics of the facility allows the execution of a large number of different thermal tests under high vacuum conditions, using: • Solar simulator • Infrared sources • Temperature controlled shrouds Mechanical operational tests can also be performed under various thermal conditions and high vacuum such as: • Dynamic testing (e.g. balancing, spin, etc.) • Deployment of large structures in static or dynamic mode (antennae, solar arrays, etc.)

Table 1: LSS main parametersDescription Main chamber dimensions 10 m x 15 m (diameter x overall height) Typical achievable pressure (HVP) 5.10-6 mbar Solar beam diameter 6 m Intensity level with 19 lamps at 20 kW 2000 W/m2 Temperatures (SNSE): • In LN2 mode 100 K • In GN2 mode 150 K to 350 K Motion System (MS) • Maximum mass test object 5000 kg • Configurations test object Vertical or horizontal Situated in class 100 000 clean room area (FED-STD-209)

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7 Detailed information

7.1 LSS chamber The LSS chamber, with an overall volume of 2150 m3 consists of the following three major parts:• Main Vacuum Chamber • Auxiliary Chamber • Seismic Block The Main Vacuum Chamber is a vertical cylinder which is closed off by a removable top lid. For facility and test object preparation purposes, an access door of 5 m diameter is situated at the level of the customer test floor (Fg102). A man-door of 1.8 m diameter is located in the 5 m diameter access door. The test object will be loaded into the main chamber via the top. The Auxiliary Chamber is a horizontal cylinder housing the collimation mirror and the cryopumps. The Seismic Block (90 000 kg) supports the seismic structure to which the test object, accommodated inside the main chamber, is mounted via an interface structure. The seismic table is decoupled from the main chamber with flexible seals. Different views of the LSS chamber are presented in annexes 1 to 6.

Table 2: LSS chamber characteristicsDescription Main chamber (C1) Usable volume, diameter x height 9.5 m x 10 m Access to main chamber • Diameter removable top lid 10 m • Diameter sliding side door 5 m • Diameter man door 1.8 m Auxiliary chamber (C2) Dimensions, diameter x height [8 ; 11.5] m x 14.5 m Access to mirror • Diameter man door 1.8 m Material C1 & C2 AISI 304 SS Seismic block Dimension of the support platform 3.2 m x 3.2 m Load capability 60 000 kg Mechanical noise transmitted to test object Less than 10-3 mg2/Hz, from 0 to 20 Hz Situated in class 100 000 clean room area (FED-STD-209)

7.2 Vacuum pumping system Depressurisation The LSS chamber is depressurized using: • Central Pumping System (CPS) to obtain a primary vacuum level of 7.10-3 mbar • High Vacuum Pumping system (HVP), to obtain a high vacuum level of 5.10-6 mbar The CPS consist of 2 rotary pumps (compressor type) and 3 Roots/Rotary pumps in parallel. The HVP system consists of: • 2x LN2 cooled cryopanels • 4x Turbo Molecular (TM) pumps and associated rotary pumps • 2x 20K-cryopumps • 1x helium cryopump (4K), designed and manufactured by ESTEC Testing Division. Note: The 4K-cryopump is used only in case of special test requirements. This pump is situated in the Auxiliary Chamber C2. Typical LSS pump down/chamber depressurisation curves are presented in annex 7.

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Repressurisation The chamber is re-pressurised with clean and dry GN2 up to 100 mbar and subsequently clean air (class 100 000) is used to reach atmospheric pressure. The re-pressurisation rate is adjustable from 100 to 250 mbar/hour.

Table 3: Vacuum pumping system characteristicsDescription Vacuum: Typical achievable pressure 5.10-6 mbar Lowest achievable pressure 3 x 10-7 mbar (4x TM pumps & LHe cryopump) Pumping speed: Central Pump Station 14 000 m3/hr for air Roots pump 20 000 m3/hr for air Turbo molecular pump 2 000 l/s for air (for each pump) 20 K-cryopump 48 000 l/s for N2

Helium Cryo-pump (4 K) 400 m3/s for N2

7.3 Shroud and Nitrogen Supply Equipment The temperature control of the LSS chamber is performed by the SNSE subsystem as follows: • Main Chamber shrouds (C1) is temperature controlled in either LN2 or in GN2 mode • Auxilary Chamber shrouds (C2) are kept at LN2 temperature (77 K) The shroud temperature is controlled automatically by PLC to the required temperature settings. Details of the SNSE are summarized in the table below. The shrouds sections of the main and auxiliary chamber are shown in annex 10.

Table 4: SNSE characteristicsDescription Thermal balance test (LN2 mode) Surface temperature 100 K Maximum heat load 170 kW Maximum gradient 10 K Thermal vacuum test (GN2 mode) Surface temperature (Min) 150 K Surface temperature (Max) 350 K Maximum heat load 10 kW Maximum gradient 30 K (in stabilized condition) Surface facing test volume (black painting) Type Chemglaze Z306 Emissivity 0.90 Absorptivity 0.95 Emissivity of remaining surface (polished stainless steel) 0.2

7.4 Sun Simulator The sun simulator provides a horizontal solar beam with ± 1% uniformity and a very high stability. An intensity level of 1 solar constant (approximately 1378 Watts per square meter, see annex 12) can be achieved by operating 12 of the available 19 xenon lamps at a nominal power of 20 kW per lamp. This sun simulator has a high degree of redundancy, which means that tests can be carried out over long durations or at elevated intensities. On request, the sun simulator can be equipped with 32 kW lamps. The solar spectrum, emitted by the lamps, is presented in annex 13. The non-filtered xenon spectral radiation coming from the lamp array is projected through an optical integrator via the chamber window on to the collimation mirror in the Auxiliary Chamber.

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The purpose of the mirror is to provide a homogeneous parallel light beam in the test volume. (See schematic in annex 11). The collimation mirror is made of 109 full and 12 half segments. The mirror structure and the 121 segments are controlled in temperature by circulation of GN2 between 26 ºC and 120 ºC to prevent contamination of the reflective surface of the mirror. The sun intensity level can be controlled in automatic or manual mode. To simulate eclipses, a shutter is placed in the solar beam between the lamps and the chamber window. Synchronisation of the shutter closure and the test object motion is possible.

Table 5: SUSI characteristicsDescription Solar beam: – Configuration Horizontal – Specified test volume, diameter x depth: 6 m x 5 m – Intensity level: • 12 Xenon lamps at 20 kW 1378 W/m² (1 Solar Constants) • 19 Xenon lamps at 20 kW 2000 W/m² (1.45 Solar Constants) • Maximum achieved 18 Lamps at 25 kW 2600 W/m² • Reproducibility ± 0.5% – Intensity distribution: Based on a sensor size of 2 cm x 2 cm • In reference plane ± 4% on a grid of 2x2cm grid • In reference volume ± 6% – Collimation angle ± 1,9° – Stability ± 0.5 % of the adjusted level Lamps: – Number total 19 – Type High pressure xenon – Power 20 kW and 25 kW types are available Collimation mirror: – Composed by hexagonal segments 121 – Thermo-Optical surface properties: • ε 0.015 • α 0.130 Transfer optics: Integrator with 55 field and projection lenses Chamber window: – Material HERASIL – Diameter 1088 mm – Thickness 84 mm

7.5 Motion System The Motion Simulation makes it possible to simulate satellite motions in orbit within a large speed range and with high angular position accuracy. The two-axis motion system allows the simulation of spin rotation and attitude positions of a satellite with relation to the solar beam. The motion simulator is equipped with thermally controlled shrouds. Two configurations are available: • Gimbal stand configuration for a vertical position of the test item (See annex 14) • Yoke configuration for a horizontal position of the test item (See annex 15)

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Table 6: Motion System characteristicsDescription General • Test volume sphere diameter [mm] 6000 • Max mass test object including adaptor [kg] 5000 • Max moment of Inertia: Ix, Iy, Iz [ kg m²] 8000 Spin Box mechanical characteristics • Max motor torque [Nm] 2000 • Max permanent breaking torque [Nm] 630 • Max 5-hour breaking torque [Nm] 1260 Spin motion characteristics Normal rotation mode with continuous rotation in either direction • Velocity range [rpm] 1 - 6 • Velocity accuracy 3 % of nominal speed • Acceleration & deceleration (maximum) [rad/s²] 1 Position mode with continuous rotation in either direction: • Velocity range [degree/min] 30 - 60 • Position accuracy [degree] ± 0.4 • Resolution [degree] ± 0.1 Slow motion mode with continuous rotation in either direction: • Velocity range [rev/day] 1 - 24 • Position accuracy [degree] ± 0.4 • Resolution [degree] ± 0.1

Yoke configuration (with Spin Box)Description • Max overturning moment wrt Turn Table I/F plane [Nm] 490 000 • Max overturning moment wrt Spin Box I/F plane [Nm] 209 000 • Max test object static imbalance Refer to SB mechanical characteristics Attitude motion characteristics • Rotation angle [degree] ± 90 • Position accuracy [degree] ± 0.4 • Resolution [degree] ± 0.1 • Positioning velocity [degree/min] 10 - 60 • Max angular acceleration & deceleration [rad/s2] 1 • Positioning hunting mode only [degree/min] 0.25 - 6

Gimbal stand configuration (with Spin Box)Description • Max overturning moment wrt tilt axis [Nm] 75 000 • Max test object static imbalance at 0° tilt angle and no spin [Nm] 118 000 • Max test object static imbalance at 0° tilt angle with spin [Nm] 2000 • Max test object static imbalance at tilt angle > 0 Refer to SB mechanical characteristics Attitude motion characteristics • Inclination angle [degree] -30 - 29 • Position accuracy [degree] ± 0.01 • Positioning velocity [degree/min] 1 - 3 • Resolution [degree] ± 0.01

7.6 Levelling System The levelling system is used only in the GS configuration. It is installed between the seismic block and the GS structure. The purpose of the levelling system is to compensate the horizontal misalignment of the test object.

Table 7: Levelling system characteristicsDescription Load capacity 17 650 kg (5 000 kg with Gimbal Stand) Level control accuracy 1 mm over 1 meter

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7.7 LSS mass spectrometer An MKS VAC-CHECK mass spectrometer is running during tests to provide real time overview of residual gases in the chamber. It has a mass range from 1 to 200 AMU and uses a desktop computer as a system controller. Ten mass units can be checked simultaneously with an adjustable time range. The mass spectrometer is normally configured for the most common gases AMU 2, 4, 14, 16, 17, 18, 28. 32. 40 and 44. Other type of gases can be analysed on request.

7.8 Scaffolding For the installation of a test object onto the Motion System or the Seismic Structure and for all pre or post-test activities, a number of dedicated places around the test object have to be accessible. Standard scaffolding with a basic structure and towers/platforms is available. This standard scaffolding can be modified to fulfil special requirements. The scaffolding can be mounted for different configurations: • Gimbal stand. • Yoke. • Without Motion Simulator A less sophisticated scaffolding, the “bridge”, can be installed in the GS configuration. This scaffolding is mainly used for small test objects. Different LSS scaffolding configurations are presented in annex 19.

Table 8: Scaffolding characteristicsDescription Scaffolding load: • 2 persons per platform 300 kg (including equipment) • 4 persons per level• Total of 6 persons maximum 1000 kg (including equipment) Dimensions and access On request

7.9 Specimen Access Device The SPAD is a customised crane, carrying a basket to move an operator inside LSS. SPAD consists of the folowing three main parts: • Main bridge running on parallel rails on the top floor of the LSS building • Trolley moving along the main bridge • Telescopic mast with the operator’s basket at the end. The aim of the SPAD is to provide immediate and easy access to the test object (specimen) in LSS chamber. This is very useful for specific situations. For example, just before the start of a test it can be necessary to change the position of some sensors or, at the end of a test, to have quick access to specific instruments on the test object. See Annex 20.

Table 9: SPAD characteristicsDescription Total mass 200 kg (operator and tools) Reachable coordinates (X ; Y ; Z) ±5 ; ±5 ; [2.5 ; 12.5] m Horizontal movements 11.5 - 200 mm/s Vertical movements 10 - 140 mm/s

7.10 Extra cooling subsystems Two subsystems are available for the cooling of extra shrouds or special targets and are controlled independently from the main and auxilary chamber shrouds. These subsystems have been developed in the frame of Metop and IASI (Infrared Atmospheric Sounding Interferometer) projects. Subsystem 1 Subsystem 1 is equipped with two LN2 lines and one He line. The LN2 from the storage tank is

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going through a phase separator (to provide a stable liquid flow) and a sub-cooler (LN2/LN2 exchanger). This system is fully automatic (control of the LN2 flow and pressure). Helium is supplied by a 500 litres dewar placed on a weight scale. A second He dewar is used to refill this dewar when necessary. A PLC controls the pressure inside the two He dewars and monitors pressure and temperature alarms. The He loop provides a 2 kg/hour GHe flow at approximately 30 K. Subsystem 2 Subsystem 2 consists of a GHe closed loop circuit with one LN2line. This system enables a close loop GHe circulation with a maximum GHe temperature below 31 K for a heat load of 20 watt.

Table 10: Extra cooling subsystems characteristicsDescription Subsystem 1 LN2 lines:

• Reachable temperature 85 K • Pressure 3 bar • Flow range 30 - 300 litre/hr (typically 200 litre/hr) LHe line: • Reachable temperature 40 K • Typical working pressure 200 mbar • Consumption 3 kg/hr Subsystem 2 He loop: • Lowest temperature 30 K at 20 W heat load • GHe flow 6 g/min

7.11 Interfaces with test object Mechanical interface The test object can be mounted either: • On the MS spin box (see drawing in annex 16) • Via an appropriate adaptor directly onto the Seismic Structure at the bottom of the Main Chamber (see drawing in annex 17) • From 3 suspension points at 9.8 m above seismic structure, loading capacity 3000 kg each (see drawing in annex 18) • On a dynamic balancing measurement machine (see document on dynamic balancing machine)

Electrical interface Flanges and ports are available for customer. Various ports of 250 mm diameter are situated around the perimeter of the chamber. For more details concerning the positions of the ports, please refer to the annex 18.

Table 11: FlangesDescription Port Type Remark Fg102/B-level B1 Facility LHe lines Fg102/B-level B2 Electrical Fixed Fg102/B-level B3 Electrical Fixed Fg102/B-level B4 Electrical Fixed Fg102/B-level B5 General Reconfigurable Fg102/B-level B6 General Reconfigurable Fg102/B-level B7 General Reconfigurable Fg102/B-level C1 Facility (General) DCU/He loop Fg102/B-level C2 General Reconfigurable Fg102/D-level D2 General Reconfigurable E-level E1 Optical window View port E-level E9 General Reconfigurable E-level E11 General Reconfigurable

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E-level E12 General Reconfigurable Fg001 A9 General (3x) Reconfigurable

7.12 Test data output Data is monitored during the test in real time using the STAMP data handling system and DynaWorks on request. Data can be provided after completion of the test in ASCII, CSV format and/or DynaWorks compatible format in standard CD-R’s. For more details concerning Thermal Data Handling, please refer to the TDH document.

Test object Different parameters are controlled and recorded on the test object: • Temperature of different location (thermocouples, Pt 100) • Voltage, current, line power, heater power and resistance measurement of heaters • Additional parameters (on request): internal pressure inside the test object, tilt sensors, etc.

Test facility Different parameters are controlled and recorded on the test facility: HVP • Chamber pressure, cryopanel temperatures, mass spectrometer data, pump parameters (speed, temperature, pressure, etc) • LN2 tanks status • Alarms SNSE • Shrouds temperature • Status of valves • Status of modes • LN2 pressure, flow • Alarms SUSI • Sun level • Temperature of the sun sensor level control • Mirror temperature • Lamps power • Lamps voltage and current • Optics temperature • Alarms MS • Spin Box speed and angular position • Yoke speed and angular position. • Turn Table speed and angular position • GS speed and angular position • Temperature (shrouds, structure, motors) • Alarms

7.13 Infrastructure LSS is located in building Fg of the ESTEC Test Centre. Please refer to the document 'ESTEC Test Centre Infrastructure' for information on the following topics: • Test and preparation areas, customer offices and check-out rooms • Access and maximum floor loading • Crane & lifting equipment • Connection to electrical public power outlets, UPS outlets and clean earth • Liquid and gas supply (air, water, N2, He) • Communication devices

7.14 Safety In case of an emergency, the ESD system allows the safe flushing of LN2 from the SNSE sub-system and the re-pressurisation of the chamber to 500 mbar with GN2. • 30 minutes for the shroud draining. • 30 minutes for the re-pressurisation with GN2 to 500 mbar.

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For safety reason, this system is fully automatic and pneumatic (no electrical power needed). For more details concerning the general safety requirements applicable to the ESTEC Test Centre, please refer to the dedicated chapter of the infrastructure document.

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8 Annexes

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Annex 1: Large Space Simulator Large Space Simulator (artist's impression)

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Annex 2: Section through building Fg & LSS/East Section through building Fg

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Annex 3: Section through building Fg & LSS/North Section through building Fg

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Annex 4: Top lid floor building Fg Plan view of the Toplid floor building Fg

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Annex 5: Plan view of the chamber & the test hall Plan view of the chamber

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Annex 6: LSS principal dimensions LSS principal dimensions

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Annex 7: LSS Pump-down curve Typical pump-down curve for LSS loaded with medium size satellite

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Annex 8: LSS repressurisation curve LSS repressurisation curve

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Annex 9: LSS shrouds cool-down & warming-up curves LSS shrouds cool-down curves

LSS shrouds warming-up curves

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Annex 10: LSS shroud sections LSS shroud sections

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Annex 11: LSS SUSI ray-trace schematic LSS SUSI ray-trace schematic

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Annex 12: Light intensity distribution in centre plane at 1378 W/m² Light intensity distribution in centre plane at 1378 W/m2

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Annex 13: SUSI spectrum SUSI irradiance at 1378 W/m2

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Annex 14: Motion System in Yoke configuration Motion System in Yoke configuration

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Annex 15: Motion System in Gimbal stand configuration Motion System in Gimbal Stand configuration

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Annex 16: Motion System - Spin Box I/F LSS Motion System - Spinbox I/F

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Annex 17: Seismic table D4-T020-FG109

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Annex 18: Main Chamber port locations Location of ports of the LSS Main Chamber

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Annex 19: Scaffolding configurations LSS Scaffolding around test object

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Annex 20: Scaffolding in bridge configuration D4-T020-FG121

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Annex 21: Specimen Access Device SPAD

SPAD deployed with an operator (left figure); Artist's impression of the SPAD in the LSS chamber (right figure)

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Annex 22: ESTEC Test Centre location Route

Route by Air From the airport Schiphol, either take a taxi to ESTEC (30 min), or a train to Leiden (15 min) and then the above bus (30 min). With a rental car, follow the instructions above from Amsterdam.

Route by Car ESTEC is located at the southern tip of Noordwijk. Coming from Den Haag (The Hague), take the A4 to Amsterdam and exit at Leiden. Follow the N206 in the direction Katwijk and Haarlem. Take the exit Katwijk Noord. From there follow the signs "ESTEC" (small white squares). From Amsterdam, take the A4 in the direction Den Haag-Rotterdam, then at the junction follow the A44. Take the exit Noordwijk-Voorhout, continue to Noordwijk and from there, follow the signs ESTEC.

Route by Train From the station of Leiden, take bus nr 32 to Katwijk. It stops in front of the entrance gate of ESTEC (it takes approximately. 30 min). Please note that this bus leaves twice an hour during rush periods and only once during normal hours.

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