Complex Space Simulation Equipment DEVELOPMENT & BUSINESS APPLICATION STCU/NATO Workshop October 11-12, 2006 Kiev Yuriy Pokhyl Tel.: Special Research & Development Bureau for Cryogenic Technologies Institute for Low Temperature Physics & Engineering National Academy of Sciences of Ukraine (SRDB ILTPE) KHARKOV

Proprietary information statement The technology material presented in this talk is available for licensing or joint product development. None of the slides contain any confidential or proprietary information which would prevent patenting the technology.

AEROSPACE ENGINEERING DEMANDS: The creation of perspective space technique has required the long-term and very expensive on- ground investigations and tests. The materials, constructions, devices and vehicles as whole needs routine on-ground tests under simulated condition of outer space environmental factors. As a rule, expenditure for this tests exceed a half of space project cost. For solution of this problems it is necessary to have the array of simulation testing and research equipment, as well as a set of research and measurement methodologies.

OUR POSSIBILITIES: Thermo-vacuum testing of space vehicles and its parts (up to 2 m cross section) Investigations of properties of space usage materials under conditions that simulate an action of space environment factors Design and manufacture of simulation testing and research equipment Development and verification of methods for accelerated testing of space technique and materials

CHAMBER FOR THERMO-VACUUM TESTING OF SPACE VEHICLES

SCHEME OF CHAMBER FOR THERMO-VACUUM TESTING

EGYPTSAT TESTING

TECHNICAL CHARACTERISTICS OF CHAMBER FOR THERMO-VACUUM TESTING Working volume of the chamber 45 m3 Vacuum p< Pa Mass of test spacecraft m 200 kg Solar simulator: - beam diameter 2.2 m - intensity 1300 – 1500 W/m2 - radiation sources 19 Xe-lamps of 5 kW Handling equipment spin motion for test spacecraft Earth radiation simulators infrared sources

ONERA – Centre National dEtudes et de Recherches Aerospatiales, France SEMIRAMIS – Space radiation Simulation Facility for Studies of External Spacecraft Surfaces Long-term space environment simulations with in-situ measurements of optical spectral reflectance (250 to 2500 nm) and solar reflectance. Simultaneous irradiations with protons, electrons and ultraviolet beams: electrons energy range: 400 keV to 2 MeV, protons energy range: 40 keV to 350 keV (2,2 MeV option). Ultraviolet radiation ranging from 0,5 to 7 sun obtained from Xenon filtered sources (with infrared and visible rejection). Contamination of sample surfaces with V.C.M. products in controled conditions (in-situ measurements with Quarz Crystal Microbalances). Pressure below Pa 10-6 torr (Cryogenic pumping units). Temperature range: 50 to 80 C (option: liquid nitrogen temperature). Irradiation zone: 120 mm square surface (25 samples 20 by 20 mm). EQUIPMENT FOR INVESTIGATIONS OF SPACE USAGE MATERIALS

GENERAL DIAGRAM OF THE TEST EQUIPMENT MSH – multi-position samples holder; OMC –optical measurements chamber; TCF – thermal cycling facility; CVC RSM – cryogenic vacuum chamber investigations of radiation stability of materials; GDS – gas-discharge source of VUV radiation; GJS – gas-jet source of VUV and USX radiation; VCMP – vacuum chamber for investigation of mechanical properties of materials; PEI – proton and electron injector based on combined beams; MS – mass-spectrometer; SS –solar simulator; RP- radiation protection.

The test equipment enables: to expose investigated objects for joint or separate influence of vacuum, ultraviolet (UV), vacuum ultraviolet (VUV) and ultrasoft X- ray (USX) radiation, action of proton and electron flux to study optical and electrical characteristics of materials inside cryogenic vacuum chamber for investigations of radiation stability of materials (CVC RSM) to study mechanical characteristics of materials, wherein samples are exposed to action of VUV and USX radiations to expose materials to influence of radiation factors and to thermal cycling for further study of their properties outside the CE RSM

MAJOR TECHNICAL CHARACTERISTICS OF TEST EQUIPMENT: Cryogenic vacuum chamber volume, l450 Pressure in working volume, Pa Accelerated protons and electrons energy range, keV Proton and electron flux currents, A Irradiated area dimensions, mm110x110 Gas- jet source of VUV and USX radiation spectral wavelength range, nm Gas- discharge source of VUV radiation spectral wavelength range, nm Solar simulator spectral wavelength range, nm Mechanical test regimes: active, creep; stress relaxation

OUR TECHNICAL PROPOSALS FOR PARTNERS AND CUSTOMERS Thermo-vacuum testing of space vehicles and its parts (up to 2 m cross section) Investigations of properties and certification of space usage materials under conditions that simulate an action of space environment factors Design and manufacture of simulation testing and research equipment Development and verification of methods for accelerated testing of space technique and materials

OUR BUSINESS PROPOSALS FOR PARTNERS AND CUSTOMERS We are ready to mutual profitable cooperation in the field of space materials and spacecraft equipment testing We need a high-level management for expansion of our design and testing service to the worldwide aerospace market We propose to create International research and certification center on the base of Ukrainian experience and equipment

OUR ADVANTAGES Existence of high-technological space simulation testing equipment with wide spectrum of characteristics Large experience of spacecraft devices and materials testing High qualification scientific and engineering personal Low prices of our research and testing service

CONTACT INFORMATION Yuriy Pokhyl Tel.: Special Research & Development Bureau for Cryogenic Technologies Institute for Low Temperature Physics & Engineering National Academy of Sciences of Ukraine Kharkov

STVT

Competition equipment WSA/TVA Dimensions of vacuum chamber dia 6.8 m, length 13 m Vacuum p< Pa Thermal shroud temperature range 100 K <Tw < 400 K, 19 circuits material stainless steel, inner surfaces black painted >0.9, s >0.95 (cylindrical shroud) Solar simulator: diameter of reference plane 3.6 m intensity 1900 W/m2 maximum (1.4 SC) uniformity 4 % in test plane 5% in test volume 1.5 m collimation angle 2 radiation sources 7 Xe-lamps of 25 kW each total efficiency >9% Earth radiation simulator No Handling equipment attitude and spin motion for test articles Weight of test article 2000 daN ( 2000 kg)

COMPETITION EQUIPMENT SEMIRAMIS ONERA – Centre National dEtudes et de Recherches Aerospatiales, France SEMIRAMIS – Space radiation Simulation Facility for Studies of External Spacecraft Surfaces Long-term space environment simulations with in-situ measurements of optical spectral reflectance (250 to 2500 nm) and solar reflectance. Simultaneous irradiations with protons, electrons and ultraviolet beams: electrons energy range: 400 keV to 2 MeV, protons energy range: 40 keV to 350 keV (2,2 MeV option). Ultraviolet radiation ranging from 0,5 to 7 sun obtained from Xenon filtered sources (with infrared and visible rejection). Contamination of sample surfaces with V.C.M. products in controled conditions (in-situ measurements with Quarz Crystal Microbalances). Pressure below Pa 10-6 torr (Cryogenic pumping units). Temperature range: 50 to 80 C (option: liquid nitrogen temperature). Irradiation zone: 120 mm square surface (25 samples 20 by 20 mm).