Complex Space Simulation Equipment DEVELOPMENT & BUSINESS APPLICATION STCU/NATO Workshop October 11-12, 2006 Kiev

1. Complex Space Simulation EquipmentDEVELOPMENT & BUSINESS APPLICATIONSTCU/NATO WorkshopOctober 11-12, 2006Kiev Yuriy Pokhyl Tel.: 38-057-340-30-19 Pokhyl@cryocosmos.com Special Research & Development Bureau for Cryogenic Technologies Institute for Low Temperature Physics & Engineering National Academy of Sciences of Ukraine (SRDB ILTPE) KHARKOV

2. 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.

3. 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.

4. 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

5. CHAMBER FOR THERMO-VACUUM TESTING OF SPACE VEHICLES

6. SCHEME OF CHAMBER FOR THERMO-VACUUM TESTING

7. EGYPTSAT TESTING

8. TECHNICAL CHARACTERISTICS OF CHAMBER FOR THERMO-VACUUM TESTING • Working volume of the chamber 45 m3 • Vacuum p<210-3 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

9. EQUIPMENT FORINVESTIGATIONS OF SPACE USAGE MATERIALS • ONERA – Centre National d’Etudes 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 110-4 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).

10. 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.

11. 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

12. MAJOR TECHNICAL CHARACTERISTICS OF TEST EQUIPMENT: • Cryogenic vacuum chamber volume, l 450 • Pressure in working volume, Pa 310-4 • Accelerated protons and electrons energy range, keV 50...200 • Proton and electron flux currents, A 0.01...20 • Irradiated area dimensions, mm 110x110 • Gas- jet source of VUV and USX radiation spectral wavelength range, nm 1.24...150 • Gas- discharge source of VUV radiation spectral wavelength range, nm 115...200 • Solar simulator spectral wavelength range, nm 200...2500 • Mechanical test regimes: active, creep; stress relaxation

13. OUR TECHNICAL PROPOSALSFOR 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

14. OUR BUSINESS PROPOSALSFOR 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

15. 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

16. CONTACT INFORMATION Yuriy Pokhyl Tel.: 38-057-340-30-19 Pokhyl@cryocosmos.com Special Research & Development Bureau for Cryogenic Technologies Institute for Low Temperature Physics & Engineering National Academy of Sciences of Ukraine Kharkov

17. STVT

18. Competition equipment WSA/TVA Dimensions of vacuum chamber dia 6.8 m, length 13 m • Vacuum p<210-4 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)

19. COMPETITION EQUIPMENT SEMIRAMIS • ONERA – Centre National d’Etudes 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 110-4 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).