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Yuriy Pokhyl Tel.: 38-057-340-30-19 [email protected] Special Research & Development Bureau PowerPoint PPT Presentation


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Complex Space Simulation Equipment DEVELOPMENT & BUSINESS APPLICATION STCU/NATO Workshop October 11-12, 2006 Kiev. Yuriy Pokhyl Tel.: 38-057-340-30-19 [email protected] Special Research & Development Bureau for Cryogenic Technologies

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Yuriy Pokhyl Tel.: 38-057-340-30-19 [email protected] Special Research & Development Bureau

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Complex Space Simulation EquipmentDEVELOPMENT & BUSINESS APPLICATIONSTCU/NATO WorkshopOctober 11-12, 2006Kiev

Yuriy Pokhyl

Tel.: 38-057-340-30-19

[email protected]

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<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


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).


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, Pa310-4

  • Accelerated protons and electrons energy range, keV50...200

  • Proton and electron flux currents, A0.01...20

  • Irradiated area dimensions, mm110x110

  • Gas- jet source of VUV and USX radiation spectral

    wavelength range, nm1.24...150

  • Gas- discharge source of VUV radiation spectral

    wavelength range, nm115...200

  • Solar simulator spectral wavelength range, nm200...2500

  • Mechanical test regimes: active, creep; stress relaxation


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


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


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.: 38-057-340-30-19

[email protected]

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<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)


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).


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