Спутник технологический. STP-R1. [Редактировать]

Экспериментальный демонстратор технологий для DARPA с целью продемонстрировать «быструю реакцию» на приказ о запуске.

Дополнительные наименования

#НаименованияПоиск в новостяхПоиск в документах
1StreakНайтиНайти
2USA 185НайтиНайти
328871НайтиНайти

Дополнительная классификация

#Наименования
1Тип оператора(владельца) - военные
2Страна оператор(владелец) - США
3Страна производитель - США

Технические характеристики

#ХарактеристикаЗначение
1Масса, кг417

Характеристики орбиты

#ХарактеристикаЗначение
1Дата (сведения с орбиты)2006-06-28

Пусковые характеристики

#ХарактеристикаЗначение
1Код NSSDC2005-037A

Информация об удачном запуске

#ХарактеристикаЗначение
1Дата пуска2005-09-23 at 02:24:00 UTC
2Полезная нагрузка 1xSTP-R1
3Ракета-носитель 1xМинотавр 1

Найдено 464 документов по запросу «STP-R1». [Перейти к поиску]


Дата загрузки: 2017-03-10
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... 2005, while a second Minotaur I launched STP-R1 in support of the Defense... Flight mission (July–August 2005), STP managed crew training, the on... F i s c a l The DOD Space Test Program (STP), Rocket Systems Launch Program 23... Air Force, US Navy, and STP, provided the remaining 20 percent...) Interplanetary probe Sept. 23, 2005 STP-R1 2005-037A OSC Minotaur Technology... Authorization Space Telescope Imaging Spectrograph STP SURF SVS Space Test Program...



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... Un dt 2 d 2 U1 dt 2 + Fтр1 + r1 + Fтрi + ri dUi + k i (2Ui − Ui... q TP τ q β θ τ p O1 l1 n q n p Rp lp r1 r2 ϕ2 ,Φ2 O2 T1 Рис. 1 Уравнения... механизм станка СТБ. На рис. 1: r1 – радиус скала; r2 – длина коромысла... механизма описывается следующими дифференциальными уравнениями: && 2 = STP r1 + r2 ( N − N J2ϕ τ q τ p ) − m gr cos ϕ 1 2 2 Умножим... 1 + J1 M, J 2 − J1 (5) & = M, (J 2 − J1 )Φ 2 &&1 , + R p l p sin θ − J1ϕ &&1 = STP − J1ϕ && 2 . J1ϕ (4) Здесь Sтр – суммарная... следующие конструктивные размеры станка СТБ: r1=0,075 м; r2=0,152 м; fтр=0,3; ρ=800... α от α 0 на величину ϕ . Так как R1 и R 2 соответствуют участкам тросов: Ri ≈ R i0... Δ i ≤ 0 или R i0 ≤ 0, R i0 ≈ ci Δ i + bi Δ& i , εi , i = 1, 2 , Δ1 = − r1β − rкϕ , Δ 2 = r2β − yг , 140 t =0 , где... и коэффициент демпфирования элементов 6 и 7 (см. рис. 1); h R1 = rк ; h P = l cos ( α 0 + ϕ + λ ) ; l – расстояние OC (см...



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FACT SHEET Minotaur I Innovation You Can Count OnTM Space Launch Vehicle JAWSAT – Jan 2000 MightySAT II.1 – Jul XSS-11 – Apr 2005 STP-R1 – Sep 2005 COSMIC – Apr 2006 Success on First Five Missions The Minotaur I Space Launch Vehicle The Minotaur I Space Launch Vehicle (SLV) provides a responsive, reliable, and cost-effective launch solution for U.S. Government sponsored spacecraft. In addition to a demonstrated successful history over its initial and subsequent launches, it builds on a long background of dependable launch systems. The Minotaur I uses residual Minuteman II first and second stages in combination with the upper two stages shared with Orbital’s Pegasus XL and Taurus XL commercial SLVs. The Minotaur family of launch vehicles is provided via the Orbital/ Suborbital Program 2 (OSP-2) of the U.S. Air Force Space and Missile 754.7 PAYLOAD FAIRING AVIONICS ASSEMBLY ORION 38 3/4 INTERSTAGE ORION 50XL 2/3 INTERSTAGE Systems Center (SMC) Rocket System Launch Program (RSLP). SR19 Features: • Inertially guided four stage solid rocket propulsion • Flight-proven systems with demonstrated success record • Multiple spaceport launch capability (California, Florida, Alaska, Virginia) using portable ground support equipment FAIRING SEP 580.85 50.0 IN. DIA S2/S3 SEP 340.52 S1/S2 SEP M55 494.75 441.05 52.0 IN. DIA MM 1/2 INTERSTAGE • Full payload integration support including mission management, spacecraft interface support (power, telemetry, sequencing, attitude control, and deployment), and launch operations • Standard 18 month mission response including payload integration and launch by Orbital’s experienced launch crews PAYLOAD I/F 650.15 289.50 274.43 65.76 IN. DIA (Dimensions in Inches) • Responsive launch solutions from 6 months to 48 hours available Minotaur I Space Launch Vehicle 51.79 0.0 Minotaur I Specifications Performance: • Flight-verified system performance • Proven secondary payload capability • Adaptable to a variety of payloads and orbital requirements with typical accuracy of 33.4 nm (3s), 0±0.1 deg inclination (3s) 87.8 22.7 AVAILABLE ENVELOPE (DYNAMIC) • Optional Soft Ride for Small Satellites (SRSS) to mitigate flight dynamics environments • Available optional enhancements include: 151.5 31.0 131.3 47.3 35.4 - Insertion accuracy of <10 nm (3s) inclinations <0.05 deg (3s) AVAILABLE - Conditioned air (Class 10K), temperature and humidity control and nitrogen purge ENVELOPE 0 NOTE: 1. Payload Mass includes Adapter Cone, Separation System and Other Mission-Specific Hardware. 1800 1600 1400 Apogee (km) INTERFACE PLANE 54.7 50.0 2000 INTERFACE PLANE Standard 50” Fairing 0.0 Optional 61” Fairing Payload Accommodations: • Standard 50 in. Pegasus-design payload fairing 1200 • Optional 61 in. fairing for larger or multiple payload missions 1000 • Thermally controlled fairing volume with Class 100K standard cleanliness CCAS 28.5° 800 • Well defined launch environments • Variety of proven payload separation systems available WFF 38° 600 VAFB 72° 400 200 0 (DYNAMIC) 47.0 - Additional payload access panels 80.1 VAFB Sun-Synch 0 100 200 300 400 Kodiak 64° 500 600 Payload (kg) Minotaur I Payload Capability Simplified Horizontal Payload Integration Point of Contact: For Technical Details, Please Contact Us At: Phone: 480.814.6566 E-mail: minotaur@orbital.com Website: www.orbital.com Program Office: Additional information should be obtained from the USAF OSP Office USAF SMC Space Development & Test Wing Rocket System Launch Program (RSLP) 3548 Aberdeen Avenue S.E. Kirtland AFB, NM 87117-5778 (505) 846-8957 FAX: (505) 846-1349 Orbital Sciences Corporation Launch Systems Group 3380 South Price Road Chandler, Arizona 85248 www.orbital.com Innovation You Can Count OnTM © 2006 Orbital Sciences Corporation BR06003



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FACT SHEET Minotaur I Innovation You Can Count OnTM Space Launch Vehicle JAWSAT – Jan 2000 MightySAT II.1 – Jul 2000 XSS-11 – Apr 2005 STP-R1 – Sep 2005 COSMIC – Apr 2006 TacSat-2 – Dec 2006 Minotaur I Has a Demonstrated Success Record and Flight-Proven Systems The Minotaur I Space Launch Vehicle The Minotaur I Space Launch Vehicle (SLV) provides a responsive, reliable, and cost-effective launch solution for U.S. Government-sponsored spacecraft. It builds on a long background of dependable launch systems and has a demonstrated successful history over its initial and subsequent launches. The Minotaur I SLV uses residual Minuteman II first and second stage rocket motors along with the upper two stages shared with Orbital’s Pegasus XL and Taurus XL commercial SLVs. The combination of decommissioned ICBM motors with commercial boosters and state-of-theart hardware is one of Orbital’s unique strengths from experience spanning several decades. The Minotaur family of launch vehicles are provided via the Orbital/ Suborbital Program 2 (OSP-2) and managed by the U.S. Air Force Space and Missile Systems Center (SMC), Space Development and Test Wing’s (SDTW) 3rd Space Test Squadron (3 STS) located at Kirtland AFB, NM. Features: • Full spacecraft integration support, including mission management, spacecraft interface support (power, telemetry, sequencing, attitude control, and deployment), through launch operations and post-launch performance evaluation. • Standard 18 month mission response including mission integration and launch by Orbital’s uniquely experienced team • Responsive launch solutions from 6 months to a few hours available • Mission success is ensured by mature systems and processes - Orbital’s rigorous mission assurance program - Full Government insight and independent assessment • Multiple spaceport launch capability (California, Florida, Alaska, MidAtlantic) using portable ground support equipment 754.7 SPACECRAFT FAIRING AVIONICS ASSEMBLY ORION 38 3/4 INTERSTAGE ORION 50XL 2/3 INTERSTAGE SR19 PAYLOAD I/F 650.15 FAIRING SEP 580.85 50.0 IN. DIA S2/S3 SEP 441.05 52.0 IN. DIA MM 1/2 INTERSTAGE 340.52 S1/S2 SEP M55 494.75 289.50 274.43 65.76 IN. DIA (Dimensions in Inches) Minotaur I Space Launch Vehicle – Ready to Launch 51.79 0.0 Minotaur I Specifications Performance: • Spacecraft mass-to-orbit of up to 580 kg to LEO (28.5 deg, 185 km) 2.23 m (87.8 in.) • Typical orbit accuracy of better than ±5 km insertion apse, ±35 km non-insertion apse, and ±0.1 deg inclination (3sigma values) • Optional enhanced insertion accuracy better than 5 km in altitude and ±0.05 deg inclination (3-sigma values) 0.787 m (31.0 in.) AVAILABLE ENVELOPE (DYNAMIC) AVAILABLE ENVELOPE (DYNAMIC) 3.335 m (131.3 in.) 2.035 m (80.1 in.) 1.19 m (47.0 in.) 0 INTERFACE PLANE 1.27 m (50.0 in.) 1.39 m (54.7 in.) INTERFACE PLANE 0.0 1.55 m (61.0 in.) 2000 NOTE: 1. Payload Mass includes Adapter Cone, Separation System and Other Mission-Specific Hardware. 1800 1600 1400 Apogee (km) 3.843 m (151.5 in.) 0.899 m (35.4 in.) 1.20 m (47.3 in.) • Cold gas attitude control system readily accomodates a variety of spacecraft mission requirements, including precise separation pointing and post-boost maneuvers 1200 1000 CCAS 28.5° 800 WFF 38° 600 VAFB 72° 400 200 0 0.576 m (22.7 in.) VAFB Sun-Synch 0 100 200 300 400 Standard 1.27 m (50 in.) Fairing Envelope Optional 1.55 m (61 in.) Fairing Envelope Payload Accommodations: • Standard 1.27 m (50 in.) dia. spacecraft fairing (Pegasus heritage design) • Optional 1.55 m (61 in.) dia. spacecraft fairing for larger and/or multiple spacecraft missions • Mission-specific fairing access doors for spacecraft support • Well-defined launch environments validated with flight data • Various flight-proven spacecraft separation systems available, including low-shock designs • Thermally controlled fairing volume with standard Class M6.5 (100k) cleanliness - Optional Class M5.5 (10k) cleanliness - Optional spacecraft nitrogen purge Kodiak 64° 500 600 Payload (kg) Performance to Orbit Is Flight-Verified and Best in Class Simplified Horizontal Payload Integration for Single and Multiple Spacecraft Program Office: S. A IR F O RC E • U. RSL P MINOTAUR n Orbital Suborbital Program bit al Sc tio Or Additional information should be obtained from the USAF OSP Office USAF SMC Space Development and Test Wing (SDTW) 3rd Space Test Squadron (3 STS) 3548 Aberdeen Avenue S.E. Kirtland AFB, NM 87117-5778 505.846.5911 505.846.6489 • For Technical Details, Please Contact Us At: Phone: 480.814.6566 E-mail: minotaur@orbital.com Website: www.orbital.com NGC Point of Contact: ie n ce s C or p o ra Orbital Sciences Corporation Launch Systems Group 3380 South Price Road Chandler, Arizona 85248 www.orbital.com Innovation You Can Count OnTM © 2006 Orbital Sciences Corporation BR06003b



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... 2415 PROGRESS M-54 ANIK F1R STP-R1 GPS 2RM-1 CRYOSAT SYRACUSE-3A...-8 BEIDUOU 1D THEMIS IGS 3B STP-1 STPSAT-1 CFESAT FALCONSAT 3 MIDSTAR-1 SKYNET...



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...: English‬‬ ‫ﳉﻨﺔ ﺍﺳﺘﺨﺪﺍﻡ ﺍﻟﻔﻀﺎﺀ ﺍﳋﺎﺭﺟﻲ‬ ‫ﰲ ﺍﻷﻏﺮﺍﺽ ﺍﻟﺴﻠﻤﻴﺔ‬ ‫ﻣﻌﻠﻮﻣﺎﺕ ﻣﻘ ‪‬ﺪﻣﺔ ﻭﻓﻘﺎ ﻻﺗﻔﺎﻗﻴﺔ ﺗﺴﺠﻴﻞ ﺍﻷﺟﺴﺎﻡ ﺍﳌﻄﻠﻘﺔ‬ ‫ﰲ ﺍﻟﻔﻀﺎﺀ ﺍﳋﺎﺭﺟﻲ‬ ‫ﻣﺬ ﹼﻛﺮﺓ ﺷﻔﻮﻳﺔ ﻣﺆﺭ‪‬ﺧﺔ ‪ ١٧‬ﻛﺎﻧﻮﻥ ﺍﻟﺜﺎﱐ‪/‬ﻳﻨﺎﻳﺮ ‪ ٢٠٠٦‬ﻣﻮ ‪‬ﺟﻬﺔ‬ ‫ﺇﱃ ﺍﻷﻣﲔ ﺍﻟﻌﺎﻡ ﻣﻦ ﺍﻟﺒﻌﺜﺔ ﺍﻟﺪﺍﺋﻤﺔ ﻟﻠﻮﻻﻳﺎﺕ ﺍﳌﺘﺤﺪﺓ ﺍﻷﻣﺮﻳﻜﻴﺔ‬ ‫ﻟﺪﻯ ﺍﻷﻣﻢ ﺍﳌﺘﺤﺪﺓ )ﻓﻴﻴﻨﺎ(‬ ‫‪‬ﺪﻱ ﺍﻟﺒﻌﺜﺔ ﺍﻟﺪﺍﺋﻤﺔ ﻟﻠﻮﻻﻳﺎﺕ ﺍﳌﺘﺤﺪﺓ ﺍﻷﻣﺮﻳﻜﻴﺔ ﻟﺪﻯ ﺍﻷﻣﻢ ﺍﳌﺘﺤﺪﺓ )ﻓﻴﻴﻨﺎ( ﲢﻴ‪‬ﺎ‪‬ﺎ ﺇﱃ‬ ‫ﺍﻷﻣﲔ ﺍﻟﻌﺎﻡ ﻟﻸﻣﻢ ﺍﳌﺘﺤﺪﺓ‪ ،‬ﻭﻳﺸﺮ‪‬ﻓﻬﺎ ﺃﻥ ﲢﻴﻞ ﺇﻟﻴﻪ‪ ،‬ﻭﻓﻘﺎ ﻟﻠﻤﺎﺩﺓ ﺍﻟﺮﺍﺑﻌﺔ ﻣﻦ ﺍﺗﻔﺎﻗﻴﺔ ﺗﺴﺠﻴﻞ‬ ‫ﺍﻷﺟﺴﺎﻡ ﺍﳌﻄﻠﻘﺔ ﰲ ﺍﻟﻔﻀﺎﺀ ﺍﳋﺎﺭﺟﻲ )ﻣﺮﻓﻖ ﻗﺮﺍﺭ ﺍﳉﻤﻌﻴﺔ ﺍﻟﻌﺎﻣﺔ ‪) ٣٢٣٥‬ﺩ‪ ،((٢٩-‬ﺑﻴﺎﻧﺎﺕ‬ ‫ﺗﺴﺠﻴﻞ ﺍﻷﺟﺴﺎﻡ ﺍﻟﻔﻀﺎﺋﻴﺔ ﺍﻟﱵ ﺃﻃﻠﻘﺘﻬﺎ ﺍﻟﻮﻻﻳﺎﺕ ﺍﳌﺘﺤﺪﺓ ﺧﻼﻝ ﺍﻟﻔﺘﺮﺓ ﻣﻦ ﺃﻳﻠﻮﻝ‪/‬ﺳﺒﺘﻤﱪ ﺇﱃ‬ ‫ﺗﺸﺮﻳﻦ ﺍﻟﺜﺎﱐ‪/‬ﻧﻮﻓﻤﱪ ‪) ٢٠٠٥‬ﺍﻧﻈﺮ ﺍﳌﺮﻓﻖ(‪.‬‬ ‫)‪60206 V.06-50444 (A‬‬ ‫*‪*0650444‬‬ ‫‪2‬‬ ‫ﺑﻴﺎﻧﺎﺕ ﺗﺴﺠﻴﻞ ﺍﻷﺟﺴﺎﻡ ﺍﻟﻔﻀﺎﺋﻴﺔ ﺍﻟﱵ ﺃﻃﻠﻘﺘﻬﺎ ﺍﻟﻮﻻﻳﺎﺕ ﺍﳌﺘﺤﺪﺓ ﺍﻷﻣﺮﻳﻜﻴﺔ ﺧﻼﻝ ﺍﻟﻔﺘﺮﺓ ﻣﻦ ﺃﻳﻠﻮﻝ‪/‬ﺳﺒﺘﻤﱪ‬ ‫ﺇﱃ ﺗﺸﺮﻳﻦ ﺍﻟﺜﺎﱐ‪/‬ﻧﻮﻓﻤﱪ ‪*٢٠٠٥‬‬ ‫ﺃﻳﻠﻮﻝ‪/‬ﺳﺒﺘﻤﱪ ‪٢٠٠٥‬‬ ‫ﻳﺴﺘﻜﻤﻞ ﺍﻟﺘﻘﺮﻳﺮ ﺍﻟﺘﺎﱄ ﺑﻴﺎﻧﺎﺕ ﺍﻟﺘﺴﺠﻴﻞ ﺍﳋﺎﺻﺔ ﺑﺎﻷﺟﺴﺎﻡ ﺍﻟﱵ ﺃﻃﻠﻘﺘﻬﺎ ﺍﻟﻮﻻﻳﺎﺕ ﺍﳌﺘﺤﺪﺓ ﺣﱴ ‪ ٣٠‬ﺃﻳﻠﻮﻝ‪/‬ﺳﺒﺘﻤﱪ ‪ .٢٠٠٥‬ﻭﻗﺪ ﹸﺃﺟﺮﻳﺖ ﲨﻴﻊ ﻋﻤﻠﻴﺎﺕ ﺍﻹﻃﻼﻕ‬ ‫ﻣﻦ ﺃﺭﺍﺿﻲ ﺍﻟﻮﻻﻳﺎﺕ ﺍﳌﺘﺤﺪﺓ‪ ،‬ﻣﺎ ﱂ ﻳﺬﻛﺮ ﺧﻼﻑ ﺫﻟﻚ‪.‬‬ ‫ﺍﻟﺘﺴﻤﻴﺔ ﺍﻟﺪﻭﻟﻴﺔ‬ ‫ﺍﺳﻢ ﺍﳉﺴﻢ ﺍﻟﻔﻀﺎﺋﻲ‬ ‫ﺗﺎﺭﻳﺦ ﺍﻹﻃﻼﻕ‬ ‫ﺍﳋﺼﺎﺋﺺ ﺍﻷﺳﺎﺳﻴﺔ ﻟﻠﻤﺪﺍﺭ‬ ‫ﻧﻘﻄﺔ‬ ‫ﺍﻟﻔﺘﺮﺓ ﺍﻟﻌﻘﺪﻳﺔ ﺯﺍﻭﻳﺔ ﺍﳌﻴﻞ‬ ‫ﺍﻷﻭﺝ‬ ‫)ﻛﻢ(‬ ‫)ﺩﺭﺟﺔ(‬ ‫)ﺩﻗﻴﻘﺔ(‬ ‫ﻧﻘﻄﺔ‬ ‫ﺍﳊﻀﻴﺾ‬ ‫)ﻛﻢ(‬ ‫ﺍﻷﺟﺴﺎﻡ ﺍﻟﺘﺎﻟﻴﺔ ﺃﻃﻠﻘﺖ ﺑﻌﺪ ﺻﺪﻭﺭ ﺍﻟﺘﻘﺮﻳﺮ ﺍﻷﺧﲑ ﻭﻻ ﺗﺰﺍﻝ ﻣﻮﺟﻮﺩﺓ ﰲ ﺍﳌﺪﺍﺭ‪:‬‬ ‫‪٩٠,٦‬‬ ‫‪ ٢٣ STP-R1 (USA 185) 2005-037A‬ﺃﻳﻠﻮﻝ‪/‬ﺳﺒﺘﻤﱪ ‪٢٠٠٥‬‬ ‫‪٩٦,٤‬‬ ‫‪٣١٧‬‬ ‫‪٣٠١‬‬ ‫‪2005...



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... и находящиеся на орбите: 2005-037A STP-R1 (USA 185) 23 сентября 2005...



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..." ITU Publication No ITU/RAF/R1.05, Geneva, 1979 - 54 PP... Final Acts of RARC MM-R1 in 1985, one administration stated... Regional Administrative Radio Conferences MM-R1 and EMA Geneva (February - March... c co ro p . o H - pi fl jc i-t) 3 c r1 (5 M rt(W I0 ^ 3 1 - 1 v; o o (D r t Oq 3 Pl rt... 0 fl K r t 3 0 x i p. rt • < 3 ' a> H- ^ r t cn 0 ^ C O i-h H- P) B H cn ^ O 1 rti i-t 3 r1 r r HID P. H ro 0 O P. O r t rtP. VO 3 ht... equipment (Equipment) SAO TOME & PRINCIPE - (3-STP-85-02) 11,400 Inter... o T3 O ro B ps HCTs< Cu r1 t- cn X X) ro O ro 5 3 s< ri o ro...



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... НАКОНЕЧНИКИ • для шланга SAE 100 R1 ПРЯМЫЕ, С ВНУТРЕННЕЙ ТРУБНОЙ РЕЗЬБОЙ R (BSP...-BL-22R08 R 1/2 24-BL-22R16 R1 24-BL-28R12 R 3/4 24-BL...-BS-16R12 R 3/4 24-BS-20R08 R 1/2 R1 24-BS-25R12 R 3/4 24-BS...-20R16 TR A O R EU R1 R 1 1/2 24-BS-30R16 R1 24-BS-38R20 R 1 1/4 24... R 1/2 50 24-HF-12 R 1/4 25 R1 24-HF-20 R 1 1/4 R 1 1/2 24-HFM...-RAL-22R R 3/4 U 24-RAL-12R R1 24-RAL-35R R 1 1/4 .R 24-RAL...-RAS-10R 24-RAS-12R R 1/2 R 1/2 R 3/4 R1 R 1 1/4 R 1 1/2 24-RAL-22R08 R 1/2 24-RAS...-RAS-12R04 24-RAS-16R06 R1 24-RAS-20R08 R 1/2 24-RAS-25R12 R 3/4 24-RAS-30R16 R1 TR A 24-RAS-20R16 ПЕРЕХОДНЫЕ... 28-STP-08X1.5 8x1,5 ZN 28-STP-10X1 10x1 ZN 28-STP-10X1.5 10x1,5 ZN 28-STP-12X1.5 12x1,5 ZN 28-STP-12X2 12x2 ZN 28-STP-15X2 28-STP-16X1.5 28-STP-16X2 28-STP-18X1.5 28-STP-20X2 28-STP-20X2.5 15x2 ZN 583 16x1,5 ZN 28-STP-25X2...-STP-22X2 15x1,5 ZN 365 ET 28-STP-15X1.5 509 U 28-STP-06X1 28-STP-08X1 Наибольшее рабочее давление, бар .R Номер изделия 28-STP-25X3 25x3 ZN 351 28-STP-28X2 28x2 ZN... 35x3 ZN 243 D 28-STP-30X3 28-STP-35X3 38x4 ZN 303 42x3 ZN 200 TR A 28-STP-38X4 28-STP-42X3 БЕСШОВНЫЕ КИСЛОТОСТОЙКИЕ СТАЛЬНЫЕ... 24 13,5 M 12x45 08-AFS106GM100 R1 25 69,85 93 35...: - M1- шпиндель фиксируется в центральном положении - R1- шпиндель фиксируется в положении «на себя...: - M1- шпиндель фиксируется в центральном положении - R1- шпиндель фиксируется в положении «на себя... 700 R 3/4 Плавная регулировкa 240 700 R1 13-11060001 13-11080001 E- НЕВОЗВРАТНЫЕ...-12080001 150 700 R1 0,5 13-12080002 150 700 R1 2 13-12080003 150 700 R1 5 EU R КОЛЛЕКТОРЫ РАЗВОДЯЩИЕ..., л / мин E- Номер изделия O R 3/8 R 1/2 500 R 3/4 500 R1 Максимальное давление, бар Внутренняя резьба....BS EU R O Соединения с внутренней резьбой: R1", R1 1/4", R1 1/2" и R2". 20-1181202073 160 OOO... FD1090-B EU R O Соединения с внутренней резьбой: R1", R1 1/4", R1 1/2" и R2". 20-1181200093 161 OOO... (FF147:EEN): Соединения с внутренней резьбой: R1", R1 1/4" и R1 1/2". 20-1111200053 FC7007.F025.BK...-V EU R O Соединения с внутренней резьбой: R3/4" и R1". 20-911045046 168 OOO "ЕвроТрейд... VITON Соединения с внутренней резьбой: R3/4" и R1". СЕРИЯ 5000 20-911045030 Комплект... EU R O TR A D Соединения с внутренней резьбой: R1", R1 1/4" и R1 1/2" 20-1111207023 FC7001.F025.BK... УПЛОТНЕНИЯ VITON Соединения с внутренней резьбой: R1", R1 1/4" и R1 1/2" 20-91145021 20-91145051 171... адаптер 908064002 Удлинительная трубка 908064003; R1 1/4" 2013/2019 Номер изделия 20..., 6 винтов, стальной оцинкованный фланец (резьба R1 1/4"), стандартные размеры крепления фланца. МАСЛЯНЫЕ...-6215 x 24-6215T x 24-6520 R1 24-6216 24-6216T 24... дюймы Корпусная часть 55-2510 R1/4 55-3810 R3/8 55-5010 R1/2 55-7510 R3/4 55-10010 R1 Ниппельная часть 55-2520 R1/4 55-3820 R3/8 55-5020 R1/2 55-7520... удар 600 бар. 55-10020S R1 R1 206 OOO "ЕвроТрейд" т.+7 (812) 9405190...ÖL-08 12-PYÖL-12 G2 A B C D E R1/2 R1/2 98 68 35 32 122... 16 36 12-PYÖR-16 R1 117 50 20 46 12... R 1/4 R 3/8 12-500 R 1/2 R 3/4 12-750 R 3/4 R1 12-1000 R1 R 1 1/4 O 12-250RF Наибольшая скорость... R Внутренняя резьба неподвижной части, дюймы R 1/4 R 3/8 R 1/2 R 3/4 R 3/4 R1 R1 R 1 1/4 EU ПРЯМЫЕ ВРАЩАЮЩИЕСЯ СОЕДИНЕНИЯ Вращающиеся... SAE-100 .R Номер изделия R2 (T) R1 (T) 03-LEP-10 03-LEP... M35X2 M42X2 M45X2 M52X2 - R1/8 R1/4 R3/8 R1/2 R3/4 R1 R1 1/4 R1 1/2 R2 R2 1/2 R3 7/16...



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... 19 11 M 10x35 08-AFS102GM R1 25 52,37 70 26... 22 13 M 12x40 08-AFS104GM100 R1 25 58,72 81 30...,5 M 12x45 08-AFS102GM034 08-AFS106GM100 R1 25 69,85 93 35... 24 13,5 M 12x45 08-AFS108GM16 R1 25 77,77 102 42... 35 21 22 11 M 10x35 R1 25 57,15 81 27... 45 27 25 15 M 14x45 R1 25 66,68 95 31... 38 M 10x35 08-AFS102/90GM R1 25 52,37 70 26... 43 M 10x35 08-AFS403/90GM R1 25 57,15 79 27... 315 PB 160 PB 160 R 1/8 R 1/4 R 1/4 R 3/8 R 1/2 R 1/2 R 3/4 R1 14 17 17 19 24... 28-STP-06X1 6x1 392 28-STP-08X1 8x1 294 28-STP-08X1.5 8x1,5 441 28-STP-10X1 10x1 249 28-STP-10X1.5 10x1,5 374 28-STP-12X1.5 12x1,5 311 28-STP-12X2 12x2 415 28-STP-15X1.5 15x1,5 249 28-STP-15X2 15x2 332 28-STP-16X1.5 16x1,5 233 28-STP-16X2 16x2 311 28-STP-18X1.5 18x1,5 207 28-STP-20X2 20x2 249 28-STP-20X2.5 20x2,5 311 28-STP-22X2 22x2 226 28-STP-25X2.5 25x2,5 249 28-STP-25X3 25x3 299 28-STP-28X2 28x2 178 28-STP-30X3 30x3 249 28-STP-35X3 35x3 213 28-STP-38X4 38x4 262 28-STP-42X3... R 3/4 280 200 1120 55-10010 R1 250 200 930 Артикул Резьба... R 3/4 300 200 1120 55-10020 R1 280 250 930 БЫСТРОРАЗЪЕМНОЕ СОЕДИНЕНИЕ... - - 3/4"-16 - 3/4"-16 - L12, S10 L2 R1/2" R5/8" - 7/8"-14 - 1/2"-14 - 7/8"-14 - 7/8"-14... - -16 -16 -16 - M30x2 M36x2 R1" - 15/16"-12 - 1-11 1/2" - 1 5/16..., S25 -20 -20 -20 M42x2 - R1 1/4" - 15/8"-12 - 1 1/4"-11 1/2" 1 5/8" - 15/8"-12 - S30 - -24 -24 -24 M45x2 - R1 1/2" - 1 7/8"-12 - 1 7/8"-12 1 1/2"-11 1/2" 1 7/8"-12 - - L35...° 45° -3 -3 -4 -5 -4 -4 -6 -6 -6 -6 M10x1,5 M12x1,5 M14x1,5 M16x1,5 - R1/8" R1/4" R3/8" - 7/16"-20 1/2"-20 9/16...