Pirs / Progress MSO-

Progress M-SO1 was the designation given to the service module section of a Progress M; the Pirs docking and airlock module for the ISS replaced the standard cargo and fuel sections.

The Russian docking and airlock module for the International Space Station. The Stikovochniy Otsek No. 1 (SO1, Docking Module 1), article 240GK No. 1L, was built by Energia and derived from Soyuz hardware. It had a mass of around 3900 kg and was a 4.1 m long, 2.6 m diameter ovoid. The SO1 was named Pirs (Russian for "pier") and was delivered to the station by Progress M-SO1 in a completely automatic rendezvous and docking operation. Pirs provided extra clearance from the Station for ships docking underneath Zvezda, and was used as an airlock for spacewalks using the Russian Orlan EVA suits.

Length: 6.40 m (20.90 ft). Basic Diameter: 2.60 m (8.50 ft). Maximum Diameter: 2.72 m (8.92 ft). Mass: 7,250 kg (15,980 lb). Payload: 3,900 kg (8,500 lb). Associated Launch Vehicle: Soyuz 11A511U.

• ISS Pirs.  Manufacturer's Designation: Energia. Part of: Progress M-SO. Class: Manned. Type: Space Station Module. Nation: Russia. Manufacturer: Korolev.

  Russian docking and airlock module for the International Space Station. The Stikovochniy Otsek No. 1 (SO1, Docking Module 1), article 240GK No. 1L, was built by Energia and derived from Soyuz hardware. It had a mass of around 3900 kg and was a 4.1 m long, 2.6 m diameter ovoid. The SO1 was named Pirs (Russian for "pier") and was delivered to the station by Progress M-SO1 in a completely automatic rendezvous and docking operation. Pirs provided extra clearance from the Station for ships docking underneath Zvezda, and was used as an airlock for spacewalks using the Russian Orlan EVA suits.

  Length: 4.10 m (13.40 ft). Basic Diameter: 2.60 m (8.50 ft). Maximum Diameter: 2.60 m (8.50 ft). Mass: 6,850 kg (15,100 lb). Associated Launch Vehicle: Soyuz 11A511U.

• Progress M PAO.  Other Designations: Priborno-agregatniy otsek. Part of: Progress M-SO. Class: Manned. Type: Spacecraft Module. Purpose: Equipment-engine section.

  Improved PAO service module derived from Soyuz 7K-S with pressure-fed main engines and unitary RCS/main engine propellant feed system.

  Length: 2.26 m (7.41 ft). Basic Diameter: 2.15 m (7.05 ft). Maximum Diameter: 2.72 m (8.92 ft). Mass: 2,950 kg (6,500 lb). RCS Coarse No x Thrust: 16 X 98 N. RCS Fine No x Thrust: 8 X 98 N. RCS Coarse Backup No x Thrust: No separate backup translation engines. RCS Propellants: N2O4/UDMH. Main Engine: KTDU-80. Main Engine: 310 kg (680 lb). Main Engine Thrust: 6.197 kN (1,393 lbf). Main Engine Propellants: N2O4/UDMH. Main Engine Propellants: 880 kg (1,940 lb). Main Engine Isp: 302 sec. Electrical System: Solar panel span: 10.60 m; area 10.00 sq.m. Electric System: 0.60 average kW.

• 2001 September 14 - Progress M-SO1 - Program: ISS. Flight: ISS EO-3. Launch Site: Baikonur. Launch Vehicle: Soyuz 11A511U. Mass: 6,900 kg (15,200 lb). Perigee: 388 km (241 mi). Apogee: 394 km (245 mi). Inclination: 51.60 deg. Duration: 12.00 days.

  Progress M-SO1 was the designation given to the service module section of a Progress M; the 3900 kg Pirs docking and airlock module for the ISS replaced the standard cargo and fuel sections. It also carried an astronaut chair, a space suit, a small crane, and some equipment for the Zvezda module of the ISS. Progress-M No. 301 was launched into an initial 180 km circular orbit. By September 16 it had maneuvered into a 238 x 264 km orbit; by 0038 GMT on September 17, a 385 x 395 km x 51.6 deg orbit upon rendezvous with the ISS. The Progress began a fly around of the station and lined up with the nadir port on Zvezda. Docking of Pirs with Zvezda came at 0105 GMT on September 17. The Progress M-SO1 later undocked from the Pirs nadir port to leave it free for future dockings. Pirs gave extra clearance from the Station for ships docking underneath Zvezda, and was also used as an airlock for spacewalks using the Russian Orlan EVA suits. Progress M-SO1 service module undocked from the Pirs module at 1536 GMT on September 26 and was deorbited over the Pacific at 2330 GMT the same day.

• NASA/GSFC Orbital Information Group Website, . Accessed at: http://oig1.gsfc.nasa.gov/.

• Space-Launcher.com, Orbital Report News Agency. Accessed at: http://www.orbireport.com/Log.html.

• National Space Science Center Planetary Page, As of 19 February 1999.. Accessed at: http://nssdc.gsfc.nasa.gov/planetary/planetary_home.html.

• McDowell, Jonathan, Jonathan's Space Report (Internet Newsletter), Harvard University, Weekly, 1989 to Present. Essential internet newsletter recording worldwide weekly space events. Accessed at: http://www.planet4589.org/jsr.html.