MS-1 Credit - Yuzhnoye

Ukrainian microsatellite bus that could be equipped with imaging or other scientific or technical equipment.

Typical application was as an earth remote sensing microsatellite with a visible range video camera. Development of the microsatellite was funded under the Ukrainian National Space Program.

Typical characteristics of an optical sensor payload:

• Spectral Range: 0.45.0.90 mm
• Swath Width (at an orbital altitude of 500-700 km): 253-391 km
• Resolution: 124-191 m
• Mass: 66 kg
• Overall Dimensions: 430 x 430 x 957 mm
• Orbital Altitude: 650 x 664 km
• Orbital Inclination: 82.5 deg
• Orientation Accuracy: 1 deg
• Daily-Average Power: 18 W
• Active Lifetime: 3 years

Length: 0.96 m (3.14 ft). Basic Diameter: 0.43 m (1.41 ft). Maximum Diameter: 0.43 m (1.41 ft). Mass: 66 kg (145 lb). Electrical System: Solar cells. Electric System: 0.0180 average kW.

• 2004 December 24 - Mikron - Launch Site: Plesetsk. Launch Complex: LC32/2. Launch Vehicle: Tsiklon. Mass: 66 kg (145 lb). Perigee: 280 km (170 mi). Apogee: 650 km (400 mi). Inclination: 82.56 deg.
  The Mikron microsatellite was equipped with a small visible range video camera. The information from the satellite was to be used to provide remote sensing of topography and meteorology. However the main purpose of the experimental satellite was to test the MS-1 microsatellite bus created under the Ukrainian National Space Program. The satellites spectral range was from 0.45 to 0.90 mm; swath width was 253-391 km; resolution 124-191 m.

• 2007 April 17 - MisrSat 1 - Launch Site: Baikonur. Launch Complex: LC109. Launch Vehicle: R-36M. Mass: 100 kg (220 lb). Perigee: 657 km (408 mi). Apogee: 667 km (414 mi). Inclination: 98.10 deg. Period: 98.00 min.
  MisrSat/Egyptsat carried an imaging payload for Egypt's National Authority for Remote Sensing and Space Sciences.