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TurkSat-3USat

TurkSat-3USat
Mission type Communications
Operator Space Systems Design and Test Laboratory, Istanbul Technical University
COSPAR ID 2013-018C[1]
SATCAT № 39152[1]
Mission duration 3 years
Spacecraft properties
Manufacturer Türksat
Launch mass 4 kilograms (8.8 lb)
Start of mission
Launch date April 26, 2013, 04:13:04 (2013-04-26T04:13:04Z) UTC
Rocket Chang Zheng 2D
Launch site Jiuquan LA-4/SLS-2
Orbital parameters
Reference system Geocentric
Regime Sun-synchronous
Semi-major axis 7,019 kilometres (4,361 mi)[1]
Perigee 635.0 kilometres (394.6 mi)[1]
Apogee 661.5 kilometres (411.0 mi)[1]
Inclination 98.1  degrees[1]
Period 97.5 minutes

TurkSat-3USat is a launched on April 26, 2013.[2][3][4]

Started with a protocol signed on November 29, 2010, TurkSat-3USat is a follow-up project based on the ITUpSAT1 mission, which was launched on September 23, 2009.[4][5][6]

Launch and orbit

TurkSat-3USat was launched as a secondary payload on April 26, 2013 at 04:13:04 UTC atop a Long March 2D satellite launch vehicle from the Launch Area 4/South Launch Site 2 of Jiuquan Satellite Launch Center in Gobi Desert, China.[3][4][5] Further payloads on this flight were:[4][6]

TurkSat-3USat was placed into a Sun-synchronous low Earth orbit at an altitude of 645 km (401 mi). It orbits 2-3 times a day over Turkey. The satellite's mission duration is expected to be at least three years.[3][4]

Spacecraft and payload

TurkSat-3USat is packed in a three-unit CubeSat[7][8] structure made by Innovative Solutions In Space BV (ISIS) from Delft, Netherlands.[4] It is 10 cm × 10 cm (3.9 in × 3.9 in) wide and 34 cm (13 in) long, and has a mass of about 4 kg (8.8 lb).[3][5]

The satellite's payload, a linear transponder and on-board computer, were designed in the RF Electronic Laboratory of ITU.[2] It is Turkey's first indigenously developed satellite. TurkSat-3USat providing SSB/CW communication in amateur radio frequency bands.[3] The transponder input is 145.940-145.990 MHz and the output is 435.200-435.250 MHz. On 437.225 MHz is either a CW beacon or 9,600 baud Audio frequency-shift keying (AFSK).[6][7]

Solar panels and lithium polymer batteries together with super capacitors provide the required power. Passive magnetic attitude control system with hysteresis rods enable satellite stabilization. A C329 UART camera module is available on board for occasional snapshots of Earth.[4][6][7][8]

The satellite features also a system to deorbit itself after the completion of its mission in compliance with the current CubeSat standard and United Nations regulations.[4][6]

References

  1. ^ a b c d e f
  2. ^ a b
  3. ^ a b c d e
  4. ^ a b c d e f g h
  5. ^ a b c
  6. ^ a b c d e
  7. ^ a b c
  8. ^ a b
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