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CE-SAT 1, 42769

Orbit data source: Space-Track

CE-SAT 1, 42769 is a payload satellite in LEO that was launched on Fri, 23 Jun 2017 UTC via a PSLV-XL launch vehicle from the Sirharikota (SRI). Payload-class satellites include a variety of spacecraft equipped with specific instruments for various scientific and technological missions. These include communications satellites like Starlink; space stations such as the ISS; scientific satellites like the Hubble; Earth observation satellites from companies like Planet Labs, Umbra, and HawkEye 360; GPS; miniature CubeSats for education and research; and military/defense satellites.

Not visible in the next 10 days

Iframe embed code

<iframe src="https://www.satcat.com/sats-embedded/42769?theme=dark&initialShowStats=false" width="600" height="400" frameborder="0" title="Kayhan Space Satcat Satellite Viewer"></iframe>

Iframe URL

https://www.satcat.com/sats-embedded/42769?theme=dark&initialShowStats=false

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ISO8601 Format

Identifier

42769, 2017-036E

Orbit

LEO

Last TLE update

4 days ago

Origin

Canon Electronics Inc. (JP)

Manufacturer

Canon STL

Mission

Decayed Commercial Imaging

Bus & Motor

CE-SAT, Unknown motor

Mass

65 kg wet, 65 kg dry

Launch date (UTC)

2017-06-23 (8 years ago)

Launch vehicle

PSLV-XL

Launch site

Sirharikota (SRI)

Object type

Payload

Rocket body

Debris

Shape & HBR

Box, 0.9 m

Radar Cross Section

0.575 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 4 days ago

0 CE-SAT 1
1 42769U 17036E   25137.02325815  .08507654  24121-5  13397-3 0  9995
2 42769  97.0675 164.9752 0009951 244.4454 115.5822 16.47907954440542

Epoch: 2025-05-17T00:33Z

TLE epoch observation values (Epoch: 2025-05-17T00:33:29.504Z)

Latitude

-0.00003°

Longitude

-78.36826°

Altitude

150.931 km

Speed

7.814 km/s

True Right ascension

10h 59m 54s

True Declination

0° 00' 00"

Sunlit

Object was in full shadow at epoch

Visualization observer readout

Observer readout values are unavailable because the object's trajectory could not be propagated. This is usually caused when the trajectory data is faulty or the object's orbit has decayed.

Visualization observer readout

Observer readout values are unavailable because the object's trajectory could not be propagated. This is usually caused when the trajectory data is faulty or the object's orbit has decayed.