Launch Date
May 3, 2024
Launch Site
Wenchang Space Launch Site, Hainan, China
Launch Pad
LC101
Launch Vehicle
Long March 5 Y8
NORAD ID
59629
International Designator
2024-082C
Epoch
Fri, 03 May 2024 16:19:12 GMT
Apogee
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Perigee
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Inclination
23.04°
Right Ascension
348.54°
Eccentricity
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Argument of Perigee
239.79°
Period
22674.85 min
Mean Motion
0.06 rev/day
Latitude
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Longitude
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Altitude
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Velocity
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Name
ICUBE-QAMAR (ICUBE-Q)
Alternative Name
ICUBE-Q
Type
Status
Owner
Institute of Space Technology (IST), Space & Upper Atmosphere Research Commission (SUPARCO)
Country
Pakistan
Constellation
N/A
Related Satellites
Major Events
Launch on May 3, 2024; successful deployment into lunar orbit on May 8, 2024; first images transmitted back to Earth on May 11, 2024.
1 59629U 24082C 24124.68000000 -.00194999 15823-2 00000+0 0 9996
2 59629 23.0390 348.5400 9762994 239.7870 5.9940 00.06350648 05
Source: Celestrak
Length
0.1
Diameter
0.2
Span
0.3
Dry Mass
6.5
Launch Mass
9
Shape
CubeSat with deployable solar panels
Radar Cross Section
Unknown
Visual Magnitude
Unknown
Color
Silver (aluminum-clad)
Material Composition
Constructed using advanced materials such as special magnesium alloy and honeycomb carbon fiber.
Payload
Two 1-megapixel cameras mounted on opposite X panels for lunar surface imaging.
Purpose
Lunar remote sensing and technology demonstration.
Mission
ICUBE-Q is Pakistan's first lunar mission, aiming to conduct remote sensing observations of the Moon's surface, capture images of the Earth and Moon, and gather lunar magnetic field data to establish a lunar magnetic field model.
Manufacturer
Institute of Space Technology (IST), Shanghai Jiao Tong University (SJTU)
Life Expectancy
The satellite is designed for a mission duration of 3 months, with a planned operational period ranging from 2 to 6 months.
Bus
CubeSat 6U
Configuration
Lunar Orbiter
Motor
None
Equipment
Two 1-megapixel optical cameras for lunar surface imaging; X-band communication system for telemetry, telecommand, and data transfer; attitude control system including reaction wheels, star sensor, and sun sensors.
Power System
The satellite is powered by a 12V, 11.6Ah battery, supplemented by two deployable solar panels.
ADCS
Three-axis control using reaction wheels, star sensor, and sun sensors.
Transmitter Frequency
X-band for telemetry, telecommand, and data transfer at a rate of 1 kbps.
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