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Thuraya 4-NGS (62483)
COSPAR: 2025-001A | Alt Name: Thuraya 4 Next Generation Satellite
Image
Additional Sources
Launch Details
Launch Date
January 4, 2025
Launch Site
Cape Canaveral Space Force Station
Launch Pad
SLC-40
Launch Vehicle
Falcon 9 Block 5
Orbital Elements
NORAD ID
62483
International Designator
2025-001A
Epoch
Sun, 19 Jul 2026 20:13:50 GMT
Apogee
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Perigee
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Inclination
0.02°
Right Ascension
76.11°
Eccentricity
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Argument of Perigee
335.73°
Period
1436.09 min
Mean Motion
1.00 rev/day
Latitude
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Longitude
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Altitude
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Velocity
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Polar Plot
3D Visualization
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Basic Satellite Info
Name
Thuraya 4-NGS
Alternative Name
Thuraya 4 Next Generation Satellite
Type
Payload
Status
Operational
Owner
Space42
Country
United Arab Emirates
Constellation
Thuraya
Related Satellites
Major Events
Launched on January 4, 2025, Thuraya 4-NGS is expected to commence operational services after reaching its designated geostationary orbit and completing in-orbit testing.
Latest TLEs
1 62483U 25001A 26200.84294183 .00000136 00000+0 00000+0 0 9998
2 62483 0.0201 76.1083 0000031 335.7287 233.5563 01.00272319 4503
Source: Celestrak
Summary
Thuraya 4-NGS (2025-001A) is a geostationary satellite designed for advanced mobile satellite communication services, launched on January 4, 2025, from Cape Canaveral Space Force Station's SLC-40 launch pad using a Falcon 9 Block 5 rocket. Operated by Space42 and manufactured by Airbus Defence and Space, it is part of the Thuraya constellation and is based on the Eurostar NEO bus configuration.
The satellite measures 8 meters in length with a diameter of 3 meters and spans up to 40 meters when its solar arrays are deployed. It has a dry mass of 5,000 kg and is equipped with high-capacity L-band transponders and a 12-meter L-band antenna, capable of handling up to 3,200 communication channels with dynamic power allocation across multiple spot beams.
Thuraya 4-NGS features two deployable solar arrays generating approximately 20 kW of power, supported by rechargeable batteries. It is equipped with a PPS-5000 electric propulsion system and employs 3-axis stabilization using reaction wheels and star trackers for precise orbit control. The satellite’s equipment includes an advanced onboard processing unit to support secure voice, data, and video transmission services.
Constructed primarily from lightweight aluminum and composite materials, the spacecraft has a box-shaped main body with large deployable antenna and solar arrays. Its design is intended to provide enhanced mobile satellite services across multiple regions for over 15 years.
Physical Characteristics
Length
8
Diameter
3
Span
40
Dry Mass
5000
Launch Mass
5000
Shape
Box-shaped main body with large deployable antenna and solar arrays
Radar Cross Section
Unknown
Visual Magnitude
Estimated at 8.0 based on size and reflectivity
Color
Predominantly white with company logos and markings
Material Composition
Constructed using lightweight aluminum and composite materials for the main structure, with a large mesh reflector for the antenna.
Technical Details
Payload
High-capacity L-band transponders
Purpose
Communication
Mission
To provide advanced mobile satellite communication services, including secure voice, data, and video transmission, supporting various sectors such as defense, government, and enterprise.
Manufacturer
Airbus Defence and Space
Life Expectancy
Designed for a mission life of over 15 years, providing enhanced mobile satellite services across multiple regions.
Bus
Eurostar NEO
Configuration
Eurostar-Neo
Motor
PPS-5000 electric propulsion system
Equipment
12-meter L-band antenna, advanced onboard processing unit capable of handling up to 3,200 communication channels with dynamic power allocation across multiple spot beams.
Power System
Two deployable solar arrays generating approximately 20 kW of power, supported by rechargeable batteries.
ADCS
3-axis stabilized using reaction wheels and star trackers
Transmitter Frequency
L-band frequencies for mobile communication services
Map
Next Pass
Azimuth Elevation Time (Local)
Start Azimuth
Max Elevation
Stop Azimuth
Time Until
Pass Duration
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