Space Brief 31 Jul 2025
Today's Space Brief brings updates on the U.S. Space Force's upcoming missions, in-space technology strategies, the challenges faced by new launchers, and advancements in satellite communication.
GSAT-2 (27807)
COSPAR: 2003-018A | Alt Name: GSAT-2
Image
Additional Sources
Launch Details
Launch Date
May 8, 2003
Launch Site
SRILR
Launch Pad
FLP
Launch Vehicle
GSLV Mk I
Orbital Elements
NORAD ID
27807
International Designator
2003-018A
Epoch
Sat, 04 Jul 2026 03:11:21 GMT
Apogee
Calculating...
Perigee
Calculating...
Inclination
11.21°
Right Ascension
41.54°
Eccentricity
Calculating...
Argument of Perigee
349.82°
Period
1442.27 min
Mean Motion
1.00 rev/day
Latitude
Calculating...
Longitude
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Altitude
Calculating...
Velocity
Calculating...
Polar Plot
3D Visualization
Basic Satellite Info
Name
GSAT-2
Alternative Name
GSAT-2
Type
Payload
Status
Non-operational
Owner
ISRO
Country
India
Constellation
N/A
Related Satellites
Major Events
N/A
Latest TLEs
1 27807U 03018A 26185.13289125 -.00000124 00000-0 00000-0 0 9997
2 27807 11.2075 41.5390 0011817 349.8220 208.5729 0.99842859 84605
Source: Celestrak
Summary
GSAT-2 is an experimental communication satellite launched by ISRO on May 8, 2003, from Sriharikota using a GSLV Mk I launch vehicle. The spacecraft has dimensions of 2.4 meters in length, 1.6 meters in diameter, and spans 9.6 meters when its solar arrays are deployed. It has a dry mass of 840 kilograms and was launched with a total mass of 1,800 kilograms. Equipped with various communication payloads including C-band and Ku-band transponders as well as an MSS payload, GSAT-2 also features deployable solar arrays for power generation. The satellite is shaped like a box with two panels and has been operational since its launch date.
Physical Characteristics
Length
2.4
Diameter
1.6
Span
9.6
Dry Mass
840
Launch Mass
1800
Shape
Box + 2 Pan
Radar Cross Section
0.003
Visual Magnitude
Unknown
Color
Unknown
Material Composition
Unknown
Technical Details
Payload
GSAT-2
Purpose
Experimental Communication
Mission
Experimental Communication
Manufacturer
ISRO
Life Expectancy
Unknown
Bus
I2K
Configuration
I-2K (I-2000) Bus
Motor
ISRO LAM
Equipment
4 C-band transponders, 2 Ku-band transponders, MSS payload (S-band forward, C-band return), TRDM, SCM, SOXS, CRABEX
Power System
2 deployable solar arrays, batteries
ADCS
Unknown
Transmitter Frequency
Unknown
Map
Next Pass
Azimuth Elevation Time (Local)
Start Azimuth
Max Elevation
Stop Azimuth
Time Until
Pass Duration
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