Reentry
What happens when space objects come home: the fiery physics of returning from orbit and why predicting where debris lands is so difficult
XSS-10 (27664)
COSPAR: 2003-005B | Alt Name: XSS-10
Image
Additional Sources
Launch Details
Launch Date
January 29, 2003
Launch Site
Launch Pad
SLC17B
Launch Vehicle
Delta 7925-9.5
Orbital Elements
NORAD ID
27664
International Designator
2003-005B
Epoch
Fri, 03 Jul 2026 19:37:08 GMT
Apogee
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Perigee
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Inclination
39.75°
Right Ascension
354.44°
Eccentricity
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Argument of Perigee
211.79°
Period
96.62 min
Mean Motion
14.90 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
Basic Satellite Info
Name
XSS-10
Alternative Name
XSS-10
Type
Payload
Status
Unknown
Owner
AFSMC
Country
United States
Constellation
N/A
Related Satellites
Major Events
N/A
Latest TLEs
1 27664U 03005B 26184.81746476 .00002676 00000-0 23186-3 0 9991
2 27664 39.7475 354.4366 0147683 211.7866 147.3937 14.90422120265117
Source: Celestrak
Summary
The XSS-10 satellite, also known by its NORAD catalog ID 27664 and object ID 2003-005B, is an integrated camera and star sensor technology demonstration satellite launched on January 29, 2003, from the Cape Canaveral Air Force Station's SLC17B launch pad using a Delta 7925-9.5 vehicle. Manufactured by AFRL for AFSMC, XSS-10 is cylindrical in shape with dimensions of 1 meter length and 0.5 meters diameter, with a span of 1 meter. It has a dry mass of 28 kg and was powered by batteries. The satellite was equipped with an integrated camera and star sensor for technology demonstration purposes and featured a lightweight bipropellant propulsion system. Its launch mass was also 28 kg, and it achieved stability on January 30, 2003. With a lifetime of just one day, XSS-10 had a radar cross-section (RCS) of 0.183 square meters.
Physical Characteristics
Length
1
Diameter
0.5
Span
1
Dry Mass
28
Launch Mass
28
Shape
Cyl
Radar Cross Section
0.183
Visual Magnitude
Unknown
Color
Unknown
Material Composition
Unknown
Technical Details
Payload
XSS-10
Purpose
Technology
Mission
Technology
Manufacturer
AFRL
Life Expectancy
1 day
Bus
XSS
Configuration
Integrated camera and star sensor
Motor
Lightweight bipropellant propulsion system
Equipment
Camera
Power System
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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