BREEZE-M R/B
NORAD 32479
Rocket Body
GEO
2008-003B
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GEO · NORAD 32479
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Altitude (km)
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Speed (km/s)
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Latitude
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Longitude
🛰️ Orbital Parameters
Perigee
33960 km
Apogee
35584 km
Inclination
11.3°
Period
1384.6 min
Mean Motion
1.04003358 rev/day
TLE Epoch
2026-06-26 05:00:00 UTC
📐 Computed Orbital Characteristics
Avg. Altitude34,772 km
Orbital Velocity11,205 km/h
Velocity3.11 km/s
Orbital Period23 hours 5 minutes
Orbits / Day1.04
Eccentricity0.0197
Semi-Major Axis41,143 km
Est. Orbital LifetimeEffectively permanent — above atmospheric drag
🚀 Launch & Identity
Country / Operator
🇷🇺 Russia (CIS)
Launch Date
2008-01-28
Launch Site
Baikonur, Kazakhstan
Int'l Designator
2008-003B
Object Type
Rocket Body
RCS Size
Large (>1 m²)
📖 About This Object
BREEZE-M R/B is a spent rocket body associated with Russia (CIS), launched on 2008-01-28 from Baikonur, Kazakhstan on the Ekspress AM-33 launch. After 18 years in orbit, it continues to be tracked by global surveillance networks. It orbits in Geostationary Orbit (GEO) at altitudes between 33,960 km and 35,584 km with an inclination of 11.3°. It travels at approximately 11,205 km/h (3.11 km/s), completing one full orbit every 23 hours 5 minutes — that’s roughly 1.04 orbits per day. Spent rocket bodies like BREEZE-M R/B are among the largest pieces of uncontrolled space debris and are priority targets for collision avoidance manoeuvres and future active debris removal efforts.
🌍 Orbit Context
BREEZE-M R/B occupies geostationary orbit at approximately 35,786 km above the equator, where its orbital period matches the Earth’s 24-hour rotation. From the ground, it appears to hover over a fixed point — ideal for broadcast television, weather monitoring and wideband communications. With an inclination of 11.3°, it traces a small figure-of-eight pattern relative to the equator rather than remaining perfectly stationary, which can indicate aging stationkeeping fuel or a deliberate inclined-orbit strategy. Russia (CIS) operates approximately 1,286 active satellites in total.
🔗 Spent Rocket Body
This is a spent rocket body — the upper stage of a launch vehicle that remains in orbit after delivering its payload. Rocket bodies are a significant contributor to the space debris population. Older stages often retained residual propellant that could later explode, creating debris fields. Modern guidelines require upper stages to either deorbit (controlled re-entry) or passivate (vent residual fuel) to reduce fragmentation risk. The FCC's 5-year deorbit rule and UN debris mitigation guidelines are increasingly enforced to address this growing problem.
❓ Frequently Asked Questions
BREEZE-M R/B orbits at approximately 34,772 km altitude, where the orbital period matches the Earth’s 24-hour rotation. This means it stays above the same point on the equator at all times. Its actual speed is still 11,205 km/h — it just keeps pace with the ground below. With an inclination of 11.3°, it actually traces a small figure-of-eight pattern rather than remaining perfectly fixed. Learn more about geostationary orbits.
BREEZE-M R/B (NORAD ID 32479) is a spent rocket body — the upper stage of a launch vehicle attributed to Russia (CIS). It no longer serves a functional purpose but continues to orbit Earth as tracked debris. Spent upper stages are among the largest uncontrolled objects in orbit and are closely monitored for collision risk.
BREEZE-M R/B was launched on 2008-01-28 from Baikonur, Kazakhstan, the world’s first and largest operational space launch facility, located in Kazakhstan. View the full satellite launch log.
Yes — Orbital Radar tracks BREEZE-M R/B (NORAD ID 32479) using the latest TLE (two-line element set) data from Space-Track and CelesTrak. Open the live tracker to see its current position, altitude, speed and orbital path updated in real time. You can also browse the satellite directory to find other tracked objects.
BREEZE-M R/B travels at approximately 11,205 km/h (6,963 mph) — roughly 3.11 km/s. Despite this high speed, it appears stationary from the ground because it matches the Earth’s rotation. Geostationary satellites are actually slower than LEO satellites because orbital velocity decreases with altitude.