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BREEZE-M R/B

NORAD 50003 Rocket Body HEO 2021-123C
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Altitude (km)
Speed (km/s)
Latitude
Longitude
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🛰️ Orbital Parameters
Perigee
16059 km
Apogee
51465 km
Inclination
5.8°
Period
1333.9 min
Mean Motion
1.07952506 rev/day
TLE Epoch
2026-06-26 02:00:00 UTC
📐 Computed Orbital Characteristics
Avg. Altitude33,762 km
Orbital Velocity11,345 km/h
Velocity3.15 km/s
Orbital Period22 hours 14 minutes
Orbits / Day1.08
Eccentricity0.4411
Semi-Major Axis40,133 km
Est. Orbital LifetimeEffectively permanent — above atmospheric drag
🚀 Launch & Identity
Country / Operator
🇷🇺 Russia (CIS)
Launch Date
2021-12-13
Launch Site
Baikonur, Kazakhstan
Int'l Designator
2021-123C
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 2021-12-13 from Baikonur, Kazakhstan on the Ekpress-AMU3/AMU7 launch. It orbits in Highly Elliptical Orbit (HEO) at altitudes between 16,059 km and 51,465 km with an inclination of 5.8°. It travels at approximately 11,345 km/h (3.15 km/s), completing one full orbit every 22 hours 14 minutes — that’s roughly 1.08 orbits per day. Its orbital eccentricity of 0.4411 gives it a noticeably elliptical path, with significant altitude variation between perigee and apogee. 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 follows a Highly Elliptical Orbit, sweeping between 16,059 km (perigee) and 51,465 km (apogee). It spends most of its 22 hours 14 minutes orbital period near apogee, effectively loitering over a region of interest before rapidly sweeping through perigee — a profile used for high-latitude communications (Molniya orbits), early-warning systems and magnetospheric science. With an inclination of 5.8°, BREEZE-M R/B passes over latitudes between 5.8°N and 5.8°S, concentrating coverage over equatorial and near-equatorial regions. Low-inclination orbits maximise revisit rates over specific tropical zones. 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 follows a Highly Elliptical Orbit, swinging between 16,059 km (perigee) and 51,465 km (apogee). It spends most of its 22 hours 14 minutes orbital period near apogee, moving slowly at high altitude — effectively loitering over a region of interest before rapidly sweeping through perigee.
BREEZE-M R/B (NORAD ID 50003) 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 2021-12-13 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 50003) 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’s speed varies dramatically throughout its orbit. At perigee it moves at its fastest, and at apogee it slows to a fraction of that — this is Kepler’s second law in action. Its average orbital velocity is approximately 11,345 km/h (3.15 km/s), completing one revolution every 22 hours 14 minutes. Learn more about highly elliptical orbits.