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BREEZE-M R/B

NORAD 40385 Rocket Body HEO 2015-005B
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Altitude (km)
Speed (km/s)
Latitude
Longitude
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🛰️ Orbital Parameters
Perigee
3236 km
Apogee
62761 km
Inclination
27.1°
Period
1296.0 min
Mean Motion
1.11107794 rev/day
TLE Epoch
2026-06-25 10:00:00 UTC
📐 Computed Orbital Characteristics
Avg. Altitude32,999 km
Orbital Velocity11,455 km/h
Velocity3.18 km/s
Orbital Period21 hours 36 minutes
Orbits / Day1.11
Eccentricity0.7560
Semi-Major Axis39,370 km
Est. Orbital LifetimeEffectively permanent — above atmospheric drag
🚀 Launch & Identity
Country / Operator
🇷🇺 Russia (CIS)
Launch Date
2015-02-01
Launch Site
Baikonur, Kazakhstan
Int'l Designator
2015-005B
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 2015-02-01 from Baikonur, Kazakhstan on the Inmarsat 5F2 launch. After 11 years in orbit, it continues to be tracked by global surveillance networks. It orbits in Highly Elliptical Orbit (HEO) at altitudes between 3,236 km and 62,761 km with an inclination of 27.1°. It travels at approximately 11,455 km/h (3.18 km/s), completing one full orbit every 21 hours 36 minutes — that’s roughly 1.11 orbits per day. Its orbital eccentricity of 0.7560 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 3,236 km (perigee) and 62,761 km (apogee). It spends most of its 21 hours 36 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 27.1°, BREEZE-M R/B passes over latitudes between 27.1°N and 27.1°S, covering the tropical and temperate zones where most of the world’s population resides. Low-to-mid inclination orbits are efficient to reach from equatorial and mid-latitude launch sites. 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 3,236 km (perigee) and 62,761 km (apogee). It spends most of its 21 hours 36 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 40385) 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 2015-02-01 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 40385) 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 11,455 km/h (3.18 km/s), completing one revolution every 21 hours 36 minutes. Learn more about highly elliptical orbits.