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ARIANE 5 R/B

NORAD 53766 Rocket Body HEO 2022-110B
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Altitude (km)
Speed (km/s)
Latitude
Longitude
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🛰️ Orbital Parameters
Perigee
157 km
Apogee
47778 km
Inclination
3.9°
Period
876.8 min
Mean Motion
1.64230507 rev/day
TLE Epoch
2026-06-18 10:00:00 UTC
📐 Computed Orbital Characteristics
Avg. Altitude23,968 km
Orbital Velocity13,049 km/h
Velocity3.62 km/s
Orbital Period14 hours 37 minutes
Orbits / Day1.64
Eccentricity0.7848
Semi-Major Axis30,339 km
Est. Orbital LifetimeEffectively permanent — above atmospheric drag
🚀 Launch & Identity
Country / Operator
🇫🇷 France
Launch Date
2022-09-07
Launch Site
Guiana Space Centre, Kourou
Int'l Designator
2022-110B
Object Type
Rocket Body
RCS Size
Large (>1 m²)
📖 About This Object
ARIANE 5 R/B is a spent rocket body associated with France, launched on 2022-09-07 from Guiana Space Centre, Kourou on the Eutelsat Konnect VHTS launch. It orbits in Highly Elliptical Orbit (HEO) at altitudes between 157 km and 47,778 km with an inclination of 3.9°. It travels at approximately 13,049 km/h (3.62 km/s), completing one full orbit every 14 hours 37 minutes — that’s roughly 1.64 orbits per day. Its orbital eccentricity of 0.7848 gives it a noticeably elliptical path, with significant altitude variation between perigee and apogee. Spent rocket bodies like ARIANE 5 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
ARIANE 5 R/B follows a Highly Elliptical Orbit, sweeping between 157 km (perigee) and 47,778 km (apogee). It spends most of its 14 hours 37 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 3.9°, ARIANE 5 R/B passes over latitudes between 3.9°N and 3.9°S, concentrating coverage over equatorial and near-equatorial regions. Low-inclination orbits maximise revisit rates over specific tropical zones. France operates approximately 115 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
ARIANE 5 R/B follows a Highly Elliptical Orbit, swinging between 157 km (perigee) and 47,778 km (apogee). It spends most of its 14 hours 37 minutes orbital period near apogee, moving slowly at high altitude — effectively loitering over a region of interest before rapidly sweeping through perigee.
ARIANE 5 R/B (NORAD ID 53766) is a spent rocket body — the upper stage of a launch vehicle attributed to France. 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.
ARIANE 5 R/B was launched on 2022-09-07 from Guiana Space Centre, Kourou, the European spaceport in French Guiana, chosen for its equatorial location which provides an energy-efficient boost for orbital insertions. At its current altitude, the estimated remaining orbital lifetime is: effectively permanent — above atmospheric drag. View the full satellite launch log.
Yes — Orbital Radar tracks ARIANE 5 R/B (NORAD ID 53766) 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.
ARIANE 5 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 13,049 km/h (3.62 km/s), completing one revolution every 14 hours 37 minutes. Learn more about highly elliptical orbits.