SL-12 R/B(2)
NORAD 15693
Rocket Body
GEO
1984-063F
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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
34891 km
Apogee
35031 km
Inclination
7.1°
Period
1394.1 min
Mean Motion
1.03289210 rev/day
TLE Epoch
2026-06-25 18:00:00 UTC
📐 Computed Orbital Characteristics
Avg. Altitude34,961 km
Orbital Velocity11,180 km/h
Velocity3.11 km/s
Orbital Period23 hours 14 minutes
Orbits / Day1.03
Eccentricity0.0017
Semi-Major Axis41,332 km
Est. Orbital LifetimeEffectively permanent — above atmospheric drag
🚀 Launch & Identity
Country / Operator
🇷🇺 Russia (CIS)
Launch Date
1984-06-22
Launch Site
Baikonur, Kazakhstan
Int'l Designator
1984-063F
Object Type
Rocket Body
RCS Size
Large (>1 m²)
📖 About This Object
SL-12 R/B(2) is a spent rocket body associated with Russia (CIS), launched on 1984-06-22 from Baikonur, Kazakhstan on the Gran' No. 27L launch. With over 42 years in orbit, it has far exceeded many satellites’ design lifetimes. It orbits in Geostationary Orbit (GEO) at altitudes between 34,891 km and 35,031 km with an inclination of 7.1°. It travels at approximately 11,180 km/h (3.11 km/s), completing one full orbit every 23 hours 14 minutes — that’s roughly 1.03 orbits per day. Spent rocket bodies like SL-12 R/B(2) 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
SL-12 R/B(2) 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 7.1°, 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. Within ±50 km of SL-12 R/B(2)’s average altitude, there are currently 0 active payloads and 12 tracked debris or rocket body fragments. Russia (CIS) operates approximately 1,287 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
SL-12 R/B(2) orbits at approximately 34,961 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 11,180 km/h — it just keeps pace with the ground below. With an inclination of 7.1°, it actually traces a small figure-of-eight pattern rather than remaining perfectly fixed. Learn more about geostationary orbits.
SL-12 R/B(2) (NORAD ID 15693) 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.
SL-12 R/B(2) was launched on 1984-06-22 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 SL-12 R/B(2) (NORAD ID 15693) 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.
SL-12 R/B(2) travels at approximately 11,180 km/h (6,947 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.