YZ-1S R/B
NORAD 60326
Rocket Body
HEO
2024-048E
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HEO · NORAD 60326
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Altitude (km)
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Latitude
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Longitude
🛰️ Orbital Parameters
Perigee
1036 km
Apogee
125273 km
Inclination
15.9°
Period
3041.2 min
Mean Motion
0.47349902 rev/day
TLE Epoch
2026-06-27 00:00:00 UTC
📐 Computed Orbital Characteristics
Avg. Altitude63,155 km
Orbital Velocity8,620 km/h
Velocity2.39 km/s
Orbital Period50.7 hours
Orbits / Day0.47
Eccentricity0.8935
Semi-Major Axis69,526 km
Est. Orbital LifetimePermanent — geostationary orbit, no atmospheric drag
🚀 Launch & Identity
Country / Operator
🇨🇳 China
Launch Date
2024-03-13
Launch Site
Xichang, China
Int'l Designator
2024-048E
Object Type
Rocket Body
RCS Size
Unknown
📖 About This Object
YZ-1S R/B is a spent rocket body associated with China, launched on 2024-03-13 from Xichang, China on the DRO-A/DRO-B launch. It orbits in Highly Elliptical Orbit (HEO) at altitudes between 1,036 km and 125,273 km with an inclination of 15.9°. It travels at approximately 8,620 km/h (2.39 km/s), completing one full orbit every 50.7 hours — that’s roughly 0.47 orbits per day. Its orbital eccentricity of 0.8935 gives it a noticeably elliptical path, with significant altitude variation between perigee and apogee. At geostationary altitude, there is no meaningful atmospheric drag — this object will remain in orbit indefinitely unless actively deorbited. Spent rocket bodies like YZ-1S 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
YZ-1S R/B follows a Highly Elliptical Orbit, sweeping between 1,036 km (perigee) and 125,273 km (apogee). It spends most of its 50.7 hours 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 15.9°, YZ-1S R/B passes over latitudes between 15.9°N and 15.9°S, concentrating coverage over equatorial and near-equatorial regions. Low-inclination orbits maximise revisit rates over specific tropical zones. China operates approximately 1,221 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
YZ-1S R/B follows a Highly Elliptical Orbit, swinging between 1,036 km (perigee) and 125,273 km (apogee). It spends most of its 50.7 hours orbital period near apogee, moving slowly at high altitude — effectively loitering over a region of interest before rapidly sweeping through perigee.
YZ-1S R/B (NORAD ID 60326) is a spent rocket body — the upper stage of a launch vehicle attributed to China. 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.
YZ-1S R/B was launched on 2024-03-13 from Xichang, China. At its current altitude, the estimated remaining orbital lifetime is: permanent — geostationary orbit, no atmospheric drag. View the full satellite launch log.
Yes — Orbital Radar tracks YZ-1S R/B (NORAD ID 60326) 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.
YZ-1S 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 8,620 km/h (2.39 km/s), completing one revolution every 50.7 hours. Learn more about highly elliptical orbits.