DELTA 4 R/B
NORAD 41585
Rocket Body
GEO
2016-036B
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GEO · NORAD 41585
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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
33811 km
Apogee
35693 km
Inclination
5.6°
Period
1383.5 min
Mean Motion
1.04079800 rev/day
TLE Epoch
2026-06-25 08:00:00 UTC
📐 Computed Orbital Characteristics
Avg. Altitude34,752 km
Orbital Velocity11,208 km/h
Velocity3.11 km/s
Orbital Period23 hours 4 minutes
Orbits / Day1.04
Eccentricity0.0229
Semi-Major Axis41,123 km
Est. Orbital LifetimeEffectively permanent — above atmospheric drag
🚀 Launch & Identity
Country / Operator
🇺🇸 United States
Launch Date
2016-06-11
Launch Site
Cape Canaveral, Florida
Int'l Designator
2016-036B
Object Type
Rocket Body
RCS Size
Medium (0.1–1 m²)
📖 About This Object
DELTA 4 R/B is a spent rocket body associated with United States, launched on 2016-06-11 from Cape Canaveral, Florida on the ORION 9 launch. After 10 years in orbit, it continues to be tracked by global surveillance networks. It orbits in Geostationary Orbit (GEO) at altitudes between 33,811 km and 35,693 km with an inclination of 5.6°. It travels at approximately 11,208 km/h (3.11 km/s), completing one full orbit every 23 hours 4 minutes — that’s roughly 1.04 orbits per day. Spent rocket bodies like DELTA 4 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
DELTA 4 R/B 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 5.6°, 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. United States operates approximately 12,413 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
DELTA 4 R/B orbits at approximately 34,752 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 11,208 km/h — it just keeps pace with the ground below. With an inclination of 5.6°, it actually traces a small figure-of-eight pattern rather than remaining perfectly fixed. Learn more about geostationary orbits.
DELTA 4 R/B (NORAD ID 41585) is a spent rocket body — the upper stage of a launch vehicle attributed to United States. 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.
DELTA 4 R/B was launched on 2016-06-11 from Cape Canaveral, Florida, one of the busiest launch facilities in the world, operated by NASA and the U.S. Space Force on Florida’s Atlantic coast. View the full satellite launch log.
Yes — Orbital Radar tracks DELTA 4 R/B (NORAD ID 41585) 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.
DELTA 4 R/B travels at approximately 11,208 km/h (6,964 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.