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FALCON 9 R/B

NORAD 58996 Rocket Body HEO 2024-035B
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Altitude (km)
Speed (km/s)
Latitude
Longitude
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🛰️ Orbital Parameters
Perigee
280 km
Apogee
54313 km
Inclination
20.0°
Period
1025.0 min
Mean Motion
1.40491239 rev/day
TLE Epoch
2026-06-18 03:00:00 UTC
📐 Computed Orbital Characteristics
Avg. Altitude27,297 km
Orbital Velocity12,387 km/h
Velocity3.44 km/s
Orbital Period17 hours 5 minutes
Orbits / Day1.40
Eccentricity0.8025
Semi-Major Axis33,668 km
Est. Orbital LifetimeEffectively permanent — above atmospheric drag
🚀 Launch & Identity
Country / Operator
🇺🇸 United States
Launch Date
2024-02-20
Launch Site
Cape Canaveral, Florida
Int'l Designator
2024-035B
Object Type
Rocket Body
RCS Size
Large (>1 m²)
📖 About This Object
FALCON 9 R/B is a spent rocket body associated with United States, launched on 2024-02-20 from Cape Canaveral, Florida on the HTS 113BT launch. It orbits in Highly Elliptical Orbit (HEO) at altitudes between 280 km and 54,313 km with an inclination of 20.0°. It travels at approximately 12,387 km/h (3.44 km/s), completing one full orbit every 17 hours 5 minutes — that’s roughly 1.40 orbits per day. Its orbital eccentricity of 0.8025 gives it a noticeably elliptical path, with significant altitude variation between perigee and apogee. Spent rocket bodies like FALCON 9 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
FALCON 9 R/B follows a Highly Elliptical Orbit, sweeping between 280 km (perigee) and 54,313 km (apogee). It spends most of its 17 hours 5 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 20.0°, FALCON 9 R/B passes over latitudes between 20.0°N and 20.0°S, concentrating coverage over equatorial and near-equatorial regions. Low-inclination orbits maximise revisit rates over specific tropical zones. 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
FALCON 9 R/B follows a Highly Elliptical Orbit, swinging between 280 km (perigee) and 54,313 km (apogee). It spends most of its 17 hours 5 minutes orbital period near apogee, moving slowly at high altitude — effectively loitering over a region of interest before rapidly sweeping through perigee.
FALCON 9 R/B (NORAD ID 58996) 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.
FALCON 9 R/B was launched on 2024-02-20 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. 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 FALCON 9 R/B (NORAD ID 58996) 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.
FALCON 9 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 12,387 km/h (3.44 km/s), completing one revolution every 17 hours 5 minutes. Learn more about highly elliptical orbits.