Layers
Active Satellites
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Debris Objects
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Rocket Bodies
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Conjunction Events
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Click fetch to load live SGP4 data
SGP4 ORBITAL SAFETY PLANNING SYSTEM · BLUDOT LABS
0
SAT
0
DEB
0
R/B
0
CONJ
LAT — LON — VIEW ALT — km
EPOCH: awaiting dataT+00:00
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Objects tracked
real SGP4 catalog
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Conjunction alerts
TCA computed
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High-risk events
Pc > 1e-4
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Objects in LEO
200–2000 km
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Non-compliant
IADC 25yr rule
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Active satellites
maneuverable
Shell distribution — object count by altitude
Top risk objects (by conjunction Pc)
Orbital Shell Density Heatmap
200–2000 km LEO · Objects per 100 km
shell
Congestion Index Legend
■ EXTREME (>8.0)
■ HIGH (5.0–8.0)
■ MEDIUM (2.5–5.0)
■ LOW (<2.5)
IADC debris mitigation guidelines — compliance status
Conjunction Decision Engine
Select a conjunction event to simulate all avoidance
maneuvers
Orbital Safety API — In-Browser Sandbox
v1 · LIVE DATA
All endpoints run against your loaded orbital catalog using real SGP4 propagation and the Jacchia-Bowman
atmospheric model. No server required — the entire engine runs in your browser.
POST
/orbit/validate
Evaluate orbit safety & IADC compliance
Request body
POST
/conjunction/check
Analyze collision risk between two objects
Request body
POST
/deorbit/plan
Generate disposal strategies for a satellite or rocket body
Request body
POST
/maneuver/recommend
Optimal avoidance maneuver for a conjunction event
Request body
POST
/orbit/congestion
Density and risk levels within an orbital shell
Request body
Hero Scenario — Debris Mitigation Planning
DEMONSTRATION · SGP4 MODEL
Use Case · Debris Mitigation
COSMOS 2251 Fragment — Debris Field Analysis
NORAD 33885 · Altitude: 780 km · Inclination: 72.1° · Type: Debris
This object is a fragment from the 2009 Cosmos/Iridium collision — one of the most significant debris-generating events in spaceflight history.
This object is a fragment from the 2009 Cosmos/Iridium collision — one of the most significant debris-generating events in spaceflight history.
Passive Decay
112 years
At 780 km, atmospheric drag is negligible
NON-COMPLIANT · IADC 25yr
→
SwachOrbit Recommendation
Active Deorbit
Hohmann transfer to 120 km perigee
ALONG-TRACK FWD · OPTIMAL
→
Mission Output
Δv 312 m/s
Transfer time: <1 orbit (~93 min)
✓ IADC COMPLIANT
112 yr
Passive decay time
312 m/s
Required Δv (active deorbit)
< 1 orbit
Time to reentry
PASS
IADC 25-year compliance
All Avoidance Maneuver Options — Ranked
Direction
Δv (m/s)
Sep (km)
Risk ↓
Fuel kg
Along-Track FwdOPTIMAL
0.212
7.1
98%
0.04
Along-Track Bwd
0.303
6.6
96%
0.06
Radial Out
0.303
5.9
97%
0.06
Radial In
0.303
5.0
91%
0.06
Cross-Track
0.364
4.4
85%
0.07
Platform Context
SwachOrbit ingests live TLE catalogs, runs real SGP4 propagation
on each object, screens all pairs for close approaches, and automatically generates IADC-referenced disposal
plans — entirely in the browser, with no backend required.
The Orbital Safety API exposes these same capabilities as callable endpoints for mission design teams and satellite operators.
The Orbital Safety API exposes these same capabilities as callable endpoints for mission design teams and satellite operators.
CONJ
OBJECT
PLAN
MANEUVER
AI
Load orbital data to detect conjunction events.
The system will compute TCA, miss distance, relative velocity and Pc for all object pairs.
The system will compute TCA, miss distance, relative velocity and Pc for all object pairs.