MAIN SPACE DEBRIS 2006 ACTIVITIES IN FRANCE · apogees between DEMETER and W23 On June 25...
Transcript of MAIN SPACE DEBRIS 2006 ACTIVITIES IN FRANCE · apogees between DEMETER and W23 On June 25...
MAIN SPACE DEBRIS 2006 ACTIVITIES IN FRANCE
Fernand ALBYCentre National d’Etudes Spatiales
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BACKGROUND
UN COPUOS STSC
Mitigation GuidelinesIADC
Mitigation GuidelinesEuropean
Code of Conduct
principles
technical guidelines
applicable rules
Applicable to new projectsRecommended for objects already in orbit
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IMPLICATIONS
�Activities of the projects to demonstrate compliance
�Activities to support the future projects:
�Knowledge of the environment: optical observation from ground
�Research and Technology: search for innovative solutionsinflatable devices, behavior of tanks under debris impact
�Operational activities for on-orbit satellites: collision risk management and atmospheric reentry
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OPTICAL OBSERVATIONS OF DEBRIS IN GEO
�System developed several years ago (Tarot)
�On-going improvements of the system:� Image processing�Accuracy of the datation process
�Operational utilization:�Participation to the IADC campaigns�Monitoring of close approaches in GEO
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Inmarsat 3F5
� Sequence � Epoch : 2006-12-09 18:10� Pointing : 25 degrees GEO
OPTICAL OBSERVATIONS OF DEBRIS IN GEO
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Inmarsat 3F5 : sequence 1
Inmarsat 3F5
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Inmarsat 3F5 : sequence 1
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Inmarsat 3F5 : sequence 1
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Inmarsat 3F1
� Sequence� Epoch : 2006-12-09 20:15� Pointing : 64 degrees GEO
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Inmarsat 3F1
Intelsat 601
Intelsat 906
Inmarsat 3F1
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Inmarsat 3F1
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Inmarsat 3F1
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Inmarsat 3F2
� Sequence� Epoch : 2006-12-10 00:20� Pointing : -15.5 degrees GEO
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Inmarsat 3F2
Inmarsat 3F2
Cosmos 2319
Telstar 12
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Inmarsat 3F2
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Inmarsat 3F2
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Inmarsat 4F1
� Sequence� Epoch : 2006-12-09 19:15� Pointing : Two line elements (inclination greater than Tarot field of
view)
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Inmarsat 4F1
Inmarsat 4F1
Gorizont 27
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Inmarsat 4F1
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Inmarsat 4F1
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Satellite Microscope:Mass 210 kgOrbit altitude around 730 kmNo propulsion system (mission constraint)Orbital lifetime close to 60 years
RESEARCH AND TECHNOLOGYsearch for innovative solutions
Increase of the cross sectionwith a deployable system
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RESEARCH AND TECHNOLOGYsearch for innovative solutions
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RESEARCH AND TECHNOLOGYsearch for innovative solutions
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Impacts sur sandwich NIDA
Aluminum honeycomb(rear)
Impact P254 projectile Ø 7 mm, v = 5.6 km/s)
RESEARCH AND TECHNOLOGYhypervelocity impacts
Test bed
43rd UN-COPUOS STSC February 2007 25Impact 4833 (Ø 6 mm, v = 6.4 km/s)
RESEARCH AND TECHNOLOGYhypervelocity impacts
Tank after impact
X-ray photo of the impact
Test facility
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OPERATIONAL ACTIVITIES
�Collision monitoringClose encounter between Demeter and the 4 Essaim satellites
Conjunctions occur every 6 months
In June 2006 several close approaches atapogees between DEMETER and W23
On June 25 difference in altitude below 150 m
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CLOSE APPROACH DEMETER-ESSAIM
ESSW23
DEMETER
ESSE12
ESSE24
ESSW11
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Method :1. Identification and monitoring of the close approaches :
� Numerical computation of minimum distance in the local orbital frames� Graphical dynamic display 2D and 3D at the risky apogees
2. Identification of the orbit determination accuracy : =>statistical determination of a « security volume » around each spacecraft
3. Definition and approval by the project : � margins
4. Determination of the avoidance strategy (mission constraints) : � Latest date for the decision af an avoidance manoeuvre� Determination and validation of the avoidance manoeuvre
� Avoidance manœuvre performed by Demeter on June 21 at 11h59mn(�V=53 mm/s, decrease of apogee altitude 200m)
CLOSE APPROACH DEMETER-ESSAIM
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� Incorrect injection on orbit of the Arabsat 4A in March 2006� The final GEO orbit cannot be reached, the mission is lost� The satellite will remain a very long time on orbit, crossing all satellites between
480 and 14700 km altitude� Decision to perform a controlled reentry to fulfill the space debris and safety
requirements� On-ground risk analysis, nominal and degraded cases� Long duration boost: 4000 s� Successful deorbiting operations on March 23, 2006 (EADS-Astrium with CNES
support)
OPERATIONAL ACTIVITIESARABSAT 4A DE-ORBITING
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ARABSAT 4ATâche d'impact ARABSAT DT=4000s avec explosion
-50,0
-48,0
-46,0
-44,0
-42,0
-40,0
-38,0
-36,0
-34,0
-32,0
-30,0204 206 208 210 212 214 216 218 220 222
longitude
latit
ude
Monte Carlo 10000 cas
boite 10-5 DOORS
OPERATIONAL ACTIVITIESARABSAT 4A DE-ORBITING
Last ground track On-ground footprint
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SUMMARY
�Experience gained through application of the Code of Conduct to CNES projects
�Difficulties: Conflict between several constraints:• Mission objectives, • debris guidelines, • technical capacities• cost
�Need for:� better knowledge of the environment: optical observations� Search for new technical solutions� Support to operations: collisions monitoring and reentry