Beihang University (BUAA)
On-orbit Satellite Collision Debris Analysis Based on Hypervelocity Impact Simulation
Student ZHANG Xiaotian（张晓天）
Supervisor Prof. HUANG Hai （黄海） A.Prof. JIA Guanghui （贾光辉） Beihang University (BUAA)
Outline
1. Introduction This presentation will show you some preliminary work of using I. Threaten of space hypervelocity impact simulation technique to analyze on-orbit debris satellite breakup problem to obtain the small debris information II. Hypervelocity which is beyond the space surveillance limit. impact simulation
III. Main idea of this 1. Introduction to space debris and HVI simulation research
2. Satellites collision 2. Satellite collision simulation and debris analysis simulation and debris analysis
I. background
II. Simulation model
III. Debris analysis
IV. Conclusion Beihang University (BUAA)
1. Introduction
1. Introduction I. Threaten of space debris I. Threaten of space debris II. Hypervelocity impact simulation II. Hypervelocity impact simulation III. Main idea of this research
III. Main idea of this research
2. Satellites collision simulation and debris analysis
I. background
II. Simulation model
III. Debris analysis
IV. Conclusion Threatening of space debris (1)
1. Introduction • Space debris:
I. Threaten of space Human space activities created lots of disused objects left in the orbit. debris These objects and the fragments created by the secondary impact of them II. Hypervelocity are called space debris. impact simulation • Catastrophic impact events (generated a large amount of space debris): III. Main idea of this research • 1991, Russian satellite COSMOS1934 and COSMOS926 hit each other
2. Satellites collision • 1996, Arianne rocket remains hit the gravity gradient pole of French simulation and debris satellite CERISE analysis • 2009, Russian satellite COSMOS2251 and American IRIDIUM33 I. background collision
II. Simulation model III. Debris analysis
IV. Conclusion Threatening of space debris (2)
1. Introduction • Space shuttles of the USA have replaced the windows over 80 times . I. Threaten of space • Hubble space telescope has encountered over 5000 times impact , 150 debris holes on in the solar array II. Hypervelocity impact simulation • Long Duration Exposure Facility (LDEF)
III. Main idea of this research
2. Satellites collision simulation and debris analysis
I. background
II. Simulation model
III. Debris analysis
IV. Conclusion Different solutions for large/small debris
1. Introduction • Debris larger than 10cm (LEO) can be observed and I. Threaten of space debris tracked ——choosing launch window and initiative II. Hypervelocity evading impact simulation • 1cm debris is enough for perforating the body of III. Main idea of this research satellite——covering important parts of the satellite with 2. Satellites collision shield simulation and debris analysis
I. background
II. Simulation model
III. Debris analysis
IV. Conclusion Beihang University (BUAA)
Hypervelocity impact simulation
1. Introduction • Hyper velocity impact (HVI) simulation: I. Threaten of space debris A numerical simulation technique of impact under hyper velocity II. Hypervelocity (v>5km/s) which can show out the whole deformation and impact simulation fracture process of the impact quantitatively. III. Main idea of this research • This technique is used to evaluate the protection ability of specific
2. Satellites collision shield simulation and debris analysis
I. background
II. Simulation model
III. Debris analysis
IV. Conclusion
Whipple shield New concept shield
1. Introduction Multi-layer Aluminum net I. Threaten of space debris
II. Hypervelocity impact simulation
III. Main idea of this research
2. Satellites collision simulation and debris Aluminum foam analysis
I. background
II. Simulation model
III. Debris analysis
IV. Conclusion Summary
1. Introduction There are many space debris I. Threaten of space debris Debris threaten our satellites II. Hypervelocity impact simulation
III. Main idea of this Large debris Small debris research
2. Satellites collision Observation & revolution Protective structure design simulation and debris prediction analysis
I. background HVI experiment HVI simulation evade II. Simulation model
III. Debris analysis expensive Just use computers
IV. Conclusion
lots of simulations to find the pattern few experiments for calibration Breakup model
1. Introduction • As more than half of the orbit debris are generated by I. Threaten of space debris collision and explosion. II. Hypervelocity impact simulation • NASA presented a standard breakup model for the III. Main idea of this debris analysis generated by on-orbit collision or research
2. Satellites collision explosion. simulation and debris • Since the main data source of creating NASA model is analysis
I. background the space surveillance data, NASA model has much II. Simulation model lower precision for small debris than that for large III. Debris analysis
IV. Conclusion debris. Main idea of this research
1. Introduction
I. Threaten of space debris
II. Hypervelocity impact simulation
III. Main idea of this research
2. Satellites collision simulation and debris analysis I. background √ II. Simulation model
III. Debris analysis Use the observation large debris data to calibrate simulation large debris data, IV. Conclusion then the small debris data is closed to the reality. Beihang University (BUAA)
2. Satellites collision simulation and debris analysis
1. Introduction I. Iridium33 and Cosmos2251 collision background I. Threaten of space debris II. Simulation model II. Hypervelocity impact simulation III. Debris analysis III. Main idea of this I. Qualitative analysis research II. Quantitative analysis 2. Satellites collision I. Fragment amount analysis simulation and debris II. Fragment mass analysis
analysis III. Fragment scattering angle analysis I. background IV. Conclusion II. Simulation model III. Debris analysis IV. Conclusion
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Collision of Iridium33 & Cosmos2251
1. Introduction
I. Threaten of space debris
II. Hypervelocity impact simulation
III. Main idea of this research
2. Satellites collision • In an unprecedented space collision, a simulation and debris commercial communications satellite analysis (IRIDIUM 33) and a defunct Russian I. background satellite (COSMOS 2251) impacted each II. Simulation model other on February 9th, 2009 above III. Debris analysis Northern Siberia, creating a cloud of IV. Conclusion debris.
• Till now, over 1719 large fragments have been observed.
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Satellite property
1. Introduction • Iridium 33 —— LM 700A (Lockheed Martin) I. Threaten of space debris • Overall length: 3.6m weight: 600kg II. Hypervelocity • Cosmos 2251 —— Strela-2M impact simulation • Height: 3m diameter: 2m weight: 900kg III. Main idea of this research • Absolute velocity of the two satellites are both 7.9km/s
2. Satellites collision • Angle of two orbit plane is about 105 degree. simulation and debris analysis
I. background
II. Simulation model
III. Debris analysis
IV. Conclusion Simulation algorithm
1. Introduction • A mixed algorithm of finite element method (FEM) and I. Threaten of space debris smoothed particle hydrodynamics (SPH) method is used to II. Hypervelocity simulate the collision process. Debris analysis method is impact simulation applied based on that. III. Main idea of this research • You can find more details of the simulation and debris 2. Satellites collision analysis method in this paper simulation and debris Xiaotian Zhang, Guanghui Jia, Hai Huang. Fragments Identification and Statistics Method analysis of Hypervelocity Impact SPH Simulation[J]. Chinese journal of Aeronautics. I. background • We cannot actually observe the collision process on orbit. II. Simulation model The way that we know the collision event is deferring from III. Debris analysis
IV. Conclusion the suddenly increase of the debris population.
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Qualitative analysis
1. Introduction Since the impact location is unknown. Firstly we just assume I. Threaten of space that the satellites hit each other’s centroid. debris
II. Hypervelocity impact simulation
III. Main idea of this research
2. Satellites collision simulation and debris analysis
I. background
II. Simulation model
III. Debris analysis IV. Conclusion Large fragment view at 1ms after the impact Most material of Iridium33 is converted into small debris while the large ones are mostly from cosmos2251. Beihang University (BUAA)
Central impact simulation result (2)
1. Introduction
I. Threaten of space debris
II. Hypervelocity impact simulation
III. Main idea of this research
2. Satellites collision small fragment view at 0-1ms after the impact simulation and debris analysis The amount of small debris is much more than large ones. The I. background material flows over a large region, metal behaves like liquid in
II. Simulation model the process.
III. Debris analysis
IV. Conclusion Beihang University (BUAA)
Cases comparison of different impact location
1. Introduction • 5 typical impact locations are compared I. Threaten of space debris • Backward-graph is used to show the spall region of the II. Hypervelocity satellites impact simulation
III. Main idea of this research
2. Satellites collision simulation and debris • Backward-graph: analysis Substitute the node coordinates in the large fragment view I. background of the result with the original coordinates before the impact. II. Simulation model
III. Debris analysis
IV. Conclusion Beihang University (BUAA)
Backward-graph
1. Introduction
I. Threaten of space debris
II. Hypervelocity impact simulation
III. Main idea of this research
2. Satellites collision simulation and debris analysis
I. background
II. Simulation model
III. Debris analysis
IV. Conclusion Beihang University (BUAA)
Backward-graph
1. Introduction
I. Threaten of space debris
II. Hypervelocity impact simulation
III. Main idea of this research
2. Satellites collision simulation and debris analysis
I. background
II. Simulation model
III. Debris analysis
IV. Conclusion Beihang University (BUAA)
Backward-graph
1. Introduction
I. Threaten of space debris
II. Hypervelocity impact simulation
III. Main idea of this research
2. Satellites collision simulation and debris analysis
I. background
II. Simulation model
III. Debris analysis
IV. Conclusion Beihang University (BUAA)
Cases comparison
1. Introduction
I. Threaten of space debris II. Hypervelocity • Comparing the 5 pictures left, impact simulation
III. Main idea of this material in the normal impact research region mostly transforms into 2. Satellites collision small fragments by impact; while simulation and debris analysis large fragments consist of I. background material not in the region. II. Simulation model
III. Debris analysis
IV. Conclusion Beihang University (BUAA)
Quantitative analysis
1. Introduction I. Threaten of space • Normal Impact Mass (NIM) debris II. Hypervelocity impact simulation
III. Main idea of this research
2. Satellites collision simulation and debris I C mn mn analysis
I. background II. Simulation model • Dimensionless Equivalent Normal Impact Mass (DENIM) III. Debris analysis CI IV. Conclusion 2minmmnn , m e mmCI Beihang University (BUAA)
DENIM distribution
1. Introduction
I. Threaten of space debris
II. Hypervelocity impact simulation
III. Main idea of this research
2. Satellites collision simulation and debris analysis I. background • Fixing the position of Iridium33 and change the impact II. Simulation model
III. Debris analysis location of Cosmos2251 we can get the DENIM IV. Conclusion distribution.
• The maximum number is 0.38.
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Fragments statistics
1. Introduction No δz δx Cosmos2251 Iridium33 DENIM DSFM DLFM Fragment I. Threaten of space (cm) (cm) NIM（kg） NIM（kg） amount debris 1 0 0 589 266 0.36 0.88 0.12 1280 II. Hypervelocity 2 0 180 444 117 0.16 0.70 0.30 1288 impact simulation 3 0 -180 261 119 0.16 0.71 0.29 1204 III. Main idea of this 4 -100 80 281 107 0.14 0.64 0.36 759 5 -200 80 238 38 0.05 0.34 0.66 379 research 6 -12 -36 586 283 0.38 0.89 0.11 1329 2. Satellites collision 7 120 -96 170 79 0.10 0.56 0.44 428 simulation and debris 8 84 204 437 76 0.10 0.53 0.47 706 analysis 9 48 132 568 151 0.20 0.75 0.25 1403 10 96 -72 331 153 0.20 0.76 0.24 749 I. background 11 -48 12 389 226 0.30 0.88 0.12 1537 II. Simulation model 12 -60 -84 337 225 0.30 0.81 0.19 1330 III. Debris analysis DENIM Dimensionless Equivalent Normal Impact Mass IV. Conclusion DLFM Dimensionless Large Fragment Mass DSFM Dimensionless Small Fragment Mass Beihang University (BUAA)
DENIM determines DLFM and DSFM
1. Introduction
I. Threaten of space debris
II. Hypervelocity impact simulation
III. Main idea of this research
2. Satellites collision simulation and debris analysis
I. background
II. Simulation model
III. Debris analysis
IV. Conclusion DENIM Dimensionless Equivalent Normal Impact Mass DLFM Dimensionless Large Fragment Mass DSFM Dimensionless Small Fragment Mass Scattering angle Beihang University (BUAA)
Collision orbits
1. Introduction
I. Threaten of space debris
II. Hypervelocity impact simulation
III. Main idea of this research
2. Satellites collision simulation and debris Cosmos2251 analysis
I. background
II. Simulation model Iridium33 III. Debris analysis
IV. Conclusion Beihang University (BUAA)
Large debris (>10cm) orbits
1. Introduction
I. Threaten of space debris
II. Hypervelocity impact simulation
III. Main idea of this research
2. Satellites collision simulation and debris analysis
I. background
II. Simulation model 30 min 10 day
III. Debris analysis IV. Conclusion Dr. Geoffrey Forden http://forden.armscontrolwonk.com/archive/2194/212-and-counting Beihang University (BUAA)
Large debris (>10cm) orbits
1. Introduction
I. Threaten of space debris
II. Hypervelocity Dr. WANG Ting impact simulation III. Main idea of this Preliminary research analysis on the collision event 2. Satellites collision 1 week 3 month between Russian simulation and debris and American analysis satellites[J]. Space Debris I. background Research and II. Simulation model Application. III. Debris analysis 2009,vol 9. IV. Conclusion
1 year 3 year Beihang University (BUAA)
Debris orbits considering both large ones and small ones
Impact location Cosmos debris Iridium debris 1. Introduction
I. Threaten of space debris
II. Hypervelocity Cosmos2251 impact simulation
III. Main idea of this Iridium33 research
2. Satellites collision Debris orbits 1 hour simulation and debris after the collision analysis including debris > 1cm. I. background It does not need 1-3 II. Simulation model years. III. Debris analysis Several hours are IV. Conclusion enough for the debris to spread over all LEOs. Beihang University (BUAA)
Different scattering angle for large and small debris
1. Introduction
I. Threaten of space debris
II. Hypervelocity impact simulation
III. Main idea of this research
2. Satellites collision simulation and debris analysis
I. background
II. Simulation model
III. Debris analysis
IV. Conclusion The projectile hits the bumper at the speed of 6km/s. The scattering angle for small debris is about 70 degree while that for large debris is about 28 degree. Beihang University (BUAA)
Conclusion (1)
1. Introduction
I. Threaten of space • Qualitative analysis debris 1. Most material of Iridium is converted into small debris II. Hypervelocity impact simulation while the large fragments are mostly from Cosmos. III. Main idea of this
research 2. Satellites collision 2. The amount of small debris is much more than large ones. simulation and debris
analysis
I. background 3. The material in the normal impact region mostly II. Simulation model transforms into small fragments while large fragments are III. Debris analysis from the material far from that region. IV. Conclusion Beihang University (BUAA)
Conclusion (2)
1. Introduction
I. Threaten of space • Quantitative analysis debris • Debris amount analysis II. Hypervelocity impact simulation 1. The amount from the simulation is close to the surveillance III. Main idea of this data. research 2. The amount of different impact location is not far from one 2. Satellites collision simulation and debris another. analysis • Debris mass analysis I. background 1. The total mass of either large fragments or small fragments is II. Simulation model determined by DENIM despite impact location. III. Debris analysis
IV. Conclusion Beihang University (BUAA)
Conclusion (3)
1. Introduction
I. Threaten of space • Quantitative analysis debris • Debris scattering angle analysis II. Hypervelocity impact simulation 1. Considering the small debris, scattering angle is much larger III. Main idea of this than that only considering large debris. research 2. Scattering angle is also related to DENIM and mainly 2. Satellites collision simulation and debris determined by DENIM. analysis 3. Only several hours after the impact the debris will spread I. background over all LEOs. II. Simulation model
III. Debris analysis
IV. Conclusion Beihang University (BUAA)
Thank you！