orbital debris: effect on spacecraft pressurized structures
TRANSCRIPT
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Orbital Debris: Effect on Spacecraft
Pressurized Structures
Igor Telichev
UNIVERSITY OF MANITOBA
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Presentation outline
Introduction
Part I: HVI on unshielded PV
Part II: HVI on shielded PV
Current/Future research plans
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o University of Manitoba • Bristol Aerospace
(Magellan), Winnipeg • Boeing, Winnipeg • Standard Aero,
Winnipeg
Canadian Space Agency
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Space Debris Population
• 17,300 objects size > 10 cm – detectable
• 300,000 objects, size 1‐10 cm – non‐detectable
• Millions objects, size < 1 cm – non‐detectable
Space debris distribution in Low Earth Orbit © NASA
(by Secure World Foundation)
Av. V=11 km/s
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Debris Source
• Rocket bodies • mission related
debris • fragmentation debris • dysfunctional
spacecraft
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Debris Source
• Trackable • Non-trackable
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• Orbital debris impacts are random events, and for the untrackable objects it is not possible to precisely determine exactly when or where an impact will occur on a spacecraft.
• The untrackable orbital debris has become a major design consideration in the development of spacecraft and vulnerability/survivability analysis.
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• Spacecraft pressurized structures are identified as the most critical components exposed directly to the orbital debris environment
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Types of Pressure Vessels
• Spacecraft pressurized modules (low pressure)
• Onboard system
pressure vessels (high pressure)
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Types of Pressure Vessels
• Spacecraft pressurized modules (low pressure)
• Onboard system
pressure vessels (high pressure)
Low internal pressure (0.1 MPa) and a relatively large size (~4 x 7 m)
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Types of Pressure Vessels
• Spacecraft pressurized modules (low pressure)
• Onboard system pressure vessels (high pressure)
Smaller size (ID<1.0 m) and significantly higher internal pressure (up to 40 MPa)
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Purpose of the study
The main purpose of the study is to define the border between simple perforation and catastrophic fracture of pressure vessels subjected to high-velocity impact
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300
150 Dhole
Dcrack
Dhole
• Impact velocity: V=0.5…2.0 km/s • Projectiles: Al, steel spheres; d=4.5…17.5 mm • Target: Al 2024-0, AlMg6, steel; ts=0.5…5.0 mm
Impact and Tensile tests Parameters of damaged
zone Impact test setup
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Residual Strength of Impacted Samples
Dcrack/d
Dhole/d
ts=3.0 mm
ts=5.0 mm
0.5 1.0 1.5 2.0 0 0.8
1.0
1.4
1.2
1.6
2.0
Impact velocity [km/s]
Dcrack/d , Dhole/d
20%
Impact velocity, [km/s] 0.5 1.0 1.5 2.0
0.45 0
0.55
0.65
0.75
0.50
0.60
0.70
0.80 Sc/Rm
ts=3.0 mm
ts=4.0 mm
ts=5.0 mm
Target: Al 2024-0 Projectile: steel, d=10.3 mm
Parameters of damaged zone
Dhole
Dcrack
Dhole
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Models of Impact Hole
L
H
Dhole
Dcrack
H
Dhole
Dcrack
H
H
L
Model of front impact hole
L
H
H
Dcrack
H
H
L Dcrack
Model of rear impact (petal) hole
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y y1
y2
y3 y4
x1 x2
x3 x4
L0 L1
L2 L3
L4
1 2 3
4
1
O O1 O2 O3 O4 y1 y2 y
y4
x1, x2 x3, x4
y3 2l4 2l3 2l0 2l1 2l2
5 4 3 2 1
KH KH 0 0
Model of Crack Initiation and Propagation
The crack will grow if the crack tip opening displacement (CTOD) exceeds its critical value (CTOD-criterion)
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y y1
y2
y3 y4
x1 x2
x3 x4
L0 L1
L2 L3
L4
1 2 3
4
1
O O1 O2 O3 O4 y1 y2 y
y4
x1, x2 x3, x4
y3 2l4 2l3 2l0 2l1 2l2
5 4 3 2 1
KH KH 0 0
Model of Crack Initiation and Propagation
0
0.1
0.2
0.3
0.4
0.5
0.6
0 5 10 15
Time [s]
CTO
D, C
OD
[mm
]
COD [mm]
CTOD [ mm]
Evolution of CTOD (crack tip opening displacement )
CTOD
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y y1
y2
y3 y4
x1 x2
x3 x4
L0 L1
L2 L3
L4
1 2 3
4
1
O O1 O2 O3 O4 y1 y2 y
y4
x1, x2 x3, x4
y3 2l4 2l3 2l0 2l1 2l2
5 4 3 2 1
KH KH 0 0
Model of Crack Initiation and Propagation
0.95
1
1.05
1.1
1.15
1.2
0 1 2 3 4 5
L rad /R hole
Hm
ax(h
ole+
crac
ks) /
Hmax
(cra
ck) Drilled hole
Impact hole
Crack
Lcrack=6.1 mmDdr.hole=6.1 mm2(Rhole+Lrad)=6.1 mm
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• Survivability analysis (burst/no burst) • Residual strength analysis (critical
pressure) • Simulation of crack propagation
Code for impact-damaged Pressure Vessels
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f.s.
r.s.
Failure analysis of pressure vessels onboard International Space Station-module Columbus
Pressure vessels failure © ESA
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Pressure Vessels Failures
a) Rear side rupture
b) Front side fracture
a) b)
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Fracture of the damaged pressure vessels under quasi-static inflation
• Test: inflation until burst occurred
• Goal: burst pressure
Test sample (AlMg3)
150
350
1
Impact hole
Rubber-sheet
Calculation/test variation < 5%
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Computed values of critical hoop stress (fracture from the front side)
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II
Basic stages of pressure vessel fracture
Reflected shock wave
Total stress: h+shock
I
Debris cloud
Shock wave
Critical stress: c(p0, Ekin)
I. Ye. Telitchev, D. Eskin, “Engineering model for simulation of debris cloud propagation inside gas-filled pressure vessels”, International Journal of Impact Engineering, Elsevier Science, Vol. 29, pp. 703-712, 2003.
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Debris Cloud
Impact of al. sphere on a titanium shield at 5.7 km/s (Fhg-EMI)
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Model of Debris Cloud
Vf
Vc Vr
Vc
Vr
Vr
Vr
Vc
III
II
I
Vc
Vc
Central element
I. Ye. Telitchev, D. Eskin, “Engineering model for simulation of debris cloud propagation inside gas-filled pressure vessels”, International Journal of Impact Engineering, Elsevier Science, Vol. 29, pp. 703-712, 2003.
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Debris Cloud/Gas Interaction
• Two-phase flow model
• Dual role of the density of gas inside the vessel:
a) protection of pressure vessel back wall due to fragments deceleration;
b) generation of the strong shock wave which can cause failure of structure.
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Model of Debris Cloud –Gas Interaction
0.0E+00
5.0E+06
1.0E+07
1.5E+07
2.0E+07
2.5E+07
3.0E+07
3.5E+07
0 20 40 60 80 100 120 140
Distance from front side, mm
Pres
sure
Am
plitu
de, P
a
0.5 mcs
2.5 mcs
5 mcs 10 mcs 15 mcs20 mcs
25 mcs
30 mcs
Front Wall Rear Wall
a)
0
100
200
300
400
500
600
0 1 2 3 4 5 6
Particle diameter, (mm)
P1 ,
(b
ar)
P0=5 barP0=10 barP0=15 barP0=20 bar
b)
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Borders between smple perforation and catastrophic facture
0
40
80
120
160
200
240
280
0 1 2 3 4
Ekin [kJ]
Hoo
p st
ress
[MPa
]
Bursting
No bursting
h,max (K cstat )
f.s.
f.s
f.s
f.s.
r.s.
r.s
f.s. - front sider.s. - rear side
h,max (K cdyn )
border 1
border 2
border 3
I. Ye. Telitchev, F. Schaefer, E. Schneider, and M. Lambert, “Analysis of the fracture of gas-filled pressure vessels under hypervelocity impact”, International Journal of Impact Engineering, Elsevier Science, Vol. 23, pp. 905-919, 1999.
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Effect of Shield on Damage Pattern
Pressure vessels failure © ESA
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Whipple Shield Concept
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Debris Cloud
Impact of al. sphere on a titanium shield at 5.7 km/s (Fhg-EMI)
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Ballistic Limit Curves
© NASA
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Effect of Shield on Damage Pattern
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Effect of Shield on Damage Pattern
traces of shield fragments
a) Oblique impact
Impact angle traces of projectile fragments
b) Normal impact
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Classification of post-impact scenarios
Case 1: Shallow craters on the surface of structure. No perforation of primary wall. No unstable crack propagation. The spacecraft is capable to continue its mission.
Case 2: Surface of primary wall is densely cratered and has few small perforations. No unstable crack propagation. Possible pressure decay. Under normal conditions the spacecraft is capable to continue its mission.
Case 3: Perforation, bulging and petalling at the pressurized wall. Possible unstable crack propagation. Possible termination of the mission.
Case 4: Large impact hole with rough rim surrounded by a densely cratered ring with small perforations in the pressurized wall. Possible unstable crack propagation. Possible termination of the mission .
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Model of shielded+damaged structure
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Exp. #20 Exp. #21 Hoop stress, MPa 80.3 83.3 Secondary impact hole, mm 36 33 Impact test result No crack propagation No crack propagation Numerical test result No crack propagation No crack propagation
Model of shielded+damaged structure
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y y1
y2
y3 y4
x1 x2
x3 x4
L0 L1
L2 L3
L4
1 2 3
4
1
O O1 O2 O3 O4 y1 y2 y
y4
x1, x2 x3, x4
y3 2l4 2l3 2l0 2l1 2l2
5 4 3 2 1
KH KH 0 0
Model of Crack Initiation and Propagation
• deviation of crack from the original path due to the structural irregularities
• Effect of stiffeners on crack propagation/arrest
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Survivability Driven Design Approach
• Traditional safety requirements only look at the “probability of no penetration”
• Survivability driven design is based on the practice of assuming the hazard has occurred
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Space Debris Study at the University of Manitoba
• The long‐term objective is to develop a strong scientific basis for design of spacecraft working in orbital debris environment
• The short‐term objective is to advance the understanding and modeling techniques of spacecraft pressurized structures response to hypervelocity impact
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Acknowledgement
• Dr. M. Lambert, ESA/ESTEC • Dr. E. Schneider, Ernst-Mach-Institute • Dr. Frank Schaefer, Ernst-Mach-Institute • Dr. Robert Sierakowski, AFRL/MN • Dr. John Rogacki, Univ. of Florida-REEF