4. HRam Sim. of ICW
Battle Damage Analysis of Aircraft Wing Fuel Tanks using CEI.EnSight
2008. 11 Jong H. Kim Aeronautical Technology Directorate, ADD Agency for Defense Development 1 / 33
Contents 1. Background 2. Intro. of Hydrodynamic Ram 3. HRam Sim. of Cubic Tank 4. HRam Sim. of ICW
*
5. HRam Sim. of Fighter Wing 6. Conclusion (*) Intermediate Complexity Wing Agency for Defense Development 2 / 33
1. Background -
Survivability
Definition of Airframe Survivability* Capability of an aircraft to avoid or withstand a man-made hostile environment.
Avoid or Withstand Susceptibility reduction – stealth, jamming, threat warning Vulnerability reduction – redundancy, damage suppression, protection
Enhance Aircraft Affordability
(*) Robert E. Ball, “The Fundamentals of Aircraft Combat Survivability Analysis and Design” Agency for Defense Development 3 / 33
1. Background –
Procedure
Analyze Battle Scenario Estimate Threats Efficient Development
Show Survivability Req. Conceptual Design Simulate Battle Damage Test Criteria & Procedure Perform Scale-Downed Live Fire Test Survivability & Repairability Consideration
Develop Survivable Airframe Agency for Defense Development 4 / 33
1. Background –
Procedure
Simulation & Validating Test
Full Scale Live Fire Test
*
$ 250M
*
$ 38M or Less (*) F-22 Case Agency for Defense Development 5 / 33
2. Intro. of HRam -
Definition
• Damage process by the impact and penetration/detonation of a ballistic projectile(shell) through the fluid(fuel) of a container(fuel tank). • Internal fluid pressure by penetration or detonation causes from perforation/petaling to complete destruction of a structure.
Perforation/Petaling (BlazeTech)
Water Bottle Test (Rhamm Tech.) Agency for Defense Development 6 / 33
2. Intro. of HRam -
Purpose
• Plenty of aircraft losses are tied to fuel system vulnerability. (75% of aircraft losses in Desert Storm were related to fuel/fire) • HRam effect of fuel tanks is one of major threats in battle environment. • Increasing terror from explosives is threatening commercial aircraft. • Fuel tank of main wing is vulnerable as it has large exposed area. • Analysis of complicated HRam physics enables the application to many other battle damage
Apply to the Survivability Design of Aircraft
Agency for Defense Development 7 / 33
2. Intro. of HRam –
Reality A-10 Wing Hit by MANPADS in Desert Storm
F-16 Detonated by MANPADS in Live Fire Test, China Lake Agency for Defense Development 8 / 33
2. Intro. of HRam –
MANPADS?
MAN-Portable Air Defense Systems - Hand-held Infrared(IR) Surface-to-Air Missile(SAM) - Very large HEI projectile w/ guidance sensor - Blast close to outside surface and wide fragments Agency for Defense Development 9 / 33
2. Intro. of HRam –
Basic Physics*
Shock Phase HEI** Case Drag Phase
Cavity Phase
(*) Robert E. Ball
API** Case
(**) HEI : High Energy Incendiary API : Armor Piercing Incendiary Agency for Defense Development 10 / 33
2. Intro. of HRam –
HRam in Fuel Tank
Projectile Splashes Fuel up into Flammable Region to Ignite
Fuel Leakage Ignited by Incendiary
Spilt Fuel Finds Secondary Fire Source
FT Catches Fire
Damage Propagates Agency for Defense Development 11 / 33
3. HRam Sim. of Cube –
Penetration
Simulate the damage and response of tank and fluid when a projectile impacts and penetrates a cubic metal tank.
Half Model
Agency for Defense Development 12 / 33
3. HRam Sim. of Cube –
Solver
Initial Condition
Coupling
Skill
Solution Method
Nonlinear Explicit
Solution Technique
Multiple Material Eulerian Solver
Failure Criteria
70% Plastic Strain
Boundary
Tank Bottom Fixed
Euler
Multiple (Adaptive) Region Defined
Projectile-Fluid
General
Tank-Fluid
General
Projectile-Tank
Adaptive MasterSlave Contact
General Coupling
Agency for Defense Development 13 / 33
3. HRam Sim. of Cube –
Procedure
MSC. Patran
MSC. Dytran
Geometry
Structure
Prop., Failure
Contact btw.
Modeling
FE Modeling
Criteria Input
API-Tank
Fluid FE Modeling, I.C.
Coupling btw. API-Fluid -Tank
MSC. Dytran (Manual Input Included)
Executive
Result Display
Control & Run
& Interpretation
MSC. Patran CEI. Ensight
Agency for Defense Development 14 / 33
3. HRam Sim. of Cube –
Result (1)
42 ksi t=1.8 msec 45000 ps i 40000
corner
35000 30000
edge
edge
25000 20000 15000 10000
corner
5000 0 0
Petaling
0.0004
0.0008
0.0012
0.0016
0.002 time 0.0024
Time-Stress at Tank Entry
Tank Stress and Displacement
Agency for Defense Development 15 / 33
3. HRam Sim. of Cube –
Result (2) : Verification AFRL
Present 0.5
0.4 in
Entry Exit
0.4
displacement(in)
0.3
Entry/Exit Deform.
0.2 0.1 0 0
0.0005
time(s)
1.5 0.0015ms
0.001
-0.1 -0.2 -0.3 -0.4
-0.35 in
50000
50 ksi
stress(psi)
40000
30000
20000
10000
Exit 0 0
0.0005
0.001 time(s)
0.0015
0.002
Stress
Two Results Agree w/ Each Other Agency for Defense Development 16 / 33
3. HRam Sim. of Cube –
Result (3)
Animation Demo
Agency for Defense Development 17 / 33
3. HRam Sim. of Cube –
Result (4)
Fluid Factor
½t with Fluid
without Fluid
Agency for Defense Development 18 / 33
3. HRam Sim. of Cube –
Detonation
t=0.85 msec
t=0.14 msec
Tank Stress & Disp.
Fluid Pressure
Animation Demo Agency for Defense Development 19 / 33
4. HRam Sim. of ICW –
Detonation
Simulate ICW tank rupture and fluid bursting by internal detonation under 6g pull-up maneuver.
AL2024-T3
oad L t h Flig ) 8 . (M0 p U u ll6g P
JP-4 inside Wing Box
Agency for Defense Development 20 / 33
4. HRam Sim. of ICW –
Procedure
MSC. FlightLoads
AeroMesh
ICW Aeroelasticity Analysis
ICW
Prop. & Failure
Fuel & HEI
FE Mesh
Criteria Input
Mesh, I.C.
ICW
ICW Geometrical Modeling
MSC. Patran Multi-Coupling Surfaces, Multi-Euler Materials
Transient Load Input
MSC. Dytran
Coupling btw. Tank-Fuel -Air-HEI
Executive
Result Display
Control & Run
& Interpretation
MSC. Dytran
MSC. Patran CEI. Ensight Agency for Defense Development 21 / 33
4. HRam Sim. of ICW –
Skill & Result (1)
Fuel-Flowing(Drain) Hole Modeling
Detonation Site Flight Load Effect
Multi-Porosities Algorithm
Tank Stress & Disp.
Agency for Defense Development 22 / 33
4. HRam Sim. of ICW –
Result (2)
Animation Demo
Agency for Defense Development 23 / 33
4. HRam Sim. of ICW –
Result (3)
V/R Demo
M&S Research Lab. in ADD
3-D Simulation Available with V/R System Agency for Defense Development 24 / 33
5. HRam Sim. of Fighter Wing –
Penetration
Wing Layout
05) Flight Load 9g Wind Up Turn(M1.
FE Model
Damage Area
Agency for Defense Development 25 / 33
5. HRam Sim. of Fighter Wing –
Result
20mm Vulcan (0.1kg, 1.03km/s) JP-8
Agency for Defense Development 26 / 33
5. HRam Sim. of Fighter Wing –
Result
Animation Demo
Agency for Defense Development 27 / 33
6. Conclusion –
Achievement
• Model and simulate hydrodynamic ram, one of major threats to aircraft. • Employ the latest FSI analysis skills to improve the reality of simulation of battle damage of wing fuel tanks. • Show feasibility of applying the simulation to the airframe design with enhanced survivability in aircraft development.
Agency for Defense Development 28 / 33
2008. 11 Jong H. Kim Aeronautical Technology Directorate, ADD Agency for Defense Development 1 / 33
Contents 1. Background 2. Intro. of Hydrodynamic Ram 3. HRam Sim. of Cubic Tank 4. HRam Sim. of ICW
*
5. HRam Sim. of Fighter Wing 6. Conclusion (*) Intermediate Complexity Wing Agency for Defense Development 2 / 33
1. Background -
Survivability
Definition of Airframe Survivability* Capability of an aircraft to avoid or withstand a man-made hostile environment.
Avoid or Withstand Susceptibility reduction – stealth, jamming, threat warning Vulnerability reduction – redundancy, damage suppression, protection
Enhance Aircraft Affordability
(*) Robert E. Ball, “The Fundamentals of Aircraft Combat Survivability Analysis and Design” Agency for Defense Development 3 / 33
1. Background –
Procedure
Analyze Battle Scenario Estimate Threats Efficient Development
Show Survivability Req. Conceptual Design Simulate Battle Damage Test Criteria & Procedure Perform Scale-Downed Live Fire Test Survivability & Repairability Consideration
Develop Survivable Airframe Agency for Defense Development 4 / 33
1. Background –
Procedure
Simulation & Validating Test
Full Scale Live Fire Test
*
$ 250M
*
$ 38M or Less (*) F-22 Case Agency for Defense Development 5 / 33
2. Intro. of HRam -
Definition
• Damage process by the impact and penetration/detonation of a ballistic projectile(shell) through the fluid(fuel) of a container(fuel tank). • Internal fluid pressure by penetration or detonation causes from perforation/petaling to complete destruction of a structure.
Perforation/Petaling (BlazeTech)
Water Bottle Test (Rhamm Tech.) Agency for Defense Development 6 / 33
2. Intro. of HRam -
Purpose
• Plenty of aircraft losses are tied to fuel system vulnerability. (75% of aircraft losses in Desert Storm were related to fuel/fire) • HRam effect of fuel tanks is one of major threats in battle environment. • Increasing terror from explosives is threatening commercial aircraft. • Fuel tank of main wing is vulnerable as it has large exposed area. • Analysis of complicated HRam physics enables the application to many other battle damage
Apply to the Survivability Design of Aircraft
Agency for Defense Development 7 / 33
2. Intro. of HRam –
Reality A-10 Wing Hit by MANPADS in Desert Storm
F-16 Detonated by MANPADS in Live Fire Test, China Lake Agency for Defense Development 8 / 33
2. Intro. of HRam –
MANPADS?
MAN-Portable Air Defense Systems - Hand-held Infrared(IR) Surface-to-Air Missile(SAM) - Very large HEI projectile w/ guidance sensor - Blast close to outside surface and wide fragments Agency for Defense Development 9 / 33
2. Intro. of HRam –
Basic Physics*
Shock Phase HEI** Case Drag Phase
Cavity Phase
(*) Robert E. Ball
API** Case
(**) HEI : High Energy Incendiary API : Armor Piercing Incendiary Agency for Defense Development 10 / 33
2. Intro. of HRam –
HRam in Fuel Tank
Projectile Splashes Fuel up into Flammable Region to Ignite
Fuel Leakage Ignited by Incendiary
Spilt Fuel Finds Secondary Fire Source
FT Catches Fire
Damage Propagates Agency for Defense Development 11 / 33
3. HRam Sim. of Cube –
Penetration
Simulate the damage and response of tank and fluid when a projectile impacts and penetrates a cubic metal tank.
Half Model
Agency for Defense Development 12 / 33
3. HRam Sim. of Cube –
Solver
Initial Condition
Coupling
Skill
Solution Method
Nonlinear Explicit
Solution Technique
Multiple Material Eulerian Solver
Failure Criteria
70% Plastic Strain
Boundary
Tank Bottom Fixed
Euler
Multiple (Adaptive) Region Defined
Projectile-Fluid
General
Tank-Fluid
General
Projectile-Tank
Adaptive MasterSlave Contact
General Coupling
Agency for Defense Development 13 / 33
3. HRam Sim. of Cube –
Procedure
MSC. Patran
MSC. Dytran
Geometry
Structure
Prop., Failure
Contact btw.
Modeling
FE Modeling
Criteria Input
API-Tank
Fluid FE Modeling, I.C.
Coupling btw. API-Fluid -Tank
MSC. Dytran (Manual Input Included)
Executive
Result Display
Control & Run
& Interpretation
MSC. Patran CEI. Ensight
Agency for Defense Development 14 / 33
3. HRam Sim. of Cube –
Result (1)
42 ksi t=1.8 msec 45000 ps i 40000
corner
35000 30000
edge
edge
25000 20000 15000 10000
corner
5000 0 0
Petaling
0.0004
0.0008
0.0012
0.0016
0.002 time 0.0024
Time-Stress at Tank Entry
Tank Stress and Displacement
Agency for Defense Development 15 / 33
3. HRam Sim. of Cube –
Result (2) : Verification AFRL
Present 0.5
0.4 in
Entry Exit
0.4
displacement(in)
0.3
Entry/Exit Deform.
0.2 0.1 0 0
0.0005
time(s)
1.5 0.0015ms
0.001
-0.1 -0.2 -0.3 -0.4
-0.35 in
50000
50 ksi
stress(psi)
40000
30000
20000
10000
Exit 0 0
0.0005
0.001 time(s)
0.0015
0.002
Stress
Two Results Agree w/ Each Other Agency for Defense Development 16 / 33
3. HRam Sim. of Cube –
Result (3)
Animation Demo
Agency for Defense Development 17 / 33
3. HRam Sim. of Cube –
Result (4)
Fluid Factor
½t with Fluid
without Fluid
Agency for Defense Development 18 / 33
3. HRam Sim. of Cube –
Detonation
t=0.85 msec
t=0.14 msec
Tank Stress & Disp.
Fluid Pressure
Animation Demo Agency for Defense Development 19 / 33
4. HRam Sim. of ICW –
Detonation
Simulate ICW tank rupture and fluid bursting by internal detonation under 6g pull-up maneuver.
AL2024-T3
oad L t h Flig ) 8 . (M0 p U u ll6g P
JP-4 inside Wing Box
Agency for Defense Development 20 / 33
4. HRam Sim. of ICW –
Procedure
MSC. FlightLoads
AeroMesh
ICW Aeroelasticity Analysis
ICW
Prop. & Failure
Fuel & HEI
FE Mesh
Criteria Input
Mesh, I.C.
ICW
ICW Geometrical Modeling
MSC. Patran Multi-Coupling Surfaces, Multi-Euler Materials
Transient Load Input
MSC. Dytran
Coupling btw. Tank-Fuel -Air-HEI
Executive
Result Display
Control & Run
& Interpretation
MSC. Dytran
MSC. Patran CEI. Ensight Agency for Defense Development 21 / 33
4. HRam Sim. of ICW –
Skill & Result (1)
Fuel-Flowing(Drain) Hole Modeling
Detonation Site Flight Load Effect
Multi-Porosities Algorithm
Tank Stress & Disp.
Agency for Defense Development 22 / 33
4. HRam Sim. of ICW –
Result (2)
Animation Demo
Agency for Defense Development 23 / 33
4. HRam Sim. of ICW –
Result (3)
V/R Demo
M&S Research Lab. in ADD
3-D Simulation Available with V/R System Agency for Defense Development 24 / 33
5. HRam Sim. of Fighter Wing –
Penetration
Wing Layout
05) Flight Load 9g Wind Up Turn(M1.
FE Model
Damage Area
Agency for Defense Development 25 / 33
5. HRam Sim. of Fighter Wing –
Result
20mm Vulcan (0.1kg, 1.03km/s) JP-8
Agency for Defense Development 26 / 33
5. HRam Sim. of Fighter Wing –
Result
Animation Demo
Agency for Defense Development 27 / 33
6. Conclusion –
Achievement
• Model and simulate hydrodynamic ram, one of major threats to aircraft. • Employ the latest FSI analysis skills to improve the reality of simulation of battle damage of wing fuel tanks. • Show feasibility of applying the simulation to the airframe design with enhanced survivability in aircraft development.
Agency for Defense Development 28 / 33
