Simulation of Hydrodynamic Ram ofAircraft Fuel Tank by Ballistic Penetrationand Detonation
Jong H. Kim, Senior Researcher, Agency for Defense Development (ADD)
Seung M. Jun, Principal Researcher/Team Lead, ADD
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ADD Overview - Organization
Board of Trustees
President
Executive Vice President
Auditor
Staff Directorate
Dual-use Technology CenterDefense S&T Academy
E-Information CenterJoint M&S Center
PEOs/PMOs
1st R&DInstitute
C4I
2nd R&DInstitute
ISR
3rd R&DInstitute
Neo Tech.& Energy
4th R&DInstitute
GroundSystems
5th R&DInstitute
NavalSystems
6th R&DInstitute
AircraftSystems
7th R&DInstitute
Test &Evaluation
DefenseSystemsCenter
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Contents
(*) Intermediate Complexity Wing
2. Intro. of Hydrodynamic Ram
3. HRam Sim. of Cubic Tank
5. HRam Sim. of Fighter Wing
4. HRam Sim. of ICW
6. Conclusion
1. Background
*
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1. Background - Survivability
Capability of an aircraft to avoid or withstand a man-made hostile
environment.
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”
Definition of Airframe Survivability*
Avoid or Withstand
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1. Background – Procedure
Analyze Battle Scenario
Estimate Threats
Show Survivability Req.
Perform Scaled-Down Live Fire Test
Test Criteria & Procedure
Develop Survivable Airframe
Survivability & RepairabilityConsideration
Conceptual Design
Simulate Battle Damage
EfficientDevelopment
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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)
A-10 Wing Hit by MANPADSin Desert Storm (SURVIAC)
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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
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2. Intro. of HRam – Basic Physics*
API** Case
HEI** Case
Shock Phase
Drag Phase
Cavity Phase
(*) Robert E. Ball
(**) HEI : High Energy Incendiary
API : Armor Piercing Incendiary
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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
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3. HRam Sim. of Cube – Skill
SolverSolution Method Nonlinear Explicit
SolutionTechnique
Multiple MaterialEulerian Solver
InitialCondi-
tion
Failure Criteria 70% Plastic Strain
Boundary Tank Bottom Fixed
Euler Multiple (Adaptive)Region Defined
Coup-ling
Projectile-Fluid General
Tank-Fluid General
Projectile-TankAdaptive Master-
SlaveContact
GeneralCoupling
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3. HRam Sim. of Cube – Procedure
Geometry
Modeling
Structure
FE Modeling
Prop., Failure
Criteria Input
Contact btw.
API-Tank
MSC. Patran
Fluid FE
Modeling, I.C.
Coupling btw.API-Fluid
-Tank
Result Display
& Interpretation
MSC. PatranCEI. Ensight
MSC. Dytran
MSC. Dytran(Manual Input Included)
Executive
Control & Run
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3. HRam Sim. of Cube – Result (1)
0
5000
10000
15000
20000
25000
30000
35000
40000
45000
0 0.0004 0.0008 0.0012 0.0016 0.002 0.0024time
ps i
edge
corner
edge
corner
42 ksi
Tank Stress and Displacement
Time-Stress at Tank EntryPetaling
t=1.8 msec
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3. HRam Sim. of Cube – Result (2)
Animation Demo
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3. HRam Sim. of Cube – Result (3)
with Fluid without Fluid
½ t
Fluid Factor
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3. HRam Sim. of Cube – Detonation
Fluid Pressure
Tank Stress & Disp.
t=0.14 msec
t=0.85 msec
Animation Demo
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4. HRam Sim. of ICW – Detonation
AL2024-T3
JP-4 inside Wing Box
Simulate ICW tank rupture and fluid bursting by internal detonation under 6g
pull-up maneuver.
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4. HRam Sim. of ICW – Procedure
ICWGeometrical
Modeling
ICW
FE MeshProp. & Failure
Criteria Input
Fuel & HEI
Mesh, I.C.
MSC. Patran
Coupling btw.Tank-Fuel-Air-HEI
Result Display
& Interpretation
MSC. PatranCEI. Ensight
MSC. Dytran
ICW
AeroMesh
ICWAeroelasticity
Analysis
MSC. FlightLoads
MSC. Dytran
TransientLoad Input
Multi-Coupling Surfaces,Multi-EulerMaterials
Executive
Control & Run
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4. HRam Sim. of ICW – Skill & Result (1)
Multi-PorositiesAlgorithm
Flight Load Effect
Detonation Site
Tank Stress & Disp.
Fuel-Flowing(Drain)Hole Modeling
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4. HRam Sim. of ICW – Result (2)
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4. HRam Sim. of ICW – Result (2)
Animation Demo
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4. HRam Sim. of ICW – Result (3)
M&S ResearchLab. in ADD
3-D Simulation Available with V/R System
V/R Demo
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5. HRam Sim. of Fighter Wing – Penetration
Wing Layout
FE ModelDamage
Area
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5. HRam Sim. of Fighter Wing – Result
20mm Vulcan(0.1kg,
1.03km/s)JP-8
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5. HRam Sim. of Fighter Wing – Result
Animation Demo
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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.
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Success Story listed in http://www.mscsoftware.com
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Contact Details :
For further information please contact
Jong H. KimAgency for Defense Development
Yuseong P.O.Box 35-7,Daejeon,305-600,South Korea