simulation of hydrodynamic ram of aircraft fuel tank by

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

MSC.Software Confidential

ADD

PGM

2009-04-22 2

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


ADD

2009-04-22 3

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

*


ADD

2009-04-22 4

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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Animation Demo


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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


ADD

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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.


ADD

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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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Animation Demo


ADD

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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.


ADD

2009-04-22 26

Success Story listed in http://www.mscsoftware.com


ADD

2009-04-22 27

Contact Details :

For further information please contact

Jong H. KimAgency for Defense Development

Yuseong P.O.Box 35-7,Daejeon,305-600,South Korea

[email protected]

simulation of hydrodynamic ram of aircraft fuel tank by

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