Multidisciplinary Design Technology for Smart Munitions

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MultidisciplinaryDesign TechnologyforSmart
Munitions
Tactical Interceptor Design Symposium January 16,
2004 UAH Bevill Center Huntsville, AL
Peter Plostins U.S.Army Research
Laboratory plostins_at_arl.army.mil voice
410-278-8878 fax [phone]
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Smart MunitionsThe Challenge

• Critical Technologies
• Multi-Disciplinary Design
• Aero, Structures, GNC
• High Performance MS
• Conduct Key Tech Demos
• High-g Electronics
• Embedded Sensor Systems
• High-g Inertial Sensors
• Insertion of MEMS
• Cost COTS
• Integrated Advanced System Simulations
• War Fighter Payoff
• Reduced logistics footprint thru extended
• range one-shot,one-kill performance
• Increased stowed kills per weapon
• Support Full RDTE Cycle

155mm XM982
Technology for FCS LOS/BLOS/NLOS
Platforms
Technology Insertion and Transition
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Structural Modeling of Smart MunitionsTechnical
Approach
Structural Model of Sensor Board
Component Evaluation
Structural Model of the Chip
High resolution structural model of electronic
component with dynamic failure criteria
Develop failure envelope for electronic components
Projectile Sub-Model
Embedded high resolution component model in
coarser gun dynamics model, with correct
interface boundaries, to predict response of
smart munitions to launch
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Interior Ballistics Launch Dynamics Couplingwith
Structural Codes

• TECHNOLOGY
• More realistic IB loading on the projectile
• Asymmetric burning effect
• Propellant interaction on the projectile
• NGEN/ DYNA3D are state of the art codes
• BENEFIT
• Analysis of Complex Configurations

Initial Time Dependent Structural Projectile
Response
FCS NLOS
Simulation of a M829A1 Launch Chamber
Pressure Contours
NGEN Results of Pressurization in Gun
ChamberMapped into the Structural Dynamics Codes
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Smart MunitionsComputational Structural Dynamics
Technology History

• Objective
• Couple advanced CFD with transient FEA techniques

DYNA 3D Simulation of Inbore Launch
SADARM EMA/Structural Modeling
M829A2
M829A1
Structural Analysis of Electronics Module
Assembly (EMA)
SADARM Internal Stack Model Transient Stress Shot
Start to 6 ms
Technology Transition to Excalibur
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Aerodynamics of Advanced Maneuvering Munitions
Planar Fins

• Excellent results have been obtained for the
  canard-controlled missile in supersonic,
  subsonic, and transonic flow
• Mach 0.6, 0.9, 1.5, and 3.0
• Planar lattice fin tail configurations
• Validated with AMRDEC/DREV wind tunnel data.
• Supersonic results
• Transferred to AMRDEC in FY02.
• Published (joint ARL/AMRDEC) in
• ARL Report (Sep 2002)
• AIAA Conf Paper (Aug 2002)
• AIAA Journal Paper (2003)
• 2002 Joint RD Award

Subsonic ResultsSide Force Coefficient
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Cp on missile and sweep of vorticity magnitude
M 0.6, d 10, a 4 Movie
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Coupled Computational Fluid Dynamics and
Structures3D Time Dependent CFD of Missile
Divert Control

• Thrust direction changes due to spin
• Spin also produces an aerodynamic interaction
  side force due to asymmetry of the flow field

Time Dependent CFD Simulation of Side Thruster

• Jet interaction side force small
• Spin reduces total jet normal force due to
  increased (negative) jet interaction normal force

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Coupled Computational Fluid Dynamics and
Structures3D Time Dependent CFD of Missile
Divert Control
Movie
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Coupled Computational Fluid Dynamics and
Structures3D Time Dependent Structural Response
to Missile Divert Control
CFD Loading on the Structural Model
Structural Response(Z displacement scaled by 100)
Movie
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Time-Accurate Sinusoidal Deflecting Canard CFD
with Coupled Structures/GNCfor Piezo-Ceramic
Actuation
Feedback control loop to determine canard dynamic
response
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Advanced G-Hardened G,NC Suites
Goal Develop advanced instrumentation and
packaging for GN C and TE of high-g,
gun-launched smart munitions Approach Utilize
COTS technology, leverage DARPA, DOD and STRICOM
investments. Transition technology to major
service programs
COMPONENTS
TRANSITIONS
IAT - EM Gun
NAVY ERGM
KE TRACER WELL
NAVY - BARRAGE
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ARL Aeroballistic Diagnostic FUZEand Inertial
Sensor Suite
Inertial Sensor Suite (ISS)
DFUZE Hardware and Portable Data
Acquisition System
3-axis Mag
4 Radial Accels (AO)
SLIT
2-axis Radial Accel
1-axis Axial Accel

• DFUZE 2000 is a Diagnostic Measurement Tool
• NATO-compatible fuze replacement to 15K gs
• Measures angular orientation and related
• derivatives for a spinning body with respect
  to
• a navigation coordinate system
• Measures in-bore and/or in-flight acceleration
• components

XM982
Scorpion
Term KE
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SOLAR and MAGNETIC Roll RatesWinstead Launch
Mission - ONR
Projectile roll rates with respect to the solar
and magnetic fields
NASA/NAVY Sounding Rocket Range 400 mi Alt 100
mi TOF 15 min
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Early Demonstration Guidance Electronics Unit
For Autonomous Naval Support Round
ANSR EDGEU
ANSR CAS and Power System
No Control
Body Roll Index
UP
Canards
Roll Direction
Roll Angles
0 deg 90 deg
Complete ANSR Guidance Section During Pop
Test On Field Test, Roll Fixture
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Early Demonstration Guidance Electronics Unit
For Autonomous Naval Support Round DFUZE
Telemetry Return
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Medium Caliber Guided Munitions
Objective Force Warrior Lethality
Supersonic
Scorpion
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Medium Caliber Guided Munition Subsonic Small
Caliber Improved Munition/DARPA Scorpion
Objective Demonstrate technology to guide
medium caliber munition using Micro-Adaptive Flow
Control (MAFC). Provide a suite of validated
advanced design tools for MAFC.
SCORPION
SCORPION Demonstration Vehicle

• Pacing Technologies
• INS for spinning projectiles
• MEMS MAFC actuators
• Packaging
• Physics of MAFC
• CFD of Microjets

• Warfighter Payoffs
• Medium Caliber Guided Grenade for the
  Objective Force
• Three fold extension of the battle space
• Increase in accuracy

GOAL Demonstrate a guided grenade
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Piezo Actuator System Layout
Tungsten Ring
Steel Jacket
Exit Port
Piezo Actuator (disk)
Aluminum Windshield
Steel Coanda Base
Steel Actuator Clamp
Sensor Board
SLIT Optical Sensors
Actuator Driver Board
Power Conversion Board
HSTSS Batteries
Processor Board
SCORPION
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Dynamic Structural Analysis During Launch
Dynamic Stress Waves Due to Launch

• Full three-dimensional dynamic analysis of
  a SCORPION projectile launch using DYNA3D

Local Transient Loads Exceed Nominal Launch
Accelerations
Enable build and design of survivable Inertial
Sensor Suites (ISS)
4 Radial Accels (AO)
3-axis Mag
1-axis Axial Accel
2-axis Radial Accel
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AERODYNAMIC FORCESSynthetic Jet Unsteady CFD
Using RANS
Computed Particle Traces U 37 m/s, a 4, Ujet
31 m/s, f 1000 Hz
40mm shell, U 82m/s, Jet velocity 31 m/s,
f1000 Hz, Spin 67 Hz
Movie
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AERODYNAMIC FORCESSynthetic Jet Unsteady CFD
using LNS
Looking from the nose
Jet on
Jet off
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Scorpion Flight Dynamics and Open Loop
Experiment Modeling
Wise Choice of Technologies Combined to Derive
Highest Fidelity Modeling
Aerodynamic Experiments
Fast and Slow Mode Yaw
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Flight Test Objective Force Munitions
HPC Enables the design flight test hardware and
electronics

• Muzzle velocities 88.4-91.8 m/s
• Fired,recovered, turned off
• Power consumption and durability
• Two (2) fired a second time.
• One (1) fired three times
• TM data was taken on all shots

Sensor Suite
Battery
Telemetry Antenna
Solar Sensor Array
Flight Test
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HPC Dynamic Structural Analysis
(LLNL DYNA3D) High performance computational
structural dynamics Technology Enabler for
Advanced Smart Munition Systems
SUB- SYSTEM DESIGN AND EVALUATION
SURVIVABILITY OF ELECTRONICS Allows stress wave
amplification and acceleration loadings to be
studied
SUB-PROJECTILE DESIGN Full dynamic response due
to gun launch Stress state of internal components
and body
ACTUATOR, CONTROL ELECTRONICS TELEMETRY SYSTEM
PATCH TX ANTENNA
BATTERY
LAUNCH SYSTEM DESIGN Full 3-D dynamic analysis of
the launch of the projectile/sabot system
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Medium Caliber Supersonic Flight Dynamics
Completed a full experimental aerodynamic
Experiments
Actuator Designs
Mach 2.0 Launch
Cavity Design 2 With compression ramp
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Aeroballistic ExperimentFlight Modeling
Static Stability Mach 2.5
Current Work Nose control using electronically
controlled oscillating flat plate with canard
confinement JHU Engineering Design Project
looking at oscillating controllers
Static Margin 0.51 Calibers
Flight Configuration
ARROW TECH
M 2.5, Alpha 0 Confinement Shock Stand Off
CFD of forward canards with deployed plate
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Divert Validation Flight Experiment Model
control mechanism
control logic
battery

• Maneuver authority from flip-out drag fin
• 26.38mm projectile
• Payload
• Control logic circuitry (SA)
• Power supply
• Flip-out drag mechanism
• Structural Design

Control logic circuitry (SA)
Flip-out drag mechanism
DYNA 3D Simulation of Divert Mechanism
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Divert Validation Flight Experiment Model
Movie
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Supersonic Divert Simulation
Transverse Maneuver Gs vs. Range
Pulse Control System
Increasing Pulse Strength
Black Blue Green Red Yellow
Lateral Velocity vs. Range
Cross Range vs. Range
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Supersonic Divert System Simulation and
Visualization
Movie
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Smart MunitionsThe Pay Off
Integrated Suite of FCS MDD/HPC Tools and
Sub-Systems
155mm XM982
Coupled HPC Physics Based Modeling Modeling
and Design of Effective Robust T E Telemetry
Sensor Systems HPC Visualization for Combat
System Simulations
Technology for FCS LOS/BLOS/NLOS
Platforms
Technology Insertion and Transition