phd thesis presentation
TRANSCRIPT
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بسم هللا الرحمن الرحيم
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Ain Shams University, Faculty of Engineering
Computer and Systems Engineering Department
3D Intelligent Object TrackingMissile Modeling and Guidance Design
Submitted By:
Eng. Mohamed Ali Ali Sobh
Supervised By:
Prof. Dr. Mohamed Abd Elhamed Sheirah
Cairo 2006
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Agenda
Objectives
Problems
Background
Survey
Achievements & Results
Conclusion
Future Work
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Agenda
Objectives
Problems
Background
Survey
Achievements & Results
Conclusion
Future Work
Home
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Objectives
Provide very accurate environment to
design and to develop different guidance
techniques for missile systems
Contribute to both Missile Modeling and
Guidance Design
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Agenda
Objectives
Problems
Background
Survey
Achievements & Results
Conclusion
Future Work
Home
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Problems
Missile system is very complex and nonlinear
Aerodynamics coefficients are not available
Actual experiments are not allowed or expensive
There is no available tools for missile modeling
Books, Publication, Researches, Datasheets, and
Experiments results are classified
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Agenda
Objectives
Problems
Background
Survey
Achievements & Results
Conclusion
Future Work
Home
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Background
Structure
Classification
Speed
Range
Size
Launcher and Target Type
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Background
Directional MotionsVertical Acceleration (w )
.
.
.
Accelerometer
CG
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Background
Rotational Motion
Rolling Rate (p)
Pitching Rate (q)
Yawing Rate (r)
Rate Gyroscope
CG
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Background
Actuators
ElevatorAileron
Rudder
Thrust
Thrust Vectoring
Actuators
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Background
Coordinates Systems
SB
SL
SI: (Global Inertial) Geocentric Inertial Coordinates System
SL: Earth Fixed Launch Site Coordinates System
SE: Earth-Centered Launch-Derived Coordinates System
SP: Launch Vehicle Platform Accelerometer Coordinates System
SN: Launch Vehicle Navigation Coordinates System
SB: Body Fixed Coordinates System
SG: Local Geocentric Coordinates System
SG': Fixed Local Geocentric Coordinates System
SC: Local Geodetic Coordinates System
SI
SC
SP
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Background
Mass Variation
CG (t)
dm
Fuel Consumption
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Background
Gravity
SGSB
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Background
Attack Angles
Angle of Attack α
Sideslip Angle β
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Background
Aerodynamics
CP
Final Aerodynamic Coefficients
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BackgroundExperimental Aerodynamics Evaluation
Physical Missile Model
Air Tunnel
Experimental Aerodynamics Evaluation
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BackgroundComputational Aerodynamics Estimation
Full Grid Multi-Grid Grid Unstructured Grid
Cube Volume
Tetrahedral Element
CFD Simulation
Results
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BackgroundComputational Aerodynamics Estimation
Bernoulli
Euler
Navier Stock Equations
For missile system (supersonic speed)
Turbulent Flow
Time Marching Numerical Calculation
Compressible Flow
Viscous Flow
No-Slip Boundary Condition
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Background
Wind
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Background
Forces and Moments
Fx
Fy
Fz
Mx
My
Mz
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Background
Flight Phases
Terminal Phase
Maneuvering
Launch, Coast
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Background
Guidance
Active
Guidance
Radar & Radar Detectors
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Background
Guidance
Semi - Active
Guidance
Radar Detectors
Radar
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Background
Guidance
Passive
Guidance
Infrared or Vision Detectors
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Background
Navigation
Local Navigation System
Radar
SP
Position Xt Yt Zt
Position Xp Yp Zp
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Background
Navigation
Local Navigation SystemSP
Orientation (Euler Angles) φ θ ψDisplacement
Gyroscope
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Background
Navigation
Global Navigation System SP
Position Xp Yp Zp
GPS
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Agenda
Objectives
Problems
Background
Survey
Achievements & Results
Conclusion
Future Work
Home
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Survey
Missile Modeling Fixed Mass Missile Model
Variable Mass Missile Model
MATLAB General Aircraft Model
Guidance Techniques LOS - Line of Sight Navigation Guidance
PN - Proportional Navigation Guidance
LQR Guidance
Fuzzy-PN Guidance
Fuzzy Guidance for High Speed Targets
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Survey
Missile Modeling Fixed Mass Missile Model
Variable Mass Missile Model
MATLAB General Aircraft Model
Guidance Techniques LOS - Line of Sight Navigation Guidance
PN - Proportional Navigation Guidance
LQR Guidance
Fuzzy-PN Guidance
Fuzzy Guidance for High Speed Targets
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Missile Modeling
Fixed Mass Missile ModelA. Aircraft
B. Missile (Symmetry)
C. Missile (Plan Separation)
Longitudinal Lateral
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Missile Modeling
Fixed Mass Missile ModelD. Missile: Linearization at certain operating point
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Missile Modeling
Variable Mass Missile Model
• Derived specially for large space rockets
• Different coordinate systems (SI, SL, SE, SP, SB, SG, SG’, SC)
• Consider mass variation
• Consider measuring elements
• Consider fuel sloshing and body bending
A. Missile
B. Missile: Linearization at certain operating point. Assume thrust vectoring control.
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Missile Modeling
MATLAB General Aircraft Model
• Provides both fixed and variable mass missile models
• Uses nonlinear model directly
• Two coordinate systems (SP, SB)
• Provide accurate models for wind, gravity and atmosphere
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Missile Modeling
MATLAB Missile Model
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Guidance Techniques
Basic Concepts / Plan Separation
Pitch Control - Vertical Plan Yaw Control - Horizontal Plan Roll Control
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Guidance Techniques
Basic Concepts / Roll Control
Roll Angle
Control
Roll Rate
Control
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Guidance TechniquesBasic Concepts / Pitch and Yaw Control
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Guidance TechniquesBasic Concepts / Autopilot
Autopilot Using Gyroscope Autopilot Using Accelerometer
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Survey
Missile Modeling Fixed Mass Missile Model
Variable Mass Missile Model
MATLAB General Aircraft Model
Guidance Techniques LOS - Line of Sight Navigation Guidance
PN - Proportional Navigation Guidance
LQR Guidance
Fuzzy-PN Guidance
Fuzzy Guidance for High Speed Targets
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Guidance Techniques
LOS - Line of Sight Navigation Guidance
PD Controller
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Guidance Techniques
PN - Proportional Navigation Guidance
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Guidance Techniques
LQR Guidance
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Guidance Techniques
Fuzzy-PN Guidance
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Guidance Techniques
Fuzzy Guidance for High Speed Targets
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Agenda
Objectives
Problems
Background
Survey
Achievements & Results
Conclusion
Future Work
Home
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Achievements & Results
Missile Modeling
Very Accurate Missile Model
Visual and Interactive Environment for Guidance Design
Guidance Techniques
New Adaptive Digital Guidance Technique (ADC)
New Technique for Exact and Realistic Target Prediction (RPPMT)
New Technique to Intercept High Speed Targets (RPPHST)
General Topics
Aerodynamic CFD Simulator to Estimate Aerodynamics Coefficients
New Method for Automatic Fuzzy Mapping
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Achievements & Results
Missile Modeling
Very Accurate Missile Model
Visual and Interactive Environment for Guidance Design
Guidance Techniques
New Adaptive Digital Guidance Technique (ADC)
New Technique for Exact and Realistic Target Prediction (RPPMT)
New Technique to Intercept High Speed Targets (RPPHST)
General Topics
Aerodynamic CFD Simulator to Estimate Aerodynamics Coefficients
New Method for Automatic Fuzzy Mapping
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Missile Modeling
Very Accurate Missile Model Coordinates Systems and Coordinates Transformation
Variable Mass Rigid Body
Aerodynamics
Engine
Actuators Aerodynamics Actuators
Thrust Vectoring Actuators
Thrust Control Actuator
Measuring Devices Rate Gyroscopes
Position Gyroscopes
Accelerometers
Attack and Sideslip Angle Detectors
Tracking Devices IR (Infrared) Detectors
Radar Detectors
Global Positioning System
Atmosphere Shear Wind
Turbulence Wind
Pressure
DensityMissile Components
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Mis
sile
Modelin
gV
ery
Accura
te M
issile
Mo
del
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Missile ModelingVisual and Interactive Environment for Guidance Design
Integrated within
SimulaWorks Simulation
Package
Programmed using Native
C/C++
High order numerical
calculations
Very fast 4 times than
MATLAB
Allow very complex control
loop design
Represent missile target
engagement visually
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Missile ModelingModel & Environment Validation
Successfully provide exact result compared with
MATLAB aerospace aircraft examples
Separate verification for each component
Visual Inspection
Provides reasonable and expected performance due to
gravity, earth rotation, wind, aerodynamics variation
Successfully used to implement several guidance
techniques like PN, TPN, LOS, LQR, Fuzzy…
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Missile ModelingEffect of Coupling
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Missile ModelingPN - Proportional Navigation Guidance
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Missile ModelingPN - Proportional Navigation Guidance
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Missile ModelingTPN – True Proportional Navigation Guidance
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Missile Modeling
LOS - Line of Sight Navigation Guidance
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Missile ModelingLQR Guidance
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Missile ModelingFuzzy-PN Guidance
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Achievements & Results
Missile Modeling
Very Accurate Missile Model
Visual and Interactive Environment for Guidance Design
Guidance Techniques
New Adaptive Digital Guidance Technique (ADC)
New Technique for Exact and Realistic Target Prediction (RPPMT)
New Technique to Intercept High Speed Targets (RPPHST)
General Topics
Aerodynamic CFD Simulator to Estimate Aerodynamics Coefficients
New Method for Automatic Fuzzy Mapping
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Guidance Techniques
New Adaptive Digital Guidance Technique (ADC)
ADC : Adaptive Dahlin Controller
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Guidance Techniques
New Adaptive Digital Guidance Technique (ADC)
Offline System
Identification
Using
GLS
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Guidance Techniques
New Adaptive Digital Guidance Technique (ADC)
Final ADC Controller
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Guidance Techniques
New Adaptive Digital Guidance Technique (ADC)
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Guidance Techniques
New Adaptive Digital Guidance Technique (ADC)
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Guidance Techniques
New Adaptive Digital Guidance Technique (ADC)
Pitch Error
Yaw Error
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Guidance Techniques
New Adaptive Digital Guidance Technique (ADC)
Roll Rate
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Guidance Techniques
New Adaptive Digital Guidance Technique (ADC)
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Guidance Techniques
New Adaptive Digital Guidance Technique (ADC)
PNManeuverability
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Guidance Techniques
New Adaptive Digital Guidance Technique (ADC)
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Guidance TechniquesNew Technique for Exact and Realistic Target Prediction (RPPMT)
Actual Inputs
for
Target Position
Applying Linear Regression
RPPMT: Realistic Path Prediction for Maneuvering Targets
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Guidance TechniquesNew Technique for Exact and Realistic Target Prediction (RPPMT)
Proposed method to
calculate the exact
interception point
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Guidance TechniquesNew Technique for Exact and Realistic Target Prediction (RPPMT)
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Guidance TechniquesNew Technique for Exact and Realistic Target Prediction (RPPMT)
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Guidance TechniquesNew Technique for Exact and Realistic Target Prediction (RPPMT)
Existing Technique
Interception Time: 4.046
IAE: 12.72
Proposed Technique
Interception Time: 4.045
IAE: 10.90
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Guidance TechniquesNew Technique for Exact and Realistic Target Prediction (RPPMT)
Existing Technique Proposed Technique
Proposed Technique
Manoeuvrable
Target
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Guidance TechniquesNew Technique to Intercept High Speed Targets (RPPHST)
RPPHST: Realistic Path Prediction for High Speed Targets
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Guidance TechniquesNew Technique to Intercept High Speed Targets (RPPHST)
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Guidance TechniquesNew Technique to Intercept High Speed Targets (RPPHST)
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Achievements & Results
Missile Modeling
Very Accurate Missile Model
Visual and Interactive Environment for Guidance Design
Guidance Techniques
New Adaptive Digital Guidance Technique (ADC)
New Technique for Exact and Realistic Target Prediction (RPPMT)
New Technique to Intercept High Speed Targets (RPPHST)
General Topics
Aerodynamic CFD Simulator to Estimate Aerodynamics Coefficients
New Method for Automatic Fuzzy Mapping
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General TopicsCFD Simulator to Estimate Aerodynamics Coefficients
Provides CFD simulation
In 2D using finite difference method
In 3D using finite volume method
Uses Multi-Grid to perform CFD calculations
Automatically generate the grid around any 3D object
Can be used to perform general fluid simulation for speeds up to 5.0
mach
Provide mach number, pressure, temperature, energy, fluid density
distribution graphs
Calculate forces, moments, center or pressure and fluid dynamics
(aerodynamics) coefficients
Optimized to run with limited memory and computation power
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General TopicsCFD Simulator to Estimate Aerodynamics Coefficients
CFD Simulator Verification
Performs CFD simulation over standard shapes like Sphere, Plate
Visual Inspection
Speed 300 Cx = 0.549
Speed 700 Cx = 0.506
Speed 1000 Cx = 0.549
Cx ≈ 0.5
Speed 700 Cx = 0.952
Cx ≈ 1.0
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Simulator
Velocity Vectors Map at Missile Head (2D)
General TopicsCFD Simulator to Estimate Aerodynamics Coefficients
Mach Number Distribution Graph (2D)
Temperature Distribution Graph (2D)
Mach Number Distribution Graph (2D)
2D (2000 Iteration, 0.005m Resolution, 10 Layers, 468,654 Cell, 45 sec)
3D (5000 Iteration , 0.005m Resolution, 10 Layers, 44,094,150 Cell, 6 hours)
Air Speed 700 m/s
Air Density 1.225
Temperature 288.16 K Velocity Distribution Graph (3D)
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General TopicsNew Method for Automatic Fuzzy Mapping
Objective: Map existing control into an equivalent fuzzy control
Offline Mode: Construct the Variables and the Rules
Online Mode: Update the Rules
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General TopicsNew Method for Automatic Fuzzy Mapping
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General TopicsNew Method for Automatic Fuzzy Mapping
Trained Fuzzy System In Pitch Plan Trained Fuzzy System In Yaw Plan
Original LOS Guidance
IAE = 32.22
Fuzzy LOS Guidance
IAE = 56.62
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Agenda
Objectives
Problems
Background
Survey
Achievements & Results
Conclusion
Future Work
Home
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Conclusion
Missile Modeling
Missile system is too complex to be modeled by a set of linear
equations
The missile model is successfully derived, implemented, and
integrated within SimulaWorks simulation environment
The proposed model and the simulation environment succeeds to
represent most of missile system behaviors and to provide a very
realistic environment for guidance design
A special simulation tool is built and used successfully to estimate
the aerodynamics coefficients by performing CFD simulation around
missile airframe
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Conclusion
Guidance Design A new guidance technique (ADC) is proposed and used successfully
to intercept different type of targets
ADC provides minimum IAE, very fast interception, high tracking and
manoeuvrability
A new realistic target prediction technique (RPPMT) is proposed
and used successfully to predict and to intercept manoeuvring
targets
A new realistic target prediction technique (RPPHST) is proposed
and used successfully to predict and to intercept high speed targets
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Agenda
Objectives
Problems
Background
Survey
Achievements & Results
Conclusion
Future Work
Home
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Future Work
More aspects and components can be included:
Fuel sloshing and body bending dynamics
More realistic models for propulsions system
Advanced CFD simulation using finite element method
Actual experiments to verify CFD simulation results
Practical implementation to verify simulation results
Apply new digital control techniques like RST
Study the effect of model parameters variation on
guidance performance
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Thank You
3D Intelligent Object TrackingMissile Modeling and Guidance Design