1/9/2009 ELF 1 Outline Introduction / Key Drivers in the Missile Design and Integration Process Aerodynamic Considerations in Missile Design and Integration Propulsion Considerations in Missile Design and Integration Weight Considerations in Missile Design and Integration Flight Performance Considerations in Missile Design and Integration Measures of Merit and Launch Platform Integration Sizing Examples Development Process Summary and Lessons Learned References and Communication Appendices ( Homework Problems / Classroom Exercises, Example of Request for Proposal, Nomenclature, Acronyms, Conversion Factors, Syllabus )
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1/9/2009 ELF 1
Outline
Introduction / Key Drivers in the Missile Design and Integration Process
Aerodynamic Considerations in Missile Design and Integration
Propulsion Considerations in Missile Design and Integration
Weight Considerations in Missile Design and Integration
Flight Performance Considerations in Missile Design and Integration
Measures of Merit and Launch Platform Integration
Sizing Examples
Development Process
Summary and Lessons Learned
References and Communication
Appendices ( Homework Problems / Classroom Exercises, Example of
Request for Proposal, Nomenclature, Acronyms, Conversion Factors,
Syllabus )
1/9/2009 ELF 2
Evaluate Alternatives and Iterate the
System-of-Systems Design
• Mission / Scenario
/ System Definition
• Weapon System
Requirements,
Trade Studies
and Sensitivity
Analysis
• Launch Platform
Integration
• Weapon Concept
Design Synthesis
• Technology
Assessment and
Dev Roadmap
Initial
Tech
Initial
Reqs
Baseline
Selected
Alt
Concepts
Initial Carriage /
LaunchIteration
Refine
Weapons
Req
Initial Revised
Trades / Eval Effectiveness / Eval
Tech
Trades
Initial
Roadmap
Revised
Roadmap
Update
Note: Typical design cycle for conceptual design is usually 3 to 9 months
Use Creative Skills to Consider Broad Range of Alternatives
Ask Why? of Requirements / Constraints
Project into Future ( e.g., 5 – 15 years )
State-of-the-art ( SOTA )
Threat
Scenario / Tactics / Doctrine
Concepts
Technology Impact Forecast
Recognize and Distill the Most Important, Key Drivers
Develop Missile Concept that is Synergistic within a
System-of-Systems
Develop Synergistic / Balanced Combination of High
Leverage Subsystems / Technologies
1/9/2009 ELF 5
Identify, Quantify, and Balance the Cost Effective Measures of Merit
Max / MinRange
Time to
TargetRobustness
WeightSurvivability
Lethality Miss Distance
Observables
Reliability
1/9/2009 ELF 6
Start with a Good Baseline
I would have
used the wheel
as a baseline.
Evaluate Prediction Methods for Uncertainty in
Accuracy and Precision
1/9/2009 ELF 7
Precision
Accuracy
1/9/2009 ELF 8
Conduct Balanced, Unbiased Trade-offs
Aerodynamics
Propulsion
Structures
Seeker
Guidance and
Control
Warhead – Fuze
Production
1/9/2009 ELF 9
AA- 8 / R-60 Python 4 Magic 550 U-Darter
Python 5 Derby / R-Darter AIM-9L Aspide
AA-10 / R-27 Skyflash AIM-7 R-37
AA-12 / R-77 AIM-9x Super 530D AIM-132
AA-11 / R-73 SD-10 / PL12 AIM-120 Mica
IRIS-T Meteor A-Darter Taildog
Evaluate Many Alternatives
Note: Although all of the above are supersonic air-to-air missiles, they have different configuration geometry
1/9/2009 ELF 10
Search a Broad Design Solution Space
( Global Optimization vs Local Optimization )
Local Optimum ( e.g., Lowest Cost Only in Local Solution Space )
Local Optimum ( e.g., Lowest Cost Only in Local Solution Space )
Global Optimum ( e.g., Lowest Cost in Global Solution Space ) within Constraints
1/9/2009 ELF 11
Evaluate and Refine as Often as Possible
1/9/2009 ELF 12
Provide Balanced Emphasis of
Analytical vs Experimental
Thomas Edison: "Genius is 1% inspiration and 99% perspiration."
Albert Einstein: "The only real valuable thing is intuition."
1/9/2009 ELF 13
Use Design, Build, and Fly Process, for Feedback
Leading to Broader Knowledge / Understanding
Design
Build
Fly ( Test )
Prediction Satisfies
Customer
Requirements?
Test Results Satisfy
Customer Requirements
and Consistent with
Prediction?
Is it Producible?
No
Yes
Data
Failure / Success
Information
Understanding
Wisdom
No
No
Where is the wisdom we have lost in knowledge? Where is the knowledge we have lost in information?--T. S. Eliot ( The Rock )
Knowledge comes by taking things apart: analysis. But wisdom comes by putting things together.--John A. Morrison
We are drowning in information but starved for knowledge.--John Naisbitt ( Megatrends: Ten New Directions Transforming Our Lives )
We learn wisdom from failure much more than from success. We often discover what will do, by finding out what will not do; and probably he who never made a mistake never made a discovery.--Samuel Smiles ( Self Help )
Knowledge
1/9/2009 ELF 14
Consider Follow-on Consequences of Decisions -Actions Have Consequences
1/9/2009 ELF 15
Keep Track of Assumptions and Develop
Real-Time Documentation
It’s finally
finished ! . . .
1/9/2009 ELF 16
Develop Good Documentation
Mission flight profiles of
preferred concept( s )
1/9/2009 ELF 17
Effectively Utilize Conceptual Design Group Skills
- Maximize Strengths and Minimize Weaknesses
Source: Nicolai, L.M., “Designing a Better Engineer,” AIAA Aerospace America, April 1992
Detail /
Production
Design –
30%
Other Than
Design –
60%
Preliminary Design – 8%Conceptual Design – 2%
(Test, Analysis,
Configuration
Management, Software,
Program Management,
Integration,
Requirements,
etc.)
1/9/2009 ELF 18
Balance the Trade-off of
Importance Versus Priority
Advanced Programs /
Conceptual Design
SDD Programs /
Preliminary Design
Production Programs /
Detail Design
1/9/2009 ELF 19
Evaluate Alternatives and Iterate the
Configuration Design
Yes
Establish Baseline
Meet
Performance?
No
No
Yes
Resize / Alt Config / Subsystems / Tech
Alt Mission
Alt Baseline
Define Mission Requirements
Aerodynamics
Propulsion
Weight
Trajectory
Measures of Merit and Constraints
1/9/2009 ELF 20
Configuration Sizing Conceptual Design
Guidelines: Aeromechanics
Configuration Sizing Parameter Aeromechanics Design Guideline Body fineness ratio 5 < l / d < 25
Nose fineness ratio lN / d 2 if M > 1
Boattail or flare angle < 10 deg
Efficient cruise dynamic pressure q < 1,000 psf
Missile homing velocity VM / VT > 1.5
Ramjet combustion temperature > 4,000 F
Oblique shocks prior to inlet normal > 2 oblique shocks / compressions if M > shock to satisfy MIL-E-5008B 3.0, > 3 shocks / compressions if M > 3.5
Inlet flow capture Shock on cowl lip at Mmax cruise
Ramjet Minimum cruise Mach number M > 1.2 x MInletStart , M > 1.2 MMaxThrust = Drag
Subsystems packaging Maximize available volume for fuel / propellant
Ashley, H. and Landahl, M., Aerodynamics of Wings and Bodies, Dover Publications, 1965
John, James E.A., Gas Dynamics, Second Edition, Prentice Hall, 1984
Zucker, Robert D., Fundamentals of Gas Dynamics, Matrix Publishers, 1977
Propulsion
Chemical Information Propulsion Agency, http://www.cpia.jhu.edu/
St. Peter, J., The History of Aircraft Gas Turbine Engine Development in the United States: A Tradition of Excellence, ASME International Gas Turbine Institute, 1999