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Configuration Research

Activities at AFRL/RBAA

Collaborative Systems Engineering andDesign Symposium

29 April 2008

Atlanta, GA

Mr. Cale ZeuneAir Force Research Laboratory

Air Vehicles DirectorateWright Patterson AFB, OHcale.zeune@wpafb.af.mil

RBO-08-342Doc. # 08-3016

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Objectives and Outline

Objective: Inform community of tools, processes, andchallenges associated with configuration analysis atthe Air Vehicles Directorate, AFRL

Outline

Overview of AFRL

Tools and frameworks in use

Common analysis processes and examples Challenges and vision for the future

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AFRL Overview

10 Technical Directorates

AFOSR, Air Vehicles, Directed

Energy, Human Effectiveness,

Information, Materials/Mfg., Munitions,

Propulsion, Sensors, Space Vehicles

10 Sites across the nation

Mission Leading the discovery, development, and integration ofaffordable warfighting technologies for our air and spaceforce.

Commander: Gen. Curtis Bedke Personnel: 5,400 (of which 1,300 are active duty

military)

Budget: ~$3.7B annually

ROME

EGLINKIRTLAND

ARLINGTON

EDWARDS

HANSCOM

TYNDALLBROOKSMESA

WRIGHTPATT

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Air Vehicles Directorate

(AFRL/RB)

Develop and Transition Superior Air VehicleDevelop and Transition Superior Air VehicleTechnology Solutions that Enable DominantTechnology Solutions that Enable DominantMilitary Aerospace VehiclesMilitary Aerospace Vehicles

Technology Developer andSystem Integrator

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Aerodynamic Configurations

Branch (AFRL/RBAA) Mission To lead the research, development and application of a broad

range of technologies which will improve the performance ofaircraft, missiles, and high speed vehicles. We provide the tools

and expertise for assessment, evaluation and transition of newtechnology in the interest of the United States Air Force.

Areas of Expertise Configuration Design and Analysis

Technology Integration and Assessment

Wind Tunnel Test Planning and Execution Computational Fluid Dynamics (CFD) Applications

Flow Control Development and Application

Aerothermodynamics

Plasma Physics and Systems Applications Organization Low Speed Team (Mach < 2)

High Speed Team ( Mach > 2)

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Low Speed Team

Low Speed Configuration

Low Speed Aerodynamics

Flow Control

Fluid Mechanics/Flow Physics

Micro Air Vehicles

Experimental Aerodynamics

Design and AssessmentMethodology

Application Areas

Multi-Mission Mobility

Persistent Intelligence,Surveillance, Reconnaissance

Micro Air Vehicles

Hunter-Killer Aircraft

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High Speed Team

High Speed Configuration

High Speed Aerodynamics

Aero-thermodynamics

Trajectory Analysis

Experimental Aerodynamics

Design and Assessment

Methodology Application Areas

Affordable, Reusable Access toSpace

Supersonic Tailless Vehicles Prompt Global Strike

Hypersonic Cruise Vehicles

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Tools Mission Performance and

Sizing FLOPS Flight Optimization System; aircraft synthesis

and mission analysis program developed byNASA Langley

Includes components for weight estimation,propulsion system performance, andaerodynamic estimation

Text based using files for input/output

CASP Combat Aircraft Synthesis Program;

developed by AFRL predecessororganization code available but notcurrently supported

Developed specifically for military aircraft;contains detailed weight estimation module

VAAAS VAAA Sizer; empirically based, simple sizing

program developed in-house

Useful for conceptual sizing and missionperformance

XML input; generates its own filewrapper

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Tools - Aerodynamics

EDET (FLOPS) Empirical Drag Estimation

Technique; a subroutine integratedwith FLOPS; computes aero basedon parameters

HASC/VORLAX a vortex lattice induced drag code;

usefully for estimating induceddrag, trim drag, S&C parameters

AVL Athena Vortex Lattice code;

distributed by MIT/Drela CBAERO NASA Ames code; panel methods

for low and high speed flows; usesunstructured geometry and alsocomputes aero-heating

CART3D NASA Ames unstructured Euler

code

AVUS AFRL/RBA developed unstructured

Navier Stokes solver

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Tools - Geometry

SolidWorks 3D CAD geometry tool developed by

Dassault Systemes S.A.

Outputs geometry in all major formats(xmt, igs, stp, stl)

Robust tool for geometry; not ideal fortypical aircraft shapes

Requires certain level of proficiency tobe productive

Developed some macros to automategeneration of wing parts

VSP

Vehicle Sketch Pad developed by NASALangley for conceptual-level sketchingof aircraft

Ability to export crude triangulated mesh

Computes common aircraft parametersof use (volume, reference quantities,wetted areas)

Integrated vortex lattice solver

AMRAVEN Aircraft geometry tool developed by

Technosoft, Inc.

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Tools - Heating, Trajectory

HEAT-TK/SHABP

Hypersonic Engineering Aerothermodynamic

Trajectory Tool Kit; runs the

Supersonic/Hypersonic Arbitrary Bodyprogram to compute high speed aero and

heating

MINIVER

Developed by McDonnell Douglas Co. Aeroand heating program

POST

Program to Optimize Simulated Trajectories

developed by the Martin Marietta Co. Trajectory analysis and optimization based

on input vehicle characteristics and

constraints

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Frameworks - ModelCenter

Produced by Phoenix Integration

Process integration environment;automates analysis execution and

facilitates design exploration (parameterstudies, optimization)

Allows linking and automation of legacycodes, Excel spreadsheets, MATLABfunctions, scripts, and more

Common uses in AFRL/RBAA

Front end for legacy, text-based codes

Managing complex processes

Running thousands of iterations in tradestudy

Simple optimizations and carpet plots

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Response Surfaces and Data

Visualization using JMP JMP is produced by the SASInstitute

Chiefly a statistical analysis

program Useful for interactively

exploring, visualizing, andfitting data sets

Common uses in AFRL/RBAA Construct complex DOEs

Visualize, sort, fit, and displaycomplex data sets

Construct Response Surface meta-models for further analysis

Constraint analysis

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Assessment / Study Planning

ProcessDefine Analysis Goals,Objectives, Products,

and Impacts

Define Analysis Goals,Objectives, Products,

and Impacts

Define Analysis Questions,Metrics, &

Expected Products

Define Analysis Questions,Metrics, &

Expected Products

Define Typesof AnalysisRequired

Define Typesof AnalysisRequired

Define ModelFidelity/Abstraction

Requirements

Define ModelFidelity/Abstraction

Requirements

Define Approachand Identify Models

& Tools

Define Approachand Identify Models

& Tools

DefineCapability Gaps

and Solution Space

DefineCapability Gaps

and Solution Space

Define Products,Project Plan, and

Team

Define Products,Project Plan, and

Team

DevelopInsight

DevelopInsight

Develop &Verify Models

Develop &Verify Models

Models

Needed

Developers &

Timeline

IntegrateModels &

Verify Integration

IntegrateModels &

Verify Integration

Fidelity Reqd& Need for

Surrogates

Define Concept &Technology Space

Define Concept &Technology Space

Concept Cars

or Parameter

Bounds

DesignExperiments

DesignExperiments

MoEs

Input

RangesScenario &

What to run

RunExperiments

RunExperiments

Run

Matrix

AnalyzeData

AnalyzeData

Output

Data

Data to Information

(Using Visualization)

Change

DOE?

Change

Concepts?

AnswerQuestions

AnswerQuestions

Information to Knowledge

(Engage Decision Makers)

Change

Goals?

Planning Process Drives ExecutionPlan & Spiral Development

Planning Process Drives ExecutionPlan & Spiral Development

Integrated

EnvironmentModels

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FLOPS

CASPwt

Propul

Takeoff

Typical Assessment Process

Establish BaselineAircraft Model

Establish Key Inputs andRanges, Tech Factors and

Ranges, Outputs (responses)[run screening test if necessary]

Construct Response SurfaceModel (RSM) using JMP

Meta-Model of ResponsesVs. Inputs and Factors

Run Model Through DOEover Ranges of Interest

Borrows heavily from Ga. Tech. (ASDL) TIF, TIES methods

Establish Technology Scenarios;Assign Factor Dist. For Scenarios

Run RSM through Monte CarloAnalysis for Each Scenario

Compile ScenarioResponse Results

Optimize Baseline Inputs (with

constraints) Quickly Using RSM

Optimized Baseline AircraftWithout Technology Applied

Quantitative Comparison ofTechnology Scenarios

(Performance & Risk/Prob.)Quantitative Technology Assessment Process Develops response surface meta-model for

further use

Optimizes (including constraints) a baseline

model (without technology) for furthercomparisons

Provides quantitative comparison of vehicle with

technology scenarios applied; performance and

risk/probability can be assessed

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Analysis ExampleLong Range Strike Study

Objective: Explore configuration; Understand impact oftechnologies on aircraft

1 2 3 4 5

Induced DragSupersonic FF Profile DragWing Weight

Best Case

Worst Case

Technology Application

GrossWeight

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Typical Manual Design ProcessLow Speed

VAAAS orSprdsht.

RequirementsMissionsAssumptions

NotionalConcepts

Vehicle SensitivitiesUnderstanding of Trade SpaceRough Sized Baseline Concepts

Baseline MissionPropulsion Parameters / DeckTechnology FactorsOther Analyses

Refined Design and LayoutRefined Weight and BalanceRefined AerodynamicsMission PerformanceTakeoff & Landing Perf.

S&C Assessment

CAD

FLOPS

CASPwt

Propul

Takeoff

6 DOF Sim

Level 0 Analysis

(Empirical)

Level 1 Analysis

(Empirical / Simple Physics)

C

hangeToolSets

ChangeToolSets

HASC/AVL

Panel methodEuler method

NS method

Optimizer /Inv. Solver

FEM / Struct.Analysis

Level 2 Analysis / Prelim. Design

(Physics Based)

~1day

~1week

~6mo.

Also:RCS Analysis

Propul. Integr.Cntl. Law Dev.

Subsys. Integr.Updated Perf.Cost Analysis

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Analysis ExampleNext Generation UCAV Design

Objective: Design affordable, lightweight, subsonic UCAV

GeometrySizing

Variable Fidelity Analysis

SolidWorks

CAD SLAWind tunnel

RCS

CFD

S&C

Physical Models

Analytical Models

FLOPS / ModelCenter tool

Performance analysis

DOE for sensitivity

analysis

Determine feasible W/S, T/W

Cost analysis

Example: Aerodynamic predictions

Low

FLOPS

empirical

Med

Vortex lattice

High

3-D CFD

ResultsPerformance Predictions Configuration Drawings

Capability as a function of size, cost

IGES, STLformats

Response Model

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Analysis ExampleCommon Mobility Planform Study

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Analysis ExampleMobility Sensitivity Study

Objective: Quantify the sensitivities of baseline theater airliftvehicle to various performance capabilities/requirements

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Challenges Facing Configuration

Analysis Geometry Generation and Manipulation Quick synthesis of parametric, well-defined, watertight aircraft

shapes/components

Design using CFD optimization / inverse design (including lower ordermethods)

Parametric structural layout, and timely analysis

Uncertainty Quantification Visualization of Complex Data Sets

Gleaning knowledge and wisdom from information

Imposed Computing Restrictions Mixed OS computing

Licensing of software

Managing and configuring computers without administrative rights

Tools for Unconventional Aircraft Morphing aircraft that change shape/state during mission

Mixed and unconventional power/propulsion sources

Low Reynolds Number / Very small UAVs

Effectiveness-based Design Evaluated at the Mission or Campaign level

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Vision for the Future

Objective: Support directorate vision vehicles and FutureCapability Leads with configuration and mission analysis andtechnology assessment service.

Robust design capability

Robust technology assessment capability

Mission Areas / Vision Vehicles

Mobility, Hunter/Killer UAV, Space Access, Hypersonic Cruise,Sensorcraft / Persistent ISR, Directed Energy platform, Long

Range Strike, etc. Analysis Starting Points

Given the Mission / Capability / Requirements design conceptvehicle

Given a highly defined vehicle / CAD model

assess vehiclecharacteristics, assess impact of technology

Given a generic set of questions regarding technology application,configuration, capability provide quantitative answers

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Vision for the Future (2)

Approach

Establish library of analysis tools that may be flight regime

or type specific (aero codes, weight estimation routines,

trajectory tools, performance programs) Establish processes for similar types of studies using

common automation and process tools (ModelCenter, JMP,

technology assessment methods)

Use common geometry tool, data formats, and bookkeeping

where possible; utilities to convert, manipulate this data

Key Features of System

Flexible and extensible Variable fidelity to the extent possible

Cross Platform / OS-independent

Utilities that generate filewrappers from input files

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Summary

Overview of AFRL, AFRL/RB, and AFRL/RBAApresented.

AFRL/RB serves as a systems integrator, bringing

technology to bear in a complete package for the Air Force.

Usage of tools and frameworks presented.

A variety of tools and frameworks are employed, from

COTS systems to specialized legacy tools. Typically conducted analyses presented.

AFRL/RBAA engages in design and technology

assessment analyses, seeking to meet configuration

research needs for AFRL/RB Discussed vision and challenges for configuration

research.

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Air Vehic les Direc tora teAir Vehic les Direc tora te

We give the Air Force its WingsWe give the Air Force its Wings

. . . 100 years of flight and c ounting . . .. . . 100 years of flight and c ounting . . .