New AFRL SBIR PHASE I, II OpenVSP Smart Conceptual Design Tool...

NASA Phase II Kickoff Meeting, June 18, 2015NNX09CC86P SBIR Review, Presented to NASA, July 7th, 2009

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Empirical Systems Aerospace, Inc. www.esaero.com OpenVSP Workshop 2017 Aug. 30th – Sept. 1st

AFRL SBIR PHASE I, II

OpenVSP Smart Conceptual Design Tool Improvements,

Including Inboard Profile Visualization

Presented by:

Nick Brake

Empirical Systems Aerospace, Inc.

[email protected], [email protected]

For:

OpenVSP Workshop 2017

Work Funded by:

AFRL Phase I, II SSBIR

Phase IIIDetail Design

Phase IConceptual Design

• Basic Mission Requirements

• Range, Altitude, Speed

• Basic Material Properties

s/r E/r $.lb

• Aeroelastic Requirements

• Fatigue Requirements

• Flutter Requirements

• Overall Strength Requirements

• Local Strength Requirements

• Producibility

• Functional Requirements

3O 5O

Vs.

Vs.

Phase IIPreliminary Design

Vs.

Geometry

Air Foil Type

R

t/c

l

D

Design Objectives

Drag Level

Weight Goals

Cost Goals

• Basic Internal Arrangement• Complete External Configuration

Camber, Twist Distributions

Local Flow Problems Solved• Major Loads, Stresses, Deflections

• Detail Design Mechanisms

Joints, Fittings & Attachments• Design Refinements as Results

of Test

Feasible Design Mature Design Shop Drawings

Kn

ow

nR

esu

lts

Ou

tpu

tT

RL

2-3 4-5 6-7

Leland Nicolai, Fundamentals of Aircraft and Airship Design, AIAA, 2010.

mailto:[email protected]



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Project Objectives

• Significantly improve OpenVSP’s utility

as a conceptual and preliminary design software by taking

advantage of new features in v3.0

• Enhance the speed and ease of the design process

in which users will establish, modify, visualize, and

analyze the internal and external aircraft configuration

• Overarching goal:

Automate portions of the conventional design

process


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Phase I & II – Tasks

Phase I (6 months)

Task 1 – Inboard Profile Visualization

Task 2 – Aircraft Subsystem User Defined Component Library

Task 3 – Advanced Parameter Linking

Task 4 – Aircraft Subsystem Advanced Parameter Link Library

Task 5 – Drag Buildup Tool

Phase II (2 years)

Task 1 – Master Aerodynamic Analysis Tool

Task 2 – Sub-Aero Tool Development and Modification

2.1 Transonic Drag Rise Module

2.2 Wave Drag Module

2.3 Induced Drag Module Through VSPAERO

Task 3 – Basic Static Stability Analysis

Task 4 – Radar Cross Section (RCS) Analysis Using Xpatch®

Task 5 – 2D Drawing Exportability

Task 6 – Saved Parameter Settings

Task 7 – Addition of Structure Modeling Capability

Task 8 – Conformal Feature

Task 9 – Blendable Wings

Task 10 – Addition of a *.VSP to *.VSP3 Converter

Task 11 – VSPAERO Verification & Validation

Task 12 – Wiki Documentation

Wave Drag

Induced Drag Module (VSPAERO)

Blendable WingsUser Parms &

Adv. Param Link

Conformal

Components

Clipping Plane /

Inboard Profile

User Components


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Task 1 – Master Aerodynamic Analysis Tool

(Aero Manager)

• Interact with internal modules and

external codes in order to gather the

necessary information to properly

analyze a configuration’s

aerodynamics.

• Acts as a liaison between OpenVSP,

VSPAero, and the modules developed

in Task 2 of this proposal.

• Provides quick analysis of lift and drag,

enabling geometric sensitivity trades

and polar generation.

Figure: Preliminary Aero Manager Flow Path


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Task 1: Master Aero Tool

GUI Overview

Progress

Updates

Tool

Selection

(Buttons to

each tool’s

GUI)

General Flow

Conditions

Geometry

Selection

Master Run

Button

Launch Plot

Screen

Applies

Geometry To

All Tools

Status: UNDER DEVELOPMENT


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Task 1: Master Aero Tool

Plot Screen Overview

Master Aero

Tool Results

Expanded Flow

Condition Selection

Legend for Multiple

Result Selection

Plot Window


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• The quick exchange of geometry

constructed in OpenVSP into the drag

tool enables rapid analysis and

sensitivities integral to concept

development.

• improve the parasite drag fidelity by

adding transonic drag rise, induced drag,

and wave drag.

Task 2 – Sub-Aero Tool Development and

Modification

Typical Drag Rise Model Wave Drag Induced Drag

[VSPAERO]

Phase I Parasite Drag

[Excel]


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Task 2: Development and Modification of

Sub Aero Tools

2.2 - Wave Drag Module

2.3 - Induced Drag Module

Through VSPAERO

2.1 – (Parasite)\Transonic Drag Rise Module


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Objectives

• Enable VSPAero to calculate basic static stability derivatives such as

𝐶𝐿𝛼, 𝐶𝑀𝛼, 𝐶𝑁𝛽

, etc. Adding sub-surfaces to the degenerate geometry tool

will be included in this work.

• OpenVSP will be modified to support control surfaces and stability

qualities such as elevator effectiveness, 𝐶𝑀𝛿𝑒.

• Extend GUI and OpenVSP API interface to fully support VSPAERO rotor

and control surface features

• Initial integration of VSPAERO 4.x feature sets

• Extend data reduction and provide top-level static stability analysis and

parameters


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Task 4 – Radar Cross Section (RCS) Analysis

Using Xpatch®

Objectives

• Add export option for Xpatch facet files for

Meshes.

• Support both CompGeom & CFDMesh

geometry discretization options.

• Support subsurface modeling capability to

the extent allowed by the facet files.

CompGeom CFDMesh


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Task 5 – 2D Drawing Exportability

Objectives

• OpenVSP will be extended to output the feature

lines as AutoCAD Drawing Exchange Format

(DXF) files.

– The DXF format has become an industry standard

CAD interchange format for 2D and 3D line drawings.

• Extend to support Scalable Vector Graphics

– Viewable in a browser


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Task 6 – Saved Parameter Settings

Objectives

• Ability to save parameter sets

Status: RELEASED

Different Model Conditions Made Available by a Saved Parameters Option


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Task 7 – Addition of Structure Modeling

Capability

Objectives

• Support structures for ALL

component types

• Support sub-surface attributes

• Support modeling full-depth

structures as FEA shell elements

• Support modeling no-depth

structures as FEA beam elements

• Support modeling of key points in

the FEA mesh

Status: UNDER DEVELOPMENT

Presentation by Justin Gravett


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Task 8, 9 – Conformal Components, Blendable

Wings

Task 8 Conformal Components

• OpenVSP will be extended to support

conformal components.

– Conformal components will derive their

shape from another component.

– Example: fuel tank, payload bay volumes

• Packaging tool: Snap-To

Presented by: Rob McDonald @ 2pm

Task 9 Blendable Wings

• Extend wing component to support

blended lofting between airfoil

sections.

Presented by: Rob McDonald @ 3pm

Blendable Wings

Conformal

Components

Snap-To


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Objectives

• OpenVSP v3 will be modified to

import existing files from v2.

• The converter will open existing

*.vsp files and will interpret the

parameters in terms of the new

v3 components.

Task 10 – Addition of a *.VSP to *.VSP3

Converterv3Counterpart EverPossible Status

Header Y Y Complete

Mainfile/modelstructure Y Y CompleteComponentTypes

GenericGeom

PositionandSymmetry Y Y Complete

MaterialandColor Y Y Complete

AttachmentandParent/Child Y Y Complete

TesselationandMassProperties Y Y Complete

Pod Y Y Complete

Blank Y Y CompleteFuse2 Y Y Complete

MS_Wing Y Y CompleteFuse1 Y Y Complete

HWB N Y Waitingonv3ImplementationProp N Y Waitingonv3Implementation

Duct N N NotPlanned

Havoc N N NotPlanned

CabinLayout N N NotPlanned

Engine N N NotPlanned

ExternalStore N N NotPlanned

Nonuser-facinglegacycomponents N N NotPlanned

CrossSectionsandAirfoilsPoint Y Y Complete

Circle Y Y Complete

Ellipse Y Y Complete

Box Y Y Complete

RoundBox Y Y CompleteGeneral Y Y Complete

File Y Y Complete

Edit(BezierCurves) N Y Waitingonv3Implementation

NACA4-Digit Y Y Complete

Biconvex Y Y CompleteWedge Y Y Complete

NACA6-Series Y Y Complete

File Y Y Complete

Other

CFDMeshsources Y Y NotYetImplementedCFDMeshglobalsettings Y Y NotYetImplemented

Userparms Y N CanNotImplement

ParameterLinks Y N CanNotImplement

WingStructurecomponents N N CanNotImplement

Textures Y Y NotPlannedLabels Y Y NotPlanned

AeroCenter,reference,andCGstuff N N CanNotImplement


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Task 11 – VSPAERO V&V

Test Picture

Hershey-Bar Wing

Swept Wing &

Bertin-Smith Wing

Warren-12 Wing

Von Karman-Trefftz Airfoil

Ellipsoid

Cessna 172

Objectives

• Verify VSPAERO results with

against authoritative theoretical

and empirical solutions

• ID bugs in UI/solver

• Develop verification toolset

• Document best analysis

practices

Presentation by Lucas Payne


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Task 12 – Wiki documentation

Objectives

• Many new analyses need

dedicated reference and

documentation to be useful

• Make verification artifacts

easily accessible

• Fill the documentation gap

for VSP

Example: Parasite drag

equations shown


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Thank You AFRL


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NASA 2016 SBIR PHASE I

Physics-Based Conceptual Design Flying Qualities Analysis using

OpenVSP and VSPAERO

Presented by:

Nick Brake

Empirical Systems Aerospace, Inc.

[email protected], [email protected]

For:

OpenVSP Workshop 2017

Work Funded by:

NASA Phase I SBIR




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Proposal:

Tool suite enhancements to enable rapid physics based handling qualities assessments through an efficient workflow

Tech. Objectives:

• Improved vehicle definition (Controls & Mass properties)

• Integrated tool suite for handling qualities with physics based models

• Simple kinematics engine

Proposal & Tech. Objectives


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1. Improve Sub-Surface Based

Control Surfaces

2. Mass Database

3. Mass Properties for Partially

Filled Fuel Tanks

4. Interactive Tail Sizing

5. Trim Solver

6. Dynamic Model Synthesis

7. Tail Size Assessment Tool

8. OpenVSP Representation of

Simple Kinematic Joints

Task Overview

1 2 3

5

7

4

8

6


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Objective:

• Improve control surface definition for better representation of real surfaces

Status: RELEASED

• Note: workaround for VSPAERO

Task 1: Improved Sub-Surface Based

Control Surfaces

Before After Before After

Root & Tip angle

Hinge Line

VisualizationImproved

curvature


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Objective:

• Increase flexibility and accessibility of mass prop. info

Sub-tasks include:

• Add override mass prop. parms. for all components

• GUI - add table buildup

• Mass prop CSV data export

• Matlab script to plot CG chart

• Add variable mass components (task 3 dependency)

Pre-requisites:

• none

Task 2 – Mass Database Tool


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Task 2 – Mass Database Tool


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Objective:

• Calculate mass properties impact of fuel tanks

Sub-tasks include:

• GUI development

• Data representation design

• Geometry computation

• Data export to file

Pre-requisites:

• none

Task 3 – Mass Properties for Partially Filled

Tanks


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Task 3 – Mass Properties for Partially Filled

Tanks

Variable wing tank

sliced in Z

Vehicle sliced in Xdirection


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Objective:

• Provide facility to interactively asses typical tail volume sizing calculations

Sub-tasks include:

• GUI development

• Algorithm implementation– SAE 670370 Fuselage

Configuration Studies by J. Morris & D. M. Ashford of Douglas Aircraft

• Testing & verification

Pre-requisites:

• none

Task 4 – Interactive Tail Sizing

Example tail sizing implementation based on SAE 670370

Source: “Betterer_Tail_Volume_Coeff.xlsx”, Andy Hahn


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Task 4 – Interactive Tail Sizing


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Objective:

• Calculate flight state and control deflection to satisfy simple user defined constraints

• Replicate AVL trim solver

Sub-tasks include:

• GUI - control allocation

• GUI - flight condition specification

• Trim solver

• API integration

Pre-requisites:

• VSPAERO control derivatives

Task 5 – Trim Solver


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Objective:

• Increase accessibility of aircraft dynamics characteristics

Sub-tasks include:

• GUI – flight condition input (trim condition)

• Dynamics model calculation

• Calculate additional flying qualities parameters

• Data export to results file

Pre-requisites:

• VSPAERO control derivatives

• Task 5 – Trim solver

Task 6 – Dynamic Model Synthesis

Parameter Equation Description

LCDP 𝐿𝐶𝐷𝑃

= 𝐶𝑛𝛽 −𝐶𝑛𝛿𝐴𝑖𝑙𝑒𝑟𝑜𝑛𝐶𝑙𝛿𝐴𝑖𝑙𝑒𝑟𝑜𝑛

∗ 𝐶𝑙𝛽

Lateral Control DivergenceParameter. This is the tendency forlateral divergence

φ/β effect 𝜙

𝛽=|𝑒𝜙|𝐷𝑅

|𝑒𝛽|𝐷𝑅

Measures the degree of rollingresponse in the Dutch roll mode.Ratio of magnitude of φ and βeigenvectors of dutch role mode

Large value: DR mode is primarilyrolling

Small value: DR mode is primarilyyawing

Table 1. Example additional flying qualities parameter output

ሶ𝑋 = 𝐴 ∗ 𝑋 + 𝐵 ∗ 𝑈

𝑋 = 𝑢,𝑤, 𝑞, 𝜃, 𝑣, 𝑝, 𝑟, 𝜙, 𝑥, 𝑦, 𝑧, 𝜓 𝑇

𝐴 = 𝑠𝑦𝑠𝑡𝑒𝑚 𝑑𝑦𝑛𝑎𝑚𝑖𝑐 𝑚𝑎𝑡𝑟𝑖𝑥𝐵 = 𝑐𝑜𝑛𝑡𝑟𝑜𝑙 𝑖𝑛𝑝𝑢𝑡 𝑚𝑎𝑡𝑟𝑖𝑥

𝑈 = [𝑐𝑜𝑛𝑡𝑟𝑜𝑙 𝑣𝑒𝑐𝑡𝑜𝑟]

State Space Dynamics Model


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Task 6 – Dynamic Model Synthesis


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Sub-tasks include:

• GUI – Input specification

• Parameter sweep

• GUI – Plot generation

• GUI – Data Export

capability

Pre-requisites:

• Task 5 – Trim Solver

• Task 6 – Dynamic Model

Synthesis

Task 7 – Tail Sizing Assessment Tool

Objective:

Visualize impact of tail size parameters


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Task 7 – Tail Sizing Assessment Tool


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Objective:

• Increase usability for modeling control surfaces, high lift devices, landing gear

Sub-tasks include:

• GUI development

• Kinematic relationship implementation

Status: RELEASED

Task 8 – Simple Kinematic Joints


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Simple Hinge

Grumman Hinge

1 2 3

4 5 6


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Phase II Objectives:

1. Extend trim solver to optimization

2. Verify underlying analysis dependency (VSPAERO)

3. Extend similar workflow for High Lift system design and analysis

4. Accessible documentation

Phase II tasks:

1. Trim solver optimization and constraints

2. Trim solver common preset wizards

3. VSPAERO Verification & Validation

4. VSPAERO v4 support

5. High lift system layout tool

6. Full span multi-element airfoils for wing geometries

7. Full span airfoil step & cove modeling

8. Partial span high lift airfoil configurations

9. 2D airfoil stack export & meta-geometry export

10. Additional documentation and Wiki site updating

Phase II (Proposed)


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Thank You NASA


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Ben Schiltgen

[email protected]

Nick Brake

[email protected]

ESAero

[email protected]

Contact Information





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OpenVSP Software Development

Improvements for Physics Base Conceptual DesignRapid Physics Based Analysis to Enable Eng.

• ESAero has been the primary OpenVSP developer since 2014

• AFRL Phase I, Phase II

• NASA Phase I

• 20+ major new features in the areas of::

• Aerodynamics – Parasite\Transonic Drag*, Wave Drag,

Induced Drag (VSPAero), Master Aero Tool*,

• Stability & Control – Non-Linear Trim Solver, Dynamic

Model Synthysis Tool, Tail Sizing & Constraint Tool

• Visualization – Inboard Profile, Constraint Plots (for

handling qual.), VSPAero Results Viewer

• Geometry – User-Defined Components, Blendable Wings*,

Conformal Compoents*, Structures*, Mass Properties

Database Tool & Custom Properties, Kinematic Constraints

• Other – Advanced parameter linking, XPatch File Export,

2D DXF & SVG File Export, Saved Parameter Settings

*In ProgressSimple Hinge

Grumman Hinge

1 2 3

4 5 6

Trim Solver, Root Locus, Constraint Plots

Wave Drag

Induced Drag Module (VSPAERO)Blendable Wings Kinematic Constraints

Conformal

Components

New AFRL SBIR PHASE I, II OpenVSP Smart Conceptual Design Tool...

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