Progress Presentation

ARDB Aircraft Systems Panel

October 22, 2002

RCI, Hyderabad

Centre for Aerospace Systems Design & Engineering

Indian Institute of Technology Bombay

Objectives, Mission

SDE EducationMulti-disciplinary Design Optimisation

System Level Studies

CASDE Shall Strive to Develop and Retain

Strong Links With Indian Aerospace Industry

And Shall

Engage in R&D Activities

With

Worldwide Visibility

October 12, 2001 to October 22, 2002

EVENTS • Oct 12, 2001 : ARDB ASP Meeting• Nov 22, 2001 : ARDB TC Meeting• Jan 2, 2002 : Prof. A Joshi is new Head• Feb 4, 2002 : VSSC hands over LVS• Apr 13, 2002 : 1-Day Workshop on MAV• Jun 4-6, 2002 : 3-Day Workshop on MDO• Jun 10, 2002 : 3rd JPC Meeting• Jun 27, 2002 : ARDB Meeting.

Visitors • Mr. Prahlada, Member, JPC• Dr. BN Suresh, Member, JPC

Visiting Faculty • Dr. Kota Harinarayana• Dr. PB Nair, Southampton• Dr. Sudhakara Rao, VSSC

http://www.casde.iitb.ac.in/History/

System Level Studies

http://www.casde.iitb.ac.in/History/PastEvents/mav-ws/mav-ws-summary.pdfhttp://www.casde.iitb.ac.in/History/PastEvents/mav-ws/mav-ws-conclusion.pdf

1-Day MAV Workshop (April 13, 2002)• OILS : Joint Conceptual Studies. CASDE & Prof. Gandhi (ME), IITB (June-July, 2002)• Propulsion systems test facility

y = 8.6958x2 + 14.881x - 6.0936

y = 8.0472x2 + 13.491x - 2.4657

-100.0

0.0

100.0

200.0

300.0

400.0

500.0

600.0

700.0

800.0

900.0

0.00 1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00

Voltage across motor (in V)

thru

st (

in m

N)

measured values

manufacturers data

Poly. (measured values)

Poly. (manufacturers data)Solar Powered Aircraft• CASDE & Tata BP Solar • Partial success

Applied MECHATRONICS Course

Course with a difference

2 theory and 3 lab hours per week.

Project on a miniature ground vehicle.

sensors, actuators, micro-controllers, etc

http://www.casde.iitb.ac.in/IMSL/

New Open M. Tech Programme

RAP - Trajectory Recording

Ram Air Parachute flight tests

GPS data for 45 mins

27.096 27.098 27.1 27.102 27.104 27.106 27.108 27.11 27.11277.9

77.92

77.94

0

2000

4000

6000

8000

10000

12000

3-Day Workshop (June 4-6, 2002)

• Progress Aero-elastic Capability Further

• Develop MDO-Framework Version-II

• Composite teams to solve problems

International Conference

“Modeling, Simulation, Optimization

For Design of Multi-disciplinary

Engineering Systems”

September 2003http://www.casde.iitb.ac.in/mso-dmes/

Ph. D Scholars • DRDL - Hypersonic Vehicles

• VSSC - Design under Uncertainty

• VSSC - Vehicle + Trajectory Optim

• VSSC - Re-usable Launch Vehicles

P&W shows interest

MDO Studies gather momentum

Software Architecture

Optimizer FSQP

I

N

T

E

R

F

A

C

E

History Block

Input Processor

Output Processor

Aerodynamics (VLM)

Structures MSC/

NASTRANNASTRAN

Interface

Analysis Block

AeroelasticityIterator

Simultaneous Aerodynamic and Structural Optimization of Aircraft Wing

NASTRAN Interface

Code

Wing Geometry Meshing

Parameters

Load Transformation

Input file for NASTRAN

Output file of NASTRAN

MSC/ NASTRAN

Loads Transferred on

FEM Nodes

FEM Nodal Co-ordinates

Aerodynamic Loads on Quarter Chord points of

VLM Panels

Max Stresses, Displacements, twist and

Wing Structural

Mass

Nodal displacements

Panel Angles of Attack

VLMWing Geometry,Mach Number

DisplacementTransformation

Analysis Block

(File parsing)

(Auto mesh & data-deck

Generation)

Figs. 1-4: Development of Wing model and loads

Figs. 5-6: Load Transformation Process

5 - Aerodynamic Loads and its Response

6 - Structurally equivalent Loads and its ResponseFEM Model

Entry Exit

y, z pmerger

x0 LmLm/2pentry

y1, z1 y2 ,z2

x

0 LL/3

Aentry

Aexit

2L/3

1

2

Mean Flow line variation

Area variation

3D duct (Y=0.1, Z=0.1, 1=0.1, 2=0.1)

Low Fidelity Analysis (LFA)• Wall angle < 6°• Diffusion angle < 3°• 6 * Eq. Radius < ROC• Pressure Recovery

Parameterization

• MFL shape is defined by two cubic splines. (y , z)

• Area variation from entry to exit is specified as cubic spline. (1 , 2)

Feasible space (LFA)

0

Response Surface Method• Define reduced design space through LFA• DOE in reduced design space• Perform high fidelity analysis at DOE

points (NS simulation for distortion and swirl)

• Replace high fidelity analysis with response surface

• Optimize using RS

3D-Duct Design using Variable Fidelity RSMhttp://www.casde.iitb.ac.in/MDO/3d-duct/

y z

Architectural Design• Intuitive GUI• object-oriented• handle large problems• multi-user support• standards based

Problem Formulation• complex branching• legacy/proprietary code• multiple optimizers

Problem Executtion• automate data movement• visualization• heterogeneous computing• distributed computing• batch processing

Information Access• database management• monitoring system status• fault tolerance

MDO Framework Requirements

DataServer

Sequence of Execution

Analysis 2 Analysis 3 Analysis 4

InitialData

Result

Analysis 1

1

23

45

6

Framework Version 1: Data server

Database

Configuration

ExecutionManager

Sequence Logic

MDOController

Status/LogHandler

DataServer

OPT1

Optimizer Manager

OPT2 OPT3

AM1

Agent

AM2 AM3

GUI

Framework Version 2: Architecture

Problems Attempted• Airborne Early Warning System• 3D Duct Design• Transport Aircraft Wing• MAV design

MDO Framework Development

CASDE – Proposal for Phase II

• 2 Years– MDO– SDE Education– Integrated Modelling & Simulation

• Funds – 53.475 + 44.275 = 97.75

• Draft Proposal pending with JPC/SPC

Interested in CASDE?

Visitors to http:// www.casde.iitb.ac.in/25 Visitors per day

htt p

: //w

ww

.ca s

de.i i

t b.a

c .in

/usa

ge/

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100th Year of First FlightTraveling CourseOn

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