Transcript No Slide Title

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 Education
Multi-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
Visiting Faculty
• Dr. Kota Harinarayana
• Dr. PB Nair, Southampton
• Dr. Sudhakara Rao, VSSC
EVENTS
• Oct 12, 2001 : ARDB ASP Meeting
•
•
•
•
•
•
•
Nov 22, 2001
Jan 2, 2002
Feb 4, 2002
Apr 13, 2002
Jun 4-6, 2002
Jun 10, 2002
Jun 27, 2002
:
:
:
:
:
:
:
ARDB TC Meeting
Prof. A Joshi is new Head
VSSC hands over LVS
1-Day Workshop on MAV
3-Day Workshop on MDO
3rd JPC Meeting
ARDB Meeting.
Visitors
• Mr. Prahlada, Member, JPC
• Dr. BN Suresh, Member, JPC
http://www.casde.iitb.ac.in/History/
System Level Studies
1-Day MAV Workshop (April 13, 2002)
• OILS : Joint Conceptual Studies.
CASDE & Prof. Gandhi (ME),
IITB (June-July, 2002)
• Propulsion systems test facility
Voltage across motor vs Thrust
900.0
2
Torque sensor setup
y = 8.0472x + 13.491x - 2.4657
800.0
y = 8.6958x2 + 14.881x - 6.0936
254
700.0
thrust (in mN)
580
Solar Powered Aircraft
• CASDE & Tata BP Solar
• Partial success
600.0
500.0
measure
400.0
manufac
Poly. (m
300.0
Poly. (m
200.0
12
100.0
Torque
sensor
0.0
0.00
1.00
2.00
3.00
4.00
5.00
6.00
-100.0
Voltage across motor (in V)
55
All dimensions
are in mm
http://www.casde.iitb.ac.in/History/PastEvents/mav-ws/mav-ws-summary.pdf
http://www.casde.iitb.ac.in/History/PastEvents/mav-ws/mav-ws-conclusion.pdf
7.00
8.00
9.00
10.00
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/
RAP - Trajectory Recording
Ram Air Parachute flight tests
GPS data for 45 mins
12000
10000
8000
6000
4000
2000
0
77.94
77.92
77.9
27.096 27.098 27.1
27.11
27.102 27.104 27.106 27.108
27.112
Ph. D Scholars
• DRDL - Hypersonic Vehicles
• VSSC - Design under Uncertainty
International Conference
“Modeling, Simulation, Optimization
For Design of Multi-disciplinary
Engineering Systems”
September 2003
• VSSC - Vehicle + Trajectory Optim
• VSSC - Re-usable Launch Vehicles
http://www.casde.iitb.ac.in/mso-dmes/
Simultaneous Aerodynamic and Structural Optimization of Aircraft Wing
Optimizer
FSQP
I
N
T
E
R
F
A
C
E
History
Block
Aerodynamics
(VLM)
Input
Processor
Aeroelasticity
Iterator
NASTRAN
Interface
Output
Processor
Structures
MSC/
NASTRAN
Analysis Block
Software Architecture
Wing Geometry,
Mach Number
Wing
Geometry
Meshing
Parameters
FEM Nodal
Co-ordinates
NASTRAN
Interface
Code
Loads
Transferred on
FEM Nodes
Load
Transformation
Input file for
NASTRAN
(Auto mesh &
data-deck
Generation)
Max Stresses,
Displacement
s, twist and
Wing
Structural
Mass
Aerodynamic Loads on
Quarter Chord points of
VLM Panels
VLM
(File parsing)
MSC/
NASTRAN
Output file of
NASTRAN
Nodal displacements Displacement
Panel Angles
of Attack
Transformation
Analysis Block
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 Response
FEM Model
3D-Duct Design using Variable Fidelity RSM
http://www.casde.iitb.ac.in/MDO/3d-duct/
3D duct (Y=0.1, Z=0.1, 1=0.1, 2=0.1)
Entry
Exit
Parameterization
Low Fidelity Analysis
(LFA)
• Wall angle < 6°
• Diffusion angle < 3°
• 6 * Eq. Radius < ROC
• Pressure Recovery
• MFL shape is defined by two
cubic splines. (y , z)
• Area variation from entry to exit
is specified as cubic spline. (1 ,
 2)
Mean Flow line variation
y, z
y
z
y1, z1
pentry
0

Aentry
0
Lm
Lm/2
Area variation
2
1
L/3
pmerger
y2 ,z2
2L/3
x
Aexit
L
x

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
MDO Framework Development
Framework Version 1: Data server
MDO Framework Requirements
Architectural Design Problem Executtion
• Intuitive GUI
• object-oriented
• handle large problems
• multi-user support
• standards based
• automate data movement
• visualization
• heterogeneous computing
• distributed computing
• batch processing
1
Initial
Data
Data
Server
6
Result
2
3
4
5
Problem Formulation Information Access
• complex branching
• legacy/proprietary code
• multiple optimizers
• database management
• monitoring system status
• fault tolerance
Analysis 1
Framework Version 2: Architecture
GUI
Configuration
Database
Status/Log
Handler
Sequence
Logic
Execution
Manager
Analysis 3
Analysis 4
Sequence of Execution
Optimizer
Manager
OPT1 OPT2 OPT3
MDO
Controller
Analysis 2
Data
Server
AM1 AM2 AM3
Agent
Problems Attempted
• Airborne Early Warning System
• 3D Duct Design
• Transport Aircraft Wing
• MAV design
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
Traveling Course
On
Design, Build, Fly
Offered at
NIAT, MIT, Parks
100th Year of First Flight
Visit 100 schools
Aerospace to
Schools & Colleges.
Lectures, Demos,
Projects, Workshops