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Progress Presentation ARDB Aircraft Systems Panel October 22, 2002 RCI, Hyderabad

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.

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Progress Presentation ARDB Aircraft Systems Panel October 22, 2002 RCI, Hyderabad

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  1. Progress Presentation ARDB Aircraft Systems Panel October 22, 2002 RCI, Hyderabad Centre for Aerospace Systems Design & Engineering Indian Institute of Technology Bombay

  2. 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

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

  4. 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 • Solar Powered Aircraft • CASDE & Tata BP Solar • Partial success 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

  5. New Open M. Tech Programme 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/

  6. RAP - Trajectory Recording Ram Air Parachute flight tests GPS data for 45 mins

  7. MDO • 3-Day Workshop (June 4-6, 2002) • Progress Aero-elastic Capability Further • Develop MDO-Framework Version-II • Composite teams to solve problems MDO Studies gather momentum P&W shows interest International Conference “Modeling, Simulation, Optimization For Design of Multi-disciplinary Engineering Systems” September 2003 http://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

  8. INTERFACE History Block Aerodynamics (VLM) Aeroelasticity Iterator Input Processor Optimizer FSQP Structures MSC/ NASTRAN NASTRAN Interface Output Processor Analysis Block Simultaneous Aerodynamic and Structural Optimization of Aircraft Wing Software Architecture

  9. Wing Geometry, Mach Number VLM Aerodynamic Loads on Quarter Chord points of VLM Panels FEM Nodal Co-ordinates Load Transformation NASTRAN Interface Code Wing Geometry Meshing Parameters Loads Transferred on FEM Nodes Input file for NASTRAN (Auto mesh & data-deck Generation) MSC/ NASTRAN Output file of NASTRAN (File parsing) Max Stresses, Displacements, twist and Wing Structural Mass Nodal displacements Displacement Transformation Panel Angles of Attack Analysis Block

  10. 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

  11. 3D-Duct Design using Variable Fidelity RSM http://www.casde.iitb.ac.in/MDO/3d-duct/ Entry Exit  Feasible space (LFA) 0  y2 ,z2 y1, z1 pentry Lm x 0 Lm/2 2 Aexit  1 Aentry x L 0 L/3 2L/3 3D duct (Y=0.1, Z=0.1, 1=0.1, 2=0.1) • Parameterization • MFL shape is defined by two cubic splines. (y , z) • Area variation from entry to exit is specified as cubic spline. (1 , 2) • Low Fidelity Analysis (LFA) • Wall angle < 6° • Diffusion angle < 3° • 6 * Eq. Radius < ROC • Pressure Recovery Mean Flow line variation y z • 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 pmerger y, z Area variation

  12. MDO Framework Requirements Framework Version 1: Data server • 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 1 6 Data Server Initial Data Result 2 Optimizer Manager 3 5 Configuration GUI 4 MDO Controller OPT1 OPT2 OPT3 Database Data Server Sequence Logic Sequence of Execution Status/Log Handler Execution Manager Analysis 1 Analysis 2 Analysis 3 Analysis 4 AM1 AM2 AM3 Agent MDO Framework Development Framework Version 2: Architecture • Problems Attempted • Airborne Early Warning System • 3D Duct Design • Transport Aircraft Wing • MAV design

  13. 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

  14. Interested in CASDE? http://www.casde.iitb.ac.in/usage/ Visitors to http:// www.casde.iitb.ac.in/ 25 Visitors per day

  15. 100th Year of First Flight Traveling Course On Design, Build, Fly Offered at NIAT, MIT, Parks Aerospace to Schools & Colleges. Lectures, Demos, Projects, Workshops Visit 100 schools

  16. Thank You

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