ACD506 Sesssion0 Aircraft Conceptual Design

M. S. Ramaiah University of Applied Sciences

1Faculty of Engineering & Technology

Module Code: ACD506

Module Title: Aircraft Conceptual Design

Module Leader:

Dr. H.K. [email protected]



Module Details

Course: M. Tech. in Aircraft Design

Department: Automotive and Aeronautical Engineering

Head of the Department: Dr. S. Srikari

([email protected])

Faculty: Engineering & Technology

Dean: Prof. H K Narahari ([email protected])



Why This module

The objectives of the course are to enable the students to:

Explain the construction, working principles and functional requirements of aircraft systems with respect to their performance

Convert the customer requirements to viable design specifications and evolve conceptual design

Model, simulate, analyse and validate aircraft conceptual design to meet operational requirements using commercially available tools

Demonstrate Critical, analytical, problem solving and research skills in the domain of Aeronautical Engineering

Develop a career in Aeronautical Engineering

Practice Teamwork, lifelong learning and continuous improvement

The module is being delivered to meet the highlighted objective of the course to meet the course aim.



Module Aim and Summary

It is intended to prepare students to understand the customer and mission requirements of an aircraft and derive a conceptual layout including wing plan form and size, choice of propulsion system along with subsystems as well as selection criteria for navigation systems. Students are taught various aircraft characteristics and their impact on performance, stability and control. They are taught to estimate thrust requirement, select the type propulsion device and arrive at its installation along with subsystems. Students will be trained on the impact design choices have on the overall performance vis--vis mission requirement, and trained to critically evaluate each choice



Module Learning OutcomesAfter undergoing this module students will be able to:

Identify and describe requirements for different classes of aircraft

Contrast and explain the design requirements obtained based on fundamental principles and historical data

Evaluate the design specifications and then critically arrive at an aircraft design that is likely to meet the requirements

Analyse the various constraints coming from specifications and choose key parameters (total weight, wing plan form, thrust/power required etc.)

Calculate and compare performance and stability characteristics against design goals and make necessary changes to choices already made and generate a layout

Analyse design issues for aerodynamics, propulsion, structure, weights, stability, cost, and performance, and then calculate range or sizing the design to a specified mission



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Module Learning Outcomes

After undergoing this module, students should be able to:

1. Identify and apply the design requirements for an aircraft in response to requirements based on fundamental principles and statistical data.

2. Describe design specifications and then critically discuss an aircraft design that is likely to meet the requirements

3. Apply engineering knowledge and applied skills to a design problem

4. Analyse design issues for aerodynamics, propulsion, structure, weights, stability, cost, and performance, and then calculate range or sizing the design to a specified mission and generate a layout.



Module indicative content :

Overview of the design process, Design requirements

Wing and tail geometry, Thrust-to-weight and wing loading

Configuration layout and loft, Wing/tail layout and location,

Passengers, payload, and crew

Aerodynamic analysis, performance Stability, control, and handling qualities

Propulsion and fuel system , Propulsion analysis , intake , nozzle integration

Loads, structures, and weights,

Cost estimation, airline economics

Module Syllabus



Method of Assessment Contd..There are two components for assessment in this subject:

Component - 1: 50% weight

Assignment (30% weight) followed by a presentation on the assignment (10% weight) and a laboratory examination (10% weight).

A word processed assignment is to be submitted followed by a presentation by the student

Component - 2 : 50% weight Written Examination (50% weight).

The assessment questions are set to test the learning outcomes. In each component certain learning outcomes are assessed. The following table illustrates the focus of learning outcome in each component assessed:



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Module Resources

Module Notes,Books

1. Ajoy Kumar Kundu, Aircraft Design, Cambridge Unversity Press, 2010

2. Daniel P Raymer, Aircraft Design A conceptual Approach, 2nd Edition, AIAA Education Series, 1992

3. Jon Roskam, Airplane Design, Vol 8, Roskam Aviation and Engineering Corporation, 1995

4. Ray Whitford, Design for Air Combat, Janes Publication Inc, 1987

5. Roskam, J. and Lan, C.-T., Airplane Aerodynamics and Performance, DAR corporation, 1997.



Module Resources

7. Kroo, Ilan., Shevell, Richard., : Aircraft Design: Synthesis and Analysis, eBook

Journals 1. Journal of Aircraft 2. Aviation Weekly 3. Flight International Web Pages 1. http://www.dept.aoe.vt.edu/~mason/Mason_f/SD1.html2. http://www.dept.aoe.vt.edu/~mason/Mason_f/MRsoft.html



Module Delivery Schedule for TheoryNumber of Module Credits: 5

LectureNo.

Date Time

Day Topic Delivered By

Additional Activity

1 06/07/2015

9:3

0A

M t

o 0

1:0

0 P

M

Mon. Aircraft Requirements Analysis HKN

2 07/07/2015 Tue. Aircraft Weight Estimation and Constraint Analysis

HKN

3 08/07/2015 Wed. Aircraft Wing Design HKN

4 09/07/2015 Thurs. Applied combustion -Gas Turbine CombustorsJet Breakup and Droplet Formation

HKN

5 10/07/2015 Fri. CFD MDD

6 13/07/2015 Mon. Aircraft Power Plant Selection QHN

7 14/07/2015 Tue. Aircraft Structural Layout VKB

8 15/07/2015 Wed. Case Study 1 : Combat Aircraft HKN

9 16/07/2015 Thurs. Case Study 2 : Commercial Aircraft HKN

10 17/07/2015 Fri. Case Study 2 : Commercial Aircraft HKN



Module Delivery Schedule for Lab Number of Module Credits: 5

LectureNo.

Date Time

Day Topic Delivered By AdditionalActivity

1 06/07/2015

2.0

0 P

M t

o 0

5:3

0 P

M

Mon. Work through Case Studies : Combat

AirplaneMSP / SHIVA

2 07/07/2015 Tue. Work through Case Studies : Commercial Airliner

MSP / SHIVA

3 08/07/2015 Wed. Aircraft Wing Design MSP / SHIVA

4 09/07/2015 Thurs. Applied combustion -Gas Turbine CombustorsJet Breakup and Droplet Formation

MSP / SHIVA

5 10/07/2015 Fri. CFD MSP / SHIVA

6 13/07/2015 Mon. Aircraft Power Plant Selection MSP / SHIVA

7 14/07/2015 Tue. CFD MSP / SHIVA

8 15/07/2015 Wed. CFD MSP / SHIVA

9 16/07/2015 Thurs. Work through Cast Study MSP / SHIVA

10 17/07/2015 Fri. Work through Cast Study MSP / SHIVA



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Module Delivery

Theory:

Dr. H.K Narahari

Laboratory:

Mr. H.G. Shivakumar

Dr. M. Sivapragasam



Lecture No. 1 :Aircraft Requirements Analysis

At the end of this lecture, student will be able to

Analyse Customer requirements : Types and differences between them

Derive components weights: Payload, Fuel, Structure, and Total Weight

Start the Design Process



Lecture No. 2 :Weight Estimation and Constraint Analysis


Collate important Statistical data

Various correlations and thumb rules

Perform Preliminary weight estimation

and check its Assumptions and sensitivity of end result

Use of requirements to derive constraint diagrams for T/W and W/S



Lecture No. 3 :Aircraft Wing Design


Choose Wing loading (W/S) based on different performance requirements

Design Planform considering its dependence on various design elements

Select a Wing cross-section (airfoil)

Choose appropriate High lift devices



Lecture No. 4 :Aircraft Fuselage and Tail Layout


Explain Fuselage layout and design including area development for transonic and supersonic aircraft

Describe the landing gear requirements

Compute Tail Plane design size and location

Design elevator size and deflection for horizontal tail plane

Design Rudder size and deflection for vertical tail

Identify various physical process and mechanism involved in designing combustion system



Lecture No. 5 :Computational Fluid Dynamics





Lecture No. 6 :Aircraft Power plant Selection





Lecture No. 7 :Aircraft Structural Layout





Lecture No. 8 :Case Study 1 : Combat Aircraft


Analyse the Requirements from the case study

Estimate the maximum takeoff weight of the aircraft from different methods

Evaluate crucial performance requirements and develop Constraint Diagram and estimate (T/W) and ( W/S)

Compare different wing configurations and choose the design which meets the requirements based on low-fidelity computational methods

Create CAD models of the wing and tail sections and verify performance using CFD tool.

Arrive at an overall configuration



Lecture No. 9 :Case Study 2 : Commercial Airliner










Lecture No. 10 :Case Study 2 : Commercial Airliner











Analyse the requirements of a Combat Aircraft

Estimate the maximum Takeoff weight and develop constraint Diagram

Lab No. 1:Work Through Case Study




Analyse the requirements of a Commercial Airliner






Analyse the requirements of a Commercial Airliner


Estimate the (T/W) and (W/S)




At the end of this Lab lecture, student will be able to

Create CATIA models for the chosen wing

Lab No. 4:Create CATIA Models



Lab No. 5:Create CATIA Models


Create CATIA models for the chosen wing




Create 3D grid over the geometry

Run CFD tool ANSYS / FLUENT on the required geometry

Lab No. 6:Run CFD tool




Create 3D grid over the geometry

Run CFD tool ANSYS / FLUENT on the required geometry

Lab No. 7:Run CFD tool




Work Through individual team case studies




Thank you !

Documents

ACD506 Sesssion0 Aircraft Conceptual Design