Proposed Scheme and Syllabus from academic year 2010-11 Aeronautical Engineering




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Proposed Scheme and Syllabus from academic year 2010-11

Aeronautical Engineering


VII Semester


Sl

No

Subject

Code

Title

Teaching Dept.

Teaching

Hours / week

Examination

Th.

Pr.

Dura-tion

I.A

Marks

Theory/

Practical

Total

Marks

1

10AE71

Control Engineering

AE/ME

04

--

03

25

100

125

2

10AE72

Aircraft Structures-II

AE

04

--

03

25

100

125

3

10AE73

Aircraft Stability and Control

AE

04

--

03

25

100

125

4

10AE74

Gas Turbine Technology

AE

04

--

03

25

100

125

5

10AE75*

*Electives II – (Group B)

AE

04

--

03

25

100

125

6

10AE76*

*Electives III –(Group C)

AE

04

--

03

25

100

125

7

10AEL77

Design, Modeling and

Analysis Laboratory

AE

--

03

03

25

50

75

8

10AEL78

Simulation Laboratory

AE

--

03

03

25

50

75

Total


24

06

24

200

700

900



Note: One question has to be set for every 6 to 8 hours of teaching.


Subject

Code

* Elective II (Group B )

Subject

Code

* Elective III (Group C )

10AE751

Optimisation Techniques

10AE761

Experimental Stress analysis

10AE752

Computational Fluid Dynamics

10AE762

Helicopter Dynamics

10AE753

Aircraft Maintenance, Repair and Overhaul

10AE763

Space Mechanics and Launch Vehicles

10AE754

Statistical Quality Control

10AE764

Smart Materials

10AE755

Theory of plates and shells

10AE765

Agile Manufacturing

10AE756

Nondestructive Testing

10AE766

Robotics

10AE757

Mechatronics and Microprocessor

10AE767

Industrial and Experimental Aerodynamics

10AE758

Total Quality Management

10AE768

Micro and Smart Systems Technology


* Students shall register for one subject from each Group B and C Electives










Control Engineering





Sub Code:

10AE71




IA Marks:

25

Hrs/ Week:

04




Exam Hours:

03

Total Hours:

52




Exam Marks:

100



Syllabus is same as existing Sub code 10ME82



Aircraft Structures - II


Sub Code:

10AE72




IA Marks:

25

Hrs/ Week:

04




Exam Hours:

03

Total Hours:

52




Exam Marks:

100



PART A


Unit 1. 06 Hrs

Introduction to Aircraft Structural Design:

Structural layout of the Airplane and components, Structural design V-n diagram,loads acting on major components such as wing, fuselage, tails, landing gear etc.,Concept of allowable stress and margin of safety.


Unit 2. 06 Hrs

Unsymmetrical Bending:

Bending stresses in beams of unsymmetrical sections – Bending of symmetric sections with skew loads


Unit 3. 06 Hrs

Shear Flow in Open Sections:

Thin walled beams, Concept of shear flow, shear centre, Elastic axis. With one axis of symmetry, with wall effective and ineffective in bending, unsymmetrical beam sections.


Unit 4. 08 Hrs

Shear Flow in Closed Sections:

Bredt – Batho formula, Single and multi – cell structures, Approximate methods, Shear flow in single & multi-cell structures under torsion. Shear flow in single and multi-cell under bending with walls effective and ineffective.


PART B


Unit 5. 06 Hrs

Buckling of Plates:

Rectangular sheets under compression, Local buckling stress of thin walled sections, Crippling stresses by Needham’s and Gerard’s methods, Thin walled column strength. Sheet – stiffener panels. Effective width, inter rivet and sheet wrinkling failures.


Unit 6. 08 Hrs

Stress Analysis in Wing And Fuselage:

Procedure – Shear and bending moment distribution for semi cantilever and other types of wings and fuselage, thin webbed beam. With parallel and non parallel flanges, Shear resistant web beams, Tension field web beams (Wagner’s).


Unit 7. 06 Hrs

Design of Aircraft Structure:

Design criteria – Safety Factor – Design life criteria – Analysis method – Life Assessment procedures – Design Principle – Future Airworthiness Requirements– Two bay crack criteria – Widespread Fatigue damage.


Unit 8. 06 Hrs

Joints and Fittings And Introduction to Post Buckling:

General theory for the design of fittings, Estimation of fitting design loads, design of riveted, bolted and welding joints, post buckling of structures, concept of effective width.


Text Books:


1. Megson, T.M.G., “Aircraft Structures for Engineering Students”, Edward Arnold,1995.


2. Peery, D.J., and Azar, J.J., “Aircraft Structures”, 2nd edition, McGraw–Hill, N.Y.,

1993.


Reference:


1. Bruhn. E.H. “Analysis and Design of Flight vehicles Structures”, Tri – state off set

company, USA, 1985.


2. Rivello, R.M., “Theory and Analysis of Flight Structures”, McGraw-Hill, 1993.


3. D Williams & Edward Arnold, An Introduction to the Theory of Aircraft Structures


Scheme of Examination:

Four questions from Part A and Four questions from Part B to be set. Students have to answer any FIVE full questions out of EIGHT questions, choosing at least 2 questions from part A and 2 questions from part B




Aircraft Stability and Control


Sub Code:

10AE73




IA Marks:

25

Hrs/ Week:

04




Exam Hours:

03

Total Hours:

52




Exam Marks:

100


PART A


Unit 1. 06 Hrs

Static Longitudinal Stability:

Historical perspective, Aerodynamic Nomenclature, Equilibrium conditions, Definition of static stability, Definition of longitudinal static stability, stability criteria, Contribution of airframe components: Wing contribution, Tail contribution, Fuselage contribution, Power effects- Propeller airplane and Jet airplane


Unit 2. 07 Hrs

Static Longitudinal Stability and Control-Stick Fixed

Introduction, Trim condition. Static margin. stick fixed neutral points. Longitudinal control, Elevator power, Elevator angle versus equilibrium lift coefficient, Elevator required for landing, Restriction on forward C.G. range,


Unit 3. 07 Hrs

Static Longitudinal Stability and Control-Stick Free

Introduction, Hinge moment parameters, Control surface floating characteristics and aerodynamic balance, Estimation of hinge moment parameters, The trim tabs, Stick-free Neutral point, Stick force gradient in unaccelerated flight, Restriction on aft C.G.


Unit 4. 06 Hrs

Static Directional Stability and Control

Introduction, Definition of directional stability, Static directional stability rudder fixed, Contribution of airframe components, Directional control. Rudder power, Stick-free directional stability, Requirements for directional control, Rudder lock, Dorsal fin. One engine inoperative condition.. Weather cocking effect.

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