M. Tech. Aeronautical Engineering

M.E. – AERONAUTICAL ENGG. 1

Hindustan Institute of Technology & Science

Syllabus with

Curriculum and Regulations

2008

M.E

AERONAUTICAL ENGINEERING



ACADEMIC REGULATIONS (M.E. / M.Tech / M.B.A. / M.C.A.) 1. Vision, Mission and Objectives

1.1 The Vision of the Institute is “To make everyone a success and no one a failure”.

In order to progress towards the vision, the Institute has identified itself with a mission to provide every individual with a conducive environment suitable to achieve his / her career goals, with a strong emphasis on personality development, and to offer quality education in all spheres of engineering, technology, applied sciences and manage-ment, without compromising on the quality and code of ethics. 1.2 Further, the institute always strives

To train our students with the latest and the best in the rapidly changing fields of Engineering, Technology, Manage ment, Science & Humanities.

To develop the students with a global

outlook possessing, state of the art skills, capable of taking up challenging responsibilities in the respective fields.

To mould our students as citizens with moral, ethical and social values so as to fulfill their obligations to the nation and the society.

To promote research in the field of

science, Humanities, Engineering, Technology and allied branches.

1.3 Our aims and objectives are focused on

Providing world class education in engineering, technology, applied science and management.

Keeping pace with the ever changing technological scenario to help our students to gain proper direction to emerge as competent professionals fully aware of their commitment to the society and nation.

To inculcate a flair for research, development and entrepreneurship.

2. Admission 2.1. The admission policy and procedure shall be decided from time to time by the Board of Management (BOM) of the Institute, following guidelines issued by Ministry of Human Resource Develop ment (MHRD). Government of India. The number of seats in each branch of the (M.E. / M.B.A. / M.C.A.) programme will be decided by BOM as per the directives from Ministry of Human Resource Development (MHRD), Government of India and taking into account the market demands. Some seats for Non Resident Indians and a few seats for Foreign nationals shall be made available. 2.2. The selected candidates will be admitted to the (M.E. / M.Tech / M.B.A. / M.C.A.) programme after he/she fulfills all the admission requirements set by the Institute and after payment of the prescribed fees. 2.3. Candidates for admission to the first semester of the Master’s Degree Programme shall be required to have passed in an appropriate Degree Examination recognized by Hindustan University 2.4. In all matters relating to admission to the (M.E. / M.Tech / M.B.A. / M.C.A.). programme, the decision of the Institute and its interpretation given by the Chancellor of the Institute shall be final. 2.5. If at any time after admission, it is found that a candidate has not fulfilled any of the requirements stipulated by the Institute, the Institute may revoke the admission of the candidate with information to the Academic Council.


3. Structure of the programme 3.1. The programme of instruction will have the following structure i) Core courses of Engineering / Technology /

Management. ii) Elective courses for specialization in

areas of student’s choice.

3.2. The minimum durations of the programmes are as given below:

Program No. of Semesters

M.E. / M.Tech 4 M.B.A. (Full Time) 4 M.B.A. (Part Time) 6 M.C.A. 6

Every (M.E./ M.Tech / M.B.A. / M.C.A.) programme will have a curriculum and syllabi for the courses approved by the Academic Council.

3.3. Each course is normally assigned certain

number of credits. The following norms will generally be followed in assigning credits for courses.

One credit for each lecture hour per week per semester;

One credit for each tutorial hour per week per semester;

One credit for each laboratory practical (drawing) of three (two) hours per week per semester.

One credit for 4 weeks of industrial training and

One credit for 4 hours of project per week per semester

3.4. For the award of degree, a student has to earn certain minimum total number of credits specified in the curriculum of the relevant branch of study. The curriculum of the different programs shall be so designed that the minimum prescribed credits required for the award of the degree shall be within the limits specified below.

Program

Minimum prescribed

credit range

M.E. / M.Tech 85 – 90 M.B.A. (Full time / Part time) 85 - 95 MCA 110 - 115 3.5. The medium of instruction, examination and the language of the project reports will be English.

4. Faculty Advisor

4.1. To help the students in planning their courses of study and for getting general advice on the academic programme, the concerned Department will assign a certain number of students to a Faculty member who will be called their Faculty Advisor. 5. Class Committee

5.1 A Class Committee consisting of the following will be constituted by the Head of the Department for each class:

(i) A Chairman, who is not teaching the class.

(ii) All subject teachers of the class.

(iii) Two students nominated by the

department in consultation with the class.

The Class Committee will meet as often as necessary, but not less than three times during a semester.

The functions of the Class Committee will include: (i) Addressing problems experienced by

students in the classroom and the laboratories.

(ii) Analyzing the performance of the

students of the class after each test and finding ways and means of addressing problems, if any.


(iii) During the meetings, the student

members shall express the opinions and suggestions of the class students to improve the teaching / learning process.

6. Grading

6.1 A grading system as below will be adhered to.

6.2 GPA & CGPA GPA is the ratio of the sum of the product of the number of credits Ci of course “i “ and the grade points Pi earned for that course taken over all courses “i” registered by the student to the sum of Ci for all “i ”. That is,

ii

iii

C

PCGPA

CGPA will be calculated in a similar manner, at any semester, considering all the courses enrolled from first semester onwards. 6.3. For the students with letter grades W / I in certain subjects, the same will not be included in the computation of GPA and CGPA until after those grades are converted to the regular grades S to U.

6.4 Raw marks will be moderated by a moderation board appointed by the Vice Chancellor of the University. The final marks will be graded using absolute grading system. The Constitution and composition of the moderation board will be dealt with separately. 7. Registration and Enrollment

7.1 Except for the first semester, registration and enrollment will be done in the beginning of the semester as per the schedule announced by the University. 7.2 A student will be eligible for enrollment only if he/she satisfies regulation 10 (maximum duration of the programme) and will be permitted to enroll if (i) he/she has cleared all dues in the Institute, Hostel & Library up to the end of the previous semester and (ii) he/she is not debarred from enrollment by a disciplinary action of the University. 7.3. Students are required to submit registration form duly filled in. 8. Registration requirement

8.1. A full time student shall not register for less than 16 credits or more than 24 credits in any 12 given semester. 8.2 If a student finds his/her load heavy in any semester, or for any other valid reason, he/she may withdraw from the courses within three weeks of the commencement of the semester with the written approval of his/her Faculty Advisor and HOD. However the student should ensure that the total number of credits registered for in any semester should enable him/her to earn the minimum number of credits per semester for the completed semesters.

9. Minimum requirement to continue the programme

9.1 For those students who have not earned the minimum required credit

Range of Marks Letter Grade Grade

points 95-100 S 10 85 - 94 A 09 75- 84 B 08 65-74 C 07 55-64 D 06 50-54 E 05 < 50 U 00

I (Incomplete) --


prescribed for that particular semester examination, awarring letter to the concerned student and also to his parents regarding the shortage of this credit will be sent by the HOD after the announcement of the results of the university examinations.

10. Maximum duration of the programme

The minimum and maximum period for the completion of various programs are given below.

Program Min.

No. of Semesters

Max. No. of

Semesters M.E . M,Tech 4 8

M.B.A. (Full Time) 4 8

M.B.A. (Part Time) 6 10

M.C.A. 6 12

11. Temporary discontinuation

11.1. A student may be permitted by the Dean to discontinue temporarily from the programme for a semester or a longer period for reasons of ill health or other valid reasons. Normally a student will be permitted to discontinue from the programme only for a maximum duration of two semesters.

12. Discipline

12.1. Every student is required to observe discipline and decorous behavior both in-side and outside the campus and not to indulge in any activity which will tend to bring down the prestige of the University. 12.2. Any act of indiscipline of a student reported to the Dean (Academic) will be referred to a Discipline Committee so constituted. The Committee will enquire into the charges and decide on suitable punishment if the charges are substantiated. The committee will also authorize the Dean

(Academic) to recommend to the Vice - Chancellor the implementation of the decision. The student concerned may appeal to the Vice Chancellor whose decision will be final. The Dean (Academic) will report the action taken at the next meeting of the Council. 12.3. Ragging and harassment of women are strictly prohibited in the University campus and hostels.

13. Attendance

13.1. A student whose attendance is less than 75% is not eligible to appear for the end semester examination for that course. The details of all students who have attendance less than 75% will be announced by the teacher in the class. These details will be sent to the concerned HODs and Dean. 13.2. Those who have 75% or more attendance for the period other than their medical leave will be considered for condonation of shortage of attendance provided the overall attendance in the course including the period of illness does not fall below 65%. Application for condonation recommended by the Faculty Advisor, concerned faculty member and the HOD is to be submitted to the Dean who, depending on the merit of the case, may permit the student to appear for the end semester examination. A student will be eligible for this concession at most in two semesters during the entire degree programme. Application for medical leave, supported by medical certificate with endorsement by a Registered Medical Officer, should reach the HOD within seven days after returning from leave or, on or before the last instructional day of the semester, whichever is earlier. 13.3. As an incentive to those students who are involved in extra curricular activities such as representing the University in Sports and Games,


Cultural Festivals, and Technical Festivals, NCC/ NSS events, a relaxation of up to 10% attendance will be given subject to the condition that these students take prior approval from the officer –in-charge. All such applications should be recommended by the concerned HOD and forwarded to Dean within seven instructional days after the programme/activity.

14. Assessment Procedure

14.1. The Academic Council will decide from time to time the system of tests and examinations in each subject in each semester. 14.2. For each theory course, the assessment will be done on a continuous basis as follows:

Test / Exam Weightage Duration

ofTest / Exam

First Periodical Test 15% 1 Period

Second Periodical Test 15% 1 Period

Third Periodical Test 20% 2 Periods

End – Semester

Examination 50% 3 Hours

14.3. For practical courses, the assessment will be done by the subject teachers as below: (i) Weekly assignment/Observation note book / lab records – weightage 60%. (ii) End semester examination of 3 hours duration including viva – weightage 40%. 15. Make up Examination/periodical Test

15.1. Students who miss the end-semester examinations / periodical test for valid reasons are eligible for make-up examination /periodical test. Those who miss the end-semester examination / periodical test should apply to the Head of the Department

concerned within five days after he / she missed examination, giving reasons for absence. 15.2. Permission to appear for make-up examination/periodical test will be given under exceptional circumstances such as admission to a hospital due to illness. Students should produce a medical certificate issued by a Registered Medical Practitioner certifying that he/she was admitted to hospital during the period of examination / periodical test and the same should be duly endorsed by parent/guardian and also by a medical officer of the University within 5 days.

15.3. The student will be allowed to make up at the most two out of three periodical tests and end – semester examination.

16. Project evaluation

16.1. For Project work, the assessment will be done on a continuous basis as follows:

Review / Exam Weightage First Review 10%Second Review 20% Third Review 20% End semester Exam 50%

For end semester exam, the student will submit a Project Report in a format specified by the Dean. The first three reviews will be conducted by a Committee constituted by the Head of the Department. The end – semester exam will be conducted by a Committee constituted by the Controller of Examinations. This will include an external expert. 17. Declaration of results

17.1 A candidate who secures not less than 50% of total marks prescribed for a course with a minimum of 50% of the


marks prescribed for the end semester examination shall be declared to have passed the course and earned the specified credits for the course. 17.2 After the valuation of the answer scripts, the tabulated results are to be scrutinized by the Result Passing Boards of UG and PG programmes constituted by the Vice-Chancellor. The recommenda- tions of the Result Passing Boards will be placed before the Standing Sub Committee of the Academic Council constituted by the Chancellor for scrutiny. The minutes of the Standing Sub Committee along with the results are to be placed before the Vice-Chancellor for approval. After getting the approval of the Vice-Chancellor, the results will be published by the Controller of Examination/Registrar. 17.3 If a candidate fails to secure a pass in a course due to not satisfying the minimum requirement in the end semester examination, he/she shall register and re-appear for the end semester examination during the following semester. However, the internal marks secured by the candidate will be retained for all such attempts. 17.4 If a candidate fails to secure a pass in a course due to insufficient internal marks though meeting the minimum requirements of the end semester examination, wishes to improve on his/her internal marks, he/she will have to register for the particular course and attend the course with permission of the HOD concerned and Dean with a copy marked to the Registrar. The sessional and external marks obtained by the candidate in this case will replace the earlier result.

17.5 A candidate can apply for the revaluation of his/her end semester examination answer paper in a theory course within 2 weeks from the declaration of the results, on payment of a prescribed fee through proper application to the

Registrar/Controller of Examinations through the Head of the Department. The Registrar/ Controller of Examination will arrange for the revaluation and the results will be intimated to the candidate concerned through the Head of the Department. Revaluation is not permitted for practical courses and for project work. 18. Grade Card

18.1. After results are declared, grade sheet will be issued to each student, which will contain the following details:

(i) Program and branch for which the student has enrolled.

(ii) Semester of registration. (iii) List of courses registered during

the semester and the grade scored.

(iv) Semester Grade Point Average (GPA)

(v) Cumulative Grade Point Average (CGPA).

19. Class / Division

Classification is based on CGPA and is as follows: CGPA≥8.0: First Class with distinction 6.5 ≥CGPA < 8.0: First Class 5.0 ≥CGPA < 6.5: Second Class.

20. Transfer of credits

20.1. Within the broad framework of these regulations, the Academic Council, based on the recommendation of the transfer of credits committee so constituted by the Chancellor may permit students to earn part of the credit requirement in other approved institutions of repute and status in the country or abroad.

20.2. The Academic Council may also approve admission of lateral entry (who hold a diploma in Engineering/ technology) candidates with advance


credit based on the recommendation of the transfer of credits committee on a case to case basis.

21. Eligibility for the award of (M.E. / M.Tech / M.B.A. / M.C.A.) Degree 21.1. A student will be declared to be eligible for the award of the (M.E. / M.Tech / M.B.A. / M.C.A.). Degree if he/she has

i) registered and successfully credited all the core courses,

ii) successfully acquired the credits in the different categories as specified in the curriculum corresponding to the discipline (branch) of his/her study within the stipulated time,

iii) has no dues to all sections of the Institute including Hostels, and

iv) has no disciplinary action pending against him/her.

The award of the degree must be recommended by the Academic Council and approved by the Board of Management of the University. 22. Power to modify 22.1. Notwithstanding all that has been stated above, the Academic Council has the right to modify any of the above regulations from time to time.


HINDUSTAN INSTITUTE OF TECHNOLOGY AND SCIENCE, PADUR M.E. AERONAUTICAL ENGINEERING

CURRICULUM 2008

SEMESTER ISl.No

CourseCode Course Title L T P C TCH

Theory1 MA1601* Advanced Engineering Mathematics 3 1 0 4 42 AE1601 Aerodynamics - I 3 0 2 4 53 AE1602 Aerospace Propulsion 3 1 0 4 44 AE1603 Aircraft Structures 3 1 0 4 45 - Elective-I 3 1 0 4 46 - Elective-II 3 1 0 4 4

Total 24 25

SEMESTER - IISl.No


Theory1 AE1604 Aerodynamics II 3 1 0 4 42 AE1605 Composite Materials and Structures 3 1 0 4 43 AE1606 Experimental Stress Analysis 3 1 0 4 44 AE1607 Finite Element Methods 3 1 0 4 45 AE1608 Rocketry and Space Mech. 3 1 0 4 46 AE1609 Theory of Vibrations 3 1 0 4 4

Practical

7 AE1625 Aircraft Structures Lab 0 0 3 1 3

Total 25 27

* Common to AERO, CAD, R&AC, ICE & THERMAL

SEMESTER IIISl.No


Theory1 -- Elective-III 3 1 0 4 42 -- Elective-IV 3 1 0 4 43 -- Elective-V 3 1 0 4 4

Practical

4 AE1626 Aircraft Systems Lab 0 0 3 1 3

5 AE1610 Project Work-Phase I 0 0 12 6 12

Total 19 27


Semester IVSl.No


Theory1 AE1611 Project Work-Phase II 0 0 24 12 24

Total 12 24

TOTAL NO. OF CREDIT = 80

ELECTIVE COURSES SEMESTER I

Sl.No


1 AE1612 Advanced Propulsion Systems 3 1 0 4 42 AE1613 Theory of Elasticity 3 1 0 4 43 AE1614 Advanced Heat Transfer 3 1 0 4 44 AE1615 Aircraft Design 3 1 0 4 4

ELECTIVE COURSES SEMESTER III

Sl.No


1 AE1616 Computational Fluid Dynamics 3 1 0 4 42 AE1617 Cryogenics 3 1 0 4 43 AE1618 Fatigue and Fracture Mechanics 3 1 0 4 44 AE1619 High Temp. Problems in Structures 3 1 0 4 45 AE1620 Theory of Plates and Shells 3 1 0 4 46 AE1621 Industrial Aerodynamics 3 1 0 4 47 AE1622 Helicopter Aerodynamics 3 1 0 4 48 AE1623 Aero Elasticity 3 1 0 4 49 AE1624 Hypersonic Aerodynamics 3 1 0 4 4


SEMESTER I

MA1601 - ADVANCED ENGINEERING MATHEMATICS

L T P C

3 1 0 4

OBJECTIVES

The course objective is to impart analytical skills, as a prerequisite for post graduate and specialized studies and research.

UNIT - I CALCULUS OF VARIATIONS 12 Conceptofvariationanditsproperties-Euler’sEquation-Functionaldependantonfirstandhigher order derivatives - Functional dependant on functions of several independent variables- Isoperimetric problems – Direct methods-Ritz and Kantrovich methods

UNIT - II TRANSFORM METHODS 12 Laplace transform methods for one dimensional wave equation – Displacements in a long string – Longitudinal vibration of an elastic bar - Fourier Transform methods for one dimensional heatconductionproblemsininfiniteandsemi-infiniterod

UNIT - III ELLIPTIC EQUATIONS 12 Laplace equation – Properties of Harmonic functions – Solutions of Laplace equation by meansofFouriertransforminahalfplaneinaninfinitestripandinasemi-infinitestrip

UNIT - IV NUMERICAL SOLUTION OF PARTIAL DIFFERENTIAL EQUATIONS 12 Solution of Laplace and Poisson equation on a rectangular region by Lieebmann’s method – Diffusion equation by the explicit and Crank Nicolson – Implicit methods – Solution of wave equations by explicit scheme Cubic spline interpolation

UNIT - V CONFORMAL MAPPING AND APPLICATIONS 12 The Schwarz – Christoffel transformation – Transformation of boundaries in parametric form –Physicalapplications-Applicationtofluidandheatflow

TOTAL: 60

REFERENCES

1. Gupta, A.S, “Calculus of Variations with Applications”, Prentice Hall of India(P)Ltd., New Delhi, 6th print, 2006

2. Sankar Rao, .K, “Introduction to Partial Differential Equations”,Prentice Hall of India(P) Ltd., New Delhi, 5th print, 2004.

3. Jain.R.K,Iyengar.S.R.K, “Advanced Engineering Mathematics”. Narosa publications 2nd Edition, 2006

4. Grewal, B.S,“Numerical Methods in Science and Engineering”., Kanna Publications, NewDelhi.

5. Kandasamy.P , Thilagavathy. K and Gunavathy. K, “Numerical Methods”., S. Chand and Co, Ltd., New Delhi, 5th Edition, 2007

6. Spiegel, M.R ,“Theory and problems of Complex Variables with an Introduction to Conformal Mapping and Its applications ”, Schaum’s outline series, McGraw Hill Book Co, 1987.


AE 1601 - AERODYNAMICS - I

L T P C

3 0 2 4

OBJECTIVE

Tounderstandthebehaviourofairflowoverbodieswithparticularemphasisonairfoilsectionsintheincompressibleflowregime

UNIT - I REVIEW OF BASIC FLUID MECHANICS 10 Continuity and Momentum equations, Point source and sink, Free and Forced Vortex, Uniform parallelflow,combinationofbasicflows,PressureandVelocitydistributionsOnbodieswithandwithoutcirculationinidealandrealfluidflows,Magnuseffect

Lab : 1. Calibration of wind tunnel

2. Pressure distribution on 3-D bodies

UNIT - II AIRFOILS 12 ConformalTransformation,Kuttacondition,Karman–Treffzprofiles,ThinaerofoilTheoryandits applications.

Lab: 1. Pressure distribution over an aerofoil at different angles of attack.

UNIT - III WING THEORY 12 Vortex line, Horse shoe vortex, Biot and savart law, lifting line theory, effects of aspect Ratio, planform and taper ratio.

Lab : 1. Drag measurements in Wind Tunnels.

UNIT - IV ELEMENTS OF COMPRESSIBLE FLOWS 14

Isentropic flows – shock and expansion waves, compressibility effects on aerodynamicCoefficients,methodofcharacteristics–smallperturbationtheory.

Lab : 1. Calibration of supersonic wind tunnel.

UNIT - V WIND TUNNELS 12

Types of wind tunnels – Flow visualization processes – Measurements in wind tunnels, 6-component balance.

Lab:1.Supersonicflowvisualizationwithschlierensystems.

TOTAL: 60REFERENCES 1. J.D. Anderson, “Fundamental of Aerodynamics”, McGraw-Hill Book Co., New York, 1985.2. E.L. Houghton and N.B. Carruthers, “Aerodynamics for Engineering Students”, Edward Arnold Publishers Ltd., London (First Indian Edition), 1988.3. W.H. Rae and A. Pope, “Low speed Wind Tunnel Testing”, John Wiley Publications, 1984.4. Shapiro, A.H., Dynamics & Thermodynamics of Compressible Fluid Flow, Ronald Press, 1982.5. Zucrow, M.J., and Anderson, J.D., Elements of gas dynamics McGraw-Hill Book Co., New York, 1989.6. Rathakrishnan.E., Gas Dynamics, Prentice Hall of India, 1995.


AE1602 - AEROSPACE PROPULSION

L T P C

3 1 0 4

OBJECTIVE

To understand the principles of operation and design of aircraft and spacecraft power plants.

UNIT - I ELEMENTS OF AIRCRAFT PROPULSION 12

Classification of power plants based on methods of aircraft propulsion – jet and rocketpropulsion – Differences between jet propulsion engines and rocket propulsion engines – Types and areas of applications – fundamental of aircraft piston engines.

UNIT - II INTRODUCTION TO GAS TURBINE ENGINES 12

Classification of air breathing engines – Principle of turbojet, turbo-prop, turbo-jet withreheat, by-pass and turbo fan concepts – Thrust augmentation in jet engines and its application to aircraft.

UNIT - III THERMODYNAMICS OF JET ENGINES 12

Thermodynamic analysis of jet engine – components of a jet engine – Compressor, combustion chamber, turbineand jetnozzle– theirefficiencies– Introduction to ramjet, pulse jetand theirapplication – Introduction to combustion and chemical kinetics.

UNIT - IV ROCKET PROPULSION 12

Introduction to rocketpropulsion–Reactionprinciple–Thrustequation–Classificationofrockets based on propellants used – solid, liquid and hybrid – Comparison of these engines with special reference to rocket performance.

UNIT - V RAMJET AND SCRAMJET PROPULSION 12 Ramjet-Operatingprinciple–Subcritical,criticalandsupercriticaloperation–Combustioninramjet engine – Ramjet performance - Fundamentals of hypersonic air birthing vehicles, Preliminary concepts in engine airframe integration, Various types of supersonic combustors, Requirements for supersonic combustors, Performance estimation of supersonic combustors.

TOTAL: 60

REFERENCES1. G.C.Oates,“AerothermodynamicsofAircraftEngineComponents”,AIAAEducationSeries,Published by AIAA, New York, 1985.

2. G.C.Oates,“AircraftPropulsionsystemtechnology&design”,AIAAEducationSeries,1989.

3. G.P.Sutton, “Rocket Propulsion Elements”, John Wiley & Sons Inc., New York, 5th Edition, 1986.

4. H.Cohen, G.F.C.Rogers & H.I.H.Saravana muttoo,“Gas turbine theory”,Longman Co., ELBS Ed., 1982.

5. W.P.Gill, H.J.Smith & J.E. Ziurys, “Fundamentals of Internal Combustion Engines as applied to Reciprocating, Gas turbine & Jet Propulsion Power Plants”, Oxford & IBH Publishing Co., 1980.

6. J.D.MattinglyandH.V.Oha, “ElementsofPropulsion -GasTurbinesandRockets”,AIAA Education Series, 2006.


AE1603 - AIRCRAFT STRUCTURES

L T P C

3 1 0 4

OBJECTIVE

To study different types of beams and columns subjected to various types of loading and support conditions with particular emphasis on aircraft structural components.

UNIT - I UNSYMMETRICAL BENDING 12

Stresses in beams of unsymmetrical sections, box beams.

Lab: 1. UseofDoubleDialgaugetofindthedeformationsofthegivenMaterial.

2. FindingtheflexibilitycoefficientsofthegivencantileverbeamandverificationofMaxwell’s reciprocal theorem and principle of superposition.

3. Unsymmetrical Bending of cantilever beam.

UNIT - II AIRCRAFT STRUCTURE MONOCOQUE AND SEMI MONOCOQUE 12

Analysisoftubular,monocoqueandsemi-monocoquestructures–Torsionandflexureofthinwalled boxes – shear centre – Flexural axis and axis of twist.

Lab: 1. Combined bending of hollow circular shaft.

2. Finding the shear center of the given C-section.

UNIT - III ANALYSIS OF STIFFENED STRUCTURES 12

Idealisation and analysis of stiffened tubular structures – Study of open tubes – Analysis of multi cell tubes. Analysis of rings and frames – Applications to aircraft structures.

UNIT - IV STABILITY PROBLEMS 12

Stabilityproblemsofthinwalledstructures–Flexural,torsionalandlocalfailures–Influenceof eccentricity and in elasticity – Buckling of plates and sheet stringer combinations - crippling loads –Tensionfieldtheory.

Lab : 1. Buckling of columns and plotting of Southwell’s plot.

UNIT V SHELLS 12

Idealizationofstiffenedshells,shearcenter,shearflowin thinwalledmulticellboxbeams,effect of taper

TOTAL :60

REFERENCES

1. E.F.Bruhn,“AnalysisandDesignofFlightVehicleStructures”,TristateOffsetCo.,1980.

2. Megson, T.M.G; Aircraft Structures for Engineering Students, Edward Arnold, 1989.

3. Peery, D.J. and Azar, J.J., Aircraft Structures, 2nd Edition, McGraw-Hill, New York, 1993.

4. Stephen P. Tinnoshenko & S.woinowsky Krieger, Theory of Plates and Shells, 2nd Edition, McGraw-Hill, Singapore, 1990.


SEMESTER II

AE1604 - AERODYNAMICS II

L T P C

3 1 0 4

OBJECTIVE

Tounderstandthebehaviourofairflowbothinternalandexternalincompressibleflowregimewithparticularemphasisonsupersonicflows.

UNIT - I INTRODUCTION TO PRINCIPLES OF FLIGHT 10

Physical properties and structure of the atmosphere, Temperature, pressure and altitude Relationship, Measurement of speed – True and Indicated Air speed, Components of an Airplane andtheirfunctions,Differenttypesofflightvehicles.

UNIT - II DRAG OF BODIES 10

Types of Drag, effects of Reynold’d number on skin friction and pressure drag, streamlined Andbluffbodies,Dragreductionofairplanes,Momentumtheoryoffinitewings,Dragpolar.

UNIT - III AIRCRAFT PERFORMANCE 14

Steady levelflightconditions forminimumdragandminimumpower required,GlidingandClimbingflight,Rangeandendurance,Take-offandlanding,Highleftdevices,ThrustAugmentation,Turning performance, V-n diagram, Froude momentum and black elements Theory of propellers, Fixed and Variable pitch propellers.

UNIT - IV NORMAL, OBLIQUE SHOCKS AND EXPANSION WAVES 14

Prandtl equation and Rankine – Hugonoit relation, Normal shock equations, Pitot static tube, corrections for subsonic and supersonic flows, Oblique shocks and corresponding equations,Hodograph andpressure turning angle, shock polars, flowpastwedges and concave corners,strong, weak and detached shocks, Rayleigh and Fanno Flow.

UNIT - V AIRCRAFT STABILITY AND CONTROL 12

Degrees of freedom of a system, statie and dynamic stability, static longitudinal stability, Static lateral stability, static directional stability, dynamic longitudinal stability, dynamic lateral And directional stability.

TOTAL: 60 REFERENCES 1. Houghton, E.L., and Carruthers. N.B., “Aerodynamics for engineering students”., Edward Amold Publishers, 1988.2. Kuethe, A.M., and Chow, C.Y., “ Foundations of Aerodynamics ”., John Wiley & Sons, 1982.3. L.J. Clancey, “Aerodynamics”., Pitman, 1986.4. Perkins C.D., & Hage, R.E, “Airplane performance, stability and control”, Wiley Toppan, 1974.5. Babister, A.W, “ Aircraft stability and Response”., Pergamon Press, 1980.6. Nelson, R.C. Flight ,“ Stability & Automatic Control ”., McGraw-Hill, 1989.7. McCornic, B.W, “Aerodynamics, Aeronautics & Flight Mechanics”. John Wiley, 1995.


AE1605 - COMPOSITE MATERIALS AND STRUCTURE

L T P C

3 1 0 4

OBJECTIVE

To understand the fabrication, analysis and design of composite materials & structures.

UNIT - I CLASSIFICATION AND CHARACTERISTIC OF

COMPOSITE MATERIALS 8

Need for the composite materials. Types of composite materials and their use in structures.

UNIT - II BASIC CONCEPTS 15

Hooke’s law for orthotropic and anisotropic materials. Micromechanics and macro mechanics. Lamina stress-strain relations referred and principal material directions and arbitrary axes.

UNIT - III ANALYSIS OF LAMINATED COMPOSITES 17

Governing equations for anisotropic and orthotropic plates. Angle-ply and cross ply laminates. Static, dynamic and stability analysis for simpler cases of composite plates. Interlaminar stresses.

UNIT - IV OTHER METHODS OF ANALYSIS AND FAILURE THEORY 10

Netting analysis, Failure criteria. Sandwich construction.

UNIT - V MANUFACTURING & FABRICATION PROCESSES 10

Manufacturingofglass,boronandcarbonfibres.Openmouldandclosedmouldprocesses.

TOTAL: 60

REFERENCES

1. R.M. Jones, “Mechanics of composite materials”, McGraw-Hill, Kogakusha Ltd., Tokyo, 1975.

2. L.R. Calcote, “Analysis of laminated structures”, Van Nostrand Reinhold Co., 1989.

3. G.Lubin, “Hand Book on Fibre glass and advanced plastic composites”, Van Nostrand Co., New York, 1989.

4. B.D.AgarwalandL.J.Broutman,“AnalysisandPerformanceoffibercomposites”,John-Wiley and Sons, 1980.


AE1606 - EXPERIMENTAL STRESS ANALYSIS

L T P C

3 1 0 4

OBJECTIVE

Tobringawarenessonexperimentalmethodoffindingtheresponseofthestructuretodifferenttypes of load.

UNIT - I INTRODUCTION 8

Extensometers–Types–Mechanical,Electrical,ElectronicandOptical–Reviewofbridgecircuits.

UNIT - II STRAIN GAUGE TECHNIQUES 12

Strain gauge and transducers for measurement of static and dynamic loads – Instrumentation, measurement and recording systems.

UNIT - III PHOTO ELASTIC TECHNIQUES 13

Stress analysis by two and three dimensional photo elasticity – Interpretation of stress patterns –Typicalapplications–Descriptionandusersofreflectionpolariscope.

UNIT - IV NON – DESTRUCTIVE TESTING 15

Fundamentals of NDT. Radiography, ultrasonic, Holography ,Laser holography magnetic particle inspection, Fluorescent penetrant technique, Eddy current testing, Acoustic Emission Technique, Moire fringes –– Grid methods

UNIT - V OTHER TECHNIQUES 12

Stress analysis by stress coat ––Induction heating instrumentation, measurement and recording techniques – Creep testing. X-ray,– applications. Fundamentals of brittle coating methods, Introduction to Moiré techniques, , ultrasonic C- Scan, Thermograph, Fiber – optic Sensors.

TOTAL: 60

REFERENCES

1. J.W. Dally and M.F. Riley, “Experimental Stress Analysis”, McGraw-Hill Book Co., New York, 1988.

2. P. Fordham, “Non-Destructive Testing Techniques” Business Publications, London, 1988.

3. M.Hetenyi, “Handbook of Experimental Stress Analysis”, John Wiley & Sons Inc., New York, 1980.

4. G.S. Holister, “Experimental Stress Analysis, Principles and Methods”, Cambridge University Press, 1987.

5. A.J. Durelli and V.J. Parks, “Moire Analysis of Strain”, Prentice Hall Inc., Englewood Cliffs, New Jersey, 1980.


AE 1607 - FINITE ELEMENT METHODS

L T P C

3 1 0 4

OBJECTIVE

To introduce the concept of numerical analysis of structural components


Reviewofvariousapproximatemethodsinstructuralanalysis.Stiffnessandflexibilitymatricesforsimplecases.Basicconceptsoffiniteelementmethod.Formulationofgoverningequationsandconvergence criteria.

UNIT - II DISCRETE ELEMENTS 12

Use of bar and beam elements in structural analysis. Computer implementation of procedure for these elements.

UNIT - III CONTINUUM ELEMENTS 12

Different forms of 2-D elements and their applications for plane stress, plane strain and axisymmetric problems. Consistent and lumped formulation. Use of local co-ordinates. Numerical integration.

UNIT - IV ISOPARAMETRIC ELEMENTS 12

Definitionanduseofdifferentformsof2-Dand3-Delements.Computerimplementationofformulation of these elements for the analysis of typical aircraft structural parts like, wing, fuselage, turbine blades.

UNIT - V SOLUTION SCHEMES 12

Different methods of solution of simultaneous equations governing static, dynamics and stability problems. General purpose Software packages.

TOTAL: 60

REFERENCES

1. L.J. Segerlind, “Applied Finite Element Analysis”, Second Edition, John Wiley and Sons Inc., New York, 1984.

2. K.J. Bathe and E.L. Wilson, “Numerical Methods in Finite Elements Analysis”, Prentice Hall of India Ltd., 1983.

3. R.D. Cook, “Concepts and Applications of Finite Element Analysis”, 3rd Edition, John Wiley & Sons, 1989.

4. C.S. Krishnamurthy, “Finite Elements Analysis”, Tata McGraw-Hill, 1987.

5. V.Ramamurthi, “Computer Aided Design in Mechanical Engineering”, Tata McGraw-Hill.


AE 1608 - ROCKETRY AND SPACE MECHANICS

L T P C

3 1 0 4

OBJECTIVE

To introduce basic concepts of design and trajectory estimation of rocket , missiles and basic concepts of orbital Mechanics

UNIT - I ORBITAL MECHANICS AND SATELLITE DYNAMICS 15

Description of solar system – Keplers Laws of planetary motion – Newton’s Law of Universal gravitation – Two body and Three-body problems – Jacobis Integral, Librations points - Estimatur of orbital and escape velocities – geosynchronous and geostationary satellites life time – satellite perturbations – Hohmann orbits – calculation of orbit parameters.

UNIT - II ROCKET MOTION 15

Principle of operation of rocket motor - thrust equation – one dimensional and two dimensional rocket motions in free space and homogeneous gravitational fields – Description of vertical,inclined and gravity turn trajectories determinations of range and altitude – simple approximations to burnout velocity – staging of rockets.

UNIT - III ROCKET AERODYNAMICS 12

Description of various loads experienced by a rocket passing through atmosphere – drag estimation – wave drag, skin friction drag, foron drag and base pressure drag – Boat-tailing in missiles – performance at various altitudes – conical and bell shaped nozzles – adapted nozzles – rocket dispersion – launching problems.

UNIT - IV MATERIALS FOR SPACECRAFT AND MISSILES 5

Selections of materials for spacecraft and missiles – special requirements of materials to perform under adverse conditions – ablative materials.

UNIT - V SATELLITE INJECTION AND SATELLITE ORBIT PERTURBATIONS 13

General Aspects of satellite Injections – Satellite Orbit Transfer –Various Cases – OrbitDeviations Due to Injection Errors – Special and General Perturbations – Cowell’s Method – Encke’sMethod–MethodofvibrationsofOrbitalElements–GeneralPerturbationsApproach.

TOTAL: 60

REFERENCES

1. G.P. Sutton, “Rocket Propulsion Elements”, John Wiley & Sons Inc., New York, 5th Edition, 1986.

2. J.W. Cornelisse, “Rocket Propulsion and Space Dynamics”, J.W. Freeman & Co., Ltd., London, 1982.

3. Van de Kamp, “Elements of astromechanics”, Pitman Publishing Co., Ltd., London, 1980.

4. E.R. Parker, “Materials for Missiles and Spacecraft”, McGraw-Hill Book Co., Inc., 1982.


AE 1609 - THEORY OF VIBRATIONS

L T P C

3 1 0 4

OBJECTIVE

To study the dynamic behaviour of different aircraft components and the interaction among the aerodynamic, elastic and inertia forces


Simpleharmonicmotion,definitionofterminologies,ReviewofNewton’s,Laws,D’Alembert’sprinciple, Energy methods.

UNIT - II SINGLE DEGREE OF FREEDOM SYSTEMS 10

Free vibrations free damped vibrations, forced excitations with and without damping, support excitation, vibration measuring instruments.

UNIT - III MULTI-DEGREE OF FREEDOM SYSTEMS 18

Two degrees of freedom systems, Static and dynamic couplings, vibration absorber, Principle coordinates, Principal modes, orthogonality conditions. Hamilton’s Prinicple, Lagrangean equation and applications. Vibrations of elastic bodies, String or stretched cord, Longitudinal vibration, Lateral vibration, Torsional vibration. Approximate methods for calculating natural frequencies.

UNIT - IV ELEMENTS OF AEROELASTICITY 10

Aeroelastic problems – Collar’s triangle of courses – Wing divergence – Aileron control reversal – Flutter.

UNIT - V SOLUTION METHOD 12

Computational technique in vibration, Vibrating string, General method, Beam element, Global matrices, Transformation of matrices, Equation of motion of complete system, Consistent and Lambard mass

TOTAL: 60

REFERENCES

1. Timoshenko.S, “ Vibration Problems in Engineering ”, John Wiley & Sons, Inc., 1987.

2. Meirovitch, L, Elements of Vibration Analysis ”, McGraw-Hill Inc., 1986.

3. F.S. Rse., I.F. Morse and R.T. Hinkle, “ Mechanical Vibrations ”, Prentice-Hall of India, 1985.

4. Fung, Y.C, “ An Introduction to the Theory of Aeroelasticity ”, John Wiley & Sons Inc., New York, 1985.

5. Rao.J.S. and Gupta.K, “ Theory and Practice of Mechanical Vibrations ”, Wiley Eastern Ltd., New Dehli, 1999.


AE1625 - AIRCRAFT STRUCTURES LAB

L T P C

0 0 3 1

OBJECTIVE

Tostudyexperimentallytheloaddeflectioncharacteristicsstructuralmaterialsunderdifferenttypesofloads,unsymmetricalbendingofbeams,tofindthelocationofshearcentre,obtainthestresses in circular discs and beams using photoelastic techniques, calibration of photo – elastic materials and study on vibration of beams.

LIST OF EXPERIMENTS

1. Stress Strain curve for various engineering materials.

2. Deflectionofbeamswithvariousendconditions.

3. VerificationofMaxwell’sReciprocaltheorem&principleofsuperposition

4. Column – Testing

5. South – well’s plot.

6. Unsymmetrical bending of beams

7. Shear centre location for open sections and closed section

8. Calibration of Photo- elastic materials

9. Stresses in circular discs and beams using photoelastic techniques

10. Vibrations of beams

LIST OF EQUIPMENTS

(For a batch of 30 students)

SL. NO. EQUIPMENTS QTY

1. Electrical stain gauge 10

2. Stain indicator 1

3. Dial Gauges 12

4. Beam Test set up with various end conditions 2

5. Maxwell apparatus 1

6. South – well’s plot 1

7. Weight 1 Kg and 2kg 10 each

8. Weight Pans 6

9. Column Test Apparatus 1

10. Beam Test set –up 2

11. Unsymmetrical sections like ‘Z’ sections 2


12. Channel ,angle open and closed section 2

13. Dial gauges 12

14. Vibration Test Set – up 2

15. Strainindicatorandstraingauges Oneset

16. Photo – elastic apparatus 1

SEMESTER III

AE1626 - AIRCRAFT SYSTEM LABORATORY

L T P C

0 0 3 1

OBJECTIVE

Totrainthestudents“ONHAND”experienceinmaintenanceofvariousairframesystemsinaircraftandrectificationofcommonsnags.

LIST OF EXPERIMENTS

1. Aircraft “Jacking Up” procedure

2. Aircraft “Levelling” procedure

3. Aircraft “Symmetry Check” procedure

4. Control System “Rigging check” procedure

5. Checks on Landing Gear assembly

6. “ Functional Test” on Aircraft Hydraulic system

7. Maintenanceandrectificationofsnagsinhydraulicandfuelsystems.

LIST OF EQUIPMENTS

SL.NO. ITEMS QUANTITY

1. Serviceable aircraft with all above systems 1

2. Hydraulic Jacks (Screw Jack) 5

3. Trestle adjustable 5

4. Spirit Level 2

5. Levelling Boards 2

6. Cable Tensiometer 1

7. Adjustable Spirit Level 1

8. Plumb Bob 1


SEMESTER III & IV

AE1610 & AE1611 - PROJECT WORK (Phase I & II)

L T P C

0 0 36 18

OBJECTIVE

The objective of the project work is to enable the students on a project involving theoretical and experimental studies related to the branch of study. Every project work shall have a guide who is the member of the faculty of the institution. Full semester shall be allotted and this time shall be utilized by the students to receive the directions from the guide, on library reading, laboratory work, computeranalysisorfieldworkasassignedbytheguideandalsotopresentinperiodicalseminarson the progress made in the project.

Eachstudentshallfinallyproduceacomprehensivereportcoveringbackroundinformation,literaturesurvey,problemstatement,projectworkdetailsandconclusion.Thisfinalreportshallbetypewrittenformasspecifiedintheguidelines.

The continuous assessment shall be made as prescribed by the regulation (Hindustan University Regulations 2008 for ME. programme)

Total : 18

ELECTIVES

SEMESTER I

AE1612 - ADVANCED PROPULSION SYSTEMS

L T P C

3 1 0 4

OBJECTIVE

To understand the principles of operation of advanced propulsion systems , working of Ramjet and Scramjet Engines.

UNIT - I THERMODYNAMIC CYCLE ANALYSIS OF AIR-BREATHING

PROPULSION SYSTEMS 12

Air breathing propulsion systems like Turbojet, turboprop, ducted fan, Ramjet and Air augmented rockets – Thermodynamic cycles – Pulse propulsion – Combustion process in pulse jet engines – inlet charging process – Supercritical charging and subcritical discharging – Subcritical charging and subcritical discharging – Subcritical charging and supercritical discharging.

UNIT - II RAMJETS AND AIR AUGMENTED ROCKETS 10

Preliminary performance calculations – Diffuser design and hypersonic inlets – combustor and nozzle design – air augmented rockets – engines with supersonic combustion.

UNIT - III SCRAMJET PROPULSION SYSTEM 14

Fundamental considerations of hypersonic air breathing vehicles – Preliminary concepts in engineairframeintegration–calculationofpropulsionflowpath–flowpathintegration–Varioustypes of supersonic combustors – fundamental requirements of supersonic combustors – Mixing of fueljetsinsupersoniccrossflow–performanceestimationofsupersoniccombustors.


UNIT - IV NUCLEAR PROPULSION 12

Nuclear rocket engine design and performance – nuclear rocket reactors – nuclear rocket nozzles–nuclearrocketenginecontrol–radioisotopepropulsion–basicthrusterconfigurations– thruster technology – heat source development – nozzle development – nozzle performance of radioisotope propulsion systems.

UNIT - V ELECTRIC AND ION PROPULSION 12

Basic concepts in electric propulsion – power requirements and rocket efficiency – thermalthrusters – electrostatic thrusters – plasma thruster of the art and future trends – Fundamentals of ion propulsion – performance analysis – electrical thrust devices – ion rocket engine.

TOTAL: 60

REFERENCES

1. John D. Anderson, Jr,. “ Hypersonic and High Temperature Gas Dynamics ”. McGraw-Hill Series, New York, 1996.

2. John. D.Anderson, Jr “, Modern Compressible Flwo with Historical perpectant ”. McGraw-Hill Series, New York, 1996.

3. William H. Heiser and David T. Pratt ,“ Hypersonic Airbreathing propulsion ”. by, AIAA Education Series.

4. John T. Bertin “ Hypersonic Aerothermodynamic ”, 1994 published by AIAA Inc., Washington D.C.

AE 1613 - THEORY OF ELASTICITY

L T P C

3 1 0 4

OBJECTIVE

To understand the theoretical concepts of material behaviour with particular emphasis on their elastic property

UNIT - I FUNDAMENTALS OF ELASTICITY 10

Assumptions In Elasticity ,Strain – displacement relations, Stress – strain relations Equilibrium equation in Cartesian and polar coordinates., Compatibility conditions. Saint-Venant’s principle.

UNIT - II BASIC EQUATIONS OF ELASTICITY 10

Lame’s constant – cubical dilation, Compressibility of material, bulk modulus, Shear modulus, Principal stresses and principal strains, Mohr’s circle

UNIT - III PLANE STRESS AND PLANE STRAIN PROBLEMS 15

Airy’s stress function, plane stress and plane strain idealization. Special problems in polar coordinates. Kirsch, Boussinasque’s and Michell’s problems.

UNIT - IV POLAR COORDINATES 10

Equations of equilibrium, Strain displacement relations, Stress – strain relations, Axi – symmetric problems, Kirsch, Michell’s and Boussinesque problems


UNIT - V TORSIONAL THEORY 15

Navier’s theory, St. Venant’s theory, Prandtl’s theory on torsion, The semi- inverse method and applications to shafts of circular, elliptical, equilateral triangular and rectangular sections

TOTAL: 60

REFERENCES

1. S.P. Timoshenko and J.N. Goodier, Theory of Elasticity, McGraw-Hill, 1985.

2. E. Sechler, “Elasticity in Engineering” John Wiley & Sons Inc., New York, 1980.

AE 1614 - ADVANCED HEAT TRANSFER

L T P C

3 1 0 4

OBJECTIVE

To introduce the concepts of heat transfer to enable the students to design components subjected to thermal loading.

UNIT - I ADVANCED HEAT CONDUCTION ANALYSIS 12

Conduction – Convection systems – Mathematical analysis of two-dimensional heat conduction – graphical and numerical analysis – Numerical solutions to problems heat conduction problems.

UNIT - II CONVECTIVE HEAT TRANSFER ANALYSIS 15

Heattransferinvolvinglaminarandturbulentflowsoveraflatplateandthroughatube-Heattransferinhighspeedflows–closedformandnumericalsolutions.

UNIT - III RADIATIVE HEAT TRANSFER 11

Physical mechanism of radiation – radiation shape factors – relations between shape factors – heat exchange between non-black bodies – radiation shields – solar radiation – radiation heat transfercoefficient.

UNIT - IV HEAT EXCHANGERS 12

Classification–TemperatureDistribution–Overallheattransfercoefficient,HeatExchangeAnalysis – LMTD Method and E-NTU Method.

UNIT - V APPLICATIONS IN AEROSPACE ENGINEERING 10

Heat transfer in gas turbine combustion chambers and rocket thrust chambers – Heat transfer in ablation cooling process.

TOTAL: 60

REFERENCES

1. John H. Lienhard, “A Heat Transfer Text Book”, Prentice Hall Inc., 1981.

2. J.P. Holman, “Heat Transfer”, McGraw-Hill Book Co., Inc., New York, 6th Edition, 1991.

3. S.C. Sachdeva, “Fundamentals of Engineering Heat & Mass Transfer”, Wiley Eastern Ltd.,


New Delhi, 1981.

4. G.P. Sutton, “Rocket Propulsion Elements”, John Wiley & Sons, 5th Edition, 1986.

5. M.Mathur and R.P. Sharma, “Gas turbine and Jet and Rocket Propulsion”, Standard Publishers, New Delhi, 1988.

AE 1615 - AIRCRAFT DESIGN

L T P C

3 1 0 4

OBJECTIVE

To introduce and develop the basic concept of aircraft design

UNIT - I REVIEW OF DEVELOPMENTS IN AVIATION 12

Categoriesandtypesofaircraftspecifications–variousconfigurations–Layoutsandtheirrelative merits – strength, stiffness, fail safe and fatigue requirements – Manoeuvering load factors – Gust and manoeuverability envelopes – Balancing and maneuvering loads on tail planes.

UNIT - II POWER PLANT TYPES AND CHARACTERISTICS 12

Characteristics of different types of power plants – Propeller characteristics and selection – Relative merits of location of power plant.

UNIT - III PRELIMINARY DESIGN 12

Selection of geometric and aerodynamic parameters – Weight estimation and balance diagram –Dragestimationofcompleteaircraft–Levelflight,climb,take–offandlandingcalculations–range and endurance – static and dynamic stability estimates – control requirements.

UNIT - IV SPECIAL PROBLEMS 12

Layout peculiarities of subsonic and supersonic aircraft – optimisation – of wing loading to achieve desired performance – loads on undercarriages and design requirements.

UNIT - V STRUCTURAL DESIGN 12

Estimation of loads on complete aircraft and components – Structural design of fuselage, wings and undercarriages, controls, connections and joints. Materials for modern aircraft – Methods of analysis, testing and fabrication.

TOTAL: 60

REFERENCES

1. G. Corning, “Supersonic & Subsonic Airplane Design”, II Edition, Edwards Brothers Inc., Michigan, 1953.

2. E.F.Bruhn, “AnalysisandDesignofFlightVehicleStructures”,TristateOffsetCo.,U.S.A., 1980.

3. A.A. Lebedenski, “Notes on airplane design”, Part-I, I.I.Sc., Bangalore, 1971.

4. E.Torenbeek, “Synthesis of Subsonic Airplane Design”, Delft University Press, London, 1976.


5. D.P. Raymer, “Aircraft conceptual design”, AIAA Series, 1988.

6. H.N.Kota, “ Integrateddesignapproach toDesignflybywire”Lecturenotes InterlinePub. Bangalore, 1992.

7. S.C. Keshu & K.K. Ganapathi “Aircraft Production Techniques and Management”, 1995.

SEMESTER – III ELECTIVESAE 1616 - COMPUTATIONAL FLUID DYNAMICS

L T P C 3 1 0 4

OBJECTIVE TostudytheflowoffluidsusingcomputationalmethodsUNIT - I NUMERICAL SOLUTIONS OF SOME FLUID DYNAMICAL PROBLEMS 12 Coordinatesystem,Bodyfittedcoordinatesystems,Stabilityanalysisoflinearsystem.Findingsolution of a simple gas dynamic problem, Local similar solutions of boundary layer equations, Numerical integration and shooting technique.UNIT - II TRANSONIC RELAXATION TECHNIQUES 14 Smallperturbationflows,Transonicsmallperturbation(TSP)equations,Centralandbackwarddifference schemes, conservation equations and shockpoint operator, Line relaxation techniques, Acceleration of convergence rate, Jameson’s rotated difference scheme stretching of coordinates, shockfittingtechniquesFlowinbodyfittedcoordinatesystem.UNIT - III TIME DEPENDENT METHODS 12 Stability of solution, Explicit methods, Time split methods, Approximate factorization scheme,Unsteadytransonicflowaroundairfoils.Sometimedependentsolutionsofgasdynamicproblems.UNIT - IV PANEL METHOD 12 Elements of two and three dimensional panels, panel singularities. Application of panel method toincompressible,compressible,subsonicandsupersonicflows.UNIT - V SPECIAL PROBLEMS 10 Grid generation techniques

TOTAL: 60REFERENCES 1. T.K.Bose, “Computation Fluid Dynamics” Wiley Eastern Ltd., 1988.2. H.J.Wirz and J.J. Smeldern “Numerical methods in fluid dynamics”, McGraw-Hill & Co., 1978.3. C.Y.Chow,“Introductiontocomputationalfluiddynamics”,JohnWiley,1979.4. A.A.Hirsch,‘Introductiontocomputationalfluiddynamics”,McGraw-Hill,1989


AE 1617 - CRYOGENICS

L T P C

3 1 0 4

OBJECTIVE

Tostudytheengineeringconceptofcryogenicanditsapplicationinvariousfield

UNIT - I FUNDAMENTALS OF CRYOGENICS 12

Theory behind the production of low temperature – expansion engine – heat exchangers – Cascade process - Joule Thomson and Magnetic effects – cryogenic liquids as cryogenic propellants for cryogenic rocket engines – properties of various cryogenic propellants – handling problems associated with cryogenic propellants.

UNIT - II CRYOGENIC SYSTEMS EFFICIENCY 12

Typesoflossesandefficiencyofcycles–amountofcooling–thefeaturesliquefied–coolingcoefficientofperformance–Thermodynamicefficiency–Theenergybalancingmethod.

UNIT - III THERMODYNAMIC CYCLES FOR CRYOGENIC PLANTS 12

Classificationof cryogenic cycles–TheStructureof cycles–Throttleexpansion cycles–Expander cycles – Mixed throttle expansion and expander cycles – Thermodynamic analysis – Numerical problems.

UNIT - IV PECULIAR PROBLEMS ASSOCIATED WITH CRYOPROPELLANTS 12

Storage problems of cryogenic propellants – cryogenic loading Aerospace Materials – zero gravity problems associated with cryopropellants – phenomenon of tank collapse – geysering effect.

UNIT - V CRYOGENIC ROCKET ENGINES 12

Peculiar design difficulties associated with the design of feed system, injector and thrustchamber of cryogenic rocket engines – Relative performance of cryogenic when compared to non-cryo engines.

TOTAL: 60

REFERENCES

1. Sutton, G.P. “Rocket Propelsion Elements”, John Wiley, 1993.

2. Hazel D.K. & Hungdh, “Design of Liquid Propellant Rocket Engines”, N.A.S.A. Special Publications – 125, 1971.

3. Haseldom, G., Cryogenic Fundamentals, Academic Press, 1971.

4. Barron,R.F.,CryogenicSystems,OxfordUniversity,1985.

5. Parner, S.F., Propellant Chemistry Reinfold Publishing Corporation, New York, 1985.


AE 1618 - FATIGUE AND FRACTURE MECHANICS

L T P C

3 1 0 4

OBJECTIVE

To study the concepts of estimation of the endurance and failure mechanism of components

UNIT - I FATIGUE OF STRUCTURES 12

S.N. curves – Endurance limit – Effect of mean stress – Goodman, Gerber and Soderberg relations and diagrams – Notches and stress concentrations – Neuber’s stress concentration factors – plastic stress concentration factors – Notched S-N curves.

UNIT - II STATISTICAL ASPECTS OF FATIGUE BEHAVIOUR 11

Lowcycleandhighcyclefatigue–Coffin-Manson’srelation–Transitionlife–CyclicStrainhardening and softening – Analysis of load histories – Cycle counting techniques – Cumulative damage – Miner’s theory – other theories.

UNIT - III PHYSICAL ASPECTS OF FATIGUE 10

Phase in fatigue life – Crack initiation – Crack growth – Final fracture – Dislocations – Fatigue fracture surfaces.

UNIT - IV FRACTURE MECHANICS 15

Strengthofcrackedbodies–potentialenergyandsurfaceenergy–Griffith’stheory–Irwin–OrwinextensionofGriffith’stheorytoductilematerials–Stressanalysisofcrackedbodies–Effectof thickness on fracture toughness – Stress intensity factors for typical geometries.

UNIT V FATIGUE DESIGN AND TESTING 12

Safe life and fail safe design philosophies – Importance of Fracture Mechanics in aerospace structure – Application to composite materials and structures.

TOTAL: 60

REFERENCES

1. W.BarroisandL.Ripley,“FatigueofAircraftStructures”,PergamonPress,Oxford,1983.

2. D.Brock, “Elementary Engineering Fracture Mechanics”, Noordhoff International Publishing Co., London, 1994.

3. C.G.Sih, “Mechanics of Fracture”, Vol.1 Sijthoff and Noordhoff International Publishing Co., Netherland, 1989.

4. J.F.Knott, “Fundamentals of Fracture Mechanics”, Butterworth & Co., (Publishers) Ltd., London, 1983.


AE1619 HIGH TEMPERATURE PROBLEMS IN STRUCTURES

L T P C

3 1 0 4

OBJECTIVE

To learn damage mechanism and failure of components of elevated temperatures

UNIT - I TEMPERATURE EQUATIONS & AERODYNAMIC HEATING 12

For condition, radiation and convection – Fourier’s equation – Boundary and initial conditions –One-dimensional problem formulations –Methods and Solutions. Heat balance equation foridealised structures – Adibatic temperature – Variations – Evaluation of transient temperature.

UNIT - II THERMAL STRESS ANALYSIS 12

Thermal stresses and strains – Equations of equilibrium – Boundary conditions – Thermoelasticity – Two dimensional problems and solutions – Airy stress function and applications.

UNIT - III THERMAL STRESS IN BEAMS, TRUSSES AND THIN CYLINDERS 12

Thermal stresses in axially loaded members, beams with varying cross sections. Effect of temperature in thin cylinders.

UNIT - IV THERMAL STRESSES IN PLATES 12

Membrane thermal stresses – Circular plates – Rectangular plates – Bending thermal stresses – Thick plates with temperature varying along thickness – Thermal vibration of plates.

UNIT - V SPECIAL TOPICS & MATERIALS 12

Thermal bucking, Fatigue and shock applications – High temperature effects on material properties.

TOTAL: 60

REFERENCES

1. A.B. Bruno and H.W. Jerome, “Theory of Thermal Stresses”, John Wiley & Sons Inc., New York, 1980.

2. D.J.Johns,“ThermalStressAnalysis”,PergamonPress,Oxford,1985.

3. N.J. Hoff, “High Temperature effects in Aircraft Structures”, John Wiley & Sons Inc., London, 1986.


AE 1620 - THEORY OF PLATES & SHELLS

L T P C

3 1 0 4

OBJECTIVE

To study the behaviour of the plates and shells with different geometry under various types of loads.


Plate and shell structures in aerospace vehicles.

UNIT - II SMALL DEFLECTION THEORY OF PLATES 15

Bendingofthinplates-isotropicandorthotropicflatplatesofdifferentgeometry–rectangular,square and skew plates-circular plates-different edge conditions-biharmonic equation for plate deflections.

UNIT - III SHEAR DEFORMATION AND LARGE DEFLECTION

THEORY OF PLATES 10

Assumptions-sheardeformation–Analysisofflatplatesandapplications.

UNIT - IV STABILITY OF PLATES 10

Instability of Plates-different edge conditions – Applications.

UNIT - V SHELLS 20

Basic concepts – Deformation – Membrance theory of shells applied to shells of form of surface of revolution. General theory of cylindrical shells – Circular cylindrical shells – spherical shells and conical shells.

TOTAL: 60

REFERENCES

1. W.Flugge, “Stresses in Shells”, II Edition Springer Verlag Co., New York, 1983.

2. A.L.Goldenvizier, “Theory of Elastic Thin Shells”, Pergamon Press, New York, 1981.

3. H.Kraus, Thin Elastic Shells”, John Wiley & Sons, Inc., New York, 1987.

4. S.P. Timoshenko and S.W.Krieger, “Theory of Plates and Shells”, II Edition McGraw-Hill, Kogakusha Ltd., Tokyo, 1989.

5. L.R. Calcote, “Analysis of Laminates Structures”, Van Nostrand Reinhold, 1989.


AE 1621 - INDUSTRIAL AERODYNAMICS

L T P C

3 1 0 4

OBJECTIVE

Tounderstandthebehaviourofairflowinvehicle,Buildingsandtheflowinducedvibrations.

UNIT - I ATMOSPHERE 12

Types of winds, Causes of variation of winds, Atmospheric boundary layer, Effect of terrain on gradientheight,Structureofturbulentflows.

UNIT - II WIND ENERGY COLLECTORS 12

Horizontalaxisandverticalaxismachines,Powercoefficient,Betzcoefficientbymomentumtheory.

UNIT - III VEHICLE AERODYNAMICS 12

Power requirements and drag coefficients of automobiles, Effects of cut back angle,Aerodynamics of trains and Hovercraft.

UNIT - IV BUILDING AERODYNAMICS 12

Pressure distribution on low rise buildings, wind forces on buildings. Environmental winds in city blocks, Special problems of tall buildings, Building codes, Building ventilation and architectural aerodynamics.

UNIT - V FLOW INDUCED VIBRATIONS 12

Effects of Reynolds number on wake formation of bluff shapes, Vortex induced vibrations, Gallopingandstallflutter.

TOTAL: 60

REFERENCES

1. M.Sovran (Ed), “Aerodynamics drag mechanisms of bluff bodies and road vehicles”, Plenum press, New York, 1978.

2. P. Sachs, “Winds forces in engineering”, Pergamon Press, 1978.

3. R.D. Blevins, “Flow induced vibrations”, Van Nostrand, 1990.

4. N.G.Calvent,“WindPowerPrinciples”,CharlesGriffin&Co.,London,1979.


AE 1622 - HELICOPTER AERODYNAMICS

L T P C

3 1 0 4

OBJECTIVE

To understand the behaviour of helicopter , elements of helicopter , power estimation and ground effect machines

UNIT - I LIFT, PROPULSION AND CONTROL OF V/STOL AIRCRAFT 12

Variousconfigurations–propeller,rotor,ductedfanandjetlift-Tiltwingandvectoredthrust–performanceofVTOLandSTOLaircraftinhover,transitionandforwardmotion.

UNIT - II ELEMENTS OF HELICOPTER AERODYNAMICS 12

Configurationsbasedontorquereaction–Jetrotorsandcompoundhelicopters–Methodsofcontrol–collectiveandcyclicpitcheschanges–Lead–lagandflappinghinges.

UNIT - III IDEAL ROTOR THEORY 12

Hovering performance – Momentum and simple blade element theories – Figure of merit – Profileandinducedpowerestimation–Constantchordandidealtwistrotors.

UNIT - IV POWER ESTIMATES 12

Induced,profileandparasitepowerrequirementsinforwardflight–performancecurveswitheffects of altitude – Preliminary ideas on helicopter stability.

UNIT - V GROUND EFFECT MACHINES 12

Types – Hover height, lift augmentation and power calculations for plenum chamber and peripheral jet machines – Drag of hovercraft on land and water. Applications of hovercraft.

TOTAL: 60

REFERENCES

1. B.W.McCormic,“AerodynamicsofV/STOLFlight”,AcademicPress,NewYork,1978.

2. A. Gessow and G.C.Meyers, “Aerodynamics of the Helicopter”, Macmillan and Co., New York, 1982.

3. G.H. Elsley and A.J. Devereux, “Hovercraft Design and Construction, David Charies, London, 1982.

4. Anderson J.D. “Aerodynamics”, John Wiley, 1995.


AE 1623 - AEROELASTICITY

L T P C

3 1 0 4

OBJECTIVE

To study the dynamic behaviour of different aircraft components and the interaction among elastic and inertia forces

UNIT - I AEROELASTIC PHENOMENA 10

Stability versus response problems – The aero-elastic triangle of forces – Aeroplasticity in Aircraft Design – Prevention of aeroelastic instabilities.

UNIT - II DIVERGENCE OF A LIFTING SURFACE 14

Simple two dimensional idealisations-Strip theory – Freedom integral equation of the second kind – Exact solutions for simple rectangular wings – ‘Semirigid’ assumption and approximate solutions – Generalised coordinates – Successive approximations – Numerical approximations using matrix equations.

UNIT - III STEADY STATE AEROLASTIC PROBLEMS 12

Lossand reversalofaileroncontrol–Criticalaileron reversalspeed–Aileronefficiency–Semirigid theory and successive approximations – Lift distribution – Rigid and elastic wings.

UNIT - IV FLUTTER PHENOMENON 14

Non-dimensional parameters – Stiffness criteria – Dynamic mass balancing – Model experiments – Dimensional similarity – Flutter analysis – Two dimensional thin airfoils in steady incompressibleflow–Quasisteadyaerodynamicderivatives–Galerkinmethodforcriticalspeed–Stabilityofdisturbedmotion–Torsionflexureflutter–Solutionoftheflutterdeterminant–Methodsofdeterminingthecriticalflutterspeeds–Flutterpreventionandcontrol.

UNIT - V EXAMPLES OF AEROELASTIC PROBLEMS IN CIVIL AND

MECHANICAL ENGINEERING 10

Galloping of transmission lines and flow induced vibrations of tall slender structures andsuspension bridges.

TOTAL: 60

REFERENCES

1. R.L. Bisplinghoff, H.Ashley, and R.L. Halfmann, “Aeroelasticity”, II Edition Addison Wesley Publishing Co., Inc., 1987.

2. E.G. Broadbent, “Elementary Theory of Aeroelasticity”, Bun Hill Publications Ltd., 1986.

3. Y.C. Fung, “An Introduction to the Theory of Aeroelasticity”, John Wiley & Sons Inc., New York, 1985.

4. R.H. Scanlan and R.Rosenbaum, “Introduction to the study of Aircraft Vibration and Flutter”, Macmillan Co., New York, 1981.


AE 1624 - HYPERSONIC AERODYNAMICS

L T P C

3 1 0 4

OBJECTIVE

Tounderstandthebehaviourofairflowinhypersonicairspeeds

UNIT - I BASICS OF HYPERSONIC AERODYNAMICS 12

Thinshocklayers–entropylayers–lowdensityandhighdensityflows–hypersonicflightpathshypersonicflightsimilarityparameters–shockwaveandexpansionwaverelationsofinviscidhypersonicflows.

UNIT - II NUMERICAL METHODS FOR HYPERSONIC AERODYNAMICS 10

Localsurfaceinclinationmethods–modifiedNewtonianLaw–Newtoniantheory–tangentwedge or tangent cone and shock expansion methods

UNIT - III HYPERSONIC INVISCID FLOWS 15

Approximate methods hypersonic small disturbance equation and theory – thin shock layer theory: exact methods of characteristics hypersonic shock wave shapes and correlations.

UNIT - IV VISCOUS HYPERSONIC FLOW THEORY 15

Navier–Stokes equations – boundary layer equations for hypersonic flow – hypersonicboundary layer – hypersonic boundary layer theory and non similar hypersonic boundary layers – hypersonic aerodynamic heating and entropy layers effects on aerodynamic heating.

UNIT - V VISCOUS INTERACTIONS IN HYPERSONIC FLOWS 8

Strong and weak viscous interactions – hypersonic shockwaves and boundary layer interactions – Role of similarity parameter for laminar viscous interactions in hypersonic viscous flow.

TOTAL: 60

REFERENCES

1. John D. Anderson “Hypersonic and High Temperature Gas Dynamics”, Jr, McGraw-Hill Series, New York, 1996.

2. John.D.Anderson “Modern Compressible Flow with Historical perpectant”, Jr. Hypersonic Series.

3. William H. Heiser and David T. Praff “Hypersonic Air breathing propulsion”, AIAA Education Series.

4. John T. Bertin “Hypersonic Aerothermodynamics”, 1994 published by AIAA Inc., Washington D.C.

Documents

M. Tech. Aeronautical Engineering