Here we are providing Airframe Structural Design Textbook Free Download Pdf. This book represents several decades of data collection, research, conversations with different airframe specialists, plus the author’s more than twenty years’ experience in airframe structural design. From structural standpoint, the book is intended to be used as a tool to help achieve structural integrity according to government regulations, specifications, criteria, etc., for designing commercial or military transports, military fighters, as well as general aviation aircraft. It can be considered as a troubleshooting guide for airline structural maintenance and repair engineers or as a supplementary handbook in teaching aircraft structural design in college. This book is divided into a total of sixteen chapter and emphasizes itemized write-ups, tables, graphs and illustrations to lead directly to points of interest. The data can be used for designing and sizing airframe structures and, wherever needed, example calculations are presented for clarification.

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About Aerodynamics -l Book

Aerodynamics is both the science of the way air moves, and furthermore essentially the way a protest’s shape influences how it travels through the air. A great part of the plan of airplanes concentrates on the aerodynamics of their wings and noses, keeping them on high and moving rapidly through the air. The word aerodynamics has been around since the mid-1800s, consolidating the Greek prefix aero-, “air,” and dynamics, a word connected to many branches of material science, from the Greek dynamikos, “effective.”

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About Aerodynamics -2 Book

Aerodynamics is the investigation of forces and the subsequent motion of articles through the air.

Concentrate the motion of air around a question enables us to quantify the forces of lift, which enables an aircraft to conquer gravity, and drag, which is the protection an aircraft “feels” as it travels through the air. Everything traveling through the air (counting airplanes, rockets, and winged creatures) is influenced by aerodynamics.

In this area, we will investigate how lift and drag function at both subsonic velocities slower than the speed of sound and, later, at supersonic rates speedier than the speed of sound.

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Syllabus of Flight Mechanics -2 Book

UNIT – I:

Aircraft in Equilibrium Flight – Elevator Anglr to Trim – Longitudinal Static and Maneuver Stability: Need for controlled flight, Equilibrium, stability, trim, control- definitions- examples. Longitudinal forces and moments on aircraft in unaccelerated flight- contribution of principlal components. Equations of equilibrium- thrust, angle of attack, elevator angle required to trim. Control gradient, total airplane lift curve slope and pitch stiffness. Tailless aircraft and aircraft with foreplanes. Longitudinal static stability- definition, relation to control gradient, pitch stiffness. Stick fixed neutral point- static margin. Effect of flaps and flight speed on force and moment coefficients, aerodynamic derivatives, stability, trim.

Steady, symmetric pull-up maneuvers-equations of motion- pitch rate, pitch damping. Control to trim, trim curves- elevator per g- maneuver point, maneuver margin- relation to static margin, Statutory limits on postion of centre of gravity. Deermination of neutral and maneuver points by flight testing.

UNIT – II:

Estimation of Aerodynamic Force and Moment Derivatives of Aircraft: Significance of aerodynamic derivatives. Derivatives of axial, normal force components and pitching moment with respect to the flight speed, angle of attack, angle of attack rate, pitch rate, elevator angle- dependence on vehicle geometry, flight configuration- effects of flaps, power, compressiblity and aeroelasticity.

Lateral directional motion- coupling- derivatives of side force, rolling and yawing moments with respect to the sideslip, rate of sideslip, roll rate, yaw rate, aileron, rudder deflections- dependence on vehicle geometry, flight configuration. Estimation- the strip theory method. Relation between dimension-less and dimensional aerodynamic derivatives.

UNIT – III:

Stick Free Longitudinal Stability- Control Forces to Trim, Lateral- Directional Static Stability and Trim: Elevator hinge moments- relation to control stick forces. Hinge moment derivatives, Stick force to trim in symmetric unaccelerated flight, maneuvering flight. Stick force gradients- effect of trim speed- role of trim tab. Effect of freeing elevator on tail effectiveness, static and maneuver stability, Elevator- free factor. Stick- free neutral and maneuver points, stability margins- relation with stick force gradients. Aerodynamic and mass balancing of control surfaces. Control tabs- types, function construction.

Lateral- directional static stability, definition, requirements. Equilibrium of forces and moments. Aileron, rudder, elevator and thrust required to trim aircraft in steady sideslip, roll, coordinated turn, engine out condition. Cross wind landings.

UNIT – IV:

Aircraft Equations of motion- Perturbed Motion- Linearised, Decoupled Equations: Description of motion of flight vehicles- systems of reference frames- Euler angles, angles of attack and sideslip- definitions- earth to body axis transformation, Rotation axis system- expressions for linear and angular momenta of rigid body, time derivatives- inertia tensor, components of linear and angular velocities, accelerations. Resolution of aerodynamic, gravity forces, moments acting on flight vehicle. Relation between angular velocity components and lateral-directional. Relation between angular velocity components and Euler angle rates, Determination of velocities of airplane in earth axis system, Determination of vehicle trajectory- outline of method.

Description of motion as pertubation over prescribed reference flight condition. Equation of motion in pertubation variables. Assumption of small pertubations, forst order approximations- linearised equations of motion. Decoupling into longitudinal and lateral-directional motions- conditions for validity- role of symmetry. Linearised longitudinal and leteral-directional equations of pertubed motion.

UNIT – V:

Longitudinal and Lateral- Directional Dynamic Stability: Linearised longitudinal equations of motion of aircraft- three degree of freedom analysis- characteristic equations- solutions- principal modes of motion- characteristics- time constant, undamped natural frequency and damping ratio- mode shapes- significance. One degree of freedom, two degree of freedom approximations- constant speed (short period), constant angle of attack (long period) approximations- solutions- comparison with three degree of freedom solutions- justification of approximations. Lateral directional equations- three degree of freedom analysis. Principal modes- characteristics- mode shapes- significance, lower order analysis- approximate solutions.

Determination of longitdinal and lateral stability from coefficients of characteristic equation- stability and lateral stability from coefficients of characteristics equation- stability criteria, approximate roots, Special problems in aircraft dynamics- roll coupling, high angle of attack operation. Aircraft spin- entry, balance of forces in steady spin, recovery, pilot techniques.

TEXT BOOKS:

1. Yechout, T. R. et al., Introduction to Aircraft Flight Mechanics, AIAA education Series, 2003, ISBN 1-56347-577-4.
2. Nelson, R. C., Flight Stability and Automatic Control, 2nd Edition., Tata Mc Graw Hill, 2007, ISBN 0-07-066110-3.

REFERENCE BOOKS:

1. Etkin, B. and Reid, L. D., Dynamics of Flight, 3rd Edition., John Wiley, 1998, ISBN 0-47103418-5.
2. Schmidt, L. V., Introduction to Aircraft Flight Dynamics, AIAA Education Series, 1998, ISBN A-56347-226-0.
3. McCormick, B. W., Aerodynamics, Aeronautics and Flight Mechanics, 2nd Edition., Wiley India, 1995, ISBN 978-.

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Contents of Flight Mechanics -1 Book

UNIT – I

Introduction to Aircraft Performance- the Force Systems of The Aircraft: The role and design mission of an aircraft. Specification of the performance requirements and mission profile. Importance of performance analysis, estimation, measurement, operational safety and economy. Scheduled performance and operational performance of aircraft. The Standard Atmosphere. Off-standard and design atmosphere. Measurement of air data. Air data computers.

Equations of motion for performance – the aircraft force system. Lift, drag, side force. Total airplance drag- estimation, drag reduction methods. The propulsive forces – the thrust production engines, power producing engines, variation of thrust, propulsive power andspecific fuel consumption with altitude and flight speed. The minimum drag speed, minimum power speed. Aerodynamic relationships for a parabolic drag polar.

UNIT – II

Cruise Performance: Maximum and minimum speeds in level flight. Range and endurance with thrust production, and power producing engines. Cruise techniques – constant angle of attack, constant Match number; constant altitude, methods- comparision of performance. The effect of alternative fuel flow laws, weight, altitude and temperature on cruise performance. Cruise performance with mixed power-plants.

UNIT – III

Climb, Descent and Manoeuvre Performance: Climb and descent techniques, safety considerations, performance analysis- maximum climb gradient, climb rate. Energy height and specific excess power, optimal climbs – minimum time, minimum fuel climbs. Measurement of climb performance. Descent performance in aircraft operations. Effect of wind on climb and descent perfomance.

Accelerated motion of aircraft – equations of motion- the manoeuvre envelope. Longitudinal manoeuvres- the pull-up, push over manoeuvres. Lateral manoeuvres- turn performance- turn rates, turn radius- limiting factors. Instantaneousand sustained turns, specific excess power, energy turns. Manouvre boundaries, Manoeuvre performance of military aircraft, transport aircraft.

UNIT – IV

Take-off And Landing- Safety Requirements – Flight Planning: Estimation of take-off distances. The effect on the take-off distance, of weight, wind, runway conditions, ground effect. Take-off performance safety factors. Estimation of landing distances – the discontinued landing, baulked landing. Air safety procedures and requirements on landing performance.

UNIT – V

Aircraft Performance Measurement and Data Handling – Application of Performance Data: Purpose of performance measurment in flight. Flight testing- principal performance variables – weight, altitude and ambient temperature (WAT). Parametric performance data analysis. Dimensional analysis. Measurement of cruise, climb, take-off and landing performance- data reduction- equivalent weight method. Corrections for weight and temperature.

Operational performance data for flight planning- take-off field performance, runway correction, aircraft datum performance (WAT) charts, determination of the maximum take-off weight. Performance summary for fleet selection – the block performance, payload-range diagram . Route analysis and optimisation. Operational analysis procedure.

TEXT BOOKS

1. Eshelby, M.E., Aircraft Performance; Theory and Practice, AIAA Education Series, AIAA, 2000, ISBN: 1-56347-398-4.
2. Brandt, S.A, et. al., Introduction to Aeronautics: A Design Perspective, Second Edition, AIAA Education Series, AIAA, 2004, ISBN: 1-56347-701-7.
3. Anderson, J.D. Jr., Aircraft Performance and Design, International edition, McGraw Hill, 1999, ISBN: 0-07-001971-1.

REFERENCES

1. Dole, C.E., Flight Theory and Aerodynamics: a Practical Guide for Operational Safety, Wiley Interscience, 1981, ISBN: 0-471-09152-9.
2. McCormick, B.W, Aerodynamics, Aeronautics and Flight Mechanics, second edition, John Wiley, 1995, ISBN: 0-471-57506-2.
3. Shevel, R.S., Fundamentals of Flight, second edition, Pearson Education, 1989, ISBN: 81-297-0514-1.
4. Raymer, D.P., Aircraft Design: A Conceptual Approach, third edition, AIAA Education Series, AIAA, 1999, ISBN: 1-56347-281-0.
5. Yechout, T.R. et al., Introduction to Aircraft Flight Mechanics, AIAA Eduction Series , AIAA, 2003, ISBN: 1-56347-577-4.

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