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Aircraft Structures (Dover Books on Aeronautical Engineering), by David J. Peery
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Still relevant decades after its 1950 publication, this legendary reference text on aircraft stress analysis is considered the best book on the subject. It emphasizes basic structural theory, which remains unchanged with the development of new materials and construction methods, and the application of the elementary principles of mechanics to the analysis of aircraft structures.
Suitable for undergraduate students, this volume covers equilibrium of forces, space structures, inertia forces and load factors, shear and bending stresses, and beams with unsymmetrical cross sections. Additional topics include spanwise air-load distribution, external loads on the airplane, joints and fittings, deflections of structures, and special methods of analysis. Topics involving a knowledge of aerodynamics appear in final chapters, allowing students to study the prerequisite aerodynamics topics in concurrent courses.
- Sales Rank: #52216 in Books
- Published on: 2011-12-14
- Released on: 2011-11-16
- Original language: English
- Number of items: 1
- Dimensions: 9.10" h x 1.20" w x 6.00" l, 1.65 pounds
- Binding: Paperback
- 576 pages
About the Author
The late David J. Peery was an Aeronautical Engineering Professor at Penn State University.
Most helpful customer reviews
13 of 13 people found the following review helpful.
One of the Finest Structures Books Ever Written
By A Reader
I got my BS in Aerospace Engineering in 1970. In order to graduate we had to design an entire airplane by hand (200+ passengers, four engines, etc.). We had to produce full drawings, a full structural analysis, full weight and balance analysis, full materials analysis, full engine analysis, i.e. enough information to start producing a real aircraft on an assembly line using only a slide rule, a hand cranked adding machine, and books. This was one of those books. There were no computers or computer programs to help with the design. Those would be invented later and I helped develop some of the first structural analysis computer programs (because we were all tired of doing structural analysis by hand).
So if the power grid is destroyed and there is no access to AutoCAD or CATIA, I can still design anything using this book (with several others), a pen, some paper, and a slide rule (which I still have). Get this book it might be a life saver.
7 of 7 people found the following review helpful.
Thorough treatment of fundamentals, broad coverage, suitable for undergraduates and practitioners
By keith towell
Second only to Bruhn and includes basics of loads analysis which Bruhn does not.
Though it doesn't cover FE techniques, it does provide the foundation on which knowledge of FE can be built. Without a good foundation like this, the student will likely struggle with FE.
Thoroughly recommended for undergraduates, homebuilders and practitioners, and not restricted to the design of aircraft but a good foundation text for civil and marine structures.
Covers equilibrium, statically determinate and indeterminate structures, shear, bending, torsion, space-frames and monocoques, combined loading, metallic material properties, air loads and inertia loads, joint design, efficient structures, and numerical methods some of which, though not widely used nowadays, give a better understanding of how the structure bears the loads than will be obtained by churning numbers through a computer.
18 of 22 people found the following review helpful.
David J. Peery, "Aircraft Structures"
By Jiri Cerny
David J. Perry's "Aircraft Structures" is indisputably a classic reference for the students and practicing engineers as well, and most likely a best text book ever written on the subject of the static strength and stability of metallic aircraft structures and its components.
However, both editions, the original from 1950, and 2nd from 1982, contain a minor error in "Joints and Fittings" Chapter (page 304 of 1950 edition, page 397 of 2nd edition):
The last paragraph contains a statement: " ... in Fig. 12.15.(c), which yields maximum bearing stresses, 4P/tb at the inside corner and 2P/tb at the outside corners." Conversely, these bearing stress expressions don't agree with those (i.e., 4P/td, 2P/td) shown in Fig. 12.15.(c). Because the text doesn't corroborate how it was arrived to the maximum pin bending moment 4Pt/27 [InLb] shown on page 305, this discrepancy may confuse the issue.
That this indeed may lead to the confusion is evident in Michael Niu's "Airframe Stress Analysis and Sizing", 2nd edition, page 275, Eq. 9.1.1. Here in all likelihood Niu copied Peery's equation (12.8), but apparently unable to reconcile mentioned discrepancies, in the equation simply left out plate width "b", and not addressing the maximum bearing stress in question, boldly claims that this tensile stress is for "1.0 inch - wide strap".
In the equation (12.8) Peery logically concludes, that if the axial stresses (as derived from the equation P/A ± M/W at both plate faces) are four times (resp. two times) of the average stress value, then same should be valid for the pin bearing stresses too. In other words, at a point, the load intensity (unit loading) producing maximum axial stress in the plate has to be equal to the load intensity causing the maximum bearing stress on the pin. This means, that the extreme load intensities on the pin will be obtained by dividing extreme plate stresses by plate width "b". Then by dividing these extreme load intensities by the pin diameter, one will obtain pin bearing stresses at both plate faces, and these expressions are in agreement with those shown in Fig. 12.15.(c).
And thus the text in last paragraph on this page should read: "...,which yields maximum bearing stresses, 4P/td at the inside corner and 2P/td at the outside corners ...".
If one constructs shear force diagram, then at the outside of the plate the pin shear
force equals to 0 [Lb], at 1/3t (measured from outside of the plate) the shear force equals to P/3 [Lb] , at 2/3t (measured from plate outside) the shear force equals to 0 [Lb] (i.e., the location of maximum bending moment), and on the inside of the plate the shear force has to balance with the applied load P [Lb].
For the moment diagram, the pin bending moments equal to zero at both plate faces, and the maximum moment, Mmax = 2 x (P/3 x 2/3 x t/3) = 4Pt/27 [InLb] exists in the location where the internal shear force in the pin changes its sign, i.e. at t/3 measured from the inside of the plate.
Perry's "Aircraft Structures", 1950 Edition, as well as Flabel's "Practical Stress Analysis for Design Engineers" are my favorite stress references, and both are highly recommended to the students and practicing engineers as well.
Jiri Cerny,
Stress Guesser (jobshopper)
[ASIN:0070491968 Aircraft Structures]
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