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## Paperback

^{$}29.78

## Overview

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.

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## Product Details

ISBN-13: | 9780486485805 |
---|---|

Publisher: | Dover Publications |

Publication date: | 12/14/2011 |

Series: | Dover Books on Aeronautical Engineering |

Pages: | 576 |

Sales rank: | 812,747 |

Product dimensions: | 6.14(w) x 9.21(h) x (d) |

## About the Author

The late David J. Peery was an Aeronautical Engineering Professor at Penn State University.

## Read an Excerpt

#### AIRCRAFT STRUCTURES

**By David J. Peery**

**Dover Publications, Inc.**

**Copyright © 2014 Dover Publications, Inc.**

All rights reserved.

ISBN: 978-0-486-26730-2

All rights reserved.

ISBN: 978-0-486-26730-2

CHAPTER 1

**EQUILIBRIUM OF FORCES**

**1.1. Equations of Equilibrium.** One of the first steps in the design of a machine or structure is the determination of the loads acting on each member. The loads acting on an airplane may occur in various landing or flight conditions. The loads may be produced by ground reactions on the wheels, by aerodynamic forces on the wings and other surfaces, or by forces exerted on the propeller. The loads are resisted by the weight or inertia of the various parts of the airplane. Several loading conditions must be considered, and each member must be designed for the combination of conditions which produces the highest stress in the member. For practically all members of the airplane structure the maximum loads occur when the airplane is in an accelerated flight or landing condition and the external loads are not in equilibrium. If, however, the inertia loads are also considered, they will form a system of forces which are in equilibrium with the external loads. In the design of any member it is necessary to find all the forces acting on the member, including inertia forces. Where these forces are in the same plane, as is often the case, the following equations of static equilibrium apply to any isolated portion of the structure:

[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII] (1.1)

The terms [summation]*Fx* and [summation]*Fy* represent the summations of the components of forces along *x* and *y* axes, which may be taken in any two arbitrary directions. The term [summation]*M* represents the sum of the moments of all forces about any arbitrarily chosen point in the plane. Each of these equations may be set up in an infinite number of ways for any problem, since the directions of the axes and the center of moments may be chosen arbitrarily. Only three independent equations exist for any free body, however, and only three unknown forces may be found from the equations. If, for example, an attempt is made to find four unknown forces by using the two force equations and moment equations about two points, the four equations cannot be solved because they are not independent, *i.e.*, one of the equations can be derived from the other three. The following equations cannot be solved for the numerical values of the three unknowns because they are not independent.

*x + y + z* = 3

*x + y* + 2*z* = 4

2*x* + 2*y* + 3*z* = 7

The third equation may be obtained by adding the first two equations, and consequently does not represent an independent condition.

In the analysis of a structure containing several members it is necessary to draw a free-body diagram for each member, showing all the forces acting on that member. It is not possible to show these forces on a composite sketch of the entire structure, since equal and opposite forces act at all joints and an attempt to designate the correct direction of the force on each member will be confusing. In applying the equations of statics it is desirable to choose the axes and centers of moments so that only one unknown appears in each equation.

Many structural joints are made with a single bolt or pin. Such joints are assumed to have no resistance to rotation. The force at such a joint must pass through the center of the pin, as shown in **Fig. 1.1**, since the moment about the center of the pin must be zero. The force at the pin joint has two unknown quantities, the magnitude *F* and the direction θ. It is usually more convenient to find the two unknown components, *Fx* and *Fy*, from which *F* and θ can be found by the equations:

*F* = √ *F*2*x* + *F*2*y* (1.2)

tan θ = *Fy/Fx* (1.3)

The statics problem is considered as solved when the components *Fx* and *Fy* at each joint are obtained.

**1.2. Two-force Members.** When a structural member has forces acting at only two points, these forces must be equal and opposite, as shown in **Fig. 1.2**. Since moments about point *A* must be zero, the force *FB* must pass through point *A*. Similarly the force *FA* must pass through point *B* for moments about point *B* to be zero. From a summation of forces, the forces *FB* and *FA* must have equal magnitudes but opposite directions. Two-force members are frequently used in aircraft and other structures, since simple tension or compression members are usually the lightest members for transmitting forces. Where possible, two-force members are straight, rather than curved as shown in **Fig. 1.2**. Structures made up entirely of two-force members are called trusses and are frequently used in fuselages, engine mounts, and other aircraft structures, as well as in bridge and building structures. Trusses represent an important special type of structure and will be treated in detail in the following articles.

Many structures contain some two-force members, as well as some members which resist more than two forces. These structures must first be examined carefully in order to determine which members are two-force members. Students frequently make the serious mistake of assuming that forces act in the direction of a member, when the member resists forces at three or more points. In the case of curved two-force members such as shown in **Fig. 1.2**, it is important to assume that the forces act along the line between pins, rather than along the axis of the members.

While Eqs. 1.1 are simple and well known, it is very important for a student to acquire proficiency in the application of these equations to various types of structures. A typical structure will be analyzed as an example problem.

**Example.** Find the forces acting at all joints of the structure shown in **Fig. 1.3**.

*Solution.* First draw free-body diagrams of all members, as shown in **Fig. 1.4**. Since *AB* and *GD* are two-force members, the forces in these members are along the line joining the pin joints of these members, and free-body diagrams of these members are not shown. The directions of forces are assumed, but care must be taken to show the forces at any joint in opposite directions on the two members, that is, *Cx* is assumed to act to the right on the horizontal member, and therefore must act to the left on the vertical member. If forces are assumed in the wrong direction, the calculated magnitudes will be negative.

For the pulley,

[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII]

Once the numerical values of these forces are obtained, they are shown on the free-body diagram. Subsequent equations contain the known numerical values rather than the algebraic symbols for the forces.

For member *CGH*,

[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII]

Since *Cx* and *Cy* are negative, the directions of the vectors on the free-body diagrams are changed. Such changes are made by crossing out the original arrows rather than by erasing, in order that the analysis may be checked conveniently by the original designer or by others. Extreme care must be observed in using the proper direction of known forces.

For member *BCDE*,

[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII]

All forces have now been obtained without the use of the entire structure as a free body. The solution will be checked by using all three equations of equilibrium for the entire structure.

Check using entire structure as free body,

**[summation] Fx = 1,250 - 1,000 - 500 cos 60° = 0**

**[summation] Fy = 1,433 - 1,000 - 500 sin 60° = 0**

**[summation] FE = 1,000 x 9 - 1,000 x 7 - 500 x 4 = 0**

This check should be made wherever possible in order to detect errors in computing moment arms or forces.

**PROBLEMS**

**1.1.** A 5,000-lb airplane is in a steady glide with the flight path at an angle θ below the horizontal. The drag force in the direction of the flight path is 750 lb. Find the lift force *L* normal to the flight path and the angle θ.

**1.2.** A jet-propelled airplane in steady flight has forces acting as shown. Find the jet thrust *T*, lift *L*, and tail load *P*.

**1.3.** A wind-tunnel model of an airplane wing is suspended as shown. Find the loads in members *B, C,* and *E* if the forces at *A* are *L* = 43.8 lb, *D* = 3.42 lb, and *M* = -20.6 in-lb.

**1.4.** For the model of Prob. 1.3 find the forces *L, D,* and *M* at a point *A*, if the measured forces are *B* = 40.2 lb, *C* = 4.16 lb, and *E* = 3.74 lb.

**1.5.** Find the horizontal and vertical components of the forces at all joints. The reaction at point *B* is vertical. Check results by using the three remaining equations of statics.

**1.6.** Find the horizontal and vertical components of the forces at all joints. The reaction at point *B* is horizontal. Check results by three equations.

**1.7.** Find the horizontal and vertical components of the forces at all joints. The reaction at point *B* is vertical. Check results by three equations.

**1.8.** Find the forces at all joints of the structure. Check results by three equations.

**1.9.** Find the forces on all members of the biplane structure shown. Check results by considering equilibrium of entire structure as a free body.

**1.10.** Find the forces at points *A* and *B* of the landing gear shown.

**1.11.** Find the forces at points *A, B,* and *C* of the structure of the bracedwing monoplane shown.

**1.12.** Find the forces *V* and *M* at the cut cross section of the beam.

**1.3. Truss Structures.** A truss has been defined as a structure which is composed entirely of two-force members. In some cases the members have a single bolt or pin connection at each end, and the external loads are applied only at the pin joints. In other cases the members are welded or riveted at the ends, but are assumed to be pin-connected in the analysis because it has been found that such an analysis yields approximately the correct values for the forces in the members. The trusses considered in this chapter are assumed to be coplanar; the loads resisted by the truss and the axes of all of the truss members lie in the same plane.

Trusses may be classified as statically determinate and statically indeterminate. The forces in all of the members of a statically determinate truss may be obtained from the equations of statics. In a statically indeterminate truss, there are more unknown forces than the number of independent equations of statics, and the forces cannot be determined from the equations of statics. If a rigid structure is supported in such a manner that three nonparallel, nonconcurrent reaction components are developed, the three reaction forces may be obtained from the three equations of statics for the entire structure as a free body. If more than three support reactions are developed, the structure is statically indeterminate externally.

Trusses which have only three reaction force components, but which contain more members than required, are statically indeterminate internally. Trusses are normally formed of a series of triangular frames. The first triangle contains three members and three joints. Additional triangles are each formed by adding two members and one joint. The number of members *m* has the following relationship to the number of joints *j*.

*m* - 3 = 2(*j* - 3)

or

*m* = 2*j* - 3 (1.4)

If a truss has one less member than the number specified by Eq. 1.4, it becomes a linkage or mechanism, with one degree of freedom. A linkage is not capable of resisting loads, and is classified as an unstable structure. If a truss has one more member than the number specified by Eq. 1.4, it is statically indeterminate internally.

If each pin joint of a truss is considered as a free body, the two statics equations [summation]*Fx* = 0 and [summation]*Fy* = 0 may be applied. The equation [summation]*M* = 0 does not apply, since all forces act through the pin, and the moments about the pin will be zero regardless of the magnitudes of the forces. Thus, for a truss with *j* joints, there are 2*j* independent equations of statics. The equations for the equilibrium of the entire structure are not independent of the equations for the joints, since they can be derived from the equations of equilibrium for the joints. For example, the equation [summation]*Fx* = 0 for the entire structure may be obtained by adding all the equations [summation]*Fx* = 0 for the individual joints. The equations [summation]*Fy* = 0 and [summation]*M* = 0 for the entire truss may similarly be obtained from the equations for the joints. Equation 1.4 may therefore be derived in another manner by equating the number of unknown forces for m members and three reactions to the number of independent equations 2*j*, or *m* + 3 = 2*j*.

It is necessary to apply Eq. 1.4 with care. The equation is applicable for the normal truss which contains a series of triangular frames and has three external reactions, such as the truss shown in **Fig. 1.5( a)**. For other trusses it is necessary to determine by inspection that all parts of the structure are stable. The truss shown in

**Fig. 1.5(**satisfies Eq. 1.4; yet the left panel is unstable, while the right panel has one more diagonal than is necessary. The truss shown in

*b*)**Fig. 1.5(**is stable and statically determinate, even though it is not constructed entirely of triangular frames.

*c*)Some trusses may have more than three external reactions, and fewer members than are specified by Eq. 1.4, and be stable and statically determinate. The number of reactions r may be substituted for the three in Eq. 1.4.

*m* = 2*j - r* (1.4*a*)

The number of independent equations, 2*j*, is therefore sufficient to obtain the *m + r* unknown forces for the members and the reactions. An example of a stable and statically determinate truss which has four reactions may be obtained from the truss of **Fig. 1.5( a)** by adding a horizontal reaction at the upper left-hand corner and removing the right-hand diagonal member.

**1.4. Truss Analysis by Method of Joints.** In the analysis of a truss by the method of joints, the two equations of static equilibrium, [summation]*Fx* = 0 and [summation]*Fy* = 0, are applied for each joint as a free body. Two unknown forces may be obtained for each joint. Since each member is a two-force member, it exerts equal and opposite forces on the joints at its ends. The joints of a truss must be analyzed in sequence by starting at a joint which has only two members with unknown forces. After finding the forces in these two members, an adjacent joint at the end of one of these members will have only two unknown forces. The joints are then analyzed in the proper sequence until all joints have been considered.

In most structures it is necessary to determine the three external reactions from the equations of equilibrium for the entire structure, in order to have only two unknown forces at each joint. These three equations are used in addition to the 2*j* equations at the joints. Since there are only 2*j* unknown forces, three of the equations are not necessary for finding the unknowns, but should always be used for checking the numerical work. The analysis of a truss by the method of joints will be illustrated by a numerical example.

**Example.** Find the loads in all the members of the truss shown in **Fig. 1.6**.

*Solution.* Draw a free-body diagram for the entire structure and for each joint, as shown in **Fig. 1.7.** Since all loads in the two-force members act along the members, it is possible to show all forces on a sketch of the truss, as shown in **Fig. 1.7**, if the forces are specified as acting on the joints. Care must be used in the directions of the vectors, since at every point there is always a force acting on the member which is equal and opposite to the force acting on the joint. If a structure contains any members which are not two-force members, it is always necessary to make separate free-body sketches of these members, as shown in **Fig. 1.4**.

*(Continues...)*

Excerpted fromAIRCRAFT STRUCTURESbyDavid J. Peery. Copyright © 2014 Dover Publications, Inc.. Excerpted by permission of Dover Publications, Inc..

All rights reserved. No part of this excerpt may be reproduced or reprinted without permission in writing from the publisher.

Excerpts are provided by Dial-A-Book Inc. solely for the personal use of visitors to this web site.

## Table of Contents

Preface

1. Equlibrium of Forces

2. Space Structures

3. Inertia Forces and Load Factors

4. Moments of Inertia, Mohr's Circle

5. Shear and Bending-Moment Diagrams

6. Shear and bending Stresses in Symmetrical Beamsd

7. Beams with Unsymmetrical Cross Sections

8. Analysis of Typical Members of Semimonocoque Structures

9. Spanwise Air-Load Distribution.

10. External Loads om the Airplane

11. Mechanical Properties of Aircraft Materials

12. Joints and Fittings

13. Design of Members in Tension, Bending, or Torison

14. Design of Compression Members

15. Design of Webs in Shear

16. Deflections of Structures

17. Statistically Indertiminate Structures

18. Special Methods of Analysis

Appendix

Index