seismic analysis and design of foundations

... Semi-Tension Field Design Part 1 Beams with Flat Webs Part 2 Curved Web Systems C12 Sandwich Construction and Design c13 Fatigue CONNECTIONS AND DESIGN DETAILS D1 Fittings and Connections Bolted and Riveted ... Example Problem Design for Compression - Design Conditions and Design Weights Design Flight Requirements for Airplane Design Loads Design for Tension Differential Equation of Deflection Surface ... Strength and Design of Round, Streamline, Oval and Square Tubing in Tension, Compression, Bending, Torsion and Combined Loadings cs Buckling Strength of Flat Sheet in Compression, Shear, Bending and

Ngày tải lên: 07/08/2014, 10:20

... and A2.51, we obtain 3528 and 504 which check the reactions obtained in Fig A2.46 A2.13 > Landing Gear Structure The airplane ig both a landborme and air- borne vehicle, and thus a means of ... a paramount design requirement of landing gear, as inerficitent structural arrangement and conservative stress analysis can add many unnecessary pounds of welght to the airplane and thus decrease ... weight of the airplane and these large loads must be carried into the supporting wing or fuselage structure Since the weight of land- ing gear may amount to around 6 percent of the weight of the

Ngày tải lên: 07/08/2014, 10:20

... Trang 1 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES *loy and Igy = moment of inertia of each portion about their own X and Y centrold- al axes Location of centroidal axes:- ... section properties of a few structural shapes common to aircraft Use of these tables Trang 3 ANALYSIS AND DESIGN OF FLIGHT VEHICLE th —Y tr Table A3 12 i\ vị: Ver Properties of Extruded Aluminum ... (under the control of the pilot) (1) Air Loads Due to Air Gusts (not under control of pilot) Landing on Land (wheel or ski type) (2) Landing Loads 4 Landing on water Arresting (Landing on Air- craft

Ngày tải lên: 07/08/2014, 10:20

... where practical analysis and design of beam~column members is considered For a com- Pleted and comprehensive treatment of beam-col- umn theory and derivation of equations, see Niles and Newell-"Airplane ... center of pressure at 27 percent of the chord from leading edge of wing and calcu~ late anc draw the front and rear deam pri- Trang 16 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES BENDING ... structural analysis of the body The load analysis of an airplane body involves a large amount of calculation, and thus the treatment in this chapter must be of 2 simplified nature, and is presented

Ngày tải lên: 07/08/2014, 10:20

... almost any shape of cross- section by the use of the membrane analogy It was pointed out by Prandtl that the equation of torsion of a bar and the equation for the deflection of a membrane subjected ... channel, and Tee Shapes catwo-P OF & bar of rectangular cross-section of width b and thickness t a mathematical elasticity analysis gives the following equations for max!- mum shearing stress and ... Torsion of Thin-Walled Closed Sections The structure of aircraft wings, fuselages and control surfaces are essentially thin-walled tubes of one or more cells Flight and landing loads often produce

Ngày tải lên: 07/08/2014, 10:20

... Example Problem 15 For the truss of Fig A7.16 determine e) the absolute rotation of member DG †) the rotation of member BG relative to Trang 6 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES Example ... There {Ss much to recommend the use of matrix methods for the handling of the quantity of data arising in the solutions of stress and deflection calculations of complex structures: The data is ... Method for Re- ducing the Analysis of Complex Redundant Structures to a Routine Procedure, Journ of Aero Sciences, 19, October T882 Trang 12 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES

Ngày tải lên: 07/08/2014, 10:20

... deflection of Trang 5 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES For this problem we need only to consider the elastic loads between points > and d as loads on a simple beam supported at b and ... cantilever beam of Fig A7.83 is loaded normal to the plane of the paper by the two loads of 100¢ each as shown Find the de- flection of point A normal to the plane of the paper by the method of virtual ... Trang 7ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES (30) For the truss of Fig A7 95 determine the influence coefficient matrix relating vertical deflections due to loads Py, Pa, P Ps and P,

Ngày tải lên: 07/08/2014, 10:20

... Section} 1 C.g of | C.g of In order to take moments of the Js values in column (4) of the table, the centrotd of each portion of the diagram must be determined For example, the centroid of the two ... resisting stress and thus consideration must be given to section and physical properties to obtain a solution of the distribution of the internal resisting forces General Methods of Analysis: There ... and 7 can be re- written using the redundants X,, Yj, and M, in Ag, 3 place of Xa, Yy and Mg respectively The axes x and y through the point (o) are centroidal axes for the values ds/EI of

Ngày tải lên: 07/08/2014, 10:20

... (0), remembering Ốg = 1 and located at point ?ixed at far end 3 and freely supported at near Trang 6 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES end A The ratio of th ore tne stiffness ... Trang 4HÀ ` ĐC ncen— ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES in Chapter AQ provides a rapid and simple method for determining these values for curved members The use of the elastic center ... members AC and FD prevent horizontal movement of joints A, C, F, and D due to bending of the two arches Any horizontal movement of these joints due to axial deforma~ tion is usually of minor importance

Ngày tải lên: 07/08/2014, 10:20

... axis x-x and at points 1-1 and 2-2 of the cross-section as shown in Fig Al4.5 The neutral axis location and moment of inertia of the section about the BENDING SHEAR STRESSES, SOUND AND OPEN SECTIONS, ... points a and b or d and c, the arm z in equation (9) Is constant and thus q varies linearly as plotted Between b and O or O and c the arm z2 changes and the area is also a function of z, thus ... inside edge of a curved unit in bending may influence the fatigue strength of unit considerably, thus a consideration of the possible influence of curvature should be a regular part of design procedure

Ngày tải lên: 07/08/2014, 10:20

... the plane of the cross~ Fig Al4.31 Trang 6ANALYSIS AND DESIGN OF section is also directed toward the common boundary line and thus 4x(ap) has a sense as shown in Fig Ald.31 The sense of the shear ... composed of individual flange members connected by thin webs it is often assumed that the flanges develop the en~ therefore means that the shear flow 1s constant Trang 4ANALYSIS AND DESIGN OF ... Figs Al4.47 and Al4.48 Ase Trang 10ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES sume flange members develop entire bending {5) Determine the shear center for the beam section of Fig Al4.49

Ngày tải lên: 07/08/2014, 10:20

... fuselage Trang 10ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES analysis, parallel to that of Art Al7.6, is to be found in reference 1, pp 4+10 A more elaborate two-dimensional analysis is shown ... of plates are small in compar- ison with the plates’ thicknesses - on the order of a tenth of the thickness On the other hand, the transverse deflections of a membrane will be on the order of ... addition of internal shear forces Q, and Qy {corresponding to the "Vv" of beam theory) and a distributed transverse pressure load q (psi) With the presence of these shears, the bending and

Ngày tải lên: 07/08/2014, 10:20

... courtesy of North American Aviation Co Trang 15 ANALYSIS AND DESIGN OF break-down of She structural parts of an air- plane of a ieading airplane company Fabri- eation and assembly of these ... pairs of mand n we find the region of stability and the critical combination of ay, Oy which ts on the periphery of the polygon rormed by the full lines of Pte 14, Fig 14 A18.19 Buckling of Simply ... 13 ANALYSIS AND DESIGN of the structural box is seldom obtained in tual airplane design due to cut-outs in whe wing surface for such items as retractable landing gears, mail compartments and

Ngày tải lên: 07/08/2014, 10:20

... combinations of and Mz, moments to cause wing failure Thus an interaction curve involving values of My and Mz, which cause failure of wing in bending is obtained and thus the margin of safety for any design ... Trang 10ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES The theoretical load in center stringer can be calculated by methods of Chapter A7 and À8, and the results would give the solid curve of Fig ... surface of beam will be assumed at SOCCO psi to use the bean This value could de calculated from a consider- Trang 8mS ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES ation of crippling and column

Ngày tải lên: 07/08/2014, 10:20

... of fabrica- tion and assembly Rib development and design involves considerable static testing to verify and assist the theoretical analysis and design A21.3 Distribution of Concentrated Loads ... important purpose or action of ribs and frames is to redistribute the shear at dis- continuities and practical wings and fuselages contain many cut-outs and openings and thus discontinuities in ... artist's drawing of the wing structure of the Beechcraft Bonanza commercial airplane It should be noticed that various types and shapes of ribs and formers are required in airplane design Photographs

Ngày tải lên: 07/08/2014, 10:20

... yal Ni %4 Trang 10 ANALYSIS AND DESIGN OF PLIGHT VEHICLE STRUCTURES of load application) Rib C-D was located at one of the actual rib locations in the NACA test specimen and was assumed rigid ... L., A Review of Certain Analysis Methods for Swept Wing Structures, Journ of Aero Sci., 19, p 615, S52 (9) Helden?els, R., Zender, G., and Libove, C., Stress and Distortion Analysis of a Swept ... Bisplinghoff, R., and Lane, 4., An In- vestigation of Deformations and Stresses in Sweptback and Tapered Wings with Dis- continuities, Mass, Inst of Tech Reot., July, 1949 (See also, Journ of Aero

Ngày tải lên: 07/08/2014, 10:20

... involves loss of the airplane and loss of life Likewise the collapse of a trut in landing gear structure during a land- 3g operation of the airplane can be a very erious failure Failure of a structural ... inch per inch of gage length per minute up to the yield point of the material Trang 9ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES and it should not exceed 1/2 inch per inch of gage length ... Journal of the Aeronautical Sciences, £0, 1953 3) Schuerch, H., Delta Wing Design Analysis, 4) Turner, M J., Clough, R W., Martin, H c., and Topp, L J., Stiffness and Deflection Analysis of Complex

Ngày tải lên: 07/08/2014, 10:20

... & ond Eg of Terosratura 0 Tempera Fig B2.27 Effect of temperature on the tensile and compressive modulus (E and E,) of 17-4 PH (H900) Trang 4 ANALYSIS AND DESIGN OF FLIGHT VEHICLE ... Physical Properties of 2014 Aluminum Alloy (Forgings} Alloy 2014 Die Hand forgings Hand forg-ngs Trang 12 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES B2.15 EFFECT OF TEMPERATURE ON 2014 ... tensile and compressive modulus {EB and Eg) of 2014 and 2017 aluminum alloys, 2024 ALUMINUM ALLOY (BARE SHEET & PLATE, EXTRUSIONS, BAR, ROD & WIRE) Trang 14 ANALYSIS AND DESIGN OF

Ngày tải lên: 07/08/2014, 10:20

... origin lay off to scale the normal stresses oy gion, they are laid off to right of point O and stress Tyg 1s laid off parallel to Og and with the sense of the Shear stress on the face DC of E the ... of AB as the center and with radius EC describe a circle cutting OB at F and shear on face AB of Fib b It can be proven that OF and 0G are the principal stresses Cmax, and Ggin respectively and ... Expeaue up 10 1000 Ww Fig B2.94 Effect of temperature on the ultimate tensile strength (Fry) of HK31A-T6 magnesium alloy (sand casting) Trang 3ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES B2 31

Ngày tải lên: 07/08/2014, 10:20

... references on seismic analysis and design These manuals provide a practical source of information for designers and serve as a commentary on the design codes They are: • Seismic Design and Retrofit Manual ... failure of an element and the loss of support a) Superstructures The analysis and design of bridge superstructures is usually controlled by non -seismic vertical loads That is, the analysis and design ... Nonlinear Static and Dynamic Analysis of Concrete Freeway Structures,” Proceedings of a seminar by the University of California at Berkeley and Caltrans on seismic design and retrofit of bridges,...

Ngày tải lên: 24/10/2014, 22:00