analysis and design of chemical reactors

... 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

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... mass of the body À3.7a Mass Moments of Inertia The product of the mass of a particle and the square of its distance from a line or plane is referred to as the moment of inertia of the mass of the ... Wheel Just Clear of Ground Tail Down Landing Fig A2.52 Fig A2.53 shows photographs of typical main gear units and Fig A2.54 for nose wheel gear units The successful design of landing gear for ... 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

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... 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

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... 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

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... twist of the cemplete cell can be found by substituting values of q and Ga in either equations (33) or (34), since twist of each cell must be the same and equal to Trang 9 ANALYSIS AND DESIGN OF ... values of q are multiplied by 100 and entered on line 2 of the table Calculation of carry factors as Trang 15 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES Cell (3) to (2) The balance of the ... angle of twist 9 under the two stress con- ditions and equatinz them Trang 17 ANALYSIS AND DESIGN OF Note: Tne deflection of a cantilever beam with a load F at its and equals FLồ/3E1, and I

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... 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

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... q,, 4 Trang 25 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES related immediately to the external equations of statics Thus a certain subset of the q,, q, 3 are redundants and are denoted ... due to the given loading The results of Trang 3 ANALYSIS AND DESIGN OF FUIGHT VEHICLE STRUCTURES Defl atc 2275 + (004408 ~ 0027)15 = 301" The slope of the elastic curve at the truss joint ... upward Due to symmetry of truss and loading of the truss we know the slope of the elastic curve at the center line of the truss is horizontal or zero Thus to find the deflection of any potnt with

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... left hand side and the right hand side of eq 31, viz (Be]{% p= Era] {Fa} they are discussed in detail below ® ~ ACCURACY OF INVERSION oF [rs | ; THE CONDITION OF THE MATRIX The characteristic of ... buildup of axial flange stresses the root of a beam under torsion when the Trang 10 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES A8, 27 found by superposing stresses for Pi, = 1 and 144 ... Because of symmetry only one half the panel was handled All member flexidility coefficients and thermal distortions were doubled where appropri- ate Trang 20 ANALYSIS AND DESIGN OF FLIGHT

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... at E of all forces on frame to right side of = and equate to zero, Trang 9 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES The frame static bending moment ciazram can now be calculated and ... FRAMES AND_ RINGS The moment of inertia of the frame cross sections are given in column Trang 15 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES Ag 13 Table A9.5 Calculation of Frame ... x and y from the yy and xx axes, we can write Where A is the area of the column cross~ section and Pa and Pb the moment of the load P about the xx and yy axes respectively If we let Pa = My and

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... displacements of the end supports of a beam and the resulting end moments om the beam Fig Al2.la shows a beam restrained at ends land 2 It is assumed unloaded and of constant cross-section or moment of ... loaded 3 span beam fixed at points (1) and (2) This fixity at Trang 18 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES Solving equations (g} and (h) for 9, and 4, gives, @a = 26.15, 95 > - ... Trang 4 HÀ ` 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

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... 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

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... in the plane of the cross~ Trang 6 ANALYSIS 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 ... torsional shear flow 9 (1) and qy(a) must act on cells (1) and (2) respectively can be found The values of at 1) and ae £ foun of Art AS by using equations (16) and (17 of Chapter AS Thus 1 Suoậy ... when subjected to the Shear flows of Figs A15.8 and 9 and equate the Tesult to zero, and then solve for the one un- kmown q Trang 16 ANALYSIS AND DESIGN _ 16.21 x 10 _ 8,21 x 24:28 ,„ 109 5=

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... x = 19.47 inches Taking moments about A15.48 and A15.49 and equating to 1000 x Trang 7 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES In row 13 of the Table, the carry over values are so small ... important consequence of this calculation is that the ratio of shell weight to shell volume is and 1s therefore independent of the combinations of Ry, Ri, G@,andQ, used The designer is thus free ... Problem 5 Trang 23 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES Nm \ w(t Z T Gœ) o/h Fig A16.9 SOLUTION: The meridian curve of the cone has a radius of curvature Ry =Seand, at any point a

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... the stringers and bulkheads of a seaplane huil bottom Equaily useful is the picture of the Trang 10 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES analysis, parallel to that of Art Al7.6, ... length of the long side of the rectangular membrane and ni and ne are given in Table Al7.2 as functions of the panel aspect ratio a/b The maximum membrane stress (SMAx) oceurs “The work of Henky and ... The sum of the corresponding deflection functions (each of the form of eq 10) gives the desired solution Details of this type of analysis are to be found in reference 1 on pp 113-176 and 199-256,

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... 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

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... (3) ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES and Wy = 5 lb./in., acting to rear and located at mid-deptn of wing Find re- actions at points (a), (b) and (d) Find axial loads on front and ... 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 ... stress at surface of beam will be assumed at SOCCO psi to use the bean Trang 8 mS ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES ation of crippling and column strength of the stiffened skin,

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... cost 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 ... x-x without twist line of action of the resultant of this shear flow force system locates the horizontal pesiticn of the shear center The Trang 19 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES ... properties of the wing cross-section Table A21.1 gives the calculation of the moment of inertia and product of inertia about centroidal Zand X axes In this example the 4 stringers a, b, ¢ and d have

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... 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

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... 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 ... 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 ... third type of testing For example, a complete airplane wing or fuselage is often subjected to elaborate fatigue Trang 21 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES The presence of cracks

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... & 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

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