head first objectoriented analysis and design flipkart

... 1 SCHOOL OF INFORMATION AND COMMUNICATION TECHNOLOGY HANOI UNIVERSITY OF SCIENCE AND TECHNOLOGY ______ * ______ SYSTEM ANALYSIS AND DESIGN REPORT Author : ... Conceptual data modeling ………………………………………… 17 B. Design I. High-level Design 1. Scenario Analysis …………… 18 2. Object Analysis ……………………………………………… 22 3. Screen Design 3.1 Log on ……………………………………………… 24 ... ……………………………………… 72 II. Detail Design 1. Scenario Design ……………………………………………… 84 2. Object Design ……………………………………………… 90 C. Testing ……………………………………………………………… 91 3 A. Analysis. I.

Ngày tải lên: 01/06/2014, 17:25

... interactive and graphical steel and concrete frame member design • Design for static and dynamic loads • Member-grouping for design envelops • SAP2000 • Ductile and non-ductile design Design Output ... Static and Dynamic Finite Element Analysis and Design of Structures T i t l e SAP2000 V8 – Non Linear A Comprehensive Software for the Finite Element Modeling, Static, Dynamic and Non-Linear Analysis ... Output Member Design SAP2000 • Detailed on-screen design information with right button cl ick Member Design Design of Concrete Members Support ACI, AASHTO, British, Canada, New Zealand and Eurocode2

Ngày tải lên: 11/06/2014, 03:16

... advantage that both the EURASIP Journal on Wireless Communications and Networking analysis and the design remain fully analytical and linear in the parameters, that is fountain distributions are ... finite length design by properly addressing the rate splitting issue, and finally, conclusions and perspectives are drawn in Section System Description and Notations 2.1 Definitions and Notations ... on Wireless Communications and Networking Volume 2009, Article ID 657970, 11 pages doi:10.1155/2009/657970 Research Article Jointly Decoded Raptor Codes: Analysis and Design for the BIAWGN Channel

Ngày tải lên: 21/06/2014, 22:20

... Article Analysis and Design of Timing Recovery Schemes for DMT Systems over Indoor Power-Line Channels Jos ´ e Antonio Cort ´ es, Luis D ´ ıez, Eduardo Martos-Naya, Francisco Javier Ca ˜ nete, and ... 5ps Figure 3: Oscillator and aperture phase noise spectra. where S s ( f ) is the PSD of the signal in (2) and dBc/Hz stands for dB below the carrier power in a 1 Hz bandwidth. L( f ) is a very ... minimize the unavoidable resonance that appears in the passband and to achieve narrowband notches. As a re- sult, ξ i is fixed to 0.1 in all filters and ω 0,i = ω z,i k(α), where k(α) = ⎧ ⎪ ⎪ ⎨ ⎪ ⎪ ⎩ 1,

Ngày tải lên: 22/06/2014, 20:20

... systems analysis and design, databases and software development / Keng Siau, editor p cm Summary: "This book is designed to provide understanding of the capabilities and features of new ideas and ... systems analysis and design, and software engineering The primary mission of ADR is to be instrumental in the improvement and development of theory and practice related to information technology and ... conceptual modeling, modeling languages and techniques for analysis and design, domain analysis, and development processes Her work has been published in journals and international conference proceedings

Ngày tải lên: 27/06/2014, 06:20

... 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 ... Virtual Work Delta Wing Example Problem Design for Compression - Design Conditions and Design Weights Design Flight Requirements for Airplane Design Loads Design for Tension Differential Equation ... Preliminary Design Section Ii Technical Analysis Section Aerodynamics Group Structures Group deignt and Balance Control Group Power Plant Analysis Group Materials and Processes Group Controls Analysis

Ngày tải lên: 07/08/2014, 10:20

... Figs A2.50 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 and B for landing T Cc the landing zear of Fig 24, A 20" s00 struccure in fig 23 the brace -‡ rovides resistance members 3 us 24" vã to V, D and § re- and BF are “43000 D actions and ... transfer shear and torque reactions between the oleo strut and member AB The brace struts GD, FD and CD are pinned at each end and wiil be assumed as 2 force members An airplane level landing condition

Ngày tải lên: 07/08/2014, 10:20

... government specifications for both military and commercial airplanes Landplanes: Level landing Level landing with side load Three point landing Three point landing with ground loop Nose over or turn ... Unit Analysis for Fuseiage Shears and Moments, Since there are many flight and landing conditions, considerable time can be saved if a unit analysis is made fcr the fuselage shears, axial and ... 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

Ngày tải lên: 07/08/2014, 10:20

... 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 the moment of tnertia ... 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 FLIGHT VEHICLE STRUCTURES ... units, thus the determination of the torsional stress and deformation of such structures plays an important part in aircraft structural analysis and design Pig A6.12 shows a portion of a thin- walled

Ngày tải lên: 07/08/2014, 10:20

... strut and axle are tubular and of constant section Solution: The loading shown causes doth bending and twisting of the strut axle unit First find pending and torsional moments on axle and strut ... For I beams and channels r is approximately 5 d and for rectangular sections r = » (4 = depth) In aircraft structures a ratio of d is seldom greater than S$ Trang 8 ANALYSIS AND DESIGN Example ... itsel? suggests new and improved metheds both of theoretical ap- proach and work division The methods and notations employed here and later are essentially those presented by Wehle and Lansing® in

Ngày tải lên: 07/08/2014, 10:20

... CE and DE were taken as the redundants and were cut at points x and y as shown The member stresses for this structure and loading are recorded on the members Figs A8.16 and A8.17 give the u, and ... not eng upen X and hence could not enter the croblem Dif- Trang 13 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES Example P' 4 micircular pin-ended, uniform ring ts supported and loaded as ... faces x and y fable A8.3 gives the complete calculations for eqs (4) and (5) The load in the redundant member CE was designated X and that in DE as Y A8 11 Solving the two equations for X and

Ngày tải lên: 07/08/2014, 10:20

... 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 VEHICLE STRUCTURES ... dae, Ga, Ga And Ga collected from the one heated flange and were only (Note that if two ad- jacent flanges are heated equally, one aust Set the corresponding dan Trang 22 ANALYSIS AND DESIGN OF ... 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 -15,0 ° 9 Pa = -l Thus, one finds that

Ngày tải lên: 07/08/2014, 10:20

... 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 ... 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 drawn as shown in Fig ... components, namely, the forces Ky and Ys and the moment M, and the structure is mow treated as a cantilever beam fixed at end (B) and carrying the redundant loads at (A) and the known external loading

Ngày tải lên: 07/08/2014, 10:20

... 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 > - ... (2) is 4 Trang 20 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES whence, 667760, + 166940, +572 20 - (8) Solving equations (1) and (5) for 6, and 9, we obtain 6, = 0.00439 and 6, =~ 0,00967 ... known the axial loads and shear reactions at A and B can be found by statics The resulting axial loads are Pac = 10400# and Pua = - 27150# and tne shear reactions, Sg = SeO# and Sg 20008 With the

Ngày tải lên: 07/08/2014, 10:20

... section Between 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 ... - (11) Where ly = / y*da and Ixy > / xyda, and My = M cos 6 In like manner, My -ksin @Iy+k cos @ Iyy ~T———~ q2) Solving equations (11) and (12) for sin @ and cos @ and substituting their values ... moments My and My produce bending about the X and Y axes as though they were neutral axes To show the error of this assumption, the stresses will be computed for Trang 9 ANALYSIS AND DESIGN OF

Ngày tải lên: 07/08/2014, 10:20

... (transverse rings and frames and longitudinal stringers) is relatively rigid and is everywhere tightly fastened to the skin, then each skin panel is restrained along its Trang 2 ANALYSIS AND DESIGN OF ... probiems of analysis of a single rectangular skin panel taken between the stringers and bulkheads of a seaplane huil bottom Equaily useful is the picture of the Trang 10 ANALYSIS AND DESIGN OF ... Plates and Shells", McGraw-Hill, N ¥., 1940 Den Hartog, J P "Advanced Strength of Materials", McGraw-Hill, N Y., 1952 Sechler, BE and Dunn, L “Airplane Struc- tural Analysis and Design& #34;,

Ngày tải lên: 07/08/2014, 10:20

... situation and rigorous methods are now being more and more used tn aircraft structural analysis A7.9 and 48.10 in Chapters A7 and AS present matrix methods for finding deflections and stresses ... 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 bomb and gun ... Nxy and Nyy: From Fig lob we find: ew ON ow 37x ~ Nxy Ft (xy + TS ax) Sy Sxay 4x) and neglecting terms of higher order: , 33w aN aw ay Gxay * Ộgx: Gp) duty - - - fe) Trang 5 ANALYSIS AND DESIGN

Ngày tải lên: 07/08/2014, 10:20

... (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 ... aircraft and also to Chapter AS, where example calculations of fuselage shears and moments are presentec Trang 15 A20 2 FUSELAGE STRESS ANALYSIS el PHOTO NO 2 Trang 16 ANALYSIS AND DESIGN ... compared to the single cell analysis Example Problem Trang 6 ANALYSIS AND DESIGN OF FLIGHT VEHICLE STRUCTURES Al9, 21 lations as was used in the previous single cell The first 7 columns of this

Ngày tải lên: 07/08/2014, 10:20

... Save command, or the Save button, to save your model. Step 8 Run the Analysis In this Step, the analysis will be run. A. Click the Analyze menu > Run Analysis command or the Run Analysis ... EFFORT AND EXPENSE HAVE GONE INTO THE DEVELOPMENT AND DOCUMENTATION OF SAP2000. THE PROGRAM HAS BEEN THOROUGHLY TESTED AND USED. IN USING THE PROGRAM, HOWEVER, THE USER ACCEPTS AND UNDERSTANDS ... stand-alone finite-element-based structural program for the analysis and design of civil structures. It offers an intuitive, yet powerful user interface with many tools to aid in the quick and...

Ngày tải lên: 06/09/2012, 15:56

... time, but want to see the results of the pushover analysis, then you can read parts A and B, skip part C and the first five steps of part D, and then open the already created model (with the ... the frame elements and joints. • Click and hold the left mouse button. • While holding, move the pointer below and to the right of the frame elements and joints. A “rubber-band” window will show ... then run the linear static and dynamic analysis by clicking Run on the Analyze menu. Next select Run Static Pushover from the Analysis menu to perform the pushover analysis. The results are now...

Ngày tải lên: 06/09/2012, 15:56