formal analysis and design of authentication protocols

... Lemma 167 167 C Proofs of Chapter C.1 Proof of Proposition C.2 Proof of Proposition C.3 Proof of Proposition C.4 Proof of Lemma 171 171 176 183 185 Bibliography ... contribution of this thesis is to provide a modeling, analysis, and design framework for WSN protocols used in control applications The protocols are designed to minimize the energy consumption of the ... engineers and Master students, Aitor Hernandez, Yian Qin, and David Andreu who struggled to reduce the gap between theory and practice I appreciate to all fellow Ph.D students and professors at...

Ngày tải lên: 01/06/2018, 15:09

... application of MATLAB to the analysis and design of control systems Presentations are limited to linear, time-invariant continuous time systems Chapters and include a great number of worked examples and ... general areas of analysis and design of feedback control systems have influenced the format of this book I would also like to thank and recognize all the undergraduate students in mechanical and electrical ... response methods of analysis, Bode, Nyquist, and Nichols plots, second order systems approximations, phase and gain margin and bandwidth, state space variable method, and controllability and observability...

Ngày tải lên: 01/01/2014, 18:43

... CONTROL Performance Analysis and Design of Feedback Systems with Nonlinear Sensors and Actuators This is a textbook on quasilinear control (QLC). QLC is a set of methods for performance analysis and design of ... and, therefore, we use the subtitle Performance Analysis and Design of Feedback Systems. .. problems, but from the point of view of design; both wide and narrow sense design ... in the design, scheduling, and operation of multi- spacecraft interferometric imaging systems, in analysis and optimization of random search algorithms, and in simultaneouspath planning andcommunication...

Ngày tải lên: 23/03/2014, 15:20

... 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 ... Modeling, Static, Dynamic and Non-Linear Analysis and Design of Structures Introduction Powerful and Integrated Structural Analysis and Desi gn Software • Fully Interactive Graphical Interface...

Ngày tải lên: 11/06/2014, 03:16

... a twofold origin: the short-term variations of the channel response and the jit- ter of the sampling process [8]. Uncompensated cyclic short- term variations of the channel, with harmonics of ... prob- ability of P e = 10 −5 and a transmitter PSD constraint of −20 dBm/kHz. BPSK and square QAM constellations with a maximum of 16 bits/symbol are employed. A system mar- gin of 6 dB is employed. ... was with the Department of Signals, Systems and Radiocommunication,... Bladel, and M Moeneclaey, “BER sensitivity of OFDM systems to carrier frequency offset and Wiener phase noise,”...

Ngày tải lên: 22/06/2014, 20:20

... 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 ... 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

... 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...

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

... 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...

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

... 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...

Ngày tải lên: 07/08/2014, 10:20

... 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...

Ngày tải lên: 07/08/2014, 10:20

... 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...

Ngày tải lên: 07/08/2014, 10:20

... 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...

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

... 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=...

Ngày tải lên: 07/08/2014, 10:20

... 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...

Ngày tải lên: 07/08/2014, 10:20

... 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,...

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