Computational Ballistics III - download pdf or read online

By C. A. Brebbia, A. A. Motta

ISBN-10: 1845640772

ISBN-13: 9781845640774

Masking a wide scope of themes relating to ballistics, this publication includes papers provided on the 3rd overseas convention on Computational Ballistics, held June 6-8, 2007, within the New woodland, united kingdom. Ballistics, as a technological know-how, has a large which means and is found in many features of our daily lives. Terminal ballistics, maybe its most vital department, specializes in the examine of the interplay among the munition and goal and has many civilian purposes, akin to in automobile crashes and fowl moves on plane, and the resultant results. This comprises the learn of effect, total and microscopic structural resistance and behaviour, and integrity.The papers conceal Fluid move aerodynamics; inside ballistics; Terminal ballistics; Experimental mechanics/ballistics and box checking out; New advancements in computational concepts; and structures and expertise.

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Figure 18: CX2 versus Mach number: 1 data point per time snippet, 4 time snippets. com, ISSN 1743-355X (on-line) Computational Ballistics III 49 Figure 19: CX2 versus Mach number: 1 data point per time snippet, 6 time snippets. Figure 20: CX2 versus Mach number: 1 data point per time snippet, 10 time snippets. com, ISSN 1743-355X (on-line) 50 Computational Ballistics III Figure 21: CMQ versus Mach number: 1 data point per time snippet, 4 time snippets. Figure 22: CMQ versus Mach number: 1 data point per time snippet, 6 time snippets.

Cna: Normal force due to angle of attack aerodynamic coefficient. Cypa: Magnus force aerodynamic coefficient. Clp: Roll damping aerodynamic coefficient. Cldd: Fin cant aerodynamic coefficient. Cmq: Pitch damping moment aerodynamic coefficient. Dcop: Distance from the mass center to the center of pressure. Dmag: Distance from the mass center to the center of Magnus. CFD: Computational Fluid Dynamics. References [1] [2] [3] [4] [5] J. Sun, R. Cummings, “Evaluation of Missile Aerodynamic Characteristics Using Rapid Prediction Techniques,” Journal of Spacecraft and Rockets, Vol 21, No 6, pp 513-520, 1984.

Gravity is neglected. For wZ << v  v  x v z = −  w1 ⋅ − v z  . v x1  (15) From eqns (1–3) one can derive [2] vm x = 0 x1 Dmx1 [  1− m 1 − 1 + D(1 − m)v0 ⋅ τ  ] m 1− m    (16) and − Dv 10− m v . = v 1 + D (1 − m)v 10− m ⋅ τ (17) Substituting eqns (16) and (17) into eqn (15) yields a first order linear inhomogeneous differential equation for vz (τ ) . Solving first the homogeneous differential equation and applying the variation of the constant yields with the boundary condition τ = 0 : vz = 0 the projectile velocity component vz as function of time.

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Computational Ballistics III by C. A. Brebbia, A. A. Motta


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