Sensitivity derivatives and optimization of nodal point locations for vibration reduction

A method is developed for sensitivity analysis and optimization of nodal point locations in connection with vibration reduction. A straightforward derivation of the expression for the derivative of nodal locations is given, and the role of the derivative in assessing design trends is demonstrated. An optimization process is developed which uses added lumped masses on the structure as design variables to move the node to a preselected location; for example, where low response amplitude is required or to a point which makes the mode shape nearly orthogonal to the force distribution, thereby minimizing the generalized force. The optimization formulation leads to values for added masses that adjust a nodal location while minimizing the total amount of added mass required to do so. As an example, the node of the second mode of a cantilever box beam is relocated to coincide with the centroid of a prescribed force distribution, thereby reducing the generalized force substantially without adding excessive mass. A comparison with an optimization formulation that directly minimizes the generalized force indicates that nodal placement gives essentially a minimum generalized force when the node is appropriately placed.

[1]  Raphael T. Haftka,et al.  Sensitivity analysis and optimization of nodal point placement for vibration reduction , 1987 .

[2]  A. Palazzolo,et al.  SYNTHESIS OF DYNAMIC VIBRATION ABSORBERS. , 1985 .

[3]  Hirokazu Miura,et al.  Applications of numerical optimization methods to helicopter design problems: A survey , 1984 .

[4]  Peretz P. Friedmann,et al.  Application of modern structural optimization to vibration reduction in rotorcraft , 1984 .

[5]  R. L. Bennett,et al.  Aeroelastic-aerodynamic optimization of high speed helicopter-compound rotor , 1984 .

[6]  M. W. Davis,et al.  Optimization of helicopter rotor blade design for minimum vibration , 1984 .

[7]  Peretz P. Friedmann,et al.  Optimum design of rotor blades for vibration reduction in forward flight , 1984 .

[8]  R. H. Blackwell,et al.  Blade Design for Reduced Helicopter Vibration , 1983 .

[9]  P. Shanthakumaran,et al.  Aeroelastic tailoring of rotor blades for vibration reduction in forward flight , 1983 .

[10]  G. Reichert,et al.  Helicopter vibration control: a survey , 1980 .

[11]  Garret N. Vanderplaats,et al.  CONMIN: A FORTRAN program for constrained function minimization: User's manual , 1973 .

[12]  R. E. Hutton,et al.  Effect of Spanwise and Chordwise Mass Distribution on Rotor Blade Cyclic Stresses , 1956 .

[13]  George W. Brooks,et al.  A dynamic-model study of the effect of added weights and other structural variations on the blade bending strains of an experimental two-blade jet-driven helicopter in hovering and forward flight , 1955 .