A self-adaptive missile guidance system for statistical inputs
National Aeronautics and Space Administration, 1960 - Technology & Engineering - 30 pages
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20-percent time limiting acceleration capability adaptive Analog computer studies analytic design assumed average g limit beam-rider guidance Block diagram Booton design based design values diagram of beam-rider dynamic performance dynamic pressure equation factor of 20 Figure 11 figure 13(b figure 17 fixed flight envelope flight regime four optimum systems ft/sec2 ft2-sec gain variation Gaussian distribution input magnitudes input signal lOg rms minimum rms error missile acceleration limit missile autopilot missile gain missile guidance system modified Wiener design modified Wiener filter modified Wiener system modified Wiener theory Newton modified Wiener nonlinear open-loop gain operating optimum linear system optimum modified Wiener optimum percent optimum Wiener filter percent time limiting power spectral density rms design acceleration rms value Root loci saturation self-adaptive loop self-adaptive missile guidance shown in figure shows statistical inputs Stewart ref structural load limit target transfer function value of gain value of percent values of limit white noise