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In the trellis of Figure 113 there are M possible transitions from stateS to all possible states S or to state S from all possible statesS Hence, there are - 1summations of the exM ponentials in the forward and backward recursion of Equation 1121 and 1122, respectively Using the Jacobian logarithmic relationship Equation 102, M - 1 summations of the exof ponentials requires2(M-1) additions/subtractions, (M - 1)maximum search operations and (M - 1)table look-up steps Together with the M additions necessitated evaluate theterm to Fk(s ,s) Ak-l(s ) and I k ( S , s ) B ~ ( s ) Equation 1121 and 1122, respectively, the in forward and backward recursion requires a total of ( 6 M - 4) additions/subtractions, 2(M1) maximum search operations and 2(M-1) table look-up steps Assuming that the term c k .

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l F ( c k ) in Equation 1123 is a known weighting coefficient, evaluating the branch metrics given by Equation 1123 requires a totalof 2 additions/subtractions, 1 multiplication and 1 division By considering a trellishaving x number of states at each trellis stage M legitimate and transitions leaving each state, there arei M x number of transitions due to thebit ck = +l Each of these transitions belongs to the set (S , S ) + Ck = +l Similarly, there will be 1 zMx number of ck = -1 transitions, which belong to the set ( S , S ) + Ck = -1 Evaluating A ~ ( s ) Bk-l(s ) and I k ( s , s ) of Equation 1121, 1122 and 11.

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(i.e., ascending from the Southern Hemisphere to the Northern Hemisphere) and ``descending''. The right ascension of the ascending node (RAAN) is the angle in the equatorial plane from the vernal equinox to the ascending node, measured counterclockwise as seen looking down from the north pole direction. (c) Orbital inclination is the dihedral angle between the orbital plane and the equatorial plane. It ranges from zero (orbit in equatorial plane) to 180 . Semimajor axis a and semiminor axis b (de ned in Section C.3.5.2 and illustrated in Fig. C.6) specify the size and shape of the elliptical orbit within the orbital plane. Orientation of the ellipse within its orbital plane, speci ed in terms of the ``argument of perigee,'' the angle between the ascending node and the perigee of the orbit (closest approach to earth), is illustrated in Fig. C.4. Position of the satellite relative to perigee of the elliptical orbit, speci ed in terms of the angle from perigee, called the ``argument of latitude'' or ``true anomaly,'' is illustrated in Fig. C.4. For computer simulation demonstrations, GPS satellite orbits can usually be assumed to be circular with radius a b R 26;560 km and inclined at 55 to the equatorial plane. This eliminates the need to specify the orientation of the elliptical orbit within the orbital plane. (The argument of perigee becomes overly sensitive to orbit perturbations when eccentricity is close to zero.)

If the surface of a metal or carbon electrode is covered with a layer of some functional material, the electrode often shows characteristics that are completely different from those of the bare electrode. Electrodes of this sort are generally called modified electrodes [9] and various types have been developed. Some have a monomolecular layer that is prepared by chemical bonding (chemical modification). Some have a polymer coat that is prepared either by dipping the bare electrode in a solution of the polymer, by evaporating the solvent (ethanol, acetone, etc.) of the polymer solution placed on the electrode surface, or by electrolytic polymerization of the monomer in solution. The polymers of the polymer-modified electrodes are either conducting polymers, redox polymers, or ion-exchange polymers, and can perform various functions. The applications of modified electrodes are really limit-

23, respectively, at , each trellis stage IC associated with a total of Mx transitions requires M x ( 6 M - 2) additions/subtractions, M x ( 2 M - 2) maximum search operations,M x ( 2 M - 2) table look-up steps, plus Mx multiplications and Mx divisions With the terms Ak ( S ) , B k - 1 ( S ) and I k(s , S ) of Equations 1121, 1122and 1123 evaluated, computing the LLR Lf(ck) of Equation 1124 using the Jacobian logarithmic relationship of Equation 102 for the summation terms ln(x(s,,s)+ck=+l exp()) ln(C(s,,s)jck=+l exp()) requires a total of and 4 ( $ M x - 1) 2 M x 1 additions/subtractions, Mx - 2 maximum search operations and Mx - 2 table look-up steps.

If you d like to switch to forced file system checks based on time interval rather than number of mounts, disable mount-count checking by setting it to negative 1 (-1):

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