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162   Introduction to Space Sciences and Spacecraft Applications


             and receiver clocks may not be in perfect synchronization. This clock off-
             set time is shown in Figure 7-5 sketch as the tc time difference between
             the satellite signal and the receiver’s replica code. If it is assumed that the
             satellite is the absolute time reference, then this clock offset time would
             produce an error in range if  not allowed for. The method for determining
             the  value  of  the clock offset time is described as part  of  the  ranging
             process described next.

             Range Determination

                The range equation (eq. 7-6) would now look like:


                R = C,  (to f t,)                                        (7-8)
             In terms of an X, Y, Z coordinate system, this equation would be of the form:

                R1 = I(X,(t,) - XI2 + (YI(t1) - YI2 + (Zl(t1) - z)211/2 cdtc)
                                                             f
             where the X1(,,,, Y1(,,), Zl(tl) terms represent the position of the transmit-
             ter (satellite) at the time of transmission (tl). X, Y,  and Z represent the
             position of  the  receiver computed from the  range information derived
             from the correlation offset time c, to, and c,,,   tc represents the range
             error due to the satellitekeceiver clock offset time.
                Assuming that the position of  the  satellite is  known precisely at  all
             times (via a navigation message as described earlier), this equation has
              four unknowns involving the X, Y,  Z position coordinates of the receiver
              and the receiver clock offset time tc. To solve for these unknowns, at least
              four range signals must be available at the same time to solve four simi-
              lar equations simultaneously:

                                        -
                R1 = [(X,,,,) - XI2 + (y~(q) Y12 + (Zl(tl) - Z)211” * Cm(tcI
                R2  = [(X2(t2) - XI2 + (Y2(t2, - Y12 + (G(t.7) - Z)21’”  cm(tc>

                R3 = [(X3(t3) - XI2 + (Y3(t3) - V2 + (Z3(t3) - Z)21’n * cm(tc)

                R4 = [(X4(,,  - X)’  + (Y4(t4) - Y)’  + (Z4(t4, - Z)21’’2 * Cm(Q
                Note that the same receiver clock offset time tc appears for each of the
              received signals. This assumes that each of the received signals comes from
              satellite transmitters synchronized exactly with absolute time. If this were
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