Patent GB-875369-A (GB)
Title: Improvements in or relating to apparatus for a doppler radar system
IPC: G01S7/288
Filed: 1957-09-03
Abstract: 875,369. Doppler radar; aerials. LABORATORY FOR ELECTRONICS Inc. Sept. 3, 1957 [Sept. 10, 1956], No. 27803/57. Class 40(7) In an aircraft Doppler radar navigation system a transmitter of frequency fo=9809 Mc/s. is coupled to an aerial system fixed relative to the aircraft which produces at least three divergent pencil beams, Fig. 1 (not shown), directed downwards at equal angles of depression # so that the frequencies of the reflected signals produced by the beams are #o + #d 1 , #o+#d 2 , #o+#d 3  &c. where fd 1 , fd 2 , fd 3  &c. are the respective Doppler shift frequencies, said reflected signals being heterodyned separately with a local oscillation of frequency #LO=#o42 Mc/s. which is phase coherent with the transmitted signal. The resultant IF signals are heterodyned with further coherent local oscillations and are then combined to give (1) three signals Cx Dx, Cy Dy and Cz Dz which are proportional to the magnitudes of the components of the aircraft velocity along orthogonal aircraft axes X2, Y2, Z2 (the X2 axis corresponding to the longitudinal axis of the aircraft) and (2) three signals Cx Dx POL, Cy Dy POL and Cz Dz POL indicating the sense of said velocity components. These six signals are applied to a base line computer together with pitch (P), roll (R) and resolved heading signals cos # H , sin # H  to give the vertical velocity and the horizontal heading and crossheading velocities of the aircraft relative to ground and the position of the aircraft in terms of latitude and longitude or distance along and lateral deviation from a desired course and distance from a desired destination. Fig. 3 shows the plan view of possible four-beam, Fig. 3a, and three-beam, Fig. 3b and c, systems; the corresponding relationships between the generalized Doppler variables Dx, Dy and Dz and fd 1 , fd 2 , fd 3  and the angle of depression # are given in Fig. 4a (not shown), and the relationships between the generalized Doppler variables Dx, Dy, Dz and the components Vx, Vy, Vz of the aircraft velocity along orthogonal axes X, Y, Z fixed relative to the ground are given in Fig. 5 (not shown). A further three-beam configuration is obtained by rotating the beams 1, 2, 3 of Fig. 3c through 90 degrees relative to the axes X2, Y2. As described the transmitted signal and local oscillation are generated alternately for substantially equal periods, the recurrence frequency being controlled in five steps by an altimeter such that the pulses of local oscillation are substantially coincident with the echo pulses. Fig. 6 shows an embodiment utilizing the symmetrical three-beam configuration, Fig. 1 (not shown), of Fig. 3c which is produced by three waveguide horns 14, 15; 16 and a lens 13 (see below). The RF source 18 is shown in Fig. 11 and comprises a stable 9800 mc./s. oscillator 91 whose output is heterodyned separately in mixers 93 and 94 with the outputs from 51 mc./s. and 9 mc./s. sources 95, 96 which are gated on alternately by push-pull square wave gating pulses derived in a gating pulse generator 22, Figs. 12 and 13 (not shown), from a 500 kc./s. source by means of a frequency divider controlled by the altimeter 23; this feature is claimed in Specification 875,371. The sum components of the outputs from mixers 93, 94 are selected by filters 97, 98 and 9809 mc./s. (i.e. fo) signal from filter 98 is applied to each horn radiator through a circular-polarization waveguide-turnstile-junction duplexer in the directional coupling unit 21, Figs. 9 and 10 (not shown), the corresponding echo signal outputs from the duplexers being heterodyned separately in a converter 17 with the 9851 mc./s. (i.e. of #Lo) signal from the filter 97 to give corresponding 42 mc./s. IF signals which are further heterodyned in an IF unit 24 with coherent 51 mc/s. and 9À5 mc./s. signals giving outputs 500 kc./s. +#d 1 , 500 kc./s. +#d 2  and 500 kc/s + #d 3 : The 9À5 mc./s. signal applied to the IF unit 24 is a continuous signal but the 51 mc./s. signal is derived from the source 95, Fig. 11, in the radio frequency source 18 which in normal operation is gated off during the transmission periods so that during such periods no 500 kc./s. signal can be produced in the IF unit 24. Below an altitude of 2,000 ft. the pulse recurrence frequency remains constant and the transmitted pulse will overlap the echo pulse; in this mode of operation the 51 mc./s. signal is continuously applied to the IF unit 24 and this results in a 500 kc./s. carrier component in each output channel from the IF amplifier 24 which is eliminated by filter circuits 25 of the type disclosed in U.S.A. Specification 2,909,656 which in effect heterodyne the input signals with a 500 kc./s. reference signal to produce signals #d 1 , fd 2  and fd 3 , the signals fd 1  and fd 2  being then heterodyned with the 500 kc./s. reference signal to produce output signals 500 kc./s.+#d 1  and 050 kc/s+#d 2  and the signal fd 3  being heterodyned with a 200 kc./s. reference signal to produce an output signal 200 kc./s.+#d 3 . The resultant outputs from filter unit 25 are combined by means of a frequency doubler 26, mixers 27, 28 and 31 and a 400 kc./s. input to mixer 31 to give three signals having frequencies (300 kc./s.+ 2 #d 1 -#d 2 -#d 3 ), (300 kc./s.+#d 2 -#d 3 ) and (300 kc./s.+#d 2 +#d 3 ) respectively which are proportional to the generalized Doppler variables Dx, Dy, Dz. Owing to the finite width of the radiation beams and the random nature of the scattering from the area on the ground illuminated by the beams, the echo signal received by any one aerial will comprise a power-frequency spectrum, Fig. 14 (not shown) with a Gaussiantype distribution centred about the single frequency #o+#d that would be obtained if the beam was a single ray. Accordingly the outputs from the mixers 27, 28, 31 will have corresponding frequency spectra and the mean frequency of each output is derived in a frequency tracker 32 as described in U.S.A. Specification 2,481,659 such that the power in the two portions of the spectrum on either side of the mean frequency are equal, the mean frequencies being then combined in a discriminator with a reference 300 kc./s. input to give the signals Cx Dx, Cx Dx POL &c., for application to the base line computer 33. Alternatively the frequency tracking may be performed on the outputs from the filter unit 25, the resultant single frequency signals being then combined as above. The computer 33 may be of the digital type employing techniques as disclosed in U.S.A. Specifications 2,910,237 and 2,913,179 and in this case the frequency discriminators may be of the type disclosed in U.S.A. Specification 2,858,425 which produce output pulse trains of recurrence frequencies proportional to the generalized Doppler variables and D.C. voltages of polarity corresponding to the sense of the velocity; the outputs from the altitude sensors may be converted to digital forms by suitable analogue to digital converters such as disclosed in U.S.A. Specification 2,866,183. The reference oscillations having frequencies 51 mc./s., 9À1 mc./s., 9 mc./s., 500 kc./s., 400 kc./s., 300 kc./s. and 200 kc./s. applied to the RF unit 18, gating pulse generator 22, IF strip 24, filter unit 25, mixer 31 and tracker 32 are derived from a common oscillator by a combination of harmonic generators and mixers so that all the reference oscillations are coherent. Aerial system. Fig. 7 shows an arrangement producing the symmetrical four-beam configuration of Fig. 3a and comprises four waveguide horns 56-59 spaced equally around a circle in the focal plane of a lens 13, each horn being inclined so that its axis passes through the centre of the lens. Figs. 9 and 10 (not shown) illustrate corresponding arrangements for the three-beam configurations of Fig. 3b and 3c, Fig. 9 showing a zoned dielectric lens mounted in a flexible ring to allow for thermal expansion and contraction. Fig. 8 shows a three-beam arrangement in which the horns 56, 57, 58 are mounted in the plane of the lens 13 and are so inclined that their axes, on reflection at a plane reflector 62 pass through the centre of the lens.