GB1219261A - Improvements in or relating to guiding systems for guided missiles - Google Patents

Abstract

1,219,261. Radar ; aerials. TELEFUNKEN G.m.b.H. 7 Dec., 1959 [6 Dec.; 1958], No. 41447/59. Headings H4A and H4D.Dec., 1958], No. A remote control missile guidance system comprises a radar installation 1 which determines continuously the positions of all missiles and targets within its coverage, tracking devices 10, 11 which select from received echoes those corresponding to selected targets and missiles to be directed to the targets, and computers 18 each fed with signals representing the positions of a target and a missile, each computer being connected to a radio transmitter 19 which controls the steering of the missile to reduce towards zero the differences between the position co-ordinates of the target and the missile. Directional aerials 2, 3 determine position in terms of azimuth and elevation and also provide signals a w , h w representing their own directions; these signals control the time bases of a P.P.I. 6 and an elevation display 7. In the embodiment shown the missiles have transponders so that the radar provides four outputs: a z and h z for target azimuth and elevation, and a k and h k for missile azimuth and elevation; the target positions are shown on displays 6, 7. The target tracker 10 has manually adjustable phase shifters which are adjusted to bring a pulse train at the P.R.F. of the transmitter into coincidence with the echoes of a selected target, as shown by markers on the displays; it thereafter feeds to the computer the position co-ordinates of the target. The missile tracker 11 has pre-set phase shifters; it provides position co-ordinates for the computer and markers for the displays. Fig. 4 shows a tracker in detail. Oscillator 37 provides oscillations at the transmitted pulse repetition frequency # 1 which are fed to phase shifter 38, which selects the range co-ordinate, and are then converted to double pulses which are fed to a phase discriminator 41; the other input of 41 receives azimuth pulses. The groups of azimuth pulses from one target are selected by gate 42. Discriminator 41 produces an error signal which controls the frequency of oscillator 37 so that pulses produced at 39 are in step with the echo pulses. Coincidence circuit 48 receives pulses of frequency f 1 and of frequency ( # 1 Œ# o ), where # a is the rotation frequency of the associated aerial; the output of 48 has repetition frequency #a and phase depending on target azimuth. This output is converted to double pulses and applied to phase discriminator 51 which keeps oscillator 44 in step with the received pulse groups. A coincidence circuit 53 receives range pulses and lengthened pulses from unit 48 ; its output is used to gate circuit 42 and to supply marker pulses to the display. Elevation is found as for azimuth. In the aerial system, Fig. 2, azimuth scanning is effected by the horn 22 and reflector 21 which rotate about the vertical axis 23. Elevation is measured by the three cheese aerials 28, 29 and 30 between the conducting plates 25, 26 and three similar aerials between plates 26 and27, which are illuminated by horns such as 31, 32 and 33 and are rotated about the axis 23 and the horizontal axis 24.