Patent GB-533538-A (GB)
Title: Improvements in or relating to systems for measuring and indicating terrain clearance and the like by the reflection of electromagnetic waves
IPC: G01S13/34
Filed: 1939-10-13
Abstract: 533,538. Radiolocation. ELECTRICAL RESEARCH PRODUCTS, Inc. Oct. 13, 1939, No. 27822. Convention date, Nov. 16, 1938. [Class 40 (v)] [Also in Group XXXVI] In a system for determining the height of aircraft by radiating a wave of short wavelength and beating the wave received after reflection with the wave being radiated, "terrain modulation," i.e. the production of frequencies other than the beat-wave frequency due to a non- uniform reflecting surface, is compensated for and is also used to indicate the nature of the terrain. In order to effect this the mean frequency of the radiated wave is of such a value that the desired range of variation of the frequency of the radiated wave is obtained with uniform transmitting efficiency a mean frequency of 450 megacycles with a variation of 12¢ megacycles on each side being mentioned. An amplifier is employed which has a frequency-gain characteristic adapted to compensate for -the attenuation of the reflected wave. The beat frequency is separated from disturbing extraneous frequencies. The frequency-gain characteristic of the amplifier may be adjustable or the response to frequencies other than the beat frequency may be controlled automatically in accordance with the beat frequency. The regulating means may be prevented from operating when no reflected wave is being received by the aircraft. A cathode ray oscillograph may be employed to detect terrain modulation, the nature of the earth's surface being indicated by the pattern obtained on the screen, e.g. water, a smooth landing field, wooded areas, and produce characteristic patterns. The system is shown in Fig. 1 in which a transmitter 14 supplies an antenna 18 through a concentric line 13. A rotary condenser 15 changes the frequency of the transmitter 14 and is driven at constant speed by a synchronous motor 16. A receiving antenna 19 receives reflected waves 10 and directly transmitted waves 9 from the antenna 18. The antenuµ 18, 19 are dipoles and are mounted on a common longitudinal axis beneath the wings of an aircraft 11. If the wings are of metal the antennµ should be spaced at a quarter of the wave-length of the mean transmitted frequency below the wings. The receiving antenna 19 is connected to a detector 21 by a coaxial line 12 and produces a beat frequency representing the predominant frequency difference between the direct and reflected waves, and possibly a number of other frequencies. The detector output is passed to an amplifier 22 and thence to a frequency meter circuit 23 which integrates the output of the amplifier and supplies a milliammeter 24 with a direct current proportional to the frequency. A cathode ray indicator 25 is employed to observe the character of the signal current and thereby the character of the country over which the aircraft is flying. The transmitting system' employs a triode 44, Fig. 3, placed between two Lecher wire systems 36, 42 which are tuned by bridging condenser pairs 37, 43. A rotary condenser 15 bridged across one Lecher system varies the transmitted frequency and is driven by a synchronous motor 16. Low frequencies are excluded by a retardation coil 38, and radio frequencies are by-passed by a condenser 40. Coils 46 are inserted in the filament circuit to prevent degenerative effects. The leads 47 are shielded by shields 48. A resistor 35 carrying the grid current provides grid bias for the valve 44. The lead 33 connected to the antenna 18 is connected to the grid wire on the right-hand Lecher system and may be adjusted along this wire to increase or decrease the effective coupling to and radiation from the antenna 18. The receiver amplifier, Fig. 5, consists of three stages employing pentodes 86. Operation of the switches 116, 118, 120 enables the frequency selective characteristics of the amplifier to be varied in order to exclude terrain modulation and unwanted or noise frequenc:ies and their harmonics; each switch position giving the amplification required for a particular beat-note frequency range or range of clearances. The frequency meter comprises a pentode 88, coupling resistor 74, screen grid battery 110, a selection of five condensers 90, 92, 94, 96, 98 of which any one may be selected by a switch 109, a fullwave rectifier 100, meter shunt 102, resistor 108, and anode battery 106. The cathode-anode impedance of the pentode 88, in the absence of a signal above a critical threshold valve, is very low and practically the total voltage of the anode battery 106 is across the resistance 108. On receipt of a signal of amplitude sufficient to block the anode circuit the cathode-anode impedance becomes very high during a portion of each half cycle when the input grid is negative. The condenser selected by the switch 109 is therefore charged by the battery 106 during the negative half cycles and discharged through the low anode-cathode impedance during the positive half-cycles. The charging and discharging pulses pass through the meter 24 in the same direction, giving a reading dependent on frequency. The scale of the instrument is changed by changing the condenser, and the dial may be marked with five scales each best suited for a particular portion of the total range of clearances. Five jacks 114 are provided in different portions of the amplifier circuit, into which a plug 144 connecting a cathode ray tube 140 may be inserted so as to permit observations of the signal form as it progresses through the amplifier. The character of the pattern is an indication of the character of the reflecting terrain.