GB1605156A

GB1605156A – Method and apparatus for warning aircraft of the presence and direction of electrical transmission lines
– Google Patents

GB1605156A – Method and apparatus for warning aircraft of the presence and direction of electrical transmission lines
– Google Patents
Method and apparatus for warning aircraft of the presence and direction of electrical transmission lines

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Publication number
GB1605156A

GB1605156A
GB28968/76A
GB2896876A
GB1605156A
GB 1605156 A
GB1605156 A
GB 1605156A
GB 28968/76 A
GB28968/76 A
GB 28968/76A
GB 2896876 A
GB2896876 A
GB 2896876A
GB 1605156 A
GB1605156 A
GB 1605156A
Authority
GB
United Kingdom
Prior art keywords
signals
coils
aircraft
output
ratio
Prior art date
1976-07-12
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)

Expired

Application number
GB28968/76A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)

UK Secretary of State for Defence

Original Assignee
UK Secretary of State for Defence
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
1976-07-12
Filing date
1976-07-12
Publication date
1982-06-09

1976-07-12
Application filed by UK Secretary of State for Defence
filed
Critical
UK Secretary of State for Defence

1976-07-12
Priority to GB28968/76A
priority
Critical
patent/GB1605156A/en

1977-07-07
Priority to IT7768576A
priority
patent/IT1082790B/en

1977-07-11
Priority to FR7721296A
priority
patent/FR2500636A1/en

1977-07-12
Priority to BE0/179296A
priority
patent/BE856753A/en

1977-07-12
Priority to DE19772731436
priority
patent/DE2731436A1/en

1980-05-06
Priority to US06/147,295
priority
patent/US4405926A/en

1982-06-09
Publication of GB1605156A
publication
Critical
patent/GB1605156A/en

Status
Expired
legal-status
Critical
Current

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Classifications

G—PHYSICS

G01—MEASURING; TESTING

G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS

G01V3/00—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation

G01V3/15—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation specially adapted for use during transport, e.g. by a person, vehicle or boat

G01V3/165—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation specially adapted for use during transport, e.g. by a person, vehicle or boat operating with magnetic or electric fields produced or modified by the object or by the detecting device

Description

PATENT SPECIFICATION
( 21) Application No 28968/76 ( 22) Filed 12 Jul 1976 ( 23) ( 44)
Complete Specification Filed 28 Jun 1977
Complete Specification Published 9 Jun 1982 ( 51) INT CL 2 G 01 V 3/165 ( 52) Indexatacceptance GIN 17 19 B 2 GX 19 D 10 19 D 11 19 D 7 19 H 7 X 19 X 5 19 X 6 K ( 72) Inventor: Keith Eric Potter ( 54) METHOD AND APPARATUS FOR WARNING AIRCRAFT OF THE PRESENCE AND DIRECTION OF ELECTRICAL TRANSMISSION LINES ( 71) I, THE SECRETARY OF STATE FOR DEFENCE, London, do hereby declare the invention, for which I pray that a patent may be granted to me, and the method by which it is to be performed, to be particularly described in and by the following statement:-
This invention relates to methods and apparatus for warning aircraft of the presence and direction of electrical transmission lines.
The invention has particular application in preventing low-flying aircraft, especially helicopters, from colliding with the electrical power transmission lines which run across the country, eg suspended from pylons These lines are not easy to see, and present a considerable hazard to such aircraft The present invention provides apparatus which can detect the presence of such lines and indicate at least their approximate direction, alerting the pilot to keep a good look-out in that direction and to take avoiding action.
The invention operates by detecting the lowfrequency ( 50 Hz in the UK) magnetic flux produced by such lines Transmission lines normally comprise separate cables carrying each of three phases With perfectly balanced phases (equal currents in each phase), the net magnetic flux at a sufficient distance from the line would be zero, ie at such a distance that the spatially separated cables appeared as a “point” source It has been found, however, that there is usually sufficient current imbalance between the phases, eg up to 10 or 15 %, to produce sufficient net flux to be detectable at a useful distance Moreover, at distances closer to the line the latter does not appear as a “point” source.
Although the direction of maximum magnetic flux in the plane parallel to the ground and which contains the line is mainly vertical, as may be appreciated by considering the line as a single current-carrying conductor, this vertical component of flux cannot be utilised to give directional information It is found, however, that owing to the aforesaid imbalance between the currents in the cables, and to the fact that at distances of interest the line is not a “point” source, there is a horizontal component of flux in the aforesaid plane of the transmission line of sufficient strength to enable its direction to be detected This flux is, 50 however, quite small, eg normally several orders of magnitude less than the “DC” flux due to the earth’s magnetic field.
According to the present invention a method of warning a low-flying aircraft of the presence 55 and direction, with respect to the aircraft, of an electrical power transmission line comprises:
intercepting the horizontal component of the resultant magnetic flux from said line by two aircraft-mounted coils having their axes 60 aligned generally horizontally and at an angle to one another; deriving two signals proportional to the e.m f ‘s induced in the respective coils by said flux; 65 and utilising the ratio of said two signals to indicate in the aircraft the direction of the transmission line with respect thereto.
Also according to the present invention, apparatus for installation in an aircraft to warn of the 70 presence and direction, with respect to the aircraft, of an electrical power transmission line, comprises:
two coils adapted for aircraft mounting with their axes aligned generally horizontally and at 75 right angles to one another; means for amplifying and rectifying the AC signals from each coil to produce corresponding DC signals; and means for comparing the ratio of the 80 two DC signals with predetermined ranges of the value of said ratio, each predetermined range of values corresponding to a given directional angular sector, said comparing means being adapted to produce predetermined 85 output conditions at a plurality of output connections dependent upon the value of the ratio.
The two coils are preferably mounted at right angles to one another, since this makes the 90 relationship between the signal ratio and the source direction a simple trigonometrical one.
The use of a pair of loop aerials at right angles to one another for measuring the direction of electromagnetic radio transmissions is, 95 of course, well known In the present invention, however, the signal detected is not a propagated RF electromagnetic radiation but the “static” \) \ O ( 11) 1605156 corresponding to the appropriate quadrant The means for deriving the quadrant-identifying signal may comprise means for multiplying together the two amplified AC signals, the condition of the multiplier output thereby 70 depending on whether the two AC signals are in phase or in antiphase.
The directional display may be of known form and may comprise a plurality of illuminatable (eg electroluminescent) elements (eg 75 six) oriented diametrically with respect to a common centre and angularly spaced apart.
Mention has been made that the vertical component of magnetic flux density is greater than the horizontal component This fact may be 80 utilised to give early warning of the presence of a power line, though not its direction, by arranging a third coil in a generally horizontal plane, whose output after amplification is applied to operate a visible or audible warning 85 device.
It may also be arranged that the appropriate element of a visible display, eg the appropriate element of the above-described electro-luminescent display, is not illuminated until the 90 input signals have reached a threshold level.
This may be arranged by summing the two rectified AC signal outputs and comparing the sum with a predetermined level so that the display is illuminated only when the sum 95 exceeds the latter level.
Mention has also been made of the 1800 ambiguity in the direction of the transmission line in the present apparatus as so far described.
Resolution of this ambiguity is not essential, 100 because in general the pilot is mainly concerned with what lies in his path ahead, rather than what lies behind him However means may be provided for resolving this ambiguity if desired.
For example two pairs of coils as aforesaid can 105 be used, located sufficiently far apart along the length of the aircraft, eg at nose and tail The relative amplitudes of the induced signals from each pair of coils then indicates which end of the aircraft is closer to the line and hence 110 whether the line is ahead or behind Alternatively the rectified outputs from a single pair of coils can be summed and differentiated with respect to time The polarity of the differentiated signal then indicates whether the signal 115 is increasing or decreasing, ie whether the aircraft is approaching or leaving the line In either case the ambiguity is only resolved if the flux direction is not at 900 to the fore-aft axis of the helicopter If the flux is in this direction, the 120 ambiguity can be resolved by the pilot rotating the aircraft in either direction to change this situation.
To enable the nature of the present invention to be more readily understood, atten 125 tion is directed, by way of example, to the drawings accompanying the Provisional Specification which is a block schematic circuit diagram of apparatus embodying the invention.
In this drawing two coils 1 and 1 ‘ are 130 Hz circumferential purely magnetic field produced by the currents flowing in the line If Vel Wt is the e m f induced in one coil when the magnetic flux lines are normal to the plane of that coil, then if the flux makes an angle 0 with this normal, the induced e m f is Ve J Wt cos 0 while the e m f induced in the other coil is Veiwt sin O (t will be noted that this is the reverse of the situation with propagated electromagnetic radiation; the corresponding induced signals in the two loop aerials are then proportional to sin o and cos O respectively, where the same angle o is the direction of the received radiation) The ratio of the two signals is thus proportional to tan 0.
In principle the two AC signals obtained from the coils may be displayed directly, after suitable equal amplifications, to indicate the direction of the transmission line, eg by applying the signals to the X and Y plates of an oscilloscope, when the slope of the resulting trace indicates the value of O In order to obtain a simple, compact, low-voltage instrument, it is preferred, however, to avoid the use of cathoderay tubes and to process the signals in such a way as to display in which of a predetermined number of angular sectors the direction of the line lies The compact electroluminescent displays now available are suitable for this purpose, or for better visibility a brighter display can be used, eg involving filament bulbs.
Thus the present apparatus may comprise means for rectifying the amplified AC signals from each coil to produce corresponding DC signals, and means, including analogue-to-digital converter means, for comparing the ratio of the two DC signals with predetermined ranges of the value of said ratio, each predetermined range of values corresponding to a given directional angular sector, whereby to produce predetermined output conditions at a plurality of output connections dependent upon the value of the ratio Said output connections may be linked to the input connections of a directional display comprising a corresponding plurality of separately energisable visible elements.
With the two coils at right angles, the numerical value of the ratio of the two signals leaves unresolved in which of two adjacent 90 quadrants the direction of the line lies, eg whether to left or right of the line of flight of the helicopter This information is obtainable from the relative phases of the AC signals from the two coils; in one quadrant they are in phase, in the adjacent quadrant in anti-phase.
(There then still remains a 1800 ambiguity, ie whether the line is ahead of or behind the aircraft, which will be referred to later) Accordo ingly the present apparatus may comprise means for deriving from the two amplified AC signals a quadrant-identifying signal, and means for combining the quadrant-identifying signal with the outputs of said analogue-to-digital converter means to produce output conditions I 1 605 156 1 605 156 Spoke illuminated 12-6 o’clock 1-7 ” 2-8 ” 3-9 4-10 ” 5-11 ” 6-12 ” 0 -15 < O < 15 < O < 45 < O < 75 < O << 105 < O < 135 6 O < 165 60 < 195 tan 0 0 < Itan O i< O 27 0.27 < I tan O 1 1 O 1.0 < Itan O II 3 7 3.7 < I tan O 1 O O 1.0 < Itan O 1 < 3 7 0.27 i< tan O 1 < 1 O 0 < Itan 16 < 0 27 Other conditions With the 1,1 ' t signals in phase With the 1,1 ' signals in anti-phase mounted in a convenient position on a helicopter (not shown), with the plane of the coils vertical The two coils are at right angles to one another, with the plane of the coils parallel to the fore-aft axis of the helicopter The coils may be about 6 inches in diameter and may each comprise about 8000 turns, though the number may be reduced by including a ferromagnetic core. The 50 Hz e m f induced in each coil by the magnetic flux from an adjacent power line is fed to matched channels comprising low-noise preamplifiers 2, 2 ' suitably having a gain of about 10, active filters 3, 3 ' having a pass-band of 50 Hz + 2 Hz and a gain of about 10 to reject unwanted frequencies, main amplifiers 4, 4 ' having a gain of about 100 to bring the signal level to a few volts, and full-wave operationalamplifier rectifiers 5, 5 ' The latter form of rectifier is known to give linear rectification down to very low signal levels The outputs of rectifiers 5, 5 are smoothed by resistors R, R' and capacitors C, C'. The 12-6 o'clock spoke corresponds to the fore-aft axis of the helicopter, as indicated by arrow 24. The circuitry for illuminating the appropriate element 7 dependent on the signal ratio comprises an analogue-to-digital converter 8 which receives four signal inputs Two of these inputs are the output of rectifiers 5, 5 ' and two are these outputs multiplied by the factor 3 7 (which is also the reciprocal of 0 27) by means of amplifiers 9,9 ' Converter 8 comprises operational-amplifier comparator circuits followed by suitable logic gates and, in a manner familiar to those skilled in the electronic art, by comparison of the values of these four imputs is arranged to deliver appropriate outputs at its four output connections The conditions of these outputs, for the corresponding value of A/B (where A/B represents the ratio of the signals induced in coils 1, 1 ', and hence of the outputs of rectifiers 5, 5) are shown at relevant output connections as a form of logical "truth table". The elements 7 are illuminated by the application of negative voltages to transistors 10. The 12-6 o'clock and 3-9 o'clock elements are illuminated by such outputs directly from converter 8 As noted in the Table, however, there are two values of A/B (ie of tan 0) for which there is an ambiguity as to the quadrant in which the elements are to be illuminated. depending on the relative phases of the 50 Hz signals, eg 0 27 < I tan 0 I 6 1 0 can require As explained earlier, the ratio of these two outputs is the tangent of the angle 0 where 0 is the angle which the horizontal component of the lines of magnetic flux make with the normal to the plane of one of the coils In the 80 present embodiment the exact value of 0 is not displayed For simplicity and clarity the display indicates in which of six directional angular sectors the flux source lies, ie the nearest point on the transmission line 85 The display is shown at 6, which represents an electroluminescent display of known form. It comprises six electroluminescent elements 7 equiangularly oriented like the spokes of a wheel and separately energisable by application 90 of a voltage thereto Illumination of each of these "spokes" indicates that O lies within the corresponding angular sector relative to the fore-aft axis of the helicopter. The value of tan 0, ie the ratio of the signal, 95 amplitudes for illumination of each "spoke" is given in the Table above: illumination of either the 1-7 o'clock spoke or of the 5-11 o'clock spoke, depending on the relative input phases The outputs (shown as 100 logical "l 's") corresponding to these two values of A/B are fed to a quadrant selection circuit 11 comprising CMOS logic circuits, which also receives a quadrant-identifying signal whose condition depends on the relative phases of the 105 two 50 Hz induced signals According to its condition, circuit 11 routes a negative illuminating voltage in a conventional manner to the element 7 of the appropriate quadrant, as shown 110 The quadrant-identifying signal is obtained by applying the AC outputs of amplifiers 4, 4 ' via X 100 amplifiers 14, 14 ' to an analogue multiplier 12, whose output, smoother by R" C", is amplified by an open-loop operational 115 amnplifier 13 Consequently with the two AC signals in phase a logical " 1 " is fed to circuit 11, and with the two in anti-phase a logical "O" is fed. The above phase relationships apply between 120 the two pairs of 180 opposed quadrants, ie the signals are N phase for quadrants 0-90 and 1800-270 , and in anti-phase for quadrants 90-1800 and 2700-3600 (see Table) There is thus a 180 ambiguity in respect of each spoke, 125 ie the apparatus as described does not distinguish between ahead-left and astern-right, or between ahead-right and astern-left Means for resolving this ambiguity are not shown in the drawing, but circuits suitable for doing so in 130 1 605 156 either of the ways earlier described will be apparent to those skilled in the electronic art. It is further arranged that the appropriate element 7 is not illuminated until the input signal level has reached a threshold value For this purpose the outputs of rectifiers 5, 5 ' are summed by an operational amplifier 15 and the sum compared with a reference level in a circuit 16 Until the sum exceeds the reference level, an inhibiting signal is fed by circuit 16 via a diode to each transister 10 base to prevent an illuminating output condition being produced thereby. Early warning of the presence of power cables, without indication of direction, is obtained from a single horizontally oriented coil 17 whose output is fed to a channel (similar to that used for coils 1, 1 ') comprising preamplifier 18, filter 19, main amplifier 20, rectifier 2 o 21 and smoothing components R", C" The smoothed value is compared with a reference level in circuit 22 and operates an audible or visible alarm 23 when it exceeds the reference level In a modified form the outputs of rectifiers 5 and 5 ' may be summed with the output of rectifier 21 for comparison with the reference level. In a modified form of the circuit shown, the arrangement is the same from the coils 1, 1 as far as the rectifiers 5, 5 ' and the subsequent sm Qothing Thereafter the amplifiers 9, 9 ' are omitted and replaced by two analogue dividers whose outputs are A/B and B/A respectively. (Two dividers are used to give a greater dynamic operating range) The analogue-todigital converter circuit 8 is retained but differs internally from that already described so that it produces logical output conditions at its four outputs appropriate to the values of the signal ratios Selector circuit 11 is retained, together with the circuit (multiplier 21 etc) for providing the quadrant-identifying signal It is desirable in this modified arrangement to make the amplifiers 4, 4 ' AGC amplifiers whose gain is controlled by the sum of their outputs, because of the smaller dynamic operating range of the divider circuits. Additionally, it may be arranged that all the spokes flash on and off if the signal level is so high that the direction indication becomes unreliable owing to overloading of the amplifiers. This arrangement may comprise an oscillator (not shown) whose output is connected via diodes to the bases of transistors 10 The oscillator is switched on by a signal derived from a comparator fed with a sum signal, as with the inhibiting signal. To reduce electrical background noise due to e.m f 's induced by mechanical vibration of the coils in the earth's magnetic field, the coils can be mounted on suitable anti-vibration mountings To reduce background noise due to the magnetic fields of aircraft generators, the coils are preferably located remote therefrom. Other possible embodiments of the invention will be apparent to those skilled in the electronic art. Claims (1) WHAT I CLAIM IS: 1 A method of warning a low-flying aircraft of the presence and direction, with respect to 70 the aircraft, of an electrical power transmission line comprising: intercepting the horizontal component of the resultant magnetic flux from said line by two aircraft-mounted coils having their axes 75 aligned generally horizontally and at an angle to one another; deriving two signals proportional to the e.m f 's induced in the respective coils by said flux; 80 and utilising the ratio of said two signals to indicate in the aircraft the direction of the transmission line with respect thereto. 2 A method as claimed in Claim 1 wherein the coils are at right angles to one another 85 3 A method as claimed in Claim 2 comprising: amplifying and rectifying the AC signals from each coil to produce corresponding DC signals; 90 comparing the ratio of the two DC signals with predetermined ranges of the value of said ratio, each predetermined range of values corresponding to a given directional angular sector; and deriving predetermined output con 95 ditions dependent upon the value of the ratio. 4 A method as claimed in Claim 3 comprising applying said output conditions to energise a directional display comprising a corresponding plurality of separately energisable 100 visible elements. A method as claimed in Claim 3 or Claim 4 comprising deriving from the two amplified AC signals a quadrant-identifying signal, and combining the quadrant-identifying signal with 105 the signals resulting from the ratio comparison to derive said output conditions. 6 A method as claimed in Claim 5 comprising multiplying together the two amplified AG signals to derive said quadrant-identifying 110 signal. 7 A method as claimed in any preceding Claim comprising intercepting and vertical component by a third aircraft-mounted coil having its axis aligned generally vertically, amplifying 115 the output from the third coil, and applying the amplified output to provide an early warning when the amplified output exceeds a predetermined level. 8 A method as claimed in any of Claims 4 120 to 7 comprising summing the signals from said first-mentioned two coils and causing the summed signals to inhibit the energising of said visible elements until said summed signals exceed a predetermined level 125 9 A method as claimed in any of Claims 2 to 8, for resolving 1800 ambiguity, comprising comparing the amplitudes of signals induced in two pairs of said first-mentioned coils similarly oriented and spaced horizontally apart 130 I 1 605 156 A method as claimed in any of Claims 2 to 8, for resolving 1800 ambiguity, comprising differtiating the rectified and summed outputs of said first-mentioned two coils with respect to time and determining the polarity of the differentiated signal. 11 Apparatus for installation in an aircraft to warn of the presence and direction, with respect to the aircraft, of an electrical power transmission line, comprising: two coils adapted for aircraft mounting with their axes aligned generally horizontally and at right angles to one another; means for amplifying and rectifying the AC signals from each coil to produce corresponding DC signals; and means for comparing the ratio of the two DC signals with predetermined ranges of the value of said ratio, each predetermined range of values corresponding to a given directional angular sector, said comparing means being adapted to produce predetermined output conditions at a plurality of output connections dependent upon the value of the ratio. 12 Apparatus as claimed in Claim 11 wherein said comparing means comprises analogue-to-digital converter means. 13 Apparatus as claimed in Claim 12 wherein said output connections are linked 3 to the input connections of a directional display comprising a plurality of separately energisable visible elements. 14 Apparatus as claimed in Claim 12 or Claim 13 comprising means for deriving from the two amplified AC signals a quadrant-identifying signal, and means for combining the quadrant-identifying signal with the outputs of said analogue-to-digital converter means to produce output conditions corresponding to the appropriate quadrant. Apparatus as claimed in Claim 14 wherein the means for deriving the quadrantidentifying signal comprises means for multiplying together the two amplified AC signals. 16 Apparatus as claimed in any of Claims 13 to 15 wherein the directional display comprises a plurality of illuminatable elements oriented diametrically with respect to a common centre and angularly spaced apart. 17 Apparatus as claimed in any of Claims 11 to 16 comprising a third coil adapted for aircraft mounting with its axis aligned generally vertically to intercept the vertical component of said alternating flux, means for amplifying 55 the output of the third coil, and early-warning means operable by said amplified output when it exceeds a predetermined level. 18 Apparatus as claimed in Claim 16 comprising means for summing the signals from said 60 first-mentioned two coils and for inhibiting illumination of any element of said directional display until said summed signals exceed a predetermined level. 19 Apparatus as claimed in any of Claims 65 11 to 18 comprising means for resolving 1800 directional ambiguity, said means comprising two pairs of said first-mentioned two coils similarly oriented and spaced apart horizontally, and means for comprising the ampli 70 tude of the signals induced in each pair of coils. Apparatus as claimed in any of Claims 11 to 18 comprising means for resolving 1800 ambiguity, said means comprising means for differentiating the summed outputs from said 75 first-mentioned two coils with respect to time and for determining the polarity of the differentiated signal. 21 Apparatus as claimed in any of Claims 11 to 20 when installed in a helicopter, wherein 80 the axis of one of said first-mentioned two coils is parallel to the fore-aft axis of the helicopter and the axis of the other said coil is at right angles to said axis. 22 Apparatus as claimed in Claim 21 as 85 dependent on Claim 19 wherein said two pairs of coils are spaced apart along the fore-aft axis of the aircraft. 23 A method or apparatus for warning aircraft of the presence and direction of an electri 90 cal power transmission line substantially as hereinbefore described with reference to the to the drawing accompanying the Provisional Specification. M GREENHILL Chartered Patent Agent Agent for Applicant Priited for Her Majesty S Statioincry Otfice by M ULTIPLEX medway Itd Maidstone Kent ME 14 IJS 1982 Published at the Patent Office 2 E Southampton Buildings London WC IAY, from which copies may he obtained. GB28968/76A 1976-07-12 1976-07-12 Method and apparatus for warning aircraft of the presence and direction of electrical transmission lines Expired GB1605156A (en) Priority Applications (6) Application Number Priority Date Filing Date Title GB28968/76A GB1605156A (en) 1976-07-12 1976-07-12 Method and apparatus for warning aircraft of the presence and direction of electrical transmission lines IT7768576A IT1082790B (en) 1976-07-12 1977-07-07 PROCEDURE AND DEVICE FOR INDICATING THE DIRECTION OF A MAGNETIC FLOW SOURCE FR7721296A FR2500636A1 (en) 1976-07-12 1977-07-11 METHOD AND APPARATUS FOR INDICATING THE DIRECTION OF AN ALTERNATING MAGNETIC FLOW SOURCE BE0/179296A BE856753A (en) 1976-07-12 1977-07-12 IMPROVEMENTS IN METHODS AND APPARATUSES FOR INDICATING DIRECTION OF A MAGNETIC FLOW SOURCE DE19772731436 DE2731436A1 (en) 1976-07-12 1977-07-12 METHOD AND DEVICE FOR INDICATING THE DIRECTION OF A SOURCE OF MAGNETIC FLOW US06/147,295 US4405926A (en) 1976-07-12 1980-05-06 Methods and apparatus for warning aircraft of the presence and direction of electrical transmission lines Applications Claiming Priority (1) Application Number Priority Date Filing Date Title GB28968/76A GB1605156A (en) 1976-07-12 1976-07-12 Method and apparatus for warning aircraft of the presence and direction of electrical transmission lines Publications (1) Publication Number Publication Date GB1605156A true GB1605156A (en) 1982-06-09 Family ID=10284118 Family Applications (1) Application Number Title Priority Date Filing Date GB28968/76A Expired GB1605156A (en) 1976-07-12 1976-07-12 Method and apparatus for warning aircraft of the presence and direction of electrical transmission lines Country Status (6) Country Link US (1) US4405926A (en) BE (1) BE856753A (en) DE (1) DE2731436A1 (en) FR (1) FR2500636A1 (en) GB (1) GB1605156A (en) IT (1) IT1082790B (en) Cited By (2) * Cited by examiner, † Cited by third party Publication number Priority date Publication date Assignee Title GB2204409A (en) * 1987-04-14 1988-11-09 Richard Weatherley Cable identification device GB2343956A (en) * 1998-09-18 2000-05-24 Safe Flight Instrument Power line detector for use in aircraft Families Citing this family (11) * Cited by examiner, † Cited by third party Publication number Priority date Publication date Assignee Title US5252912A (en) * 1989-06-28 1993-10-12 William E. Merritt System for warning aircraft pilot of potential impact with a power line and generating time-to-time impact signal US5859597A (en) * 1997-11-05 1999-01-12 Cornelio; C. Joseph Helicopter electronic system for detecting electric power lines during landing DE19925760C2 (en) * 1999-06-05 2003-02-20 Hagenuk Kmt Kabelmestechnik Gm Device for determining the direction of incidence of electromagnetic waves US7286912B2 (en) * 2001-12-10 2007-10-23 Bae Systems Information And Electronic Systems Integration Inc. Method and apparatus for avoidance of power lines or trip wires by fixed and rotary winged aircraft WO2006083408A1 (en) * 2004-12-31 2006-08-10 Bae Systems Information And Electronic Systems Integration Inc. Method and apparatus for avoidance of power lines or trip wires by fixed and rotary winged aircraft DE102006018130A1 (en) * 2006-04-19 2007-10-25 Hagenuk KMT Kabelmeßtechnik GmbH Device for determining a laying depth of metallic lines US7920975B2 (en) * 2006-08-18 2011-04-05 The United States Of America As Represented By The Secretary Of The Army Methods of detecting anomalies in ambient alternating current fields EP2237055A1 (en) * 2009-03-31 2010-10-06 Eurocopter Deutschland GmbH Wide-band electromagnetic field detector and analysis system for aircraft US9372275B2 (en) * 2009-11-27 2016-06-21 Geotech Airborne Limited Receiver coil assembly with air and ferromagnetic cored sensors for geophysical surveying NO340705B1 (en) * 2014-12-22 2017-06-06 Kleon Prosjekt As Method and apparatus for detecting an airspace from an aircraft US9964658B2 (en) * 2015-10-06 2018-05-08 The United States Of America As Represented By The Secretary Of The Army Method of autonomous power line detection, avoidance, navigation, and inspection using aerial crafts Family Cites Families (9) * Cited by examiner, † Cited by third party Publication number Priority date Publication date Assignee Title GB399957A (en) 1931-08-06 1933-10-19 Soc Ind Des Procedes Loth Improvements in apparatus for determining the direction of magnetic or electro-magnetic fields US2623924A (en) * 1950-08-11 1952-12-30 Int Nickel Canada System of airborne conductor measurements US2794949A (en) * 1955-02-03 1957-06-04 Hedstrom Erik Helme Laurentius Electromagnetic induction method and apparatus for prospecting US3046549A (en) * 1959-08-07 1962-07-24 Henry P Kalmus Short range tracking system GB1056768A (en) 1963-09-24 1967-01-25 London Electricity Board Improvements in or relating to electric conductor identification apparatus US3344430A (en) * 1966-02-21 1967-09-26 Verne E Hildebrand Signal azimuth detector US3568048A (en) * 1968-12-09 1971-03-02 Mcphar Geophysics Ltd Three coil system for geophysical prospecting utilizing magnetic time transients US3774216A (en) * 1971-06-30 1973-11-20 Gen Electric Direction finder GB1370187A (en) * 1972-04-11 1974-10-16 Barringer Research Ltd Geophysical prospecting apparatus 1976 1976-07-12 GB GB28968/76A patent/GB1605156A/en not_active Expired 1977 1977-07-07 IT IT7768576A patent/IT1082790B/en active 1977-07-11 FR FR7721296A patent/FR2500636A1/en not_active Withdrawn 1977-07-12 DE DE19772731436 patent/DE2731436A1/en not_active Withdrawn 1977-07-12 BE BE0/179296A patent/BE856753A/en not_active IP Right Cessation 1980 1980-05-06 US US06/147,295 patent/US4405926A/en not_active Expired - Lifetime Cited By (4) * Cited by examiner, † Cited by third party Publication number Priority date Publication date Assignee Title GB2204409A (en) * 1987-04-14 1988-11-09 Richard Weatherley Cable identification device GB2204409B (en) * 1987-04-14 1991-07-10 Richard Weatherley Cable identification device GB2343956A (en) * 1998-09-18 2000-05-24 Safe Flight Instrument Power line detector for use in aircraft GB2343956B (en) * 1998-09-18 2003-09-03 Safe Flight Instrument In-flight aid for detecting power lines Also Published As Publication number Publication date IT1082790B (en) 1985-05-21 FR2500636A1 (en) 1982-08-27 US4405926A (en) 1983-09-20 BE856753A (en) 1983-07-15 DE2731436A1 (en) 1983-10-06 Similar Documents Publication Publication Date Title US4405926A (en) 1983-09-20 Methods and apparatus for warning aircraft of the presence and direction of electrical transmission lines US3121228A (en) 1964-02-11 Direction indicator US2456666A (en) 1948-12-21 Radio direction finding system US3471772A (en) 1969-10-07 Instrument for measuring the range and approximate size of buried or hidden metal objects US2412822A (en) 1946-12-17 Photoelectric device US2407287A (en) 1946-09-10 Course beacon US3905121A (en) 1975-09-16 Device for indicating a direction on the earth{3 s surface US2430244A (en) 1947-11-04 Radio beacon system US3848182A (en) 1974-11-12 Apparatus for limiting phase-angle response range, particularly in eddy current testing apparatus US2527559A (en) 1950-10-31 Method of geophysical exploration US4194206A (en) 1980-03-18 Instantaneous frequency measurement (IFM) receiver with capability to separate cw and pulsed signals US2568250A (en) 1951-09-18 Phase comparator circuits SU841610A3 (en) 1981-06-23 Electromagnetic gage sensitive to change of magnetic field US2308521A (en) 1943-01-19 Automatic radio direction indicator US3601899A (en) 1971-08-31 Single core solid-state compass GB599339A (en) 1948-03-10 Improvements in or relating to discriminator circuits for signal modulated electric pulses US2942180A (en) 1960-06-21 Magnetic field measuring system US3646537A (en) 1972-02-29 Automatic gain control for an electromechanical transducer US2485582A (en) 1949-10-25 Receiver system US2418308A (en) 1947-04-01 Radio direction finder US2485847A (en) 1949-10-25 Combination magnetometer and gradiometer US2403956A (en) 1946-07-16 Storage amplifier circuit US3757100A (en) 1973-09-04 Trigonometric segment discriminator US3274546A (en) 1966-09-20 Aircraft guidance, approach, and landing system with yaw detection and metering US2005962A (en) 1935-06-25 Electromotive forces comparing device Legal Events Date Code Title Description 1982-08-25 PS Patent sealed [section 19, patents act 1949] 1986-02-26 PCNP Patent ceased through non-payment of renewal fee
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