US3031663A - Magnetic antenna systems - Google Patents

Magnetic antenna systems Download PDF

Info

Publication number
US3031663A
US3031663A US706912A US70691258A US3031663A US 3031663 A US3031663 A US 3031663A US 706912 A US706912 A US 706912A US 70691258 A US70691258 A US 70691258A US 3031663 A US3031663 A US 3031663A
Authority
US
United States
Prior art keywords
windings
winding
aircraft
magnetic
antenna
Prior art date
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 - Lifetime
Application number
US706912A
Other languages
English (en)
Inventor
Wennerberg Gunnar
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.)
Motorola Solutions Inc
Original Assignee
Motorola Inc
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.)
Filing date
Publication date
Application filed by Motorola Inc filed Critical Motorola Inc
Priority to US706912A priority Critical patent/US3031663A/en
Priority to GB35312/58A priority patent/GB842246A/en
Priority to FR781732A priority patent/FR1216607A/fr
Priority to JP3541662U priority patent/JPS3930773Y1/ja
Application granted granted Critical
Publication of US3031663A publication Critical patent/US3031663A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q7/00—Loop antennas with a substantially uniform current distribution around the loop and having a directional radiation pattern in a plane perpendicular to the plane of the loop
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/286—Adaptation for use in or on aircraft, missiles, satellites, or balloons substantially flush mounted with the skin of the craft

Definitions

  • MAGNETIC ANTENNA sYsTEMs Filed Jan. I5, 1958 3 Sheets-Sheet 2 3,9%,663 Patented Apr. 24, 1962 3,031,663 MAGNE'HC AN'EENNA SYSTEMS Gunnar Wennerberg, Paciiic Palisades, Calif., assigner, by mesme assignments, to Motorola, lne., Chicago, Ill., 1 a corporation of Hlinois Filedlan. 3, 1953, Ser. N 7il6,912 Y lll ⁇ Claims. (Cl. 343-117) receiver, or as a pair of crescent-shaped magnetic elements between which arrotatable coil is mounted.
  • YAn antennasystem comprising such numerous parts'of course takes considerable time and pains to assemble, a factor which contributes considerably to its cost.
  • the use of any rotating parts in the vicinity of the surface at which the antenna is mounted necessitates strengthening of the aircraft frame in the immediate vicinity, all of which contributes to the weight and bulk of the system.
  • quadrantal error compensation with ferrite antennas is achievedwith undesirable structure conigurations.
  • Different schemes fhave lbeen proposed for quadrantal error compensation in liiush mounted antenna systems; in each, two or moreferriteelements are spaced from a rotatable coil, and meansl are employed lto vary the shape vand/ or positions of such elements.
  • Such means take the form either of ferrite stubs hired across the outer or of means to vary the spacing between the elements'. All sucharrangements require painstaking care and machining to proper dimensions, and of course add tothe weight, cost and bulk of the antenna structure.
  • FIG. 1 is a perspective view of an antenna structure employing a square magnetic element, in accordance with thisv invention
  • FIG. 2 is a schematic diagram illustrating an automatic directionnder system incorporating the antenna of FIG, l, also in accordance with this invention
  • FIG. 3 is a sectional View, taken along line 3--3 of FIG. l of the structure mounted on an aircraft,
  • FIG. 4 is a top plan View of an antenna structure employing a circular magnetic element, also in accordance with this invention.
  • FIG. 5 ⁇ isV a perspective view of an antenna illustrating a rectangular magnetic'element for quadrantal error compensation, in accordance ⁇ with this invention, p
  • FIG. 6 is a perspectiveV view of the structure of FIG. 5 mounted on an aircraft
  • NFIG. 7 is a sectional' View taken along-'line 7-7 of FIG. 6, f l
  • PEG. '8 is a plan view of a rectangular magnetic element with a modilied winding arrangement, further in accord- ⁇ ance lwith this invention, and
  • FIGS. 9 and l0 are plan views of different shapes of magnetic elements employing a winding arrangement as in FIG. 8. l
  • FIG. l one embodiment of a magnetic antenna structure in accordance with this inventionV ern- V.l ploys a iiat square-element lil of high-frequency, highpermeability material, which may be a dust iron or ferrite slab, upon which are mounted windings 12, 14.
  • Winding 12 is formed of apair of coils 16, 18 made of conductive ribbons Wound in one direction about ele ⁇ ment 1t); similarly, winding 14 is formed of a pair of coils 2t), 22. made of conductive ribbons ywound at right angles to Winding 12.
  • Each coil has one end conductively connected, as by solder connections, to one end of the metallic cylinder 24 of a terminal socket centered in element 1t); the remaining ends of coils 16, 18 are connected to respective terminal pins 26, 23 and the remaining ends of coils 20, 22 are connected to respective pins 30, 32'which are xedin an insulating support 34 disposed within ring 24.' In this manner, the pairs of coils 16-18 and Ztl-Z2 are connected'in series to form the respective windings i2, 14.
  • y Ring Z4 will be recognized as used as a ground connecportions of one or more of the other coils.- To prevent use in direction iinding applications on aircraft, wherein ⁇ a pair of windings form the antenna and are not subject 55 Another object of this invenion is to provide a tiredv l to variations in inductance.
  • remote goniometer means are employed to effect translation of received signals to an ADF receiver, and wherein remote.
  • connections areA made from pins 26,72% and from pins 30, 32 to the ends of respective stator windings 35, 35 of a conventional goniometer device 49;
  • the goniometer is mounted within the aircraft, preferably on the instrument panel in the cockpit, in a position where movement of a pointer 42 carried by its 'rotor is visible to the pilot.
  • the rotor winding 44 of the goniometer is connected to the input of an ADF receiver 46 in aV conven-V tional manner, ,the rotor winding 44 being inductively 42, a synchro device (not shown) may be operated by motor shaft 56, from which repeater synchro means may present indications elsewhere in the aircraft.
  • windings 12, 14 each have the same inductance. This is effected by proper choice of number of turns and suitably spacing the turns of the windings. Thus, since the windings are fixed, no variations in inductance can occur; further, since they are Wound at right angles to each other, there is no mutual inductance between them.
  • one winding 14 being wound over the other winding 12, effectively supports such other winding in assembly.
  • the procedure for winding can be varied as desired; for example, the windings may be assembled in a basket-weave pattern, i.e., with their turns interlaced, so they are mutually supporting in assembly. Electrically, basket-weaving achieves symmetry as to winding capacity.
  • the structure is mounted on the surface of the aircraft, eg., the belly of the aircraft, in a depression in the metallic yskin 6d.
  • a suitable insulation material 62 which may be a thermoplastic resin, covers the outer surface of element 10 and, if desired, tills the crevices between the edges of the element and skin di?.
  • the metallic ring 24 extends to the interior of the aircraft, where the electrical connections previously described are led to the goniomcter in the cockpit.
  • stator windings 35, 36 of goniometer 4d are wound so as to be 90 apart electrically, as is conventional.
  • a signal is picked up only in winding l2; the signal appearing in the output of receiver d6 causes motor 52 to position the rotor shaft so that winding 4d is at right anglesA to stator winding 35, at which point the induced signal disappears.
  • Pointer 42 in this position indicates a null point Ialigned with the heading of the aircraft. 'lf the station is directly to the rear of the aircraft, rotor winding 44 is positioned at right angles to stator winding 35, but reversed 180 from its position when the aircraft is flying directly .toward the station. aPointer 42 in this situation would indicate that the station was 180 from null. Such ambiguity resolution will be recognized as conventional.
  • the magnetic field threads both windings and induces a signal in each; the magnitude of one signal corresponds lto the sine and -the other to the cosine of the angle lbetween the station and the aircraft.
  • motor I52 causes rotor winding 44 to assume a position between stator windings 35, 36 which corresponds to the ⁇ vector addition of ⁇ the signals.
  • yPointer 42 here indicates the direction of the station relative to the line of ight.
  • FIG. 4 illustrates windings l2, i4 are placed on a hat circular element 7i! of ferrite. So long as the turns of the respective windings are symmetrically arranged on the element, and the windings are at right angles to each other, there is no lmutual inductance. With the same inductance for each winding, the antenna functions in the same manner as that of FIG. l.
  • FIGS. 5-7 illustrate an antenna structure arranged in accordance with this invention to insure complete quadrantal error compensation. This is achieved by placing windings 12, 14 on an oblong ferrite bar 3i? (in which caso the turns of winding l2 are longer than those of winding 14) having a length-to-width ratio such that the previously indicated differences in field pickup are eliminated.
  • windings l2, i4 have their axes in the same plane, Ithey have the same inductance, and there is no mutual inductance.
  • the placement of ferrite bar 3d with its greater dimension parallel to the line of ight has the effect of making the pickup sensitivities of the windings the same. Therefore, for liight in any direction relative to the station, pointer 42 indicates the true direction of ⁇ the station from the heading ofthe aircraft.
  • FIGS. 6 and 7 illustrate an arrangement to aliix the structure of FIG. 5 to an aircraft.
  • the structure is placed within a thin plastic housing S2, here illustrated as transparent, which is secured to the skin Gil of the aircraft, eg., by riveting.
  • lthe skin does not have to be modied to provide a depression in which the structure is fitted; all that is necessary is to bore a hole in which the terminal socket is inserted, and from which connections to the goniometer are made as previously described.
  • Element 84 is suiiiciently long to span ⁇ all ythe turns of winding 14, and
  • a sheet 86 of insulation material separates element $4 from the windings l2, 14.
  • Element 84 may be the same metal as the skin of the aircraft, in which case the antenna elements are sandwiched between layers of aluminum. The effect of these layers is to minimize magnetic leakage in the vicinity of the windings and to irnprove shielding against capacitive pickup, thereby to enhance their pickup sensitivity.
  • a further important advantage of the compensated antenna is that, since there is no problem of variation in inductan-ces of the windings, and there is no mutual inductance, the windings and their associated structure resonate lat the same frequency in all posi-tions of the rotor lwinding of the goniometer.
  • FIG. 8 illustrates an arrangement for achieving quadrantal error compensation wherein wind-ings 10, 12 of equal dimensions' are wound Aacross; bar 80 so that the angle a between their axes which intercepts the major axis of bar :Sti -is bisected by suchmajor axis; Theangle a preferably is'chos'en so that for the dimensions of the ferrite element, the mutual inductance is zero. For vzero mutual inductance, angled is greater than 90, due to the effect of the ferrite.
  • ⁇ such angle may begreater or smaller than 90, depending upon the coniigurationof the ferrite element.
  • the proper orientation of the windings for zero or .tolerable mutual inductance may be determined by conv ⁇ necting a Q-meter to one winding and lorienting -the windings until the Q-meter shows no change when the other winding is alternately open-circuited and short-circuited.
  • FIGS. 9 and 10 illustrate an arrangement wherein windings 12, 14 are positioned on respective tear-drop and rhombic ferrite elements 90 and it) in the manner shown in FIG. 8.
  • elements 90and 10d each lhave an axis Vof symmetry" and the windings crisscross such axis so that their axes formequal angles with it.
  • the windings are arranged for zero or minimum mutual inductance; and in each theorientation of the ferrite element .with its major axis parallel to the longitudinal centerline of the aircraft insures .that the windings have the same pickup characteristics.
  • windings are disposedfto equalize or balance temperature Yand capacitanceelects between them.
  • the open-circuit ⁇ magnetic pathsfor the two windings contain equal lengths of ferrite and equal air-gaps. With windings of -the'samedimensiong their stray capacitances arethe'same, in which case the capacitance effects between them are balanced. Also, since the temperature coeicients of 'equal lengths of the ferrite are equal, then with windings of equal dimensions dis' posed as in FIGS. 8-10, temperature effects in onepath are matched in the other, whereby. pickup characteristics for both windings remain equal.
  • an antenna system comprising a thin solid magnetic ele# ment of uniform thickness between at surfacesV thereof, iirst and second antenna windings wound one over the other and about said element and on said hat surfaces, -V
  • Vprinted strips or anyof numerous types.
  • windings having axes in the same plane, andpositioned so there is substantially no mutual inductance.
  • the ferrite element be elongated in one dimensionalong an axis of symmetry, and that the windings be disposed about such axis.
  • the ferrite element be hat, and shaped to. permit turnsA to be wound thereon to form two' axis, said windings being positioned sothere is no mutual inductance when a magnetic field set up by a transmitter station threads said element', a goniometer device having iirst and second stator windings respectively' connected to said first and second antenna windings, said stator windings being displaced electrical degrees from each other, a rotor'for said goniometer device having a winding sup# ported thereon, said rotor winding being inductively coupled to the tuner, said rotor winding having induced a signal representing the vector addition of signals inwinding is reduced to zero, and indicating means operable in said position of said rotor to indicate the direction to the station.
  • An antenna structure comprising a flat magnetic element, said element having at least one axis of symmetry V.and being elongated in theV direction of said one axis, a
  • said Windings having their Vaxesin the same plane, said Velement being adapted to be positioned so that a magnetic held established by a transmitter station passes through said element in the direction of said plane, and said winding elongated in the directioniof flight of the aircraft, a pair of windings having equal inductances supported one over the other on said element with their axes in a common plane, a goniometer device having'rst and second stator windings disposed at right angles to each other, a rotor having a winding thereon coupled to the input of the receiver, a motor connected between the output of the receiver and said rotor, said element being positioned so that a magnetic field established by an automatic direction ⁇ finder transmitter station threads said element and induces signals in said windings, said stator windings causing a signal to be induced in said rotor winding which represents the position of said rotor relative to the station, and said receiver applying a signal to the motor to effect positioning of said rotor so that the signal
  • An antenna structure for use on a movable vehiclev including in combination, a thin magnetic element having ilat parallel surfaces and adapted to be mounted on the vehicle, said element being elongated in the direction of movement of the vehicle and being symmetrical about an axis extending in such direction, and a pair of windings having turns on said dat surfaces and having axes in the same piane, said windings being disposed with the axis thereof at an angle with respect to each other and with one winding being wound over the other, said windings having the same inductance and being disposed about said axis of symmetry so that the mutual inductance therebetween is substantially zero.
  • a directional antenna structure for use on a movable vehicle including in combination, a thin solid magnetic element adapted to be mounted in tixed'position on the vehicle, said element having ilat rectangular surfaces each having one pair of parallel sides which are parallel to the direction of movement of the vehicle, and a pair of windings about said element having turns extending across said fiat surfaces, said windings having axes iu the same plane and one winding being wound over the other, one of said windings having turns extending parallel to the direction of movement and the other of said windings having turns extending perpendicular to the direction of movement, said windings having the same inductance and being disposed so that the mutual inductance therebetween .is substantially zero.

Landscapes

  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Astronomy & Astrophysics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Physics & Mathematics (AREA)
  • Remote Sensing (AREA)
  • Details Of Aerials (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
US706912A 1958-01-03 1958-01-03 Magnetic antenna systems Expired - Lifetime US3031663A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US706912A US3031663A (en) 1958-01-03 1958-01-03 Magnetic antenna systems
GB35312/58A GB842246A (en) 1958-01-03 1958-11-04 Magnetic antenna systems
FR781732A FR1216607A (fr) 1958-01-03 1958-12-16 Système d'antennes magnétiques
JP3541662U JPS3930773Y1 (en, 2012) 1958-01-03 1958-12-23

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US706912A US3031663A (en) 1958-01-03 1958-01-03 Magnetic antenna systems

Publications (1)

Publication Number Publication Date
US3031663A true US3031663A (en) 1962-04-24

Family

ID=24839589

Family Applications (1)

Application Number Title Priority Date Filing Date
US706912A Expired - Lifetime US3031663A (en) 1958-01-03 1958-01-03 Magnetic antenna systems

Country Status (4)

Country Link
US (1) US3031663A (en, 2012)
JP (1) JPS3930773Y1 (en, 2012)
FR (1) FR1216607A (en, 2012)
GB (1) GB842246A (en, 2012)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4087817A (en) * 1977-01-17 1978-05-02 The Bendix Corporation ADF antenna
EP0285303A1 (en) * 1987-03-24 1988-10-05 Nippon Antenna Co., Ltd. Broadcasting wave reception antenna
US6873302B1 (en) * 2002-12-09 2005-03-29 Raytheon Company Signal detection antenna
US11085989B2 (en) 2019-05-31 2021-08-10 Craig Russell Armstrong Low-frequency radio navigation system
CN117465655A (zh) * 2023-12-28 2024-01-30 山河星航实业股份有限公司 轻型飞机机翼及轻型飞机

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2024522A (en) * 1978-05-09 1980-01-09 Secr Defence Aerofoil-Mounted Antenna
GB2258952A (en) * 1991-08-20 1993-02-24 Marconi Gec Ltd Antennas

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2297466A (en) * 1935-04-24 1942-09-29 Funke Walter Frame aerial
GB751138A (en) * 1953-04-04 1956-06-27 Standard Telephones Cables Ltd Antenna, in particular a turnable or swivelling antenna

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2297466A (en) * 1935-04-24 1942-09-29 Funke Walter Frame aerial
GB751138A (en) * 1953-04-04 1956-06-27 Standard Telephones Cables Ltd Antenna, in particular a turnable or swivelling antenna

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4087817A (en) * 1977-01-17 1978-05-02 The Bendix Corporation ADF antenna
EP0285303A1 (en) * 1987-03-24 1988-10-05 Nippon Antenna Co., Ltd. Broadcasting wave reception antenna
US6873302B1 (en) * 2002-12-09 2005-03-29 Raytheon Company Signal detection antenna
US11085989B2 (en) 2019-05-31 2021-08-10 Craig Russell Armstrong Low-frequency radio navigation system
US11656313B2 (en) 2019-05-31 2023-05-23 Arbiter Systems, Inc. Low-frequency radio navigation system
US12181557B2 (en) 2019-05-31 2024-12-31 Arbiter Systems, Inc. Low-frequency radio navigation system
CN117465655A (zh) * 2023-12-28 2024-01-30 山河星航实业股份有限公司 轻型飞机机翼及轻型飞机
CN117465655B (zh) * 2023-12-28 2024-03-01 山河星航实业股份有限公司 轻型飞机机翼及轻型飞机

Also Published As

Publication number Publication date
GB842246A (en) 1960-07-27
FR1216607A (fr) 1960-04-26
JPS3930773Y1 (en, 2012) 1964-10-19

Similar Documents

Publication Publication Date Title
US2740113A (en) Magnetic antenna systems
US4074268A (en) Electronically scanned antenna
US5442280A (en) Device for measuring an electrical current in a conductor using a Rogowski coil
GB1211726A (en) Loop antenna
US3735306A (en) Magnetic field shim coil structure utilizing laminated printed circuit sheets
US3031663A (en) Magnetic antenna systems
US3339205A (en) Utilizing segmented dipole elements to decrease interaction between activated and deactivated antennas
US2420967A (en) Turnstile antenna
US3949345A (en) Multiple magnetoresistance element
US3334317A (en) Ferrite stripline circulator having closed magnetic loop path and centrally located, conductive foil overlying radially extending center conductors
US3334318A (en) Stripline circulator having means causing electrostatic capacitance between adjacent pairs of terminals to be substantially equal to each other
US3090934A (en) Reduction of unwanted coupling between transformer members of position-measuring transformers
US4766444A (en) Conformal cavity-less interferometer array
US3719950A (en) Antenna system for vhf and uhf radio direction finders
US2465381A (en) Loop antenna system
US2660681A (en) Winding arrangement for variable transformers
US2955286A (en) Plural loop antenna having ferrite cores
GB1271346A (en) Flush mounted steerable array antenna
US3611389A (en) Vor antenna
US2474268A (en) Radio-frequency in-phase indicator
US2755468A (en) Antenna combined with magnetic coupling core
US4117490A (en) Inconspicuous antenna system employing the airframe as an antenna
US3066291A (en) Antenna structure and system
US2888635A (en) Stick force transducer
US2297466A (en) Frame aerial