US3242491A - Inverted v-beam antenna system - Google Patents

Inverted v-beam antenna system Download PDF

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US3242491A
US3242491A US244059A US24405962A US3242491A US 3242491 A US3242491 A US 3242491A US 244059 A US244059 A US 244059A US 24405962 A US24405962 A US 24405962A US 3242491 A US3242491 A US 3242491A
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antenna
shaped
inverted
beams
along
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Charles F Winter
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Raytheon Co
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Raytheon Co
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Priority to US244059A priority patent/US3242491A/en
Priority to GB43308/63A priority patent/GB1024804A/en
Priority to DER36552A priority patent/DE1246052B/de
Priority to FR954388A priority patent/FR1381622A/fr
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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q25/00—Antennas or antenna systems providing at least two radiating patterns
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S1/00—Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith
    • G01S1/02—Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith using radio waves
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/88—Radar or analogous systems specially adapted for specific applications
    • G01S13/91—Radar or analogous systems specially adapted for specific applications for traffic control
    • G01S13/913—Radar or analogous systems specially adapted for specific applications for traffic control for landing purposes
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q19/00—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
    • H01Q19/10—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
    • H01Q19/12—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave
    • H01Q19/17—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave the primary radiating source comprising two or more radiating elements
    • H01Q19/175—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave the primary radiating source comprising two or more radiating elements arrayed along the focal line of a cylindrical focusing surface
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H01Q3/02—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole

Definitions

  • the present -invention relates to shaped beam antenna systems, and, more particularly, to a system which orients at least one beam of a plurality of shaped beams along a small circle arc.
  • V-beam antenna system which shows the greatest potential for meeting the problem of handling an unlimited number of airborne vehicles.
  • the V-beam approach towards meeting this problem of provid-ing target elevation dates back to World War II; however, to the present time, the disadvantages have outweighed the advantages.
  • the simple V-beam radiation coverage consists of two distinct beams, each of said beams lying on great circles of a sphere and having their antennas positioned at the center of said sphere no matter what position either of the antennas radiating the beams are slanted, and both shaped in their vertical directions and of narrow beam widths in any azimuthal plane.
  • the definition of a great circle and a small circle are found in Websters New International Dictionary, 2nd edition unabridged, which under the heading of Circles of Sphere statesA a circle upon the surface of the sphere, specifically of. the earth or of the heavens, called a great circle when its plane passes through the center of.
  • One beam is koriented in the conventional shaped-beam Search fashion, i.e., the plane in which the shaping occurs makes an angle of 90 with the horizon plane for any azimuthal pointing of the antenna.
  • the other beam is tilted over at a slant, i.e., its plane of shaping makes an angle of less than 90 with the horizon.
  • a stationary airborne vehicle may be hit by radiations from both antennas.
  • the angle between hits (which can be determined by a time measurement) can be seen to be a function of the elevation angle of the airborne target. If the tilt angle of the slant antenna is known, then it is possible to solve for the tangent of the angle between beam lhits and, therefore,
  • the principal disadvantages of a simple V-beam antenna are that the highest elevation angle that can be determined is a function of the tilt angle. A large tilt angle with respect to the horizontal severely limits elevation coverage for two reasons. First, the slant beam never rises above the complement of the tilt angle. Second, the angle between hits becomes progressively wider as the elevation angle increases. Furthermore, the rate of change of the slope for each radiation curve is a minimum at low elevation angles and, therefore, sensitivity is least near the horizon instead of at the higher angles where accuracy for ground based applications is typically less critical.
  • the difference between slope angles on any radiation curve at two elevation angles represents the amount of rotation that aV linearly polarized eld vector undergoes and, therefore, for a one way beacon V-beam transmission approach, signal loss at the receiving antenna generally results because of the misalignment between the polarizations of the receiving and transmitting antennas.
  • an object of the invention is to provide an improved antenna system which is capable of providing accurate elevation measurements over a broad range of angles and simultaneously of providing the greatest sensitivity of measurement at the low elevation of angles.
  • an inverted V-shaped beam antenna system such as used in a beacon guidance system, comprises a transmitter providing energy to a first means for radiating a shaped beam along a great circle and to a second means for radiating a shaped beam along a small circle.
  • a system used as a three dimensional or 3D radar having height finding as one of its functions, comprises a first transmitter, providing energy to an isolation means, such as a dupleXer to a first means for radiating a shaped beam along a great circle and a second transmitter, providing energy through a second isolation means to a second means for radiating a shaped beam along a small circle, and a receiver-computer coupled to each of said isolation means for determining a targets position in 3D.
  • an isolation means such as a dupleXer to a first means for radiating a shaped beam along a great circle
  • a second transmitter providing energy through a second isolation means to a second means for radiating a shaped beam along a small circle
  • a receiver-computer coupled to each of said isolation means for determining a targets position in 3D.
  • FIG. 1 illustrates a geometry for an inverted V-beam antenna system showing arcs of radiation along two small circles
  • FG. 2 illustrates a beacon helicopter system in block form utilizing an inverted V-shaped beam antenna
  • FIG. 3 illustrates a geometry of the Ibeacon helicopter system of FIG. 2 having an inverted V-shaped lbeam antenna radiating arcs of radiation 4along one great circle and one small circle,
  • FIG. 4 illustrates a pair of shaped beam antennas for use as an inverted V-shaped beam antenna of FIG. 2,
  • FG. 5 illustrates a section of t-he feed of the slant antenna of FIG. 4,
  • FIG. 6 illustrates the curvature of the reflector of the slant anntenna of FIG. 4, I
  • FIG. 7 illustrates a section of the feed of the vertical antenna of FIG. 4,
  • FIG. 8 illustrates the curvature of the reector of the vertical antenna of FIG. 4,
  • FIG. 9 illustrates an arrangement of a three dimensional or 3D radar system in block form utilizing an inverted V-shaped beam antenna.
  • FIG. 1 there is shown an illustration of a geometry for an inverted V beam antenna system showing arcs of radiation along two small circles.
  • this invention 1s not limited to two shaped beams, nor is it limited to radiations along small circles; great circle radiations can also be used provided there is at least one shaped beam of a plurality of shaped beams which is oriented along a small circle arc.
  • FIG. 1 shows a representation of two shaped beams oriented upon spatial loci, previously unconsidered, which are used to establish one particular spatial coordinate. Typically, this ⁇ coordinate can be the elevation angle A as shown in FIG. l.
  • One shaped beam is oriented along the locus of intersection of a unit sphere whose center is at a point and a cone about Y' axis whose cone angle is 2B and whose Vertex is at point 0.
  • the Y' axis makes an angle C with the Y axis.
  • the Y axis is shown in the YZ-plane but this is n-ot a restriction on the principle of the invention.
  • the second shaped beam lies along the locus of intersection of the same sphere and a cone about the Y" axis whose cone angle is 2D and whose vertex is also at point 0.
  • This locus is the small circle G", P", S" for D+90".
  • the Y" axis makes an angle E with the Y axis and again, for simplicity only, is pictured in the YZ-plane.
  • a functional relationship for example, between the elevation angle A and the angle F measured in a plane parallel to the XY-plane can be solved mathematically for the coordinate A, for each determination of the angle F existing between the corresponding points P', P", one on each shaped beam at the same height lz above the XY -plane.
  • this arrangement is illustrative of the basic principles involved in considering shaped beams oriented along small circle arcs.
  • FIG. 2I there is shown a general arrangement of a beacon helicopter system in block form utilizing an inverted V beam antenna sub-system.
  • a surface complex 1 having a transmitter 2 of the type generally used in radar systems which could comprise either magnetron or traveling Wave tube power amplifiers or other types of power amplifiers to generate a source of electromagnetic radiation.
  • a power divider 3 is coupled to the transmitter 2 and, in turn, a slant antenna 4 and a vertical :antenna 5, which are adapted for rotation in the surface complex 1 and which comprise the inverted V-beam antenna 6, are coupled to power divider 3.
  • Antenna 4 produces a shaped beam, which will hereafter be called the slant beam which is directed along a small circle arc and the antenna 5, which hereafter will be referred to as the vertical beam antenna, has its radiation directed along a great circle arc.
  • the helicopter 7 is also shown in a spaced relationship to the surface complex 1.
  • Helicopter 7 includes an antenna 8 for receiving radiations from antennas 4 and 5 of inverted V- beam antenna 6, a receiver 9 coupled to antenna 8 for detecting the radiations of antennas 4 and 5 from inverted V-beam antenna 6, a timer 10 coupled to the receiver 9 for timing the timed difference in the detection of radiations from antennas 4 and 5 from inverted V-beam antenna 6, computer 11 coupled to the timer 10 for calculating the angle of descent of said helicopter 7 to said surface complex 1 and a display 12 for displaying the angle of descent information to the pilot of helicopter 7.
  • FIG. 3 there is shown the geometry of a ground complex surface based beacon helicopter landing system as shown in FIG. 2 having an inverted V-beam antenna sub-system radiating arcs of radiation along one great circle and one small circle.
  • the antennas 4 and 5 of the inverted V-beam antenna 6 are positioned at point 0, point 0 being the center of the sphere of -which one -octant abc is shown in FIG. 3.
  • the XY-plane represents the surface and the Z axis lpoints to the zenith of the sphere.
  • This small circle arc is seen to be parallel to only one great circle GLV' on the sphere.
  • the shaped beam, approximately l.5 beamwidth in this case, of the antenna 5, hereafter called the vertical beam antenna is directed along a great circle arc GPV.
  • the significant radiation of the vertical-ly shaped beam from the vertical beam antenna 5 is contained between 4the elevation angles of approximately 6 to 75 along t-he great circle arc GPV.
  • the two shaped beams from :antennas 4 and 5 are oriented such that the Ibeam from the vertical beam antenna along the arc GPV is functioning in a conventional Search radar fashion and that of the slant beam along a small circle arc GP'V in a previously unconventional manner.
  • the angle F hereafter called the azimuth-response angle
  • an airborne vehicle such as helicopter 7 of FIG. 2
  • hovering on an arc between the point-s P and P', represented by point K must maintain to arrive at a predetermined point over the surface complex 1.
  • the azimuth-response angle F can be determined by measuring the time between successive detections of the radiation beams from antennas 4 and 5 by the combination of the timer 10 and the receiver 9 of helicopter 7, dividing this time by the time for one rotation of the inverted V-beam beacon antenna sub-system 6 and multiplying the resulting fraction by 360. It is therefore seen that the period -between detection increases in duration as the helicopter moves toward a lower elevation due to increase in spread between the beams at lower elevations.
  • the elevation angle A of FIG. 3 can be determined by the computer 11 of hel-icopter 7 using the timing information from timer 10 to solve the equation sin R Sin F COS A -l-tan C tan A Referring particularly to FIG.
  • Inverted V-shaped beam antenna 6 comprises a motor ⁇ 20 for rotating shaft 21.
  • Slant beam antenna 4 comprises a reector 22 and a slotted aperture feed 23 positioned at the focal point of reiiector 22.
  • vertical antenna 5 mounted on shaft Z1 is shown vertical antenna 5 positioned parallel to surface 1 and rotated 10 with respect to slant antenna 4 about shaft 21.
  • Vertical antenna 5 cornprises a reflector 24 and a slotted aperture feed 25 positioned at the focal point of reflector 24.
  • mounted on motor 20, a dual channel rotary coupler for feeding energy from power divider 3 to each of the antenna feed-s 23 and 25. The phasing of the antenna feeds causes the antenna beam to radiate along la lar-ge or small circle.
  • section of feed 23y comprises -a piece of RG-SZU waveguide having interior dimensionsv .900" by .400".
  • the waveguide feed 23 comprises an aperture ⁇ 67 in length having a plurality of slots 31, numbering 110 overall, each .595" long and .125" wide, and being spaced .607" from each other. The spacing and the number of slots has been determined in order to provide a half power beamwidth of 1.5 in the azirnuth-response plane.
  • the slot spacing is determined from Taylors beamwidth aperture length relationship for a -db sidelobe level, see T. T. Taylor, Design of Line Sources for Narrow Beamwidth and Low Sidelobes, Tech. Memo No. 316, Hughes Aircraft Company, July 31, 1953, ASTIA Document Contract No. AF19(604)-262F8, July 31, 1953 and Design of Line- Source Antennas f or Narrow Beamwidths and Low Sidelobes, IRE Transaction on Antennas and Propagation AP-3(1), pp.
  • the displacement of the slots from the centerline is determined in accordance with the amount of energy to be extracted from the waveguide feed.
  • the displacements are found sucessively, starting w-ith the slot farthest from the input and using monok, Antenna Engineering Handbook, McGraw-Hill, 1961, sections 9-11 through 9-14 for 9375 megacycles. It is to be understood that other spacings would be obtained at different operating frequencies and the said spacing at other operating frequencies could be obtianed by one skilled in the art using the above references.
  • FIGS. 2 and 4 there is shown the curvature of reflector 22 of slant antenna 4.
  • the focus of reiiector 22 is at a point 15.0 along the positive X axis of FIG. 6.
  • the curvature ofr the reflector is represented by the accompanying Table B, showing X and Y coordinates of the curvature. Particularly point 1 along the curvature is seen from the Table B to be +4624 along the X axis and 7.538 along the Y axis. The other points 2-38 are similarly obtained from the accompanying Table B.
  • the design of the curvature of the slant beam reector is based on geometrical optics considerations. The standard technique appears in the literature, S.
  • FIG. 7 there is shown a section of feed 25 of vertical antenna 5 to illustrate the slotted aperture dimensions of the feed directed toward the reector 24.
  • a section 40 of feed comprising a piece of RG-52U waveguide having interior dimensions .900 x .400.
  • the waveguide feed 25 comprises an aperture 60 in length having a plurality of slots 41, numbering 63 overall, each .630 long and .125 wide, and being spaced .950 from each other.
  • the spacing and the number of slots has also been determined for the vertical antenna in order to provide a half power beamwidth of l.5 in the azimuth-response plane.
  • the slot spacing is also determined from Taylors beamwidth aperture length relationship for a -db sidelobe level, sec T. T. Taylor, Design of Line Sources for Narrow Beamwidth and Low Sidelobes, Tech. Memo No. 316, Hughes Aircraft Company, July 31, 1953, ASTIA Document Contract No.
  • Each of the slots 41 are spaced from the centerline 42 of the feed waveguide 40, as shown in the accompanying Table C, beginning with Slot #1 and ending with Slot #63.
  • the displacement of the slots from the centerline is determined considering the amount of energy to be extracted from the waveguide feed. The displacements are found successively, starting with the slot farthest from the input and using ⁇ lasik, Antenna Engineering Handbook, McGraw-Hill, 1961, sections 9-11 through 9-14 for 9375 megacycles. It is to be understood that other spacings would be obtained at different operating frequencies and the said spacing at other operating frequencies could be obtained by one skilled in the art using the above references.
  • Displace- Slot N o. Displace- (Inches) kannt ment (Inches) (Inches) 1 0.007 Left 039 R .085 L .007 Right .041 L .087 R L 044 R .088 L R 046 L .089 R L 048 R .090 L R 050 L .090 R L .053 R .089 L R 055 L .088 R L 057 R .086 L R 060 L 083 R.
  • the curvature of the reector is represented by the accompanying Table D, showing X and Y coordinates of the curvature. Particularly, point 1 along the curvature is seen from Table D to be +4624" along the X axis and 7.538 along the Y axis. The other points 2-40 are similarly obtained from the accompanying Table D.
  • the design of the curvature of the slant beam reector is based on geometrical optics considerations. The standard technique appears in the literature, S. Silver, Microwave Antenna Theory and Design, McGraw-Hill, New York, pp. 497-500, 1949; A. S. Dunbar, Calculations of Doubly Curved Reflectors for Shaped Beams, Proc. IRE, vol.
  • a 3D radar system in block form utilizing an inverted V-shaped beam antenna.
  • a surface complex 50 having a transmitter 51 and a receiver 52 coupled to a duplexer 53 which, in turn, is coupled to slant antenna 54 of inverted V-shaped beam antenna 55.
  • the combination being adapted to transmit a shaped beam along a small circle locus from slant antenna 54 and receive reflections from a target, such as aircraft 56, flying above the surface complex.
  • a second transmitter 57 and a receiver 58 coupled to a duplexer 59 which, in turn, is coupled to vertical antenna 60 of inverted V-shaped beam antenna 55.
  • a computer-display 61 adapted to provide range and azimuth information from reflections received from the vertical antenna which is scanning in the conventional two dimensional radar fashion.
  • inventions of the invention can include electronic beam scanning from a fixed aperture in lieu of mechanica-l rotation of the inverted V-beam ant-enna. Additionally, it is possible toobtain greater accuracies if more than two beams are used so as to provide additional redundant information. For example, three shaped slant beams can be used along with one vertical shaped beam so as t ⁇ provide additional useable information.
  • the present invention provides an antenna system permitting accurate measurement of steeper elevation angles than heretofore in the stat-e of the art and simultaneously provides greater angular response sensitivity due to beam orientation as illustrated in the preferred embodiments. Accordingly, it is desired that this invention not be limited to the particular details of the embodiments disclosed except as defined by the appended claims.
  • An inverted V-'beam antenna system comprising a first shaped beam antenna having a reflector and a feed, said reflector and feed, in combination, providing a first shaped beam oriented along a great circle arc, and a second shaped beam antenna having a reflector and feed, said second reflector and feed, in combination, providing a second shaped beam along a small circle arc such that the .spready between said beams always decreases with increasing height above said antenna system so as to proinverted V-beam.
  • An inverted V-beam antenna system comp-rising a first shaped beam antenna, and a second shaped beam antenna, said rst and second antennas providing shaped beams along small circle arcs such that the spread between said shaped beams always decreases with increasing height above said antenna system so as to produce an inverted V-beam.
  • An inverted V-beam system adapted to scan a portion of a spherical volume of space comprising a first shaped beam antenna, a second shaped beam antenna, and means for simultaneously rotating said first and second antennas, said first antenna providing a vertical beam having its principle radiation directed along a great circle arc intersecting the zenith, said second antenna providing a slant beam having its principle radiation directed along a small circle arc intersecting the zenith of said volume such that the spread between said beams decreases with increasing height above said antenna system.
  • An inverted V-beam antenna system adapted to scan a portion of 4a spherical volume of space comprising means for providing a plurality of shaped beams, and means for electronically scanning at least one of said plurality of beams along a lsmall circle arc intersecting the zenith of said volume such that the spread between said at least one beam and at least one other beam decreases with increasing height above said antenna system.
  • a beacon system comprising a surface complex, said surface complex comprising a transmitter, a power divider coupled to said transmitter, first and second shaped beam antennas, each coupled to said power divider, means for simultaneously rotating said first and second antennas, said lfirst and second 'shaped beam antennas radiating a pair of shaped beams, and including means for directing at least one of said shaped beams along a small circle arc such that the spread between said pair of beams decreases with increasing height above said antennas, and a vehicle means in a spaced relationship to said complex, said vehicle means comprising means for detecting said pair of shaped beams radiated from said first and second antennas.
  • a beacon guidance system adapted to scan a portion of a spherical volume of space for helicopter landing operations comprising a surface ⁇ based complex, said complex comprising a transmitter, ⁇ a first vertical shaped beam antenna coupled to said transmitter, a second slant shaped beam antenna coupled to said transmitter, said first antenna adapted to radiate a first shaped beam oriented along a great circle arc, intersecting the zenith of said volume, said second antenna adapted to radiate a second shaped beam oriented along a small circle arc intersecting the zenith such that the spread between said beams decreases with increasing height above said antennas, an airborne vehicle .adapted for flight in a spaced relationship to lsaid surface based complex, said vehicle comprising means for detecting said first and second shaped radiated beams.
  • a beacon system adapted to scan .a portion of a spherical volume of space comprising means for providing energy for radiation, means for providing a first shaped beam along a great circle intersecting the zenith of ⁇ said volume and being coupled to said means for providing energy for radiation, means for providing a second shaped beam along a small circle intersecting the zenith such that the spaced between said beams decreases with increasing height and being coupled to said means for providing energy for radiation, and vehicle means in a spaced relationship to said means for providing said first and second shaped beams, said vehicle means comprising means for detecting said rst and second beams.
  • a beacon system as claimed in claim 8 including means for scanning said rst and second shaped beams.
  • a system adapted to scan a portion of a spherical volume of space for detecting .a target comprising means for providing energy to be radiated, means for providing a first shaped beam along a great circle intersecting the zenith of said volume and being coupled to said means for providing energy to be radiated, means for providing a second shaped beam along a small circle intersecting the zenith such that the spread between said beams decreases with increasing height and being coupled to said means for providing energy to be radiated, and means for determining range, height and azimuth of said target from said system comprising means yfor detecting rst and second beam target reections.
  • a system adapted to scan a portion of a spherical volume of space for detecting a target comprising means for providing energy to be radiated, means for radiating a plurality of shaped beams coupled to said means for providing energy, and means for orienting at least one of said plurality of shaped beams along a small circle arc intersecting the zenith of said volume such that the spread between said at least one beam and at least one other beam decreases with increasing heights, and means for detecting target retlections from said plurality of radiated beams.
  • a three dimensional radar system adapted to scan a portion of a spherical volume of space for determining range, height and azimuth of a target comprising means for providing energy to be radiated, means for providing .a slant beam along a small circle arc intersecting the zenith and being coupled to said means for providing 40 energy to be radiated, means for providing a vertical beam along a great circle arc intersecting the zenith of said volume such that the spread between said beams decreases with increasing height and being coupled to said means for providing energy to be radiated, and means for receiving shaped beam radiation reections from said target.
  • a radar system adapted to scan a portion of a spherical volume of space comprising means for providing energy to be radiated, means for radiating a plurality of shaped beams, vand means for orienting at least one of said shaped beams along a small circle arc intersecting the zenith of said volume such that the spread between said at least one beam and at least one other beam decreases with increasing height and means for receiving radi-ation reflections from said shaped beams hitting a target.
  • a beacon system adapted to scan a portion of a spherical volume of space ⁇ for helicopter landing operations comprising means for providing energy to be radiated, means for radiating a plurality of shaped beams, and means for orienting at least one of said shaped beams along a small circle larc intersecting the zenith of said volume such that the spread between said .at least one beam and at least one other beam decreases with increasing height, and means for detecting said beams positioned at a spaced relationship with respect to said means for radiating a plurality of shaped beams.

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  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • General Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
US244059A 1962-12-12 1962-12-12 Inverted v-beam antenna system Expired - Lifetime US3242491A (en)

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Application Number Priority Date Filing Date Title
NL301079D NL301079A (enrdf_load_stackoverflow) 1962-12-12
US244059A US3242491A (en) 1962-12-12 1962-12-12 Inverted v-beam antenna system
GB43308/63A GB1024804A (en) 1962-12-12 1963-11-01 Antenna systems
DER36552A DE1246052B (de) 1962-12-12 1963-11-13 Richtantenne fuer die Azimut- und Hoehenbestimmung fliegender Objekte
FR954388A FR1381622A (fr) 1962-12-12 1963-11-20 Système d'antennes

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DE (1) DE1246052B (enrdf_load_stackoverflow)
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GB (1) GB1024804A (enrdf_load_stackoverflow)
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EP0027643A1 (de) * 1979-10-22 1981-04-29 Siemens Aktiengesellschaft Einem mit Radar arbeitenden Ziel nachführbare Störsender-Richtantennenanordnung
US4621267A (en) * 1984-09-28 1986-11-04 The Boeing Company Bearing intersection deghosting by altitude comparison system and methods
US4626861A (en) * 1984-09-28 1986-12-02 The Boeing Company Two angle range and altitude measurement system and methods
US4670758A (en) * 1984-09-28 1987-06-02 The Boeing Company Depression angle ranging system and methods
WO1987006335A1 (en) * 1986-04-18 1987-10-22 Sundstrand Data Control, Inc. Passive radio altimeter
US5359334A (en) * 1993-01-14 1994-10-25 Hazeltine Corporation X-scan aircraft location systems

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DE4438723A1 (de) * 1994-10-29 1996-05-02 Daimler Benz Aerospace Ag Transportable Radaranlage

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EP0027643A1 (de) * 1979-10-22 1981-04-29 Siemens Aktiengesellschaft Einem mit Radar arbeitenden Ziel nachführbare Störsender-Richtantennenanordnung
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Also Published As

Publication number Publication date
DE1246052C2 (enrdf_load_stackoverflow) 1968-02-15
FR1381622A (fr) 1964-12-14
GB1024804A (en) 1966-04-06
NL301079A (enrdf_load_stackoverflow)
DE1246052B (de) 1967-08-03

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