US3245080A - Aircraft radome-anemometer boom having means to destroy any spurious surface wave - Google Patents

Aircraft radome-anemometer boom having means to destroy any spurious surface wave Download PDF

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Publication number
US3245080A
US3245080A US158493A US15849361A US3245080A US 3245080 A US3245080 A US 3245080A US 158493 A US158493 A US 158493A US 15849361 A US15849361 A US 15849361A US 3245080 A US3245080 A US 3245080A
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United States
Prior art keywords
boom
anemometer
radome
spurious
surface wave
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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
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US158493A
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English (en)
Inventor
Beuvain Rene
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Thales SA
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Csf
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Publication date
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Publication of US3245080A publication Critical patent/US3245080A/en
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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/42—Housings not intimately mechanically associated with radiating elements, e.g. radome
    • H01Q1/421—Means for correcting aberrations introduced by a radome
    • 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
    • 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
    • H01Q1/281—Nose antennas
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/42—Housings not intimately mechanically associated with radiating elements, e.g. radome

Definitions

  • the present invention relates to radomes provided with an anemometer boom.
  • radomes i.e. housings of dielectric material adapted to ensure the protection of aerials, and especially of airborne radar aerials, are sometimes equipped with an anemometer boom or tube which extends from the body of the radome, this location being advantageous for protection against disturbances due to shock-waves during high-speed flights.
  • the radiation from the radar antenna may, under certain conditions, give rise to a surface wave along the boom, the latter thus behaving like a substantially directive, secondary radiator.
  • the desired radiation may be considerably affected by interferences from these spurious radiations, particularly when the radar antenna is coaxial with the boom.
  • the transmission losses i.e. the quantity of energy absorbed or reflected by the radome and the refraction errors due to the radome are thus substantially increased in this area.
  • the radiation from the anemometer boorn is modified by depositing a metal coating on a dielectric portion of it so that the interferences with the main radiation do not cause any significant disturbance.
  • FIG. l shows an anemometer boom of dielectric material according to the invention
  • FIGS. 2 and 3 are graphs illustrating the improvements obtained in one embodiment of the invention, in so far as transmission losses and the refraction errors are respectively concerned;
  • FIG. 4 represents an anemometer boom which is made of metal over the greater part of its length but comprises a dielectric portion modified according to the invention.
  • FIGS. 5a and 5b are sketches showing the elements of the device according to the invention functionally related in an aircraft application.
  • the dielectric anemometer boom which is shown in section in FIGS. 1, 5a and 5b is shaped as an elongated truncated cone 5 and is connected to the body, 1 of the radome, also having the shape of a truncated cone. Boom 5 extends from the transversal section 2 to the transversal section 3.
  • FIG. 5 Inside the radome body is placed a rotatable antenna forming a part of the radar system carried by the aircraft shown FIGS. 5a and 5b.
  • This antenna is shown FIG. 5 in cross-section by a plane whose trace on the figure is along x'-x, the dashed and dotted circle representing the inner profile of the radome body in this plane.
  • the boom has a metal coating obtained for example by metallization over a certain length thereof.
  • the spurious radiation instead of occuring over the whole length of the boom with a substantial directivity, is now essentially localized at the ends ofthe metallized area.
  • the radiation is considerably more diluse and two parameters are now available, for reducing the disturbing interference with the desired radia- 3,245,080 Patented Apr. 5, 1966 ICC tion, namely the axial distances a and b from the transversal sections limiting the metallized portion, which is hatched in the drawing, to the free end of the boom.
  • b is taken equal to zero and cannot be shown; both parameters a and b are more clearly shown in FIG. 4.
  • the optimum arrangement depends upon the position of the radar antenna and the diagram of the desired radar radiation and on the shape of the radome body and boom. In practice, the exact area to be metallized is Ito be experimentally determined, the accuracy desired in so far as to the two above parameters are concerned, being of the order of, say, A/ 10, where A is the operating wave length.
  • the metallized area will cover the major portion of the boom outer surface.
  • FIGS. 2 and 3 show graphically the results obtained in one specic case: the aerial includes a paraboloid of a diameter of 50 cm., illuminated by a four-channel source, of the monopulse type, the sum signals of which are subject to transmission losses, and dilference signals of which are subject to transmission losses, and refraction errors.
  • the aerial is protected by a radome of laminated polyester glass.
  • FIG. 3 the refraction errors expressed in minutes are plotted on the ordinates, the same magnitude as in FIG. 2 being plotted on the abscissa.
  • the dotted curve and the solid curve give the Values measured before and after the adjunction of the metal coating according to the invention.
  • the major portion of the anemometer boom i.e. the portion comprised between sections 6 and 3, is of metal, as is the case for boom 5 shown in FIG. 4,. there still exists a dielectric portion 7 comprised between sections 2 and 6, this portion connecting the boom to the radome body 1.
  • the parasitic sources exist at ends 6 and 3 of the metal portions but the position of these sources is generally not the optimum one.
  • part 8 of portion 7 of the boom is covered with a metal coating providing two further radiation sources at respective ends of part 8.
  • the location of the coating is in practice determined experimentally, two parameters, corresponding to the transversal sections limiting the coating, being available.
  • the metal coating may be obtained as well by metallizing the dielectric portion concerned as by mean a metal sheath which surrounds this portion.
  • a radome for protecting a radiation source located therein, said radorne comprising an elongated anemometer boom, whose spurious surface Wave disturbs the forward radiation pattern of said source, said boom comprising at least a dielectric tubular outer portion, and a tubular metallic coating partially covering said dielectric portion, to compensate for the presence of said spurious wave.
  • a radorne for protecting a radiation source located therein, said radorne comprising an elongated dielectric boom, whose spurious surface wave disturbs the forward radiation pattern of said source, said boom having a free end, and a metallic tubular coating covering only partially an outer portion of said boom, said portion extending from said free end, to compensate for the presence of said spurious wave.
  • a radorne for protecting a radiation source located therein, said radome comprising an elongated anemometer boom, whose spurious surface wave disturbs the forward radiation pattern of said source, said boom comprising a metallic tubular outer portion and a dielectric tubular outer portion, and a metallic tubular coating partially covering said dielectric portion, to compensate for the presence of said spurious wave.

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  • 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)
  • Joining Of Glass To Other Materials (AREA)
US158493A 1960-12-15 1961-12-11 Aircraft radome-anemometer boom having means to destroy any spurious surface wave Expired - Lifetime US3245080A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR846972A FR1283884A (fr) 1960-12-15 1960-12-15 Perfectionnements aux radomes à perche

Publications (1)

Publication Number Publication Date
US3245080A true US3245080A (en) 1966-04-05

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Family Applications (1)

Application Number Title Priority Date Filing Date
US158493A Expired - Lifetime US3245080A (en) 1960-12-15 1961-12-11 Aircraft radome-anemometer boom having means to destroy any spurious surface wave

Country Status (5)

Country Link
US (1) US3245080A (fr)
CH (1) CH406329A (fr)
DE (1) DE1190526B (fr)
FR (1) FR1283884A (fr)
GB (1) GB975962A (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3798652A (en) * 1972-09-11 1974-03-19 Gen Electric Pitot tube dielectric antenna system
US4847627A (en) * 1987-09-08 1989-07-11 Lockheed Corporation Compact wave antenna system

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2583540A (en) * 1947-02-11 1952-01-29 Willard H Bennett Means for discharging static electricity from airplane radio antennas
FR1004622A (fr) * 1949-12-21 1952-04-01 Csf Perfectionnements aux appareils à très haute fréquence comportant des parois diélectriques
US2607009A (en) * 1948-10-08 1952-08-12 Philco Corp Electromagnetic wave transmissive structure
US2814800A (en) * 1955-07-19 1957-11-26 Lockheed Aircraft Corp Broadband pitot tube antenna
US2820964A (en) * 1955-01-17 1958-01-21 Bell Telephone Labor Inc Antenna
US2921307A (en) * 1955-12-13 1960-01-12 Risk George Lead through antenna mast body construction
US2929065A (en) * 1957-02-27 1960-03-15 Hughes Aircraft Co Surface wave antenna
US3063654A (en) * 1959-02-03 1962-11-13 Fred R Youngren Radome with boresight error reduction means
US3081051A (en) * 1959-03-05 1963-03-12 Jr Ralph O Robinson Radome structure

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2583540A (en) * 1947-02-11 1952-01-29 Willard H Bennett Means for discharging static electricity from airplane radio antennas
US2607009A (en) * 1948-10-08 1952-08-12 Philco Corp Electromagnetic wave transmissive structure
FR1004622A (fr) * 1949-12-21 1952-04-01 Csf Perfectionnements aux appareils à très haute fréquence comportant des parois diélectriques
US2820964A (en) * 1955-01-17 1958-01-21 Bell Telephone Labor Inc Antenna
US2814800A (en) * 1955-07-19 1957-11-26 Lockheed Aircraft Corp Broadband pitot tube antenna
US2921307A (en) * 1955-12-13 1960-01-12 Risk George Lead through antenna mast body construction
US2929065A (en) * 1957-02-27 1960-03-15 Hughes Aircraft Co Surface wave antenna
US3063654A (en) * 1959-02-03 1962-11-13 Fred R Youngren Radome with boresight error reduction means
US3081051A (en) * 1959-03-05 1963-03-12 Jr Ralph O Robinson Radome structure

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3798652A (en) * 1972-09-11 1974-03-19 Gen Electric Pitot tube dielectric antenna system
US4847627A (en) * 1987-09-08 1989-07-11 Lockheed Corporation Compact wave antenna system

Also Published As

Publication number Publication date
FR1283884A (fr) 1962-02-09
DE1190526B (de) 1965-04-08
CH406329A (fr) 1966-01-31
GB975962A (en) 1964-11-25

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