US3544998A - Plasma coated antenna - Google Patents

Plasma coated antenna Download PDF

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Publication number
US3544998A
US3544998A US689151A US3544998DA US3544998A US 3544998 A US3544998 A US 3544998A US 689151 A US689151 A US 689151A US 3544998D A US3544998D A US 3544998DA US 3544998 A US3544998 A US 3544998A
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Prior art keywords
plasma
antenna
sheath
coated
thickness
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Expired - Lifetime
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US689151A
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English (en)
Inventor
Paul E Vandenplas
Andre M Messiaen
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ANDRE M MESSIAEN
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ANDRE M MESSIAEN
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    • 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
    • H01Q19/06—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 refracting or diffracting devices, e.g. lens
    • H01Q19/09—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 refracting or diffracting devices, e.g. lens wherein the primary active element is coated with or embedded in a dielectric or magnetic material

Definitions

  • This invention relates to antennas and more particularly to a novel plasma coated antenna wherein the thickness of the plasma sheath is varied to produce a desired resonant frequency.
  • the present invention provides a novel plasma coated antenna enclosed within a low-pressure housing.
  • a plasma environment exists within the housing that exhibits a sheath located between -the plasma and the outer extremities of the antenna.
  • the antenna may be selectively tuned by varying either the thickness of the sheath or the density of the plasma.
  • Several antennas may -be adapted to cooperate with each other to provide for the detection of operating frequencies of other radiation devices.
  • FIG. 1 is a perspective view of a plasma coated antenna system shown partially sectioned in accordance with the present invention
  • FIG. 2 is a theoretical curve calculated from the parameters exhibited by the plasma coated antenna system of FIG. 1;
  • FIG. 3 is an experimental curve of the results obtained in the study of a plasma coated antenna system shown in FIG. l;
  • FIG. 4 is a functional block diagram of a typical aireraf-t having several plasma coated antennas therein.
  • FIG. 1 there is shown one of the em- Ibodiments of a plasma coated antenna system 10 constructed in accordance with the principles of this invention in which a spherical antenna 11 is enclosed within a discharge tube 12.
  • the spherical antenna 11 comprises two isola-ted hemispheres 11a and 11b, respectively, which may be made of any suitable metallic material.
  • the discharge tube 12 may be a low-pressu-re mercury-discharge tube constructed of any suitable material, such as a ceramic material, for example, glass or liber glass.
  • a plas-ma 13 is contained within the discharge tube 12.
  • a cathode 14 and anode 15 are located in their respective lateral tubes 16 and 17 of the discharge tube 12.
  • the lateral tubes 16 and 17 may be covered by two high frequency absorbers 18 and 19, respectively, in order to minimize spurious effects.
  • the cathode 14 and the anode 15 are connected to a source 26, via lines 26a and 2611, which may be utilized to control the density of the plasma 13.
  • the density of the plasma 13 may be Varied by adjusting the cur-rent of the discharge Where the density of the plasma 13 is approximately proportional to the current density. .When the density of the plasma 13 is changed, the frequency at which the antenna 20 will resonate will change. Thus, the antenna 11 may be tuned by varying the density ofthe plasma 13.
  • a bias source 20 which may be a typical DC source, is shown connected to the two hemispheres 11a and 11b by the lines 20a and 20b, respectively.
  • the bi-as source 20 may be utilized to vary the voltage potential of the antenna 20 and consequently the lradial thickness of the sheath 23.
  • the plasma sheath 23 While the plasma 13 has an electron-plasma density, ne, the plasma sheath 23 has an electron-plasma density nearly equal to zero (178:0).
  • the plasma sheath 23 can be physically observed as less luminous than the plasma 13.
  • the plasma sheath 23 is shown as having a thickness (b-a), Where (a) is the radius of the antenna 11 and (b) is the distance from the center of the antenna 11 to the outer limits of the plasma sheath 23.
  • the distances from the center of the antenna 11 to the inner rim and outer rim of the discharge tube 12 are shown as (c) and (d), respectively.
  • the plasma 13 When operated in the condition useful to this invention, the plasma 13 has an inductive reactance as opposed to the capacitive reactance of the plasma sheath 23 and the area exterior to the discharge tube 12. There is a resonance phenomenon between the plasma 13 and the area exterior to the discharge tube 12 and a corresponding resonance phenomenon between the plasma 13 and the plasma sheath 23.
  • the resonance phenomenon which results from the interaction of the plasma and the area exterior to the discharge tube is insensitive to the thickness of the plasma sheath 23.
  • the resonance phenomenon experienced between the plasma 13 and the plasma sheath 23 is strongly influenced by the thickness of the plasma sheath 23.
  • the thickness of the plasma sheath 23 is determined by the direct voltage applied to the antenna from the bias source 20.
  • the antenna 11 may be tuned.
  • the antenna 20 may be selectively tuned by either changing the thickness of the plasma sheath 23 or by varying the density of the plasma 13.
  • the antenna 20 ⁇ may be rapidly tuned by the two aforementioned operations.
  • An ultra-high frequency generator 28 may be utilized to excite the antenna 11.
  • a coaxial cable 21 is shown connecting the ultra-high frequency generator 28 to the antenna 11.
  • a typical Balsun 22 may be placed around the coaxial cable 21 to match the generator 28 to the antenna 11.
  • the plasma is assumed uniform and collision-free and described in the cold-plasma limit by its equivalent permittivity epgeoU-weZ/), where w is the H.F. angular frequency and we the electron-plasma frequency.
  • the plasma sheath or we has a vacuum permittivity eo.
  • the Helmholtz equation may be solved in the different media, that is the plasma sheath 23, the plasma 13, the wall of the discharge tube 12, and the outer vacuum.
  • the distance (b-a) is the thickness of the plasma sheath 23.
  • the distance (c-b) is the thickness of the plasma 13
  • the distance (dc) is the thickness of the wall of the discharge tube 12.
  • the radiated field exhibited was 20 ⁇ times stronger than the field in the absence of plasma; therefore, the radiated power was 400 times greater than without plasma.
  • This radiation factor results from the fact that the reactance is practically zero and the impedance is thus resistive (in this particular experiment the radiation resistance was very small and was approximately equal to 0.39).
  • the A experimentally observed radiated power was limited by the internal impedance of the generator.
  • FIG. 4 there is shown a typical aircraft 40, including plasma coated antennas 41 through 44. While it is understood that the plasma coated antennas 41 through 44 could be placed in numerous locations throughout the aircraft 40, the antennas 41 through 44 are shown in their respective locations for sake of clarity.
  • the plasma coated antennas 41 and 42 may be utilized for transmitting information to and receiving information from targets located forward of the aircraft 40, while the plasma coated antennas 43 and 44 may be utilized for transmitting information to and receiving information from targets off to the side of the aircraft 40.
  • the plasma coated antennas 41 through 44 are shown in their different configurations from the plasma coated antenna 11 of FIG. 1. It should be understood that the antennas 41 through 44 are constructed to adapt themselves to the aircraft 40. Furthermore, while the first ernbodiment was described with particular reference to antennas having a spherical configuration, it should be understood that the practice of this invention is not necessarily limited thereto, but may be practiced to equal advanage utilizing other configurations, such as, rectangular configurations. It can be appreciated that the plasma coated antenna system 10 was shown in a spherical configuration in order that the mathematical equations would be of the type that would faciliate solving.
  • the anennas 41 and 42, and 43 and 44, respectively, may be utilized to provide the detection of the operating frequency of targets, for example, jamming and counterjamming systems.
  • targets for example, jamming and counterjamming systems.
  • One of the capabilities of a plasma coated antenna, as described earlier in this invention is the ability to rapidly tune the antenna. This capability is very significant when one is involved with jamming and counter-jamming techniques,
  • FIG. 4 shows a typical aircraft 40, it should be understood that the practice of this invention is not necessarily limited thereto, but may be practiced t equal advantage utilizing other air vehicles, such as, spacecraft.
  • a spacecraft may utilize the plasma coated antenna of the type shown in either FIG. l or FIG. 4 for transmitting and receiving purposes.
  • a plasma coated antenna may be utilized in a spacecraft to overcome problems encountered during re-entry into the earths atmosphere, for example, problems of radio blackout.
  • An antenna system comprising:
  • second means surrounding said first means for providing a low pressure housing, said second means having a plasma condition provided therein adapted to exhibit an expandable plasma sheath adjacent to the outer edge of said iirst means;
  • third means including a iirst source adapted to change the bias voltage applied to said first means and a second source adapted to control the discharge current of said second means.
  • An antenna system as recited in claim 3 wherein said antenna comprises two members located in proximity to each other.
  • said third means comprises a bias voltage source adapted to vary the thickness of said plasma sheath and a voltage source with an anode and cathode located within said second means for changing the density of said plasma.
  • An antenna system proviling detection capabilities operating in an aircraft, comprising:
  • iirst means respectively housing each said pair of plasma coated antennas, said first means having plasma conditions provided therein attached to exhibit expandable plasma sheaths respectively adjacent to the outer edges of said plasma coated antennas;

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  • Plasma Technology (AREA)
US689151A 1966-12-19 1967-12-08 Plasma coated antenna Expired - Lifetime US3544998A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE691389 1966-12-19

Publications (1)

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US3544998A true US3544998A (en) 1970-12-01

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Application Number Title Priority Date Filing Date
US689151A Expired - Lifetime US3544998A (en) 1966-12-19 1967-12-08 Plasma coated antenna

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US (1) US3544998A (ko)
BE (1) BE691389A (ko)
DE (1) DE1591805A1 (ko)
GB (1) GB1179918A (ko)
NL (1) NL6717290A (ko)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3766562A (en) * 1972-06-21 1973-10-16 Us Army Control of electron density enveloping hypersonic vehicles
US4116405A (en) * 1977-03-28 1978-09-26 Grumman Aerospace Corporation Airplane
US5043739A (en) * 1990-01-30 1991-08-27 The United States Of America As Represented By The United States Department Of Energy High frequency rectenna
US20110025565A1 (en) * 2009-08-03 2011-02-03 Anderson Theodore R Plasma devices for steering and focusing antenna beams
US20140333485A1 (en) * 2013-05-13 2014-11-13 Smartsky Networks, Llc Plasma aviation antenna

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2525624A (en) * 1946-03-13 1950-10-10 William F Stahl Glow lamp combination
US2615126A (en) * 1948-12-03 1952-10-21 Paul A Kennebeck Narrow beam receiving antenna
US2641702A (en) * 1948-10-22 1953-06-09 Int Standard Electric Corp Control of wave length in wave guide and coaxial lines
US2703363A (en) * 1951-01-23 1955-03-01 Robert H Rines Radiation modulating system
US2968037A (en) * 1957-04-08 1961-01-10 Thomas F Thompson High frequency receiving antenna
US3080523A (en) * 1958-04-07 1963-03-05 Westinghouse Electric Corp Electronically-controlled-scanning directional antenna apparatus utilizing velocity modulation of a traveling wave tube

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2525624A (en) * 1946-03-13 1950-10-10 William F Stahl Glow lamp combination
US2641702A (en) * 1948-10-22 1953-06-09 Int Standard Electric Corp Control of wave length in wave guide and coaxial lines
US2615126A (en) * 1948-12-03 1952-10-21 Paul A Kennebeck Narrow beam receiving antenna
US2703363A (en) * 1951-01-23 1955-03-01 Robert H Rines Radiation modulating system
US2968037A (en) * 1957-04-08 1961-01-10 Thomas F Thompson High frequency receiving antenna
US3080523A (en) * 1958-04-07 1963-03-05 Westinghouse Electric Corp Electronically-controlled-scanning directional antenna apparatus utilizing velocity modulation of a traveling wave tube

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3766562A (en) * 1972-06-21 1973-10-16 Us Army Control of electron density enveloping hypersonic vehicles
US4116405A (en) * 1977-03-28 1978-09-26 Grumman Aerospace Corporation Airplane
US5043739A (en) * 1990-01-30 1991-08-27 The United States Of America As Represented By The United States Department Of Energy High frequency rectenna
US20110025565A1 (en) * 2009-08-03 2011-02-03 Anderson Theodore R Plasma devices for steering and focusing antenna beams
US8384602B2 (en) * 2009-08-03 2013-02-26 Theodore R. Anderson Plasma devices for steering and focusing antenna beams
US20140333485A1 (en) * 2013-05-13 2014-11-13 Smartsky Networks, Llc Plasma aviation antenna
WO2014186180A2 (en) 2013-05-13 2014-11-20 Smartsky Networks LLC Plasma aviation antenna
US8922436B2 (en) * 2013-05-13 2014-12-30 Smartsky Networks LLC Plasma aviation antenna
WO2014186180A3 (en) * 2013-05-13 2015-05-07 Smartsky Networks LLC Plasma aviation antenna
US9444132B2 (en) 2013-05-13 2016-09-13 Smartsky Networks LLC Plasma aviation antenna
EP2997625A4 (en) * 2013-05-13 2017-01-18 Smartsky Networks LLC Plasma aviation antenna
US10276930B2 (en) 2013-05-13 2019-04-30 Smartsky Networks LLC Plasma aviation antenna

Also Published As

Publication number Publication date
NL6717290A (ko) 1968-06-20
DE1591805A1 (de) 1971-03-04
BE691389A (ko) 1967-06-19
GB1179918A (en) 1970-02-04

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