US2235055A - Antenna system - Google Patents
Antenna system Download PDFInfo
- Publication number
- US2235055A US2235055A US303509A US30350939A US2235055A US 2235055 A US2235055 A US 2235055A US 303509 A US303509 A US 303509A US 30350939 A US30350939 A US 30350939A US 2235055 A US2235055 A US 2235055A
- Authority
- US
- United States
- Prior art keywords
- antenna system
- dipoles
- radiation pattern
- field intensity
- landing
- 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
Links
- 230000005855 radiation Effects 0.000 description 9
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Classifications
-
- 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
Definitions
- the above-mentioned copending application relates to a system for landing aircraft according to the glide path or slip-way principle, in which landing curves of constant field intensity to be followed by a descending airplane are produced by radiating a spatial radiation pattern and causing another radiated wave energy to intersect the spatial radiation pattern at such angle as to 15 establish points of constant field intensity on a locus of an inclined plane.
- the spatial radiation pattern produced for the above-mentioned purpose preferably comprises two regions of higher field intensities and an intermediate re-entrant 0 portion of lower field intensity within which an airplane is guided from the moment at which the landing descent is commenced until the moment at which it touches ground on the landing place.
- the guide beams thus produced fully com- 25 ply with the aeronautic requirements.
- FIG. 1 schematically shows the structure of an antenna system as proposed according to this in- 35 vention
- Fig. 2 embodies a radiation pattern as produced by the antenna system shown in Fig. 1.
- Di and D2 denote two dipoles spaced apart from one another at a distance equal to one operating wavelength. These 5 two dipoles are energized in phase opposition by a transmitter. However, the antenna currents supplied to the dipoles are of different magnitudes, the amplitude ratio being 11 /3, for example. The size and shape of the re-entrant portion of lower field intensity of the resulting radiation pattern shown in Fig. 2 may be varied by adjusting the ratio of the currents supplied to the dipoles DI and D2 in order to comply with the aeronautic requirements of the landing place 15 in question.
- a reflector comprising units RI and R2, respectively, is located behind the dipole Di and D2, respectively, at a distance of one-quarter of an operating wavelength. These reflectors are excited by radiation from the appertaining dipoles and act to intensify the effect of radiation therefrom in the desired direction.
- An antenna system comprising two radiating dipoles spaced apart from one another at a dis- 5 tance equal to one operating wavelength, a reflector behind each of the said dipoles at a distance of one-quarter of an operating wavelength therefrom, and means for energizing the said dipoles by currents of opposite phase and. different 3 magnitude for producing a radiation pattern having two lateral regions of higher field intensity and an intermediate re-entrant portion of lower field intensity.
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- Engineering & Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Description
March M3, WM. R, VON OTTENTHAL.
ANTENNA SYSTEM Filed NOV. 9, 1939 Patented Mar. 18, 1941 UNITED STATES PATENT OFFICE ANTENNA SYSTEM Application November 9, 1939, Serial No. 303,509 In Germany November 9, 1938 1 Claim.
The present application constitutes an improvement relating to the copending application Serial No. 244,440, filed December '7, 1938, in the names of Walter Max Hahnemann and Ernst Kramar for System for landing aircraft assigned to the same assignee.
The above-mentioned copending application relates to a system for landing aircraft according to the glide path or slip-way principle, in which landing curves of constant field intensity to be followed by a descending airplane are produced by radiating a spatial radiation pattern and causing another radiated wave energy to intersect the spatial radiation pattern at such angle as to 15 establish points of constant field intensity on a locus of an inclined plane. The spatial radiation pattern produced for the above-mentioned purpose preferably comprises two regions of higher field intensities and an intermediate re-entrant 0 portion of lower field intensity within which an airplane is guided from the moment at which the landing descent is commenced until the moment at which it touches ground on the landing place. The guide beams thus produced fully com- 25 ply with the aeronautic requirements.
It is the object of this invention to provide an antenna system of simple structure capable of emitting radiation pattern involving the abovementioned proper-ties.
30 My invention will be more readily understood from the following description taken in conjunction with the accompanying drawing, in which Fig. 1 schematically shows the structure of an antenna system as proposed according to this in- 35 vention, while Fig. 2 embodies a radiation pattern as produced by the antenna system shown in Fig. 1.
Referring to Fig. 1, Di and D2 denote two dipoles spaced apart from one another at a distance equal to one operating wavelength. These 5 two dipoles are energized in phase opposition by a transmitter. However, the antenna currents supplied to the dipoles are of different magnitudes, the amplitude ratio being 11 /3, for example. The size and shape of the re-entrant portion of lower field intensity of the resulting radiation pattern shown in Fig. 2 may be varied by adjusting the ratio of the currents supplied to the dipoles DI and D2 in order to comply with the aeronautic requirements of the landing place 15 in question. A reflector comprising units RI and R2, respectively, is located behind the dipole Di and D2, respectively, at a distance of one-quarter of an operating wavelength. These reflectors are excited by radiation from the appertaining dipoles and act to intensify the effect of radiation therefrom in the desired direction.
What is claimed is:
An antenna system comprising two radiating dipoles spaced apart from one another at a dis- 5 tance equal to one operating wavelength, a reflector behind each of the said dipoles at a distance of one-quarter of an operating wavelength therefrom, and means for energizing the said dipoles by currents of opposite phase and. different 3 magnitude for producing a radiation pattern having two lateral regions of higher field intensity and an intermediate re-entrant portion of lower field intensity.
RUDOLF VON OTTENTHAL.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE231658X | 1938-11-09 | ||
| CH228970T | 1939-09-20 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2235055A true US2235055A (en) | 1941-03-18 |
Family
ID=25727287
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US303509A Expired - Lifetime US2235055A (en) | 1938-11-09 | 1939-11-09 | Antenna system |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US2235055A (en) |
| BE (1) | BE436719A (en) |
| CH (1) | CH231658A (en) |
| FR (1) | FR51283E (en) |
| NL (1) | NL53288C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2620471A (en) * | 1945-03-28 | 1952-12-02 | Rca Corp | Radio direction finder |
-
0
- BE BE436719D patent/BE436719A/xx unknown
-
1939
- 1939-09-20 CH CH231658D patent/CH231658A/en unknown
- 1939-09-21 NL NL95295A patent/NL53288C/en active
- 1939-11-09 US US303509A patent/US2235055A/en not_active Expired - Lifetime
-
1940
- 1940-12-27 FR FR51283D patent/FR51283E/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2620471A (en) * | 1945-03-28 | 1952-12-02 | Rca Corp | Radio direction finder |
Also Published As
| Publication number | Publication date |
|---|---|
| BE436719A (en) | |
| CH231658A (en) | 1944-03-31 |
| NL53288C (en) | 1942-10-15 |
| FR51283E (en) | 1942-02-18 |
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