RU2429499C2 - Glide-path beacon (versions) - Google Patents

Abstract

FIELD: radio engineering.

SUBSTANCE: versions of glide-path beacon (GPB) are intended to provide instrument aircraft approach to aerodromes with high-level snow cover and terrain compartments in aircraft approach zone, which cause interference of radio waves in glide path zone, without snow removal or compaction in front of GPB. At that, it is not required to retune GPB during transition from summer to winter season and vice versa. GPB includes antenna array of N radiating elements of summary channel and antenna array of 2N radiating elements of difference channel (N lower and N upper ones), which are located symmetrically relative to radiating elements of summary channel at distance ±d,

where λ - wave length; θ_GL - specified glide path angle, and amplitudes of currents in radiators of summary channel have been chosen from condition of attenuation of radiation of radio waves towards terrain compartments.

EFFECT: improving stability of angle of glide path and steepness of zone of glide-path beacon at change of height of underlying surface or during the change of properties of underlying surface.

3 cl, 13 dwg

Description

FIELD OF THE INVENTION

The invention relates to radio engineering and can be used in instrumentation support systems for aircraft to land. Glide path beacons (GRM) of the meter and decimeter wave ranges included in the aforementioned systems form a glide path zone designed to control the aircraft in a vertical plane. The glide path beacon in accordance with the present invention allows instrumental approach of aircraft to land at aerodromes with a high level of snow cover and folds of terrain, causing interference of radio waves in the area of the glide path.

State of the art

Instrument landing systems (ILS) were developed before and after 1946, when ILS was adopted as an international standard and could be categorized in one of three groups: with a reference zero, a side-band system, or a system with type M lattice

The simplest of these systems is a reference zero system. It includes two antennas, the lower antenna being located at a height two times smaller than the height of the upper antenna. The lower antenna emits a so-called reference signal, modulated equally by 90 and 150 Hz tones with phase synchronization (also called a sum signal or a carrier signal). The lower antenna forms a petal radiation pattern in the vertical plane with the first maximum above the Earth at an angle of 3 ° and the first zero at an angle of 6 °. The upper antenna emits only a sideband signal of 90 and 150 Hz (called a side-frequency signal or a difference signal) and forms a lobe pattern with the first maximum at an angle of 1.5 ° and the first zero at an angle of 3 °. This first zero of the sideband signal at an angle of 3 ° sets the glide path angle. The width of the glide path zone is formed in the vicinity of zero in the radiation pattern. The signals are phased so that the sideband signal emitted by the upper antenna and the reference signal emitted by the lower antenna are summed below zero and give predominantly side signals of 150 Hz (150> 90) and above zero they give predominantly side signals of 90 Hz (90> 150) . Thus, the radio path, called the glide path, is formed in the area of the high-intensity signal, and the receiver simply divides and compares the sound tones.

A system with a zero zone usually requires an even plane in front of the timing belt with a length of 800 m for a glide path angle of 3 °, and since the level in the directional pattern of the side strip grows from 0 ° almost linearly, the system is very sensitive to reflections of radio waves from Earth's irregularities.

Glide paths are rarely ideal, antennas often have to work when there is a short area in front of the timing or if there are folds of terrain in the aircraft landing area. Any of these adverse conditions can greatly degrade the performance of the system with a zero zone, and in order to solve these problems with the site, a timing belt with a ratio of side frequencies and a timing belt with type M grating has been proposed.

Since 1960, a glide path antenna with a side-frequency ratio has been widely used abroad. It also has two antennas. The upper antenna is excited by the side frequency signal, and the lower one by the side frequency signal and the carrier signal. The side signal in the lower antenna is 180 ° offset from the side signal in the upper antenna. This system is also sensitive to reflections of radio waves from obstacles in front of the antenna, but requires only 700 m of a flat platform for a glide path with an angle of 3 °.

An M-type timing belt has a three-element antenna array in which the upper, lower, and middle elements are excited by sideband signals, and the middle and lower elements are also excited by carrier frequencies. The side frequency signals for driving the upper and lower elements have an amplitude and phase of 1/0 °, and the side frequency signal in the middle element has an amplitude and phase of 2/180 °. The excitation signals of the carrier of the middle element have an amplitude and phase of 1/0 °, and the carrier signal in the lower element is 2/180 °.

Each of the above radiating element may consist of a separate dipole located in the corner reflector to obtain the desired directivity. However, such a radiating element may consist of a lattice of radiating elements (for example, a director antenna) to obtain desired directivity characteristics.

Known for the first timing of the decimeter wave range with a reference zero [G.A. Pakholkov, V. V. Kashinov and others. "Goniometric radio engineering landing systems." - M .: Transport. - 1982.], comprising a device for generating a signal of the total channel, a device for generating signals of the differential channel, the first and second antennas spaced vertically, the lower antenna being fed by the signals of the total channel, and the upper antenna being fed by the signals of the differential channel. The signal of the total channel refers to the signal generated by the modulation of high-frequency oscillations by vibrations with frequencies of Ω ₁ and Ω ₂ that are identical in amplitude, while the vibrations of Ω ₁ and Ω _{2 are in} phase with each other. Difference channel signals are understood to mean side-frequency signals generated by modulating high-frequency oscillations by vibrations with frequencies of frequencies ₁ and ₂ equal in amplitude, while high-frequency oscillations have a phase shift of 180 °. In meter-range landing systems, the carrier frequency is included in the signal spectrum of the total channel. The information parameter in the landing systems of the meter wavelength range is the difference in the modulation depths (RGM) of the emitted signal by oscillations with frequencies of Ω ₁ and Ω ₂ , and in the systems of the decimeter wave range of waveforms the so-called signal audibility coefficient (Raman) with modulation frequencies of Ω ₁ and Ω ₂ . Timing with a reference zero is the simplest type of timing, it is widely used at aerodromes of civil and military aircraft.

However, timing with a reference zero has a number of disadvantages:

- in a timing case with a reference zero, the glide path angle is set by the height of the suspension of the upper antenna relative to the underlying surface. With a change in the level of the underlying surface, as well as with a change in its electrical characteristics, for example, with a change in the height of the snow cover, with a change in the humidity of the snow, with grass growth, the glide path angle changes, the steepness of the glide path zone changes [Vaksenburg S. I., Voitovich N. I. . et al. Influence of snow cover on the characteristics of a glide path beacon. // Questions of radio electronics. The series is general technical. - 1972, issue 14, pp. 76-90 //];

- if outside the planned site in front of the timing (in the aircraft approach zone) there are areas with an upward slope, then due to the reflection of the radio waves emitted by the timing antennas, these sections of the glide path are “distorted”; at aerodromes in gully-ravine terrain, in hilly and foothill terrain, timing with a reference zero, as a rule, does not provide the required characteristics;

- the antenna gain is small. At airfields with forests located near the end of the runway, the range of the timing decreases.

The second timing is known (1545035 [Application No. 44640/77] UNIVERSITY OF SYDNEY Instrument landing system glidepath antenna array and drive therefor [Australia No. 8121/76, filed 12 Nov. 1976] H4D H1Q Int Cl ³ G018 1/18) containing the device the formation of the signals of the total channel, the device for generating the signals of the differential channel, the first and second, third and fourth antennas spaced vertically at equal distances from each other, and (when counting from the bottom up) the second and fourth antennas are powered by the signals of the differential channel, and the first and third antennas are powered by signals of the total channel. Due to the out-of-phase feeding of the second and fourth antennas, the level of irradiation of the folds of the terrain in the zone of aircraft approach to landing is reduced, as a result of which the amount of curvature of the glide path decreases.

However, the second known timing has disadvantages:

- the angle and steepness of the glide path zone change with a change in the level of the underlying surface and with a change in the reflective properties of the underlying surface due to exposure to meteorological factors,

- at aerodromes in hilly and foothill areas, due to a decrease in the level of radiation of waves at angles below the glide path, the range of the beacon decreases.

There are other technical solutions designed to ensure the operation of timing at airfields with a varying level of snow cover, presented in the USSR copyright certificates for inventions and the RF patent for an invention:

A.S. No. 711845. - 2591230. Priority 03.20.78. Zaregistr. 09/28/79;

A.S. No. 1396781. - 4125531. Priority 09/30/86. Zaregistr. 01/15/88;

A.S. No. 1426260. - 4125479. Priority 09/30/86. Zaregistr. 05/22/88;

A.S. No. 275692. - 3163500. Priority 11.02.87. Zaregistr. 06/01/88;

A.S. No. 287782. - 3195405. Priority 03/31/88. 3 register. 01/02/89;

A.S. No. 1623443. - 4619435 / 24-09. Priority 12.13.88. Zaregistr. 09/22/90;

A.S. No. 1626884. - No. 4619434/09. Priority 12.13.88. Zaregistr. 10/08/90;

A.S. No. 1690468. - 4619436/09. Priority 12.13.88. Zaregistr. 07/08/91;

A.S. No. 1690469. - 4619436/09. Priority 12.13.88. 3 register. 07/08/91;

A.S. No. 1695758. - 4731827/09. Priority 08.22.89. Zaregistr. 08/01/91;

A.S. No. 1715060. - 4673557/09. Priority 04.04.89. Zaregistr. 10/22/91;

A.S. No. 1730923. - 4731828/09. Priority 08.22.89. Zaregistr. 01/03/92;

A.S. No. 1734471. - 4673558/09. Priority 04.04.89. Zaregistr. 1/15/92;

A.S. No. 1752075. - 4756469/22. Priority 11/01/89. 3 register. 11/26/92;

A.S. No. 1785350. - 4755385/22. Priority 11/01/89. Zaregistr. 09/01/92;

A.S. No. 1802602. - 4873721/09. Priority 11.10.90. Zaregistr. 10/9/92;

A.S. No. 1822264. - 4870495/09. Priority 1.10.90. Zaregistr. 10/12/92;

A.S. No. 1822265. - 4887243/09. Priority 11.28.90. Zaregistr. 10/12/92;

A.S. No. 1828278. - 4809235/09. Priority 02.04.90. Zaregistr. 10/12/92; RF patent №21222216. - 94032782. Priority 09/08/94. Zaregistr. 11/20/98.

Their common drawback is the low level of emitted signals at the lower boundary of the timing zone. Earlier, the lower boundary of the timing zone passed at an angle of 0.45 θ _hl . In accordance with current standards, the lower boundary of the timing zone passes at an angle of 0.3 θ _gl . New standards regarding timing parameters require new technical solutions.

Known timing, presented in the patent: Alfred R. Lopez Non-imaging glideslope antenna systems (US No. 5546095, Aug. 13, 1996).

The disadvantage of timing in the aforementioned patent is the reduction of the level of emitted signals in the area of the timing zone.

Disclosure of invention

The aim of the present invention is to increase the stability of the glide path angle and the steepness of the glide path beacon zone when the height of the underlying surface changes due to snow or grass growth or when the reflective properties of the underlying surface change due to the influence of meteorological factors while providing a given timing zone.

, λ - длина волны; θ_гл - заданный угол глиссады, Н₀ - высота подвеса первого нижнего излучающего элемента антенной решетки разностного канала Δн₁ относительно поверхности Земли, примерно равная 1÷2 м для радиомаяков дециметрового диапазона волн, 1÷4 м для радиомаяков метрового диапазона волн. Нижние Δн_n и верхние Δв_n излучающие элементы разностного канала с номером n расположены симметрично относительно излучающего элемента ∑_n антенной решетки суммарного канала на расстоянии ±d относительно упомянутого элемента. При этом устройство формирования сигналов суммарного канала соединено с входом первого делителя мощности на N направлений, выходы которого последовательно соединены с имеющими такие же порядковые номера фазовращателями суммарного канала и излучающими элементами ∑_n упомянутой антенной решетки; устройство формирования сигналов разностного канала соединено с входом второго делителя мощности на N направлений, выходы которого соединены последовательно с фазовращателями разностного канала и входами совпадающих по номерам делителей мощности на два направления с одним входом и первым и вторым выходами; первый выход каждого упомянутого делителя мощности соединен с соответствующим по номеру нижним излучающим элементом, а каждый второй выход соединен с соответствующим по номеру верхним излучающим элементом. Каждая тройка излучающих элементов запитана синфазными токами, причем амплитуды токов в излучающих элементах разностного канала Δн_n и Δв_n равны друг другу, амплитуды токов в излучающих элементах разностного канала пропорциональны токам в излучающих элементах суммарного канала с некоторым коэффициентом, одинаковым для всех троек излучателей. Амплитуды токов в излучателях суммарного канала выбираются из условия обеспечения зоны глиссады и ослабления излучения радиоволн в направлении складок рельефа местности в зоне захода самолетов на посадку.This goal is achieved in that the glide path beacon containing a device for generating signals of the total channel, a device for generating the differential channel, the antenna array of the radiating elements of the total channel, the antenna array of the radiating elements of the differential channel, further comprises a first power divider with one input and N outputs, a second power divider with one input and N outputs, where N is an integer greater than or equal to 2, N power dividers in two directions with one input and two outputs each, N phase holders of the total channel, N phase shifters of the difference channel, the antenna array of the total channel containing N radiating elements ∑ _n , and the antenna array of the differential channel containing N lower Δн _n and N upper Δв _n radiating elements. Each radiating element of the total channel ∑ _{n is} associated with one upper Δв _n and one lower Δн _n radiating element of the antenna array of the difference channel with the formation of an ordered family of triples of radiating elements (∑ _n , Δв _n , Δн _n ); in each triple, the lower and upper radiating elements of the antenna array of the difference channel have the same serial number n as the number of the radiating element of the antenna array of the total channel. The radiating elements of the antenna array of the total channel are arranged sequentially one above the other at heights H _n in the order of increasing the number of the antenna n from 1 to N, and the height H _{1 of the} first radiating element is equal to: H ₁ = d + H ₀ , where

, λ is the wavelength; θ _hl is the given glide path angle, Н ₀ is the suspension height of the first lower radiating element of the antenna array of the difference channel Δн ₁ relative to the Earth’s surface, approximately equal to 1 ÷ 2 m for decimeter wave beacons, 1 ÷ 4 m for meter beacons. The lower Δн _n and upper Δв _n radiating elements of the difference channel with number n are located symmetrically relative to the radiating element ∑ _{n of the} antenna array of the total channel at a distance of ± d relative to the said element. The signal conditioning device of the total channel is connected to the input of the first power splitter in N directions, the outputs of which are connected in series with the phase shifters of the total channel having the same serial numbers and radiating elements ∑ _{n of the} aforementioned antenna array; a differential channel signal generating device is connected to the input of the second power divider in N directions, the outputs of which are connected in series with phase shifters of the difference channel and the inputs of two-direction power dividers with one input and the first and second outputs; the first output of each said power divider is connected to the corresponding lower radiating element, and each second output is connected to the corresponding upper radiating element. Each triple of radiating elements is powered by common-mode currents, and the amplitudes of the currents in the radiating elements of the difference channel Δн _n and Δв _n are equal to each other, the amplitudes of the currents in the radiating elements of the difference channel are proportional to the currents in the radiating elements of the total channel with a certain coefficient that is the same for all triples of radiators. The amplitudes of the currents in the emitters of the total channel are selected from the conditions for providing the glide path zone and attenuating the emission of radio waves in the direction of the folds of the terrain in the zone of aircraft landing.

Introduction to the timing system additionally the first power divider with one input and N outputs, the second power divider with one input and N outputs (where N is an integer greater than or equal to 2), N power dividers in two directions with one input and two outputs each , N phase shifters of the total channel, N phase shifters of the differential channel, and the use of N radiating elements ∑ _n in the antenna array of the total channel, and N lower Δн _n and N upper Δв _n radiating elements in the difference channel array and their placement and excitation, as follows, pos It made it possible to create a timing device that, by combining the phase center of the antenna array of the radiating elements of the total channel and the phase center of the antenna array of the radiating elements of the difference channel, forms a glide path zone, independent of the level and properties of the underlying surface, with a reduced amount of glide path curvature due to a decrease in the level of irradiation of terrain in the aircraft landing zone. These timing advantages are achieved due to the fact that each radiating element of the total channel ∑ _{n is} associated with one upper Δв _n and one lower Δн _n element of the difference channel with the formation of an ordered family of triples of radiating elements (∑ _n , Δв _n , Δн _n ). The radiating elements of the antenna array of the total channel are arranged sequentially one above the other at heights H _n in order of increasing number of the antenna n from 1 to N, and the height H _{1 of the} radiating element is

H ₁ = d + H ₀ ,

,Where

,

λ is the wavelength; θ _hl is the given glide path angle, Н ₀ is the suspension height of the first radiating element Δн ₁ , relative to the Earth’s surface, approximately equal to 1-2 m, the lower Δн _n and upper Δв _n radiating elements of the difference channel with number n are located symmetrically relative to the radiating element ∑ _n total channel in the region ± d with respect to said member, wherein the amplitudes of the currents in the radiating elements of the difference channel? H _n and Δv _n equal to each other, amplitude of the currents in the radiating elements of the difference channel are proportional to currents in the radiating element sum signal with some coefficient is the same for all triples emitter currents to the emitter of the amplitude sum signal are selected from the conditions of maintenance glide zone and attenuation of radio waves in the radiation level in the direction of the folds of the terrain in aircraft approach area.

In another embodiment, the glide path radio beacon comprising a sum channel signal generating device, a differential channel signal generating device, an equidistant antenna array further comprises a first power divider with one input and N outputs, a second power divider with one input and N outputs, where N is an integer greater than or equal to three, N power dividers in two directions with one input and two outputs each, N phase shifters of the total channel, N difference channel phase shifters, N sum signal adders the difference and channels with the first and second inputs and one output each, N-2 adders of signals of the difference channel with two inputs and one output each, the equidistant antenna array consists of N internal radiating elements, an external lower radiating element, an external upper radiating element, and the internal elements ∑ _{n of the} antenna array are excited by the signals of the total channel, the internal and external lower and external upper radiating elements are excited by the signals of the difference channel; each radiating element ∑ _{n is} associated with one upper Δв _n and one lower Δн _n radiating element with the formation of an ordered family of N triples of radiating elements (∑ _n , Δв _n , Δн _n ), in which each triple has lower and upper radiating elements excited by differential signals channel, have the same number n as the number of the radiating element ∑ _n , excited by the signals of the total channel; the radiating elements ∑ _n are arranged sequentially one above the other at heights H _n in increasing order of the number n of the radiating element from 1 to N, and the height H _{1 of the} first radiating element ∑ ₁ is equal to:

H ₁ = d + H ₀ ,

,Where:

,

d is the period of the antenna array, λ is the wavelength; θ _hl is the given glide path angle, H ₀ is the suspension height of the lower external radiating element of the antenna array relative to the Earth's surface, approximately equal to 1 m; lower Δн _n and upper Δв _n radiating elements with number n, excited by the signals of the difference channel, are located symmetrically with respect to the nth radiating element ∑ _n at a distance d relative to the said element; the output of the nth adder of the signals of the sum and difference channels is connected to the nth internal radiating element ∑n, the device for generating the signals of the sum channel is connected to the input of the first power divider in N directions, the outputs of which are connected in series with the phase shifters of the sum channel and the first inputs of the adders signals of the total and differential channels; a differential channel signal generating device is connected to the input of the second power divider in N directions, the outputs of which are connected in series with the phase shifters of the difference channel and the inputs of two-directional power dividers; the first output of the first power divider in two directions is connected to the external lower radiating element Δn _{1 of the} antenna array, and the second output is connected in series with the first input of the first adder of the difference channel signals, the second input of the second adder of the signals of the total and difference channels; the first output of the second power divider in two directions is connected in series with the second input of the first adder of the signals of the total and differential channels, and the second output of the said divider is connected in series with the first input of the second adder of the signals of the differential channel, the second input of the third adder of signals of the total and difference channels; the first output of the third and subsequent power dividers in two directions is connected in series with the second input of the adder of the signals of the differential channel, whose number is two units less than the number of the said power divider, with the second input of the adder of the signals of the total and difference channels with a number one less than the number of the aforementioned power divider in two directions, and the second output of the said power dividers in two directions is connected in series with the first input of the adder signals of the differential channel with a number equal to the number of the said power divider in two directions, with the second input of the adder signals of the total and difference channels with a number one unit greater than the number of the said power divider; the first output of the N-1 power divider in two directions is connected in series with the second input N-3 of the adder of the signals of the difference channel, with the second input N-2 of the adder of the signals of the total and difference channels, and the second output is connected with the second input of the N-adder of the signals of the total and differential channels; the first output of the N-th power divider in two directions is connected in series with the second input N-2 of the adder of signals of the difference channel, with the second input N-1 of the adder of signals of the total and difference channels, and the second output is connected with the external upper radiating element of the antenna array Δв _N : each triple of radiating elements (∑ _n , Δв _n , Δн _n ) is powered by common-mode currents, and the amplitudes of the currents in the radiating elements Δн _n and Δв _n are equal to each other, the amplitudes of the currents in the radiating elements Δn _n and Δв _{n are} proportional to the amplitudes of the currents in the radiating their elements ∑ _n ; the amplitudes of the currents in the elements emitting the signals of the total channel are selected from the condition of attenuation of radio waves in the direction of the folds of the terrain in the zone of aircraft approach.

The use in another version of the glide path beacon additionally N adders of signals of the total and difference channels with two inputs and one output each, N-2 adders of signals of the difference channel with two inputs and one output each allowed to reduce the total number of radiating elements in the antenna array. The proposed technical solution provides, by combining the phase center of the antenna array of the radiating elements of the total channel and the phase center of the antenna array of the radiating elements of the difference channel, the formation of a glide path zone, independent of the level and properties of the underlying surface, with a reduced amount of curvature of the glide path due to a decrease in the level of irradiation of terrain in aircraft landing area.

In another embodiment, a glide path radio beacon comprising a sum channel signal generating device, a differential channel signal generating device, a four-element equidistant antenna array of radiating elements, an external lower radiating element, an external upper radiating element, further comprises a first power divider with one input and two outputs, a second divider power with one input and two outputs, two power dividers in two directions with one input and two outputs each, two phases raschatelya total channels, two phase shifter difference channel, two adders signals sum and difference channels to first and second inputs and one output each, equidistant antenna array consists of two internal radiating elements, outer lower izluchayuschnego element external of the upper radiating element, wherein the internal elements Σ _{n, n} = 1, 2, the antenna array are excited by the total channel signals, inner and outer lower and outer upper radiating elements are excited difference channel signals ; each radiating element ∑ _{n is} associated with one upper Δв _n and one lower Δн _n radiating element with the formation of an ordered family of two triples of radiating elements (∑ _n , Δв _n , Δн _n ), in which each triple has lower and upper radiating elements excited by differential signals channel, have the same number n as the number of the radiating element ∑ _n , excited by the signals of the total channel; the radiating elements ∑ _n are located one above the other at heights H _n , and the height H _{1 of the} first radiating element ∑ ₁ is equal to:

H ₁ = d + H ₀ ,

,Where:

,

d is the period of the antenna array, λ is the wavelength; θ _hl is the given glide path angle, H ₀ is the suspension height of the lower external radiating element of the antenna array relative to the Earth's surface, approximately equal to 1 m; lower Δн _n and upper Δв _n radiating elements with number n, excited by the signals of the difference channel, are located symmetrically with respect to the nth radiating element ∑ _n at a distance d relative to the said element; the output of the nth adder of the signals of the total and difference channels is connected to the nth internal radiating element ∑ _n , the device for generating the signals of the total channel is connected to the input of the first power divider in two directions, the outputs of which are connected in series with the phase shifters of the total channel and the first inputs of the adders signals of the total and differential channels; a differential channel signal generating device is connected to the input of the second power divider in two directions, the outputs of which are connected in series with the phase shifters of the difference channel and the inputs of two-directional power dividers; the first output of the first power divider in two directions is connected to the external lower radiating element Δн _{1 of the} antenna array, and the second output is connected to the second input of the second adder of the sum and difference channel signals; the first output of the second power divider in two directions is connected to the second input of the first adder of the signals of the total and difference channels, and the second output of the said divider is connected to the external upper radiating element of the antenna array: each three of the radiating elements (∑ _n , Δв _n , Δн _n ) are fed in-phase currents, and the amplitudes of the currents in the radiating elements Δн _n and Δв _n are equal to each other, the amplitudes of the currents in the radiating elements Δн _n and Δв _{n are} proportional to the amplitudes of the currents in the radiating elements ∑ _n ; the amplitudes of the currents in the elements emitting the signals of the total channel are selected from the condition of attenuation of radio waves in the direction of the folds of the terrain in the zone of aircraft approach. The solution to these and other problems is explained below with text and drawings.

Brief Description of the Drawings

Figure 1 presents a structural electrical diagram of a glide path beacon in accordance with the present invention.

Figure 2 presents a structural electrical diagram of another embodiment of a glide path beacon in accordance with the present invention.

Figure 3 shows the polar coordinate system with the origin at point O, located at the interface between the media air - underlying surface.

Figure 4 presents a structural electrical diagram of a glide path beacon with two triples of antennas in accordance with examples of implementation No. 1 and No. 2 of the present invention.

Figure 5 presents the radiation patterns in the vertical plane of the analog antennas - timing with "zero lattice"; the dotted line shows the radiation pattern for the total channel, the dashed line for the difference signal and the solid line shows the dependence of the cattle on the elevation angle.

Figure 6 shows the calculated radiation pattern of the horn antenna in the plane of the vector H in free space.

7 shows the radiation pattern in the vertical plane of the antenna array of 4 horn antennas (dashed line, difference channel) corresponding to the implementation example No. 1, the radiation pattern of the antenna array of 2 horn antennas (dashed line, total channel), and dependence of cattle on elevation (solid line). The lower horn is located at a height of 1 m relative to the underlying surface.

On Fig shows the corresponding radiation pattern example No. 1 in the vertical plane along the total (dashed line) and difference (dashed line) channels in the extreme case when H ₀ → 0.

Figure 9 shows the radiation pattern of a resonator antenna with a partially transparent surface with a vertical opening equal to 0.9 m

Figure 10 shows the radiation pattern of the antenna array of 4 flat resonator antennas (dashed line) corresponding to the example of implementation No. 2, the radiation pattern of the antenna array of 2 flat resonator antennas (dashed line), and the dependence of the RGM on the elevation angle (solid line ) In this case, the lower antenna is located at a height of 1.5 m relative to the surface of the Earth; the angle of inclination of the maximum radiation pattern relative to the horizon is 12 °, the phase difference of the currents in the emitters of the total and difference channels is 180 °.

11 shows the radiation pattern of an antenna array of 4 flat resonator antennas (dashed line), the radiation pattern of an antenna array of 4 flat resonator antennas (dashed line), and the dependence of the RGM on the elevation angle (solid line) in the extreme case, when in example No. 2 of the implementation of the present invention H ₀ → 0.

On Fig presents the radiation pattern of the antenna array of 8 horn antennas (dashed line) corresponding to the implementation example No. 3, the radiation pattern of the antenna array of 4 horn antennas (dashed line), and the dependence of the RGM on the elevation angle (solid line).

On Fig presents the radiation pattern of the antenna array of 10 horn antennas (dashed line) corresponding to the example of implementation No. 4, the radiation pattern of the antenna array of 5 horn antennas (dashed line), and the dependence of the RGM on the elevation angle.

The implementation of the invention

Turning to FIG. 1, a structural electrical diagram of a glide path beacon in accordance with the present invention is presented. The glide path beacon contains a device for generating signals of the total channel 10, a device 20 for generating signals of the differential channel, an antenna array 30 consisting of N radiating elements ∑ _n (301, 302, ..., 30n, ..., 30N) of the total channel (hereinafter, N is the integer a number greater than or equal to 2, n is the serial number of the device in a homogeneous group of devices: radiating elements of the antenna array, phase shifters, power dividers in two directions; n≥1), antenna array 40 of radiating elements of the difference channel, consisting of N lower Δн _n ( 401, 403, ..., 40 (2 n-1), ..., 40 (2N-1)) and N upper Δв _n (402, 404, ..., 40 (2n), ..., 40 (2N)) radiating elements, the first power divider 50 with one input and N outputs (501, 502, ..., 50n, ..., 50N), a second power divider 60 with one input and N outputs (601, 602, ..., 60n, ..., 60N), N power dividers 70 (701, 702, ..., 70n, ..., 70N) in two directions with one input and first and second outputs each, N phase shifters of the total channel 80 (801, 802, ..., 80n, ..., 80N), N phase shifters of the differential channel 90 (901, 902, ..., 90n, ..., 90N). Each radiating element of the antenna array of the total channel ∑ _{n has} one upper Δв _n and one lower Δн _n radiating element of the antenna channel of the difference channel with the formation of an ordered family of triples of radiating elements (∑ _n , Δв _n , Δн _n ); in each triple, the lower and upper radiating elements of the antenna array of the difference channel have the same serial number n as the serial number of the radiating element of the antenna array of the total channel. The radiating elements of the antenna array of the total channel are arranged sequentially one above the other at heights H _n in increasing order of the number n of the radiating element from 1 to N, and the height H _{1 of the} first radiating element is equal to:

H ₁ = d + H ₀ ,

Where:

,

,

λ is the wavelength; θ _hl - the given angle of the glide path,

H ₀ is the suspension height of the first lower radiating element of the antenna array of the difference channel Δн ₁ relative to the Earth's surface, approximately equal to 1 ÷ 2 m for beacons of the decimeter wave range, 1 ÷ 4 m for beacons of the meter wavelength range.

The lower Δн _n and upper Δв _n radiating elements of the antenna array of the difference channel with the same number n are located symmetrically relative to the radiating element ∑ _{n of the} antenna array of the total channel at a distance of ± d relative to the mentioned element ∑ _n .

The listed devices: device 10 generating signals of the differential channel, device 20 generating signals of the total channel, power dividers 70 in two directions - made as they are in serial beacons of the meter wavelength range SP-90, produced by the Chelyabinsk Radio Plant "Flight" and operated at aerodromes civil aviation, or as in serial beacons of the decimeter wave band PRMG-76U, operated at military aerodromes. Power dividers 50 and 60 in N directions can be made on the basis of a radial transmission line or in strip design and are calculated according to formulas from well-known reference books. As radiating elements 301 ... 30N, 401 ... 40 (2N) in the antenna arrays 30 and 40 in the timing of the decimeter range, antennas of the Uda-Yagi type, horn antennas that are part of the PRMG-6 stationary beacon, or antennas with narrower antennas can be used radiation patterns in the vertical plane, for example resonator antennas with a partially transparent surface. In the timing of a meter range, antennas in the form of a horizontal linear array of dipole emitters with a common reflector or resonator antennas with a partially transparent surface can be used as emitting elements 301 ... 30N, 401 ... 40 (2N).

These devices are interconnected as follows. The signal conditioning device of the total channel 10 is connected to the input of the first power divider 50 in N directions, the outputs of which 501, 502, ..., 50N are connected in series with the phase shifters of the total channel 801, 802, ..., 80N and radiating elements ∑ _n 301 , 302, ..., 30N of the antenna array 30 of the total channel. The signal conditioning device of the differential channel 20 is connected to the input of the second power divider 60 in N directions, the outputs of which 601, 602, ..., 60N are connected in series with the phase shifters of the differential channel 901, 902, ..., 90N and the inputs of the power dividers 701, 702, ..., 70N in two directions, the first output of each said divider is connected to the corresponding lower radiating element 401, 403, ..., 40 (2N-1), and each second output is connected to the corresponding upper radiating element 402, 404, ..., 40 (2N) difference channel.

Each triple of radiating elements (∑ _n , Δв _n , Δн _n ) is fed by common-mode currents, and the amplitudes of the currents in the radiating elements of the difference channel Δн _n and Δв _n are equal to each other, the complex amplitudes (hereinafter, the amplitudes) of the currents in the radiating elements of the difference channel proportional to the amplitudes of the currents in the radiating elements of the total channel; the amplitudes of the currents in the radiating elements of the total channel are selected from the condition of attenuation of radio waves in the direction of the folds of the terrain in the zone of approach of aircraft for landing.

Let us now turn to figure 2, which presents another version of the glide path beacon for instrumental approach of aircraft for landing at aerodromes with a high level of snow cover and folds in the area of approach of aircraft for landing, causing interference of radio waves in the area of the glide path. The timing includes a signal generating device for the total channel 10, a signal generating device for the differential channel 20, an equidistant antenna array of radiating elements 30, 40, further comprises a first power divider 50 with one input and N outputs, a second power divider 60 with one input and N outputs, where N is an integer greater than or equal to three, N power dividers in two directions 70 with one input and two outputs each, N phase shifters 80 of the total channel, N phase shifters 90 of the differential channel, N totalizers of signal sums the difference and channel 100 with the first and second inputs and one output each, N-2 adders of signals of the difference channel 110 with two inputs and one output each, the equidistant antenna array 30, 40 consists of N internal radiating elements ∑ _n 301 ... 30N, external lower radiating element 401, the outer upper radiating element 40 (2N), wherein the internal elements Σ _n array are excited by signals overall channel internal Σ _n 301 ... 30N and the outer bottom 401 and an outer top 40 (2N) radiating elements are excited by signals spacing Nogo channel; each radiating element ∑ _{n is} associated with one upper Δв _n and one lower Δн _n radiating element with the formation of an ordered family of N triples of radiating elements (∑ _n , Δв _n , Δн _n ), in which each triple has lower and upper radiating elements excited by differential signals channel, have the same number n as the number of the radiating element ∑ _n , excited by the signals of the total channel; the radiating elements ∑ _n are arranged sequentially one above the other at heights H _n in increasing order of the number n of the radiating element from 1 to N, and the height H _{1 of the} first radiating element ∑ ₁ is equal to:

H ₁ = d + H ₀ ,

,Where:

,

d is the period of the antenna array, λ is the wavelength; θ _hl is the given glide path angle, H ₀ is the suspension height of the lower external radiating element of the antenna array relative to the Earth's surface, approximately equal to 1 m; lower Δн _n and upper Δв _n radiating elements with number n, excited by the signals of the difference channel, are located symmetrically with respect to the nth radiating element ∑ _n at a distance d relative to the said element; the output of the nth adder of the signals of the total and difference channels 100n is connected to the nth internal radiating element ∑ _n , the signal generating device of the total channel 10 is connected to the input of the first power divider in N directions, the outputs of which are connected in series with the phase shifters 80 of the total channel and the first inputs of the adders 100 signals of the total and differential channels; the signal generating device of the differential channel 20 is connected to the input of the second power divider 60 into N directions, the outputs of which are connected in series with the phase shifters of the differential channel 90 and the inputs of the numbers matching the power dividers into two directions 110; the first output of the first power divider in two directions 701 is connected to the external lower radiating element 401 of the equidistant antenna array, and the second output is connected in series with the first input of the first adder of the signals of the differential channel 1101, the second input of the second adder of the signals of the sum and difference channels 1002; the first output of the second power divider in two directions 702 is connected in series with the second input of the first adder of the signals of the total and difference channels 1001, and the second output of the said divider is connected in series with the first input of the second adder of the signals of the difference channel 1102, the second input of the third adder of signals of the total and difference channels 1003 ; the first output of the third 703 and subsequent power dividers in two directions is connected in series with the second input of the adder of the signals of the difference channel, whose number is two units less than the number of the said power divider, with the second input of the adder of the signals of the total and difference channels with a number one less than the number the said power divider in two directions, and the second output of the said power dividers in two directions is connected in series with the first input of the adder signals of the differential channel a number equal to the number of said power divider into two, a second adder input signals sum and difference channels with a number one greater than the number of said power divider; the first output 70 (N-1) of the power divider in two directions is connected in series with the second input 110 (N-3) of the adder of the signals of the difference channel, with the second input 100 (N-2) of the adder of the signals of the sum and difference channels, and the second output is connected to the second input of the 100Nth adder of the signals of the total and differential channels; the first output of the 70Nth power divider in two directions is connected in series with the second input 110 (N-2) of the adder of signals of the difference channel, with the second input 100 (N-1) of the adder of signals of the sum and difference channels, and the second output is connected to an external upper radiating by an antenna array element Δв _N : 40 (2N): each triple of radiating elements (∑ _n , Δв _n , Δн _n ) is fed by common-mode currents, and the amplitudes of the currents in the radiating elements Δн _n and Δв _n are equal to each other, the amplitudes of the currents in the radiating elements Δн _n and Δin _{n are} proportional to the amplitudes of the currents in radiating elements ∑ _n ; the amplitudes of the currents in the elements emitting the signals of the total channel are selected from the condition of attenuation of radio waves in the direction of the folds of the terrain in the zone of approach of aircraft for landing.

For the convenience of describing the device and operation of this variant of the timing, as well as another variant of the timing of the present invention presented below, we will conditionally assume that there are two antenna arrays of radiating elements: the antenna array of the total channel and the antenna array of the difference channel. The composition of the lattice of the total channel conditionally included internal emitting elements. The structure of the lattice of the difference channel conditionally includes internal radiating elements, a lower external radiating element and an upper external radiating element.

In Fig.2, the elements of the equidistant antenna array emitting simultaneously the signals of the total and difference channels are indicated by triangles, one half of which is painted black and the other half is white. Next to the triangle are the numbers of the radiating elements in the corresponding antenna arrays. Black color means conditionally belonging of this element to the antenna array of the radiating elements of the total channel. White color means that this element conditionally belongs to the antenna array of the radiating elements of the difference channel.

Another variant of a glide path radio beacon for instrumental approach of aircraft for landing at aerodromes with a high level of snow cover and terrain folds in the zone of aircraft approach for landing, causing interference of radio waves in the area of the glide path, contains a device for generating total channel signals, a device for generating differential channel signals, an equidistant antenna the grating further comprises a first power divider with one input and two outputs, a second power divider with one input and two I have outputs, two power dividers in two directions with one input and two outputs each, two phase shifters of the total channel, two phase shifters of the differential channel, two adders of the signals of the total and difference channels with the first and second inputs and one output each, the antenna array consists of two internal radiating elements izluchayuschnego outer lower member, the upper external radiating element, wherein the internal elements Σ _{n, n} = 1, 2, the antenna array are excited by the total channel signals, internal and external audio Nij and outer upper radiating elements are excited difference channel signals; each radiating element ∑ _{n is} associated with one upper Δв _n and one lower Δн _n radiating element with the formation of an ordered family of two triples of radiating elements (∑ _n , Δв _n , Δн _n ), in which the lower and upper radiating elements excited in each triple the difference channel signals have the same number n as the number of the radiating element ∑ _n , excited by the signals of the total channel; the radiating elements ∑ _n are located one above the other at heights H _n , and the height H _{1 of the} first radiating element ∑ ₁ is equal to:

H ₁ = d + H ₀ ,

,Where:

,

d is the period of the antenna array, λ is the wavelength; θ _hl is the given glide path angle, H ₀ is the suspension height of the lower external radiating element of the antenna array relative to the Earth's surface, approximately equal to 1 m; lower Δн _n and upper Δв _n radiating elements with number n, excited by the signals of the difference channel, are located symmetrically with respect to the n-th radiating element E _n at a distance d relative to the said element; the output of the nth adder of the signals of the sum and difference channels is connected to the nth internal radiating element ∑ _n , the device for generating the signals of the sum channel is connected to the input of the first power divider in two directions, the outputs of which are connected in series with the phase shifters of the total channel and the first inputs of the signal adders total and differential channels; a differential channel signal generating device is connected to the input of the second power divider in two directions, the outputs of which are connected in series with the phase shifters of the difference channel and the inputs of two-directional power dividers; the first output of the first power divider in two directions is connected to the external lower radiating element Δн _{1 of the} antenna array, and the second output is connected to the second input of the second adder of the sum and difference channel signals; the first output of the second power divider in two directions is connected to the second input of the first adder of the signals of the total and difference channels, and the second output of the said divider is connected to the external upper radiating element of the antenna array: each three of the radiating elements (∑ _n , Δв _n , Δн _n ) are fed in-phase currents, and the amplitudes of the currents in the radiating elements Δн _n and Δв _n are equal to each other, the amplitudes of the currents in the radiating elements Δн _n and Δв _{n are} proportional to the amplitudes of the currents in the radiating elements ∑ _n ; the amplitudes of the currents in the elements emitting the signals of the total channel are selected from the condition of attenuation of radio waves in the direction of the folds of the terrain in the zone of aircraft approach.

Other timing options. Obviously, this invention allows a large number of modifications of the glide path beacon: from modifications of the timing, using two triples of radiating elements, to timing, using seven or more triples of radiating elements. Apart from the horn and flat resonator antennas, other types of antennas can be used as radiating elements of the antenna arrays of the total and difference channels: Uda-Yagi antennas, Cheese antennas, linear or flat antenna arrays of vibrators with a common reflector, and other antennas. Moreover, in different triples in the first variant of the timing, different types of antennas can be used as radiating elements.

The glide path beacon operates as follows. The signals of the total channel from the device 10 (Fig. 1) using a power divider 50 are divided into N parts and sent through phase shifters 801, 802, ..., 80N to the radiating elements 301, 302, ..., 30N of the antenna array 30 of the total channel, which are emitted in space.

The signals of the difference channel from the device 20 using the power divider 60 are divided into N parts and sent through the corresponding phase shifters 901, 902, ..., 90N to the power dividers 70 in two directions, from the first output of which the signals are sent to the lower radiating elements 401, 403, ... , 40 (2N-1) of the antenna array 40. From the second output of the said dividers, the signals are fed to the upper radiating elements 402, 404, ..., 40 (2N). The lower and upper elements 401, ..., 40 (2N) emit the signals of the difference channel into space.

The presented timing diagram provides the formation of the amplitude-phase distribution for the signals of the difference and total channels at the outputs of the radiating elements in accordance with the following tables 1-4.

Table 1 The first three radiating elements Designation and number of the radiating element Amplitude Phase Δn ₁

ψ ₁ Σ ₁

ψ ₁ Δ in ₁

ψ ₁

Table 2 The second three radiating elements Designation and number of the radiating element Amplitude Phase Δn ₂

ψ ₂ Σ ₂

ψ ₂ Δv ₂

ψ ₂

Table 3 nth three radiating elements Designation and number of the radiating element Amplitude Phase Δn _n

ψ _n Σ _n

ψ _n Δ in _n

ψ _n

Table 4 Nth Antenna Three Designation and number of the radiating element Amplitude Phase Δn _N

ψ _N Σ _N

ψ _N Δ in _N

ψ _N

The amplitudes of the currents a _n in the radiating elements of the total channel are set using a power divider 50, the phases of the currents ψ _n are set using phase shifters 80. The amplitudes of the currents in _n in the radiating elements of the difference channel are set using a power divider 60, the phases of the currents ψ _n are set using phase shifters 90. In each triple, the radiating elements (30n, 40 (2n-1), 40 (2n)) are powered by common-mode currents, and the amplitudes of the currents in the radiating elements of the difference channel Δн _n and Δв _n are equal to each other.

Moreover, when the following conditions are met, the glide path parameters (glide path angle and slope of the glide path zone) are independent of the height of the suspension of the radiating elements of the antenna arrays.

1. Each radiating element of the antenna array of the total channel ∑ _{n is} associated with two radiating elements of the antenna array of the difference channel: Δн _n and Δв _n , and the latter should be located at an equal distance ± d from the radiating element of the antenna array of the total channel. In the triple of radiating elements (∑ _n , Δн _n , Δв _n ), the element Δн _n is located below the element ∑ _n (at the distance-d), and the element Δв _n is located above the element ∑ _n (at the distance + d).

2. The radiation _patterns F _∑n (θ), F _Δn (θ) of the n-th radiating elements of the antenna array of the total and difference channels in free space are the same in each of the above n-th elements.

3. The initial phases of the currents in the elements in each triple of elements must be equal to each other (φ _n = ψ _n ). The amplitudes of the currents b _n in the lower Δн _n element and in the upper Δin _n element in each triple of elements are equal to each other.

4. The amplitudes of the currents in _n in the radiating elements Δн _n , Δв _{n of the} antenna array of the difference channel are proportional to the amplitudes a _{n of the} currents in the elements ∑ _{n of the} total channel with the same coefficient α / 2, which determines the slope of the glide path.

5. The distance d between adjacent antennas in claim 1 is determined based on the condition of providing a given glide path angle θ ₀ , i.e. from the condition that the information parameter is equal to zero (RGM in the beacons of the meter wavelength range or cattle in the beacons of the decimeter wave range) to zero:

cos (kd sinθ _ch ) = 0.

It follows that

.

.

We show that when the above conditions 1–4 are fulfilled, the glide path zone remains unchanged, despite the change in the height of the emitter suspension due to snow or snow melting or changes in the reflective properties of the underlying surface. To this end, we consider the operation of the timing, taking into account the influence of the underlying surface of the Earth.

Our goal is to determine the requirements for antenna arrays for the emission of the total and difference signals of a glide path beacon, in which the glide path would not depend on the level of snow cover and reflective properties of the underlying surface (i.e., on the height of the suspension of the radiating elements of the antenna arrays relative to the underlying surface and the coefficient Fresnel reflection of electromagnetic waves from the interface between the air - the underlying surface (earth, water or snow)).

We introduce the polar coordinate system with the origin at the point O located at the interface of the media air - underlying surface (figure 3). We will count the polar angle θ from the plane tangent to the underlying surface at the location of the antenna system, counterclockwise.

Above, the notation was introduced:

∑ _n is the nth radiating element of the antenna array of the total channel;

n = 1, 2, ..., N;

H _n - suspension height of the n-th radiating element of the antenna array of the total channel relative to the surface of the Earth, n = 1, 2, ..., N;

Δн _n (Δв _n ) is the n-th lower (n-th upper) radiating element of the antenna array of the difference channel; n = 1, ..., N;

d is the distance from the radiating element ∑ _{n of the} antenna array of the total channel to the lower (upper) radiating element Δн _n (Δв _n ) in the antenna array of the difference channel;

a _n (ψ _n ) is the amplitude (phase) of the current in the nth radiating element of the antenna array of the total channel;

b _n (φ _n ) is the amplitude (phase) of the current in the nth lower and upper radiating elements of the antenna array of the difference channel.

We additionally introduce the following notation:

; κ - волновое число;

; κ is the wave number;

λ is the wavelength in free space;

F _∑n (θ), [F _Δn (θ)] - radiation pattern of the nth radiating element of the antenna array of the total channel [upper and lower difference channel elements] in free space;

F ^Δ (θ, H) is the radiation pattern of the antenna array for the difference signal, taking into account the influence of the underlying surface;

F ^∑ (θ, H) - radiation pattern of the antenna array for the total signal, taking into account the influence of the underlying surface;

- комплексный коэффициент Френеля отражения плоской волны от плоской подстилающей поверхности;

- the complex Fresnel coefficient of reflection of a plane wave from a flat underlying surface;

RGM - the difference in depth of modulation;

Cattle - coefficient of audibility of signals.

Consider the radiation patterns of the antenna arrays of the total F ^∑ (θ, H) and the difference channels F ^Δ (θ, H) in the far zone, i.e. at distances when the rays from the antennas and their mirror images can be considered parallel.

Let the power P _∑ (P _Δ ) be supplied to the input of the antenna array of the total (difference) channel:

where R is the input impedance of the antenna, which for simplicity will be assumed to be material and equal for all radiating elements.

Let it go

Then the radiation patterns F ^∑ (θ, Н) and F ^Δ (θ, H), taking into account the influence of the underlying surface, are described by relations (4) and (5):

On the right-hand side of (5) in the first sum, the first and second terms with index n (related to the first lower Δн _n and the first upper Δв _n radiating elements) have a common factor:

and in the second sum, the first and second terms with index n have a common factor:

We group the adjacent terms in (5) related to the lower and upper radiating elements with number n (n = 1, 2, ..., N), and select the factor exp (-ikdsinθ) + exp (ikdsinθ) in the resulting pairs of terms. Then (5) can be represented as the product of two factors:

The first factor in (8) is equal to:

The difference in modulation depths (RGM) is determined by the ratio of the difference signal to the total signal:

Or

In the ideal case, the RGM value is determined by the ratio

where α is a constant number that determines the steepness of the glide path zone.

To ensure the identity between the right-hand sides of equations (11) and (12), it is enough to require the equalities:

The information parameter of cattle - the coefficient of earshot signals - in the landing systems of the decimeter wave range is determined by the ratio

where β is a constant coefficient that determines the steepness of the glide path zone. When the sum and difference signals at the input of the antenna arrays are in phase, which is performed by the phasing procedure in the beacon using phase shifters (not shown in the drawings), formula (14) becomes similar to formula (9). Therefore, all the conclusions arising from the presented analysis for the timing of the meter band are also valid for beacons of the decimeter wave band.

Due to the interference of radio waves emitted directly by the antenna arrays and radio waves reflected from the underlying surface, additional (interference) minima and maxima appear in the directivity characteristics of the antenna arrays for the total F ^∑ (θ, H) and difference F ^Δ (θ, H) signals. However, since the phase centers of the antenna arrays of the sum and difference signals coincide, the positions of these additional minima and maxima also coincide and do not distort the dependence of the information parameter (RGM or KRS) on the elevation angle.

In order that additional minima do not lead to a decrease in the range of radio beacons due to a decrease in the electromagnetic field strength in the direction of the minimum angles, it is necessary to ensure the corresponding amplitude-phase current distribution in the radiating elements of the antenna array of the total (difference) channel and (or) as radiating elements use vertical directional antennas. In this case, the maximum radiation pattern of the antennas used as radiating elements of the arrays should be directed at a certain angle relative to the horizon. Preferably, the maximum is directed at an angle such that the level in the radiation pattern in the horizontal direction is 0.7.

Examples

.Numerical studies of the effect of changing the height of the suspension of the radiating elements on the timing characteristics in accordance with the present invention have been carried out. It was assumed that the operating frequency is 953 MHz (λ = 0.315 m). Glide path angle θ ₀ = 3 °. At θ ₀ = 3 ° at a frequency of 953 MHz, the distance between the radiating element of the antenna array of the total channel and the lower (upper) radiating element of the difference channel is

.

In all of the examples below, it was assumed that equal power is supplied to the input of the antenna array of the total channel. In this case, the normalized radiation pattern for the signals of the total channel has the form:

Normalized radiation pattern for difference channel signals:

The radiation patterns of the "zero" lattice are shown in Fig.5.

Implementation example No. 1

In the example No. 1, the timing includes (FIG. 4) a device for generating signals of the total channel, a device 20 for generating signals of the differential channel, an antenna array 30 consisting of 2 radiating elements ∑ _n (301, 302) of the total channel, an antenna array 40 radiating elements of the difference channel, consisting of 2 lower Δн _n (401, 403) and 2 upper Δв _n (402, 404) radiating elements, the first power divider 50 with one input and two outputs (501, 502), the second power divider 60 with one input and two outputs (601, 602), 2 power dividers 70 (701, 702) with one input and two each, 2 phase shifters of the total channel 80 (801, 802), 2 phase shifters of the differential channel 90 (901, 902). Each radiating element of the total channel ∑ _{n is} associated with one upper Δв _n and one lower Δн _n element of the difference channel with the formation of two triples of radiating elements: (∑ ₁ , Δв ₁ , Δн ₁ ) and (∑ ₂ , Δв ₂ , Δн ₂ ). The radiating elements of the antenna array of the total channel are arranged sequentially one above the other at heights H ₁ and H ₂ , and the height H _{1 of the} first antenna is equal to:

H ₁ = d + H ₀ ,

Where:

,

,

λ is the length of the working wave;

θ _hl - the given angle of the glide path,

H ₀ - suspension height of the first lower antenna Δn ₁ relative to the Earth's surface, taken equal to 1.5 m

The lower Δн _n and upper Δв _n radiating elements of the difference channel with numbers n = 1 and n = 2 are located symmetrically respectively with respect to the radiating elements ∑ ₁ and ∑ _{2 of the} total channel at a distance d relative to the mentioned elements. As radiating elements, serial horn antennas with a vertical aperture size of 0.28 m were used. The calculated radiation pattern of the horn antenna in free space is shown in the form of a graph in FIG. 6.

Tables 5 and 6 show normalized amplitudes and phases of currents relative to amplitudes and phases of currents in the radiating elements of the first three emitters.

Table 5 The first three radiating elements Designation and number of the radiating element Suspension height of the radiating elements of the antenna array relative to the underlying surface Normalized amplitude Phase Δn ₁ N _n = N ₀ = N ₁ -d = 1.5 m b ₁ = 1 ψ ₁ = 0 Σ ₁ H ₁ = 3 m a ₁ = 1 ψ ₁ = 0 Δ in ₁ H _in = H ₁ + d = (3 + 1,5) m = 4,5 m b ₁ = 1 ψ ₁ = 0

Table 6 The second three radiating elements installed at a distance of 1.2 m from the first three elements Designation and number of the radiating element Suspension height of the radiating elements of the antenna array relative to the underlying surface Amplitude Phase Δn ₂ H _2n = H ₂ -d = 4.2-1.5 = 2.7 m b ₂ = 1 ψ ₂ = 90 ° Σ ₂ H ₂ = H ₁ +1.2 m = (3.0 + 1.2) m = 4.2 m a ₂ = 1 ψ ₂ = 90 ° Δv ₂ H _in = H ₂ + d = (4.2 + 1.5) m = 5.7 m b ₂ = 1 ψ ₂ = 90 °

7 shows the directivity pattern of the antenna array of 4 horn antennas (dashed line), the directivity pattern of the antenna array of 4 horn antennas (dashed line), and the dependence of the RGM on the elevation angle (solid line). In this case, the lowest antenna is located at a height of 1.5 m.

As can be seen from the graphs in Fig.7, the glide path angle is 3 °. The level in the radiation pattern for the total channel within the glide path zone (0 ° 54 '÷ 4 ° 35') has values greater than 1, which indicates that the range of the timing is provided with a margin.

With the advent of snow cover, the height of H ₀ will decrease by an amount equal to the height of the snow cover. With a change in the density and humidity of snow, the Fresnel coefficient of reflection of electromagnetic waves from the underlying surface will change. As a result, the shape of the antenna array will change. In this case, with a decrease in height H ₀ , the signal level at the minima will increase. In the extreme case, when H ₀ → 0, the radiation patterns will take the form indicated in Fig. 8.

The law of the dependence of the cattle on the angle θ does not change with a change in H ₀ - the height of the suspension of the lower antenna (and therefore other antennas). At Н ₀ = 1 m, at Н ₀ → 0, as well as at any other value of Н ₀ , the cattle changes from the elevation angle θ according to the cosine law.

It is advisable to use this variant of the timing of the decimeter wave range at aerodromes located in an area with a snow depth of up to 130 cm, without towering folds of the terrain in the aircraft landing area.

Implementation example No. 2

Implementation example No. 2 differs from implementation example No. 1 in a different amplitude-phase current distribution in the radiating elements of the antenna array, as well as the antenna used as the radiating element, and the height of the suspension of the radiating elements relative to the underlying surface. In example No. 2, the amplitudes of the currents in the emitters forming the second three are two times less than the amplitudes of the currents in the corresponding emitters of the first three emitters. The phases of the currents in the emitters forming the second three differ by 180 ° from the phases of the currents of the respective emitters of the first three emitters. The suspension height of the first lower antenna is 1.5 m. As a radiating element of the antenna arrays of the total and difference channels, a flat resonator antenna with an opening of 0.9 m is used. The radiation pattern of the flat resonator antenna is shown in Fig. 9. The principle of operation of the aforementioned antenna and examples of the implementation of the resonator antenna in the frequency range 2.4 GHz are given in the patent application of the Russian Federation for invention No. 2007137544/09 (041063) "Flat resonator antenna" by N. Voitovich et al., As well as in the article: Voitovich N.I., Bukharin V.A., Repin N.N. Flat resonator antenna. Proceedings of the Second All-Russian NTK "Radio Altimetry-2007". Kamensk-Uralsky. - Yekaterinburg: Publishing House "Third Capital". - 2007. - Pages 160-164.

As can be seen from the comparison of the graphs in Fig.6 and Fig.9, the resonator antenna has a narrower radiation pattern compared to the horn antenna. Due to the mechanical rotation of the antenna, the maximum of its radiation pattern is deflected by an angle of 12 ° relative to the horizon. As a result, the level of the antenna pattern in the direction to the horizon (polar angle θ = 0 °) is 0.7.

The initial data for triples of radiating elements are given in Table 7 and Table 8.

Table 7 The first three radiating elements Designation and number of the radiating element Suspension height of the radiating elements of the antenna array relative to the underlying surface Normalized amplitude Phase Δn ₁ H _n = H ₁ -d = 1.5 m b ₁ = 1 ψ ₁ = 0 Σ ₁ H ₁ = 3 m a ₁ = 1 ψ ₁ = 0 Δ in ₁ H _in = H ₀ + d = (3 + 1,5) m = 4,5 m b ₁ = l ψ ₁ = 0

Table 8 The second three radiating elements installed at a distance d + 3λ from the first three Designation and number of the radiating element Suspension height of the radiating elements of the antenna array relative to the underlying surface Amplitude Phase Δn ₂ H _2n = H ₀ + d + 3λ = 1.5 + 1.505 + 3 · 0.315 = 3.95 (m) b ₁ = 0.5 ψ ₂ = 180 ° Σ ₂ H ₂ = H ₁ + d + 3λ = 3 + 1.5 + 3 0.315 = 5.455 (m) a ₁ = 0.5 ψ ₂ = 180 ° Δv ₂ H _in = H ₂ + d + 3λ = 5.455 + 1.5 + 3 · 0.315 = 7.96 (m) b ₁ = 0.5 ψ ₂ = 180 °

.Figure 10 presents the irregular radiation pattern of the antenna array of 4 resonator antennas (dashed line), designed to emit signals of the differential channel, the radiation pattern of the antenna array of 2 resonator antennas (dashed), designed to emit signals of the total channel, and RGM dependence on elevation (solid line). It was assumed that the height H _{0 of the} suspension of the lowest antenna of the difference channel relative to the Earth’s surface is 1.5 m. The underlying surface is a perfectly conducting plane and, therefore, the Fresnel reflection coefficient

.

The maximum values in the radiation pattern for the signals of the difference and total channels are not equal to 1. This is explained by the use of 4 and 2 radiating elements, respectively, in antenna arrays. The radiation pattern for the signals of the difference channel takes a zero value at θ = 3 °. The zero value in the radiation pattern for the difference channel (if the value in the radiation pattern for the signal of the total channel is not equal to zero) corresponds to the zero value of the Raman at θ = 3 °. The angle θ = 3 ° corresponds to the position of the glide path. The graph of the dependence of the timing information parameter (RRS) on the elevation angle is described by a cosine function that takes maximum values in absolute value at θ = 0 ° and when the glide path angle is doubled θ = 6 °.

The level in the radiation pattern for the total channel in the glide path zone has values greater than 1, which indicates that the range of the timing is provided with a margin.

As can be seen from the consideration of the graphs in figure 10, in the zone of the glide path (0.3 θ _hl ÷ 1, ... θ _hl ) there is an interference minimum at θ ₁ = 4 °. However, the signal level at this minimum is such that a predetermined range of the beacon at a specified elevation angle is provided.

With the advent of snow cover, the height of H ₀ will decrease by an amount equal to the height of the snow cover. As a result, the shape of the antenna array will also change in such a way that the signal level at a minimum will increase. In the extreme case, when H ₀ → 0, the radiation patterns will take the form shown in Fig.11.

The law of dependence of the RGM on the angle θ does not change with a change in H ₀ - the height of the suspension of the lower antenna. At Н ₀ = 1 m, at Н ₀ → 0, and at any other value of Н _{0, the} RGM changes from the angle θ according to the cosine law.

This timing option is advisable to use at aerodromes with a snow depth of up to 100 cm and a complex terrain in the area of aircraft landing.

Implementation example No. 3

In the example No. 3, the timing includes (Fig. 4) a device for generating signals of a total channel, a device 20 for generating signals of a difference channel, an antenna array 30 consisting of 4 radiating elements ∑ _n (301, 302, 303, 304) of the total channel, antenna array 40 of radiating elements of the differential channel, consisting of 4 lower Δн _n (401, 403, 405, 407) and 4 upper Δв _n (402, 404, 406, 408) radiating elements, the first power divider 50 with one input and 4- with outputs (501, 502, 503, 504), a second power divider 60 with one input and 4 outputs (601, 602, 603, 604), 4 power dividers 70 (701, 702, 7 03, 704) with one input and two outputs each, 4 phase shifters of the total channel 80 (801, 802, 803, 804), 4 phase shifters of the differential channel 90 (901, 902, 903, 904). Each radiating element of the total channel ∑ _{n is} associated with one upper Δв _n and one lower Δн _n element of the difference channel with the formation of four triples of radiating elements: (∑ ₁ , Δв ₁ , Δн ₁ ), (∑ ₂ , Δв ₂ , Δн ₂ ), ( ∑ ₃ , Δv ₃ , Δn ₃ ), (∑ ₄ , Δv ₄ , Δn ₄ ). The radiating elements of the antenna array of the total channel are arranged sequentially one above the other at heights H ₁ , H ₂ , H ₃ and H ₄ , and the height H _{1 of the} first antenna is equal to:

H ₁ = d + H ₀ ,

Where:

,

,

H ₀ = H _n1 is the suspension height of the first lower antenna Δn ₁ relative to the surface of the Earth. The lower Δн _n and upper Δв _n radiating elements of the difference channel are located symmetrically with respect to the corresponding radiating elements ∑ _{n of the} total channel at a distance of ± d relative to the mentioned elements. As the radiating elements, the above mentioned serial horn antennas with a vertical aperture size of 0.28 m are used. Table 9-12 shows the suspension heights, normalized amplitudes and phases of the currents relative to the amplitudes and phases of the currents in the radiating elements of the first three emitters.

Table 9 The first three radiating elements Designation and number of the radiating element Suspension height of the radiating elements of the antenna array relative to the underlying surface Normalized amplitude Phase Δn ₁ H _n = H ₁ -d = 1 m b ₁ = 1 ψ ₁ = 0 Σ ₁ H ₁ = 2.50 m a ₁ = l ψ ₁ = 0 Δ in ₁ H _in = H ₁ + d = (2.5 + 1.5) m = 4.00 m b ₁ = 1 ψ ₁ = 0

Table 10 The second three radiating elements installed at a distance of 0.75 m from the first three elements Designation and number of the radiating element Suspension height of the radiating elements of the antenna array relative to the underlying surface Amplitude Phase Δn ₂ H _2n = H ₂ -d = 3.25-1.5 = 1.75 m b ₂ = l ψ ₂ = 90 ° Σ ₂ H ₂ = H ₁ +0.75 m = 2.5 + 0.75 = 3.25 m a ₂ = 1 ψ ₂ = 90 ° Δv ₂ H _in = H ₂ + d = (3.25 + 1.50) m = 4.75 m b ₂ = 1 ψ ₂ = 90 °

Table 11 The third three radiating elements installed at a distance of 1 m from the first three elements Designation and number of the radiating element Suspension height of the radiating elements of the antenna array relative to the underlying surface Amplitude Phase Δn ₃ H _n3 -d = 3.5-1.5 = 2.0 m b ₃ = 0.8 ψ ₂ = 180 ° Σ ₃ H ₃ = H ₁ +1 m = 2.5 + 1 = 3.50 m a ₃ = 0.8 ψ ₂ = 180 ° Δv ₃ H _3B = H ₃ + d = 3,5 + 1,5 = 5 m b ₃ = 0.8 ψ ₂ = 180 °

Table 12 The fourth three radiating elements installed at a distance of 1.75 m from the first three elements Designation and number of the radiating element Suspension height of the radiating elements of the antenna array relative to the underlying surface Amplitude Phase Δn ₄ H _4n = H ₄ -d = 4.25-1.5 = 2.75 m b ₄ = 0.8 ψ ₁ = 270 ° Σ ₄ H ₄ = H ₁ +1.75 m = 2.5 + 1.75 = 4.25 m a ₄ = 0.8 ψ ₁ = 270 ° Δv ₄ Н _4в = Н ₄ + d = 4,25 + 1,5 = 5,75 m b ₄ = 0.8 ψ ₁ = 270 °

On Fig presents the radiation pattern of the antenna array of the difference channel of 8 horn antennas (dashed line), the radiation pattern of the antenna array of the total channel of 8 horn antennas (dashed line), and the dependence of the RGM on the elevation angle (solid line).

. Представленные на фиг.12 данные свидетельствуют о больших потенциальных возможностях ГРМ с точки зрения снижения величины искривлений глиссады на аэродромах с неблагоприятной формой рельефа местности в зоне захода самолетов на посадку. Изменяя относительную амплитуду сигналов в третьей и четвертой тройках, можно регулировать величину ослабления сигналов под малыми углами места. Выбирая другие значения для высот подвеса антенн третьей и четвертой троек, можно изменять величину сектора углов места в окрестности направления на горизонт, в котором выполняется "вырезка" в диаграммах направленности антенных решеток суммарного и разностного каналов.As can be seen from the graphs in Fig.12, the glide path angle is 3 °. The glide path zone is formed with a large signal of the total channel. The level of the sum and difference signals in the vicinity of the direction to the horizon (up to an elevation angle of 45 ') is attenuated by more than 20 dB compared to the level of the signal with a "zero" grating. With an increase in the angle in the region above the frontier of the timing, the signals of the total and difference channels rapidly increase. The maximum radiation pattern for the signals of the difference channel is observed at

. The data presented in Fig. 12 testify to the great potential of timing in terms of reducing glide path curvatures at aerodromes with an unfavorable terrain in the aircraft landing area. By changing the relative amplitude of the signals in the third and fourth triples, you can adjust the amount of attenuation of the signals at low elevation angles. Choosing other values for the suspension heights of the antennas of the third and fourth triples, it is possible to change the magnitude of the sector of elevation angles in the vicinity of the direction to the horizon in which the notch is performed in the radiation patterns of the antenna arrays of the total and difference channels.

Implementation example No. 4

We now turn to FIG. 13, which shows the radiation patterns and the dependence of the RGM on the elevation angle for a beacon, which includes an antenna array of the total channel with five radiating elements and an antenna array of the difference channel, which includes ten radiating elements. The timing includes a total channel signal generating device 10, a differential channel signal generating device 20, an antenna array 30 consisting of 5 radiating elements ∑ _n (301, 302, 303, 304, 305) of the total channel, an antenna array 40 of the differential channel radiating elements consisting of 5 lower Δн _n (401, 403, 405, 407, 409) and 5 upper Δв _n (402, 404, 406, 408, 410) radiating elements, the first power divider 50 with one input and 5 outputs ( 501-505), the second power divider 60 with one input and 5 outputs (601-605), 5 power dividers 70 (701-705) with one input and two you each, 5 phase shifters of the total channel 80 (801-805), 5 phase shifters of the differential channel 90 (901-905), 5 adders 1001-1005 of the signals of the total and difference channels with the first and second inputs and one output each, 1 adder of the signals of the differential channel with the first and second inputs and one output 1101, it is accepted that the lower inputs of the said adders 100 and 110 are the first inputs, and the upper ones are the second. The radiating elements 301, 302, ..., 30N of the antenna array of the total channel 30 are located at a distance from each other equal to d. The radiating elements 301-305 of the antenna array of the total channel are used to emit signals of both the total and differential channels. The output of the nth adder 100n is connected to the nth radiating element of the antenna array 30n of the total channel.

The signal generating device of the total channel 10 is connected to the first power splitter 50, the outputs of which 501-505 are connected in series with the phase shifters 801-805 of the total channel and the first inputs of the adders 1001-1005 of the total and difference channels.

The signal generating device of the differential channel 20 is connected to the input of the second power divider 60, the outputs of which 601-605 are connected in series with the phase shifters 901-905 of the difference channel and the inputs of the power divider matching the first and second outputs 701-705. It is further assumed that the lower outputs of the dividers 701, 702, ..., 70N in FIG. 10 are the first outputs, and the upper outputs are the second.

The first output of the first divider 701 in two directions is connected to the first lower radiating element 401, and the second output is connected in series with the first input of the first adder 1101 of the signals of the differential channels, the second input of the second adder 1003 of the signals of the total and difference channels.

The first output of the second power divider 702 is connected to the antenna 403, and the second output of the said divider 702 is connected in series with the first input of the adder 1104 of the signals of the total and difference channels.

The first output of the third divider 703 is connected to the second input of the adder 1001 of the signals of the total and difference channels, and the second output is connected to the first input of the adder 1005 of the signals of the total and difference channels.

The first output of the fourth divider 704 is connected to the second input of the adder 1002 of the sum and difference channel signals, and the second output is connected to the antenna 408.

The first output of the first divider 705 in two directions is connected in series with the second input of the adder 1101 signals of the differential channel, the second input of the adder 1003 signals of the sum and difference channels, and the second output is connected to the antenna 410.

Each radiating element of the total channel ∑ _{n is} associated with one upper Δв _n and one lower Δн _n element of the difference channel with the formation of five triples of radiating elements: (∑ ₁ , Δв ₁ , Δн ₁ ) ÷ (∑ ₅ , Δв ₅ , Δн ₅ ).

H₁+d,

H₁+2d причем высота H₁ первой антенны равна:The radiating elements of the antenna array of the total channel are arranged sequentially one above the other at heights H ₁ ,

H ₁ + d

H ₁ + 2d and the height H _{1 of the} first antenna is equal to:

H ₁ = d + H ₀ ,

Where

,

,

λ is the length of the working wave;

θ _hl - the given angle of the glide path;

H ₀ - suspension height of the first lower antenna Δн ₁ relative to the Earth's surface, adopted in this example is equal to 1 m

The lower Δн _n and upper Δв _n radiating elements of the difference channel with odd and even numbers are located symmetrically respectively with respect to the radiating elements ∑ _{n of the} total channel at a distance of ± d relative to the mentioned elements. Serial horn antennas with a vertical aperture size of 0.28 m were used as radiating elements.

Table 13 shows the normalized amplitudes and phases of the currents relative to the amplitudes and phases of the currents in the radiating elements of the first three emitters.

Table 13 First Second Third Fourth Fifth Height, m 2.5 3.25 4.0 4.75 5.5 Relative amplitude in _n one one 0.75 0.75 0.1 Relative amplitude a _n one one 0.75 0.75 0.1 Phase ψ _n 0 ° 90 ° 180 ° 270 ° 0 °

On Fig presents the amplitude radiation pattern of the antenna array of the difference channel of 10 horn antennas (dashed line), the amplitude radiation pattern of the antenna array of the total channel of 5 horn antennas (dashed), and the dependence of cattle on elevation (solid line) Timing.

. Представленные на фиг.13 данные свидетельствуют о больших потенциальных возможностях построения ГРМ с точки зрения снижения величины искривлений глиссады на аэродромах с неблагоприятными складками рельефа местности в зоне захода самолетов на посадку, образующие угол закрытия до величины

. Изменяя относительную амплитуду сигналов в третьей, четвертой и пятой тройках, можно регулировать величину ослабления сигналов под малыми углами места. Выбирая другие значения для высот подвеса антенн третьей и четвертой троек, можно изменять величину сектора углов места в окрестности направления на горизонт, в котором выполняется "вырезка" в диаграммах направленности антенных решеток суммарного и разностного каналов. Рассмотренный вариант реализации №4 с 5-ю тройками антенн отличается от предыдущего варианта №3 с 4-мя тройками большей крутизной амплитудной диаграммы направленности в окрестности нижней границы зоны действия ГРМ.As can be seen from the graphs in Fig.14, the glide path angle is 3 °. The glide path zone is formed with a large signal of the total channel. The level of the total and difference signals in the vicinity of the direction to the horizon (up to an elevation angle of 45 ') is attenuated by more than 20 dB in comparison with the level of the timing signal with a "zero" grating. With an increase in the angle in the region above the boundary 45 ', the signals of the total and difference channels rapidly increase in amplitude. The maximum radiation pattern for the signals of the difference channel is observed at

. The data presented in Fig. 13 indicate great potential for constructing the timing from the point of view of reducing glide path curvatures at aerodromes with unfavorable folds of the terrain in the aircraft approach zone, forming a closing angle of up to

. Changing the relative amplitude of the signals in the third, fourth and fifth triples, you can adjust the amount of attenuation of the signals at small elevation angles. Choosing other values for the suspension heights of the antennas of the third and fourth triples, it is possible to change the magnitude of the sector of elevation angles in the vicinity of the direction to the horizon in which the notch is performed in the radiation patterns of the antenna arrays of the total and difference channels. The considered implementation option No. 4 with 5 triples of antennas differs from the previous embodiment No. 3 with 4 triples by the greater steepness of the amplitude radiation pattern in the vicinity of the lower boundary of the timing zone.

Other timing options. Obviously, this invention allows a large number of modifications of the glide path beacon, from the timing variant using two triples of radiating elements to the timing variants using seven or more triples of radiating elements. Apart from the horn and flat resonator antennas, other types of antennas can be used as radiating elements of antenna arrays: Uda-Yagi antennas, Cheese antennas, linear or flat antenna arrays of vibrators with a common reflector, and other antennas. Moreover, in different triples in the same timing, different types of antennas can be used as radiating elements.

It is advisable to use this variant of the timing of the decimeter wave range at aerodromes located in an area with a snow depth of up to 150 cm, with folds of the terrain in the landing zone of the aircraft at an angle of closure of up to 1 °.

Application of the invention

Glide path beacon in accordance with the present invention can be used:

- at aerodromes with a high level of snow cover;

- at aerodromes with a high level of snow cover and difficult terrain in the aircraft approach zone for landing: at aerodromes in beam-ravine terrain, in hilly and foothill terrain; at aerodromes where the terminal safety strip breaks abruptly to the sea; at aerodromes where the runway and the timing site are located on an artificial embankment;

- at airfields located in a forest area;

- at aerodromes with a high level of snow cover, with a difficult terrain and forests in the area of aircraft landing.

At all of the listed aerodromes using the timing of the present invention, the need for snow removal or snow packing in the area in front of the lighthouse is excluded (in the so-called timing zone A, the dimensions of which are determined by the dimensions of the Fresnel zone on the earth's surface and amounting to tens of thousands of square meters).

The use of the timing of the present invention eliminates the need for flight timing settings during the transition from autumn to winter and from winter to summer.

Claims (3)

1. Glide path radio beacon for instrumental approach of aircraft for landing at aerodromes with a high level of snow cover and terrain folds in the area of aircraft approach for landing, causing interference of radio waves in the glide path area, comprising a signal generating device for the sum channel, a device for generating differential channel signals, an antenna array radiating elements of the total channel, antenna array of radiating elements of the differential channel, the first power divider with one input and N outputs, sec oh power divider with one input and N outputs, where N is an integer greater than or equal to two, N power dividers in two directions with one input and two outputs each, N phase shifters of the total channel, N phase shifters of the differential channel, and the antenna array of the total channel contains N radiating elements ∑ _n , the antenna array of the difference channel contains N lower Δн _n and N upper Δв _n radiating elements; each radiating element of the antenna array of the total channel ∑ _{n is} associated with one upper Δв _n and one Δн _n lower element of the antenna array of the difference channel with the formation of an ordered family of N triples of radiating elements (∑ _n , Δв _n , Δн _n ), in which each triple has lower and the upper radiating elements of the antenna array of the difference channel have the same number n as the number of the radiating elements of the antenna array of the total channel; the radiating elements of the antenna array of the total channel are arranged sequentially one above the other at heights H _n in order of increasing number n of the radiating element from 1 to N, and the height H _{1 of the} first radiating element of the antenna array of the total channel is:
H ₁ = d + H ₀ ,
Where

,
λ is the wavelength; θ _hl - the given angle of the glide path; H ₀ - suspension height of the first lower radiating element of the antenna array relative to the surface of the Earth, approximately equal to 1 m; lower Δн _n and upper Δв _n radiating elements of the difference channel with number n are located symmetrically with respect to the n-th radiating element ∑ _{n of the} total channel at a distance d relative to the said element; wherein the signal generating device of the total channel is connected to the first power divider in N directions, the outputs of which are connected in series with the identical numbers of phase shifters of the total channel and radiating elements ∑ _{n of the} aforementioned antenna array; the difference channel signal generating device is connected to the input of the second power divider in N directions, the outputs of which are connected in series with the phase shifters of the difference channel and the inputs of two-directional power dividers, the first output of each said divider is connected to the lower radiating element of the same number, and every second output is connected to the same number of the upper radiating element of the antenna array; each triple of radiating elements (∑ _n , Δв _n , Δн _n ) is powered by common-mode currents, and the amplitudes of the currents in the radiating elements Δн _n and Δв _n are equal to each other, the amplitudes of the currents in the radiating elements Δn _n and Δв _{n are} proportional to the amplitudes of the currents in the radiating elements ∑ _n ; the amplitudes of the currents in the radiating elements ∑ _n are selected from the condition of attenuation of radio waves in the direction of the folds of the terrain in the zone of approach of aircraft for landing. 2. Glide path beacon for instrumental approach of aircraft for landing at aerodromes with a high level of snow cover and terrain folds in the area of aircraft entry for landing, causing interference of radio waves in the area of the glide path, containing a signal generating device for the sum channel, a device for generating differential channel signals, an antenna array radiating elements, the first power divider with one input and N outputs, the second power divider with one input and N outputs, where N is an integer greater than or equal to three, N power dividers in two directions with one input and two outputs each, N phase-shifters of the total channel, N phase-shifters of the differential channel, N totalizers of signals of the total and difference channels with the first and second inputs and one output each, N-2 difference signal adders the channel with two inputs and one output each, with each radiating element sum signal Σ _n signals correlated Δv _n one upper and one lower radiating element _n? H to form an ordered family of n radiating triples elements (Σ _n, Δv _n,? H _n), wherein each triplet in the upper and lower radiating elements have the same number n, and that the number of the radiating element Σ _n; the radiating elements ∑ _n are arranged sequentially one above the other at heights H _n in increasing order of the number n of the radiating element from 1 to N, and the height H _{1 of the} first radiating element ∑ ₁ is equal to:
H ₁ = d + H ₀ ,
Where

,
d is the distance from the radiating element ∑ _n to the lower Δн _n (upper Δв _n ) of the radiating element; λ is the wavelength; θ _hl - the given angle of the glide path; H ₀ - suspension height of the lower radiating element of the antenna array relative to the surface of the Earth, approximately equal to 1 m; lower Δn _n and upper Δin _n radiating elements with number n are located symmetrically with respect to the n-th radiating element ∑ _n at a distance d relative to the said element; the output of the nth adder of the sum and difference channel signals is connected to the nth radiating element ∑ _n , the device for generating the signals of the sum channel is connected to the input of the first power divider in N directions, the outputs of which are connected in series with the phase shifters of the sum channel and the first inputs of the sum and total signal adders differential channels; a differential channel signal generating device is connected to the input of the second power divider in N directions, the outputs of which are connected in series with the phase shifters of the difference channel and the inputs of two-directional power dividers; the first output of the first power divider in two directions is connected to the lower radiating element Δn ₁ , the antenna array, and the second output is connected in series with the first input of the first adder of the difference channel signals, the second input of the second adder of the signals of the total and difference channels; the first output of the second power divider in two directions is connected in series with the second input of the first adder of the signals of the total and differential channels, and the second output of the said divider is connected in series with the first input of the second adder of the signals of the differential channel, the second input of the third adder of signals of the total and difference channels; the first output of the third and subsequent power dividers in two directions is connected in series with the second input of the adder of the signals of the differential channel, whose number is two units less than the number of the said power divider, with the second input of the adder of the signals of the total and difference channels with a number one less than the number of the aforementioned power divider in two directions, and the second output of the said power dividers in two directions is connected in series with the first input of the adder signals of the differential channel with a number equal to the number of the said power divider in two directions, with the second input of the adder signals of the total and difference channels with a number one unit greater than the number of the said power divider; the first output of the N-1 power divider in two directions is connected in series with the second input N-3 of the adder of the signals of the difference channel, with the second input N-2 of the adder of the signals of the total and difference channels, and the second output is connected with the second input of the N-adder of the signals of the total and differential channels; the first output of the Nth power divider in two directions is connected in series with the second input N-2 of the adder of the signals of the difference channel, with the second input N-1 of the adder of the signals of the total and difference channels, and the second output is connected with the upper radiating element of the antenna array Δв _n : each the three radiating elements (∑ _n , Δв _n , Δн _n ) are powered by common-mode currents, and the amplitudes of the currents in the radiating elements Δн _n and Δв _n are equal to each other, the amplitudes of the currents in the radiating elements Δн _n and Δв _{n are} proportional to the amplitudes of the currents in the radiating element ntah ∑ _n ; the amplitudes of the currents in the radiating elements ∑ _n are selected from the condition of attenuation of radio waves in the direction of the folds of the terrain in the zone of approach of aircraft for landing. 3. Glide path beacon for instrumental approach of aircraft for landing at aerodromes with a high level of snow cover and terrain folds in the area of aircraft entry for landing, causing interference of radio waves in the area of the glide path, containing a device for generating signals of the total channel, a device for generating signals of the difference channel, antenna array radiating elements, the first power divider with one input and two outputs, the second power divider with one input and two outputs, two power dividers in two directions with one input and two outputs each, two phase shifters of the total channel, two phase shifters of the differential channel, two adders of the signals of the total and difference channels with the first and second inputs and one output each; each radiating element of the total channel ∑ _n , n = 1, 2, of the antenna array has one upper Δв _n and one lower Δн _n radiating element with the formation of an ordered family of two triples of radiating elements (∑ _n , Δв _n , Δн _n ), n = 1, 2, in which in each triple the lower and upper radiating elements have the same number n as the number of the radiating element ∑ _n ; the radiating elements ∑ _n are located one above the other at heights H _n , and the height H _{1 of the} first radiating element ∑ ₁ is equal to:
H ₁ = d + H ₀ ,
Where

,
λ is the wavelength; θ _hl - the given angle of the glide path; H ₀ - suspension height of the first lower radiating element of the antenna array relative to the surface of the Earth, approximately equal to 1 m; lower Δn _n and upper Δin _n radiating elements with number n are located symmetrically with respect to the n-th radiating element ∑ _n at a distance d relative to the said element; the output of the nth adder of the signals of the sum and difference channels is connected to the nth radiating element ∑ _n , the device for generating the signals of the sum channel is connected to the input of the first power divider in two directions, the outputs of which are connected in series with the phase shifters of the total channel and the first inputs of the signal adders total and differential channels; a differential channel signal generating device is connected to the input of the second power divider in two directions, the outputs of which are connected in series with the phase shifters of the difference channel and the inputs of two-directional power dividers; the first output of the first power divider in two directions is connected to the lower radiating element Δn _{1 of the} antenna array, and the second output is connected to the second input of the second adder of the sum and difference channel signals; the first output of the second power divider in two directions is connected to the second input of the first adder of the signals of the total and difference channels, and the second output of the said divider is connected to the upper radiating element of the antenna array: each three radiating elements (∑ _n , Δв _n , Δн _n ) are fed by common-mode currents moreover, the amplitudes of the currents in the radiating elements Δн _n and Δв _n are equal to each other, the amplitudes of the currents in the radiating elements Δн _n and Δв _{n are} proportional to the amplitudes of the currents in the radiating elements ∑ _n ; the amplitudes of the currents in the elements emitting the signals of the total channel ∑ _n are selected from the condition of attenuation of radio waves in the direction of the folds of the terrain in the zone of aircraft landing.

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