RU2624263C1 - Dual-frequency glide-path radio beacon - Google Patents

Abstract

FIELD: radio engineering, communication.

SUBSTANCE: dual-frequency glide-path radio beacon (GPRB) contains a narrow channel transmitter with an output "lateral frequencies" and an output "carrier frequency plus lateral frequencies", a wide channel transmitter with an output "lateral frequencies" of the wide channel and an output "ccarrier frequency plus lateral frequencies" of the wide channel, a distribution device with four inputs and four outputs, an antenna grid of four radiating elements mounted on the vertical mast with the suspension height of: H_{0 -} the suspension height of the first radiating element, H₀+d _- the suspension height of the second radiating element, H₀+2d - the suspension height of the third radiating element, H₀+3d the suspension height of the fourth radiating element, where H₀≤2.5 m,

, λ - the wavelength, θ_g - the given glide angle. Each radiating element comprises an aperture sensor for detecting emitted signals (hereinafter, an aperture sensor), further comprises an adder with four inputs and four outputs, and a four-input modulation depth difference measuring device.

EFFECT: increasing the glide path angle stability and the glide path beacon zone steepness, when the height of the underlying surface changes due to snow falling or grass growth or the reflecting properties of the underlying surface change due to meteorological factors while providing requirements for the magnitude of the glide path curves and the specified timing zone.

3 cl, 6 dwg, 20 tbl

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) meter waves included in the aforementioned systems form a glide path zone designed to control the aircraft in a vertical plane. The dual-frequency glide path beacon in accordance with the present invention allows instrumental approach of aircraft for landing at aerodromes with a high level of snow cover and folds of the terrain, causing interference of radio waves in the area of the glide path.

BACKGROUND OF THE INVENTION The main means of providing instrumental approach of civil aircraft for landing and landing are radio-beacon landing systems (SP) of the meter wavelength range (MB) of the ILS format (Instrument Landing System). Beacon landing systems have an almost century-old history of development. The history of the development of the joint venture in the USA is described in [Watts, S.V., Jr. Instrument Landing Scrapbook / C.V., Jr. Watts. - Trafford Publishing, 2005. 392 p.p.]. The main milestones of the development of the MB joint venture for civil aviation and the decimeter wavelength joint venture for military aviation in our country are highlighted in [NII-33 / VNIIRA. The history of the formation and development of the All-Union Scientific Research Institute of Radio Equipment - St. Petersburg: 2007. - 291 p.].

A beacon joint venture includes a course VHF radio beacon (CRM), a glide path VHF radio beacon (GRM), marker VHF radio beacons, or rangefinder equipment (DME).

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

Гц,

Гц. Поверхность, на которой разность глубин модуляции (РГМ) сигналами

и

равна нулю, называют поверхностью глиссады. Линию пересечения поверхности глиссады с вертикальной плоскостью, формируемой КРМ и проходящей через ось взлетно-посадочной полосы, называют глиссадой.The timing is installed at a point located at a distance of 200-400 m from the threshold of the runway and at a distance of 120-180 m from the axis of the runway. The timing antenna emits electromagnetic waves into the surrounding space in the frequency range 328-335 MHz, modulated in amplitude by the signals of tonal frequencies

Hz

Hz The surface on which the difference in modulation depths (RGM) signals

and

is zero, called the surface of the glide path. The line of intersection of the surface of the glide path with a vertical plane formed by the CRM and passing through the axis of the runway is called the glide path.

The simplest timing in the above systems is timing with a reference zero. It includes two antennas, the lower antenna being located at a height half that of the upper antenna. The lower antenna emits the so-called reference signal, modulated with equal modulation depth by tones of 90 and 150 Hz with phase synchronization (also called the total signal or the signal "carrier plus side frequencies"). The lower antenna, taking into account the influence of the Earth, 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 difference signal or a “side frequency” signal) and generates (taking into account the radio waves reflected from the Earth’s surface) a lobe pattern with the first maximum at an angle of 1.5 ° and the first zero at angle 3 °. This first zero signal of the "side frequencies" at an angle of 3 ° sets the glide path angle θ _gl . The glide path zone width is formed in the vicinity of said zero in the radiation pattern. The signals are phased in such a way that the “side frequency” signal emitted by the upper antenna and the reference signal “carrier plus side frequencies” (reference signal) emitted by the lower antenna are summed so that modulation by a tone signal of 150 Hz prevails below the glide path angle, and above it, at least up to an angle of 1.75θ _hl , modulation by a signal of a tone frequency of 90 Hz predominates. 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 severely degrade the performance of a zero-zone system.

In addition, during the operation of the first joint venture beacon systems, a relationship was found between the precision characteristics of the joint venture and the size and location of the terrain folds in the aircraft landing area. It should be noted that the problem of the influence of waves reflected from the surrounding area exists for all radio engineering goniometric navigation systems. However, for the joint venture this problem is critical. This is due to the high requirements for ILS accuracy, which are an order of magnitude higher than those for other aerodrome navigation and radar systems.

The natural desire of the developers of radio beacon systems to solve the problem of the influence of the terrain in the approach zone for landing on the glide path behavior was to narrow the radiation pattern of the timing antenna in a vertical plane, in which the folds of the terrain would not be irradiated with timing signals. However, it is difficult for the pilot to get into a narrow zone. The International Civil Aviation Organization (ICAO) has established the minimum angular dimensions of the ILS system coverage area. In particular, the timing must emit signals ensuring satisfactory operation of typical on-board equipment in the vertical sector with an upper boundary at an angle of 1.75θ _gl and a lower boundary at an angle of 0.45θ _gl relative to the horizontal plane or at a smaller angle of up to 0.3θ _gl , which is required to ensure compliance with the declared ILS glide path entry scheme [clause 3.1.5.3.1 in Appendix 10 to the Convention on International Civil Aviation. Aviation telecommunications. Volume 1. Radio navigation aids. ICAO, Montreal (Canada), 2006. - 606 p.].

The problem of ensuring, on the one hand, the high accuracy of setting the flight path by narrowing the antenna beams and, on the other hand, the wide areas of the SRM and the timing, was solved in beacons with a dual-frequency operating mode. In this case, the so-called capture effect is used. The dual-frequency ILS mode involves the formation of two high-frequency signals: the main signal of the narrow channel (CC) and the additional signal of the wide channel (CC). The task of the Criminal Code is the formation of narrow angular zones: glide path zones within ± 0.45θ _hl . In these zones, a linear relationship is established between the value of the RGM information parameter and the angular deviation of the aircraft from a given trajectory. The wide channel provides the pilot with information in the rest of the coverage area, "indicating" the direction of the "correct" movement towards the descent trajectory. In this case, the carrier frequency of the CC signal is shifted relative to the frequency of the CC signal by ± (5 ÷ 15) kHz.

By forming a special-purpose beam pattern, a significant increase in the level of CC signals is achieved in comparison with the level of HF signals within the narrow zone and a significant excess of the level of HF signals is compared to the level of CC signals within the guidance zone: θ≥0.45θ _gl .

In the onboard equipment, the “capture mode” is implemented, which consists in the fact that the equipment emits a signal with a larger amplitude. As a result, in a narrow sector of angles in the direction of continuation of the runway axis, the aircraft is guided by the CC signals, and beyond it - by the CC signals.

The same antenna array (AR), the so-called type M antenna array, was then used to emit CC and HF signals in the timing, then a narrow and wide channel power distribution device turned out to be a part of the two-frequency timing, which allowed the same AR to emit simultaneously the signals of the Criminal Code and the HQ.

A M-type timing belt has a three-element antenna array in which the upper, lower, and middle radiating elements are excited by the CC “side frequencies” signal, and the middle and lower radiating elements are excited by the “carrier plus side frequencies” signal. The signal "side frequencies" for the excitation of the upper and lower radiating elements have an amplitude and phase of 1/0 °, and in the middle radiating element has an amplitude and phase of 2/180 °. The carrier plus side frequencies signal in the middle radiating element has an amplitude and phase of 1/0 °, and in the lower radiating element 2/180 °.

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

Another important requirement for the timing parameters is the requirement to install and maintain a given glide path angle θ _gl .

In accordance with the ICAO recommendation [paragraph 3.1.5.1.2 in [1]), the slope angle θ _gl should be equal to 3 °. The glide path angle is set and maintained within the following limits (clause 3.1.5.1.2.1 in Appendix 10 to the Convention on International Civil Aviation. Aeronautical Telecommunications. Volume 1. Radio Navigation Aids. ICAO, Montreal (Canada), 2006. - 606 p.]:

a) 0.07θ _hl for the ILS glide path of categories I and II;

b) 0.04θ _hl for ILS category III glide path.

In connection with this Operational Guide for Civil Aerodromes of the Russian Federation, the requirements are set for the underlying surface in front of the State Russian Register [REGA 94 "Operation Manual for Civil Aerodromes of the Russian Federation, M: Air Transport. - 1996. - Table 2.2]:

- height of grass cover, not more than 0.2 m;

- thickness of virgin or compacted snow, not more than 0.2 m.

Similar requirements for the height of the grass and snow cover were established by the developers of glidepath beacons of foreign companies.

These requirements follow from the following. The principle of operation of the glide path beacon suggests that the reflection of radio waves from the Earth's surface is equivalent to the existence of a mirror image of the antenna. The glide path angle is determined by the distance between the real antenna and its mirror image, i.e. the height of the suspension of the radiating elements relative to the boundary of the air - underlying surface. With the advent of snow cover, the level of the underlying surface increases, and the height of the suspension of the radiating elements decreases accordingly, which leads to an increase in the glide path angle. Based on the permissible values of the change in the angle of glide path, restrictions are set on the permissible height of the snow cover equal to 20 cm (Operating Instructions for the landing system SP-90). The snow depth in many regions of the Russian Federation exceeds the specified value of 20 cm. For snow cover heights of more than 20 cm, it is necessary to turn off the glide path radio beacon, remove snow from the site in front of the timing antenna array with an area of 200 × 600 m, after cleaning, perform flight verification of the radio beacon parameters, after which put the timing into operation. As a result of disabling the timing for the time of snow removal and flight inspection, the airfield remains without radio support for the glide path. This reduces the regularity and safety of aircraft. Snow removal is associated with large material and time costs, since the volume of snow removed can exceed 24,000 m3.

Proposed in RF patent No. 2429 499 C2, IPC G01S 1/16 (2006.01), Glide path radio beacon, authors Voitovich N.I., Zhdanov B.V., Sokolov A.N., by application 2009116323/09 04/28/2009. (priority 04/28/2009) the antenna array as part of a glide path radio beacon solves the problem of snow influence, namely, it forms a stable glide path with changes in snow depth to the maximum height observed at airfields of the Russian Federation (equal to 80 cm), unlike existing analogues for which the maximum permissible snow depth is 20 cm. Thus, during operation landing systems with the aforementioned antenna array there is no need to turn off the timing for the snow removal period (reducing safety and regularity of flights) and to perform snow removal from the site in front of a 200 × 600 m glide path beacon.However, at aerodromes that simultaneously have large terrain folds in the approach zone of the aircraft for landing (commensurate with the size of the Fresnel zone), and the height of the snow cover significantly exceeds 20 cm, the application of the technical solution according to patent No. 2429499, as shown below, in one frequency beacons difficult.

So, the first timing of the decimeter wave range with a reference zero is known [G.A. Pakholkov, V.V. Kashinov et al. "Goniometric radio engineering landing systems." - M .: Transport.- 1982, p. 18], comprising a signal generating device for the total channel, a signal generating device for the differential channel, the first and second antennas spaced vertically, the lower antenna being powered by the signals of the total channel, and the upper antenna powered by the signals of the differential channel. The signal of the total channel refers to the signal generated by modulating high-frequency oscillations with meanders with frequencies of Ω ₁ and Ω ₂ that are identical in amplitude, while the oscillations 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 with meanders with frequencies Ω ₁ and Ω ₂ that are identical in amplitude, while high-frequency oscillations have a phase shift of 180 °. (In the landing systems of the meter range, the carrier frequency is included in the spectrum of the signals of the total channel). The information parameter in the landing systems of the meter wavelength range is the difference in modulation depths (RGM) of the emitted signal by vibrations with tonal frequencies Ω ₁ and Ω ₂ , and in the systems of the decimeter wavelength range the so-called signal hearing coefficient (KRS) with modulation frequencies Ω ₁ and Ω ₂ .

Timing with a reference zero is the simplest type of timing; it has been widely used at aerodromes of civil and military aviation.

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 area), 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. As a result, at airfields with forests located near the end of the runway, the range of the timing decreases.

The second timing is known [Australian Patent No. 1545035, Application No. 44640/77, Instrument landing system glidepath antenna array and drive therefor [Australia No. 8121/76, filed 12 Nov. 1976; Int. CL ² G01S 1/18], comprising a sum channel signal generating device, a differential channel signal generating device, first and second, third and fourth antennas spaced vertically at equal distances from each other, wherein (when counting from the bottom up) the second and fourth the antennas are powered by the signals of the difference channel, and the first and third antennas are powered by the 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.

, λ - длина волны, θ_г - заданный угол глиссады. В упомянутом патенте передатчик узкого канала с выходом "боковые частоты" и выходом "несущая плюс боковые частоты" представлен двумя устройствами: устройством формирования сигналов разностного канала и устройством формирования сигналов суммарного канала.The third timing is known (Patent No. 2429499, Russian Federation C2, IPC G01S 1/16 (2006.01) Glide path beacon (options). Voitovich NI, Zhdanov BV, Sokolov AN, Applicants and patent holders: Voitovich N .I., Zhdanov B.V. No. 2009116323/09 claimed on April 28, 2009; published on September 20, 2011, Bull. No. 26. - 40 pp., Ill.) Containing a narrow channel transmitter with an output of “side frequencies” "and with the output" carrier plus side frequencies ", an antenna array of four radiating elements mounted on a vertical mast with suspension heights: Н ₀ - suspension height of the first radiating element, Н ₀ + d second suspension height radiating element, Н ₀ + 2d - suspension height of the third radiating element, Н ₀ + 3d suspension height of the fourth radiating element, where Н ₀ ≤2.5 m,

, λ is the wavelength, θ _g is the given glide path angle. In the aforementioned patent, a narrow channel transmitter with an output of “side frequencies” and an output of “carrier plus side frequencies” is represented by two devices: a device for generating signals of a difference channel and a device for generating signals of the total channel.

A disadvantage of the well-known third timing is the presence of a deep interference minimum in the region above the glide path when adjusting the timing with deep notch in the radiation pattern for the signal in the region below the glide path angle, which is required to form the glide path without curvature at aerodromes with high folds in the landing area of the aircraft.

The fourth timing is known. [SP-90, glide path radio beacon (RMG). Technical description ICRV.461512.020TO, NIIIT-RTS, 1996-1999], comprising a narrow channel transmitter with a narrow channel side frequency output and a narrow channel carrier plus side frequency output, a wide channel transmitter with a carrier plus side frequency output a wide channel, a linear M type antenna array of three radiating elements located on a vertical mast, a switchgear with three inputs and three outputs, an aperture control device.

However, the fourth known timing has disadvantages:

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

- the difference in depths of the modulation signal of the wide channel signal is constant throughout the timing zone, i.e. the 150 Hz tone signal prevails over the 90 Hz tone signal both below the glide path angle and above the glide path angle. The predominance of a 150 Hz tone signal over a 90 Hz tone signal below the glide path angle over a wide channel coincides with that in a narrow channel. However, above the glide path angle, this predominance contradicts the ratio of tone signals in a narrow channel, which is a disadvantage of the well-known fifth timing.

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 01.11.89. 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.

US patent No. 5546095, Alfred R. Lopez, Non-imaging glideslope antenna systems, publ. 08/13/2006, H01Q 3/30, H01Q 21/10.

Patent Alfred R. Lopez. Non-imaging glideslope antenna systems (US patent No. 5546095, publ. 13.08 1996, Int. CL ⁶ H01Q 3/30, H01Q 21/10).

Their common disadvantage is the low level of emitted signals in the vicinity of the lower boundary of the timing zone.

As a prototype, the authors selected the third known timing.

Disclosure of invention

The technical result of the invention is aimed at improving the stability of the glide path angle and the steepness of the zone of the glide path beacon 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 meteorological factors.

, λ - длина волны, θ_г - заданный угол глиссады, при этом каждый излучающий элемент содержит датчик апертурного контроля излучаемых сигналов (далее, апертурный датчик), дополнительно содержит передатчик широкого канала с выходом "боковые частоты" широкого канала и выходом "несущая плюс боковые частоты" широкого канала, распределительное устройство с четырьмя входами и четырьмя выходами, сумматор с четырьмя входами и с четырьмя выходами и устройство измерения разности глубин модуляции с четырьмя входами, при этом выход "боковые частоты" передатчика узкого канала соединен с первым входом распределительного устройства, выход "боковые частоты" широкого канала передатчика широкого канала соединен со вторым входом распределительного устройства, выход "несущая плюс боковые частоты" узкого канала передатчика узкого канала соединен с третьим входом распределительного устройства, выход "несущая плюс боковые частоты" широкого канала передатчика широкого канала соединен с четвертым входом распределительного устройства, каждый К-ый (К=1, …, 4) выход распределительного устройства соединен с входом К-го излучающего элемента, апертурный датчик К-го излучающего элемента соединен с К-ым входом сумматора, а К-ый выход сумматора соединен с К-ым входом измерителя разности глубин модуляции.The technical result is achieved by the fact that a two-frequency glide slope beacon containing a narrow channel transmitter with an output of "side frequencies" and an output of "carrier plus side frequencies", an antenna array of four radiating elements mounted on a vertical mast with suspension heights: H ₀ - height of the first suspension radiating element, Н ₀ + d suspension height of the second radiating element, Н ₀ + 2d - suspension height of the third radiating element, Н ₀ + 3d suspension height of the fourth radiating element, where Н ₀ ≤2.5 m,

, λ is the wavelength, θ _g is the given glide path angle, each emitting element contains an aperture control sensor of the emitted signals (hereinafter, the aperture sensor), further comprises a wide channel transmitter with a wide channel side output and a carrier plus side output the frequency of the wide channel, a switchgear with four inputs and four outputs, an adder with four inputs and four outputs and a device for measuring the difference in modulation depth with four inputs, while the output is "side frequencies" the narrow channel sensor is connected to the first input of the switchgear, the wideband transmitter side channel output is connected to the second switchgear input, the carrier plus side frequencies of the narrow channel transmitter narrow channel is connected to the third switchgear input, the carrier plus output lateral frequencies "of the wide channel of the wide channel transmitter is connected to the fourth input of the switchgear, each K-th (K = 1, ..., 4) output of the switchgear is is dined with the input of the Kth emitting element, the aperture sensor of the Kth emitting element is connected to the Kth input of the adder, and the Kth output of the adder is connected to the Kth input of the meter for the difference in modulation depths.

, четыре согласованные нагрузки, причем, каждый направленный ответвитель состоит из первой линии передачи с первым и третьим плечами и второй линии передачи со вторым и четвертым плечами, связь между которыми определяется коэффициентом связи α_n (n=1, …, 4), для первого и шестого направленного ответвителя

, где 0≤а≤0,8; для второго и четвертого направленного ответвителя величина коэффициента связи α₂=α₄=β, 0,2<β<0,7; для третьего и пятого направленного ответвителя величина коэффициента связи равна

; при этом, первый вход распределительного устройства последовательно соединен с первой линией передачи первого направленного ответвителя, первым фазовращателем на, первой линией передачи второго направленного ответвителя, первой линией передачи пятого направленного ответвителя и первой согласованной нагрузкой, вторая линия передачи второго направленного ответвителя вторым плечом соединена со второй согласованной нагрузкой, а четвертым плечом последовательно соединена со вторым фазовращателем и первой антенной; второй вход распределительного устройства последовательно соединен со второй линией передачи первого направленного ответвителя, первой линией передачи четвертого направленного ответвителя, второй линией передачи пятого направленного ответвителя и третьей согласованной нагрузкой, вторая линия передачи четвертого направленного ответвителя вторым плечом соединена с третьей согласованной нагрузкой, а четвертым плечом последовательно соединена с третьим фазовращателем и четвертой антенной; третий вход распределительного устройства последовательно соединен со второй линией передачи шестого направленного ответвителя, четвертым фазовращателем, первой линией передачи пятого направленного ответвителя и второй антенной; четвертый вход распределительного устройства последовательно соединен с первой линией передачи шестого направленного ответвителя, второй линией передачи третьего направленного ответвителя и третьей антенной.Also, the technical result is achieved in that the switchgear with four inputs and four outputs contains six directional couplers, four fixed phase shifters on

, four matched loads, each directional coupler consisting of a first transmission line with first and third shoulders and a second transmission line with second and fourth shoulders, the connection between which is determined by the coupling coefficient α _n (n = 1, ..., 4), for the first and the sixth directional coupler

where 0≤ a ≤0.8; for the second and fourth directional coupler, the coefficient of coupling α ₂ = α ₄ = β, 0.2 <β <0.7; for the third and fifth directional coupler, the coupling coefficient is

; wherein, the first input of the switchgear is connected in series with the first transmission line of the first directional coupler, the first phase shifter on, the first transmission line of the second directional coupler, the first transmission line of the fifth directional coupler and the first matched load, the second transmission line of the second directional coupler with the second arm connected to the second matched load, and the fourth arm is connected in series with the second phase shifter and the first antenna; the second input of the switchgear is connected in series with the second transmission line of the first directional coupler, the first transmission line of the fourth directional coupler, the second transmission line of the fifth directional coupler and the third matched load, the second transmission line of the fourth directional coupler with the second arm connected to the third matched load, and the fourth arm in series connected to the third phase shifter and fourth antenna; the third input of the switchgear is connected in series with the second transmission line of the sixth directional coupler, the fourth phase shifter, the first transmission line of the fifth directional coupler and the second antenna; the fourth input of the switchgear is connected in series with the first transmission line of the sixth directional coupler, the second transmission line of the third directional coupler and the third antenna.

; причем, каждый направленный ответвитель состоит из первой линии передачи с плечами 1 и 3 и второй линии передачи со вторым и четвертыми плечами, для первого и третьего направленных ответвителей коэффициент связи χ_n между первой и второй линиями передач равен χ₁=χ₃=0,707, а для второго и третьего направленных ответвителей коэффициент связи между первой и второй линиями передач равен

; при этом первый вход сумматора последовательно соединен с первым фиксированным фазовращателем, первой линией передачи первого направленного ответвителя, вторым фиксированным фазовращателем, вторым плечом второго направленного ответвителя; второй вход сумматора последовательно соединен с третьим фиксированным фазовращателем, первой линией передачи третьего направленного ответвителя, первым плечом второго направленного ответвителя; третье плечо второго направленного ответвителя соединено с первым выходом сумматора; четвертое плечо второго направленного ответвителя соединено со вторым выходом сумматора; третий вход сумматора последовательно соединен со второй линией передачи первого направленного ответвителя, вторым плечом четвертого направленного ответвителя; четвертый вход сумматора последовательно соединен со второй линией передачи третьего направленного ответвителя, четвертым фиксированным фазовращателем, первым плечом четвертого направленного ответвителя; третье плечо четвертого направленного ответвителя соединено с третьим выходом сумматора; четвертое плечо третьего направленного ответвителя соединено с четвертым выходом сумматора.An adder with four inputs and four outputs contains four directional couplers and four fixed phase shifters on

; moreover, each directional coupler consists of a first transmission line with arms 1 and 3 and a second transmission line with second and fourth arms, for the first and third directional couplers, the coupling coefficient χ _n between the first and second transmission lines is χ ₁ = χ ₃ = 0.707, and for the second and third directional couplers, the coupling coefficient between the first and second transmission lines is

; wherein the first input of the adder is connected in series with the first fixed phase shifter, the first transmission line of the first directional coupler, the second fixed phase shifter, the second shoulder of the second directional coupler; the second input of the adder is connected in series with the third fixed phase shifter, the first transmission line of the third directional coupler, the first shoulder of the second directional coupler; the third arm of the second directional coupler is connected to the first output of the adder; the fourth arm of the second directional coupler is connected to the second output of the adder; the third input of the adder is connected in series with the second transmission line of the first directional coupler, the second shoulder of the fourth directional coupler; the fourth input of the adder is connected in series with the second transmission line of the third directional coupler, the fourth fixed phase shifter, the first arm of the fourth directional coupler; the third arm of the fourth directional coupler is connected to the third output of the adder; the fourth arm of the third directional coupler is connected to the fourth output of the adder.

The use of an antenna array with the indicated suspension heights and the specified amplitude-phase distribution of currents of the UK signals in the radiating elements ensures independence of the glide path angle from the height of the snow cover.

The out-of-phase feeding of the first three IEs, consisting of the first, second, and third antennas, with respect to the second three of antennas, consisting of the second, third, and fourth antennas, allows one to “cut” in radiation patterns for narrow channel signals at small elevation angles and thereby significantly weaken the influence of the folds of the relief on the magnitude of the curvature of the glide path.

The use of an antenna array with the indicated height of the suspension and the specified amplitude-phase distribution of the currents of the HF signals in the radiating elements ensures the formation of the glide path zone along the HF with a change in the sign of the RGM when crossing the glide path angle. As a result, a tone with a sound frequency of 150 Hz prevails both in a narrow and a wide channel below the glide path angle, and a tone with a sound frequency of 90 Hz prevails above the glide path angle.

The inclusion of an additional wide-channel transmitter in the timing system with the wide channel side frequencies output and the wide channel carrier plus side frequencies output, a switchgear with four inputs and four outputs, and their connection in the aforementioned manner, made it possible to provide a "free" timing zone in vertical plane.

The inclusion of an additional adder with four inputs and four outputs and a device for measuring the difference in modulation depth with four inputs made it possible to provide control signals and measure the timing parameters in a simple way (without resorting to signal delay in the circuit using transmission line segments); "0 RGM UK", "0 RGM ShK", "the steepness of the RGM UK" and "the steepness of the RGM ShK".

The solution to these and other problems is further illustrated by the text and figures in the figures.

Brief Description of the Drawings

In FIG. 1 is an electrical structural diagram of a dual frequency glide path beacon of the present invention. In FIG. 1 adopted the following notation:

1 - dual-frequency glide path beacon;

2 - a narrow channel transmitter with an output of the "side frequencies" of the narrow channel (BCh CC) and the output of the "carrier plus side frequencies" of the narrow channel (BCH CC);

3 - a wide channel transmitter with an output of the "side frequencies" of the wide channel (BF HF) and the output of the "carrier plus side frequencies" of the wide channel (NFC HF);

4 - switchgear with four inputs: 411, 412, 413 and 414 and four outputs: 421, 422, 423 and 424;

5 - antenna array of radiating elements 51, 52, 53 and 54;

6 - aperture sensors 61, 62, 63 and 64;

7 - adder with four inputs: 711, 712, 713 and 714 and with four outputs; 721, 722, 723 and 724;

8 - a device for measuring the difference in modulation depths (RGM meter) with four inputs: 81, 82, 83 and 84.

In FIG. 2 shows a switchgear 4 comprising:

9 - the first directional coupler (HO1);

10 - second directional coupler (HO2);

11 - the third directional coupler (HO3);

12 - fourth directional coupler (HO4);

13 - fifth directional coupler (HO5);

14 - sixth directional coupler (HO6);

;15 - the first fixed phase shifter on

;

;16 - the second fixed phase shifter on

;

;17 - the third fixed phase shifter on

;

;18 - fourth fixed phase shifter on

;

19 - the first agreed load;

20 - the second agreed load;

21 - the third agreed load;

22 - fourth agreed load.

In FIG. 3 shows an adder 7 with four inputs: 711, 712, 713 and 714 and with four outputs: 721, 722, 723 and 724, containing:

23 - the first directional coupler (HO7);

24 - second directional coupler (HO8);

25 - the third 25 directional coupler (HO9);

26 - the fourth directional coupler (HO10);

27 - the first fixed phase shifter at π / 2;

28 - second fixed phase shifter at π / 2;

29 - the third fixed phase shifter at π / 2;

30 - fourth fixed phase shifter at π / 2.

In FIG. 4 are presented:

31 is the radiation pattern F of the _{warhead of the criminal code} (θ) in the vertical plane, taking into account the influence of the Earth for the signal “side frequencies” of a narrow channel;

32 is a directivity pattern F of the _{NCH of the CC} (θ) in the vertical plane, taking into account the influence of the Earth for the signal "carrier plus side frequencies" of a narrow channel.

In FIG. 5 are presented:

33 is a radiation pattern F of a _{warhead of a barcode} (θ) in a vertical plane, taking into account the influence of the Earth for a “side frequency” signal of a wide channel;

34 is a directivity pattern F of the _{NCH of the CC} (θ) in the vertical plane, taking into account the influence of the Earth for the signal "carrier plus side frequencies" of a wide channel.

In FIG. Figure 6 shows the dependence 35 of the difference in modulation depths on the elevation angle θ.

, λ - длина волны, θ_гл - заданный угол глиссады.Turning to FIG. 1, which shows, in accordance with the present invention, an electrical structural diagram of a two-frequency glide path beacon for instrumental approach of aircraft for landing at aerodromes with a high level of snow cover and terrain folds in the aircraft approach zone for landing, causing interference of radio waves in the area of the glide path. The glide path beacon 1 contains a narrow channel transmitter 2 with a narrow channel (side frequency) “side frequency” output and a narrow channel (carrier plus side frequency) output (narrow frequency channel), a wide channel 3 transmitter with a wide channel “side frequency” output (base frequency CC) ) and a “carrier plus side frequencies” output of a wide channel (NFB ШК), switchgear 4 with first 411, second 412, third 413 and fourth 414 inputs and first 421, second 422, third 423 and fourth 424 outputs, antenna array 5 of four radiating elements 51, 52, 53 and 54 with aperture sensors 61, 62, 63 and 64, respectively, the adder 7 with the first 711, second 712, third 713 and fourth 714 inputs and with the first 721, second 722, third 723 and fourth 724 outputs and a device for measuring the difference in modulation depths (RGM meter) with first 81, second 82 , third 83 and fourth 84 entrances. Antenna array 5 of four radiating elements 51, 52, 53, 54 is mounted on a vertical mast with suspension heights: Н ₀ - suspension height of the first radiating element 51, H ₀ + d - suspension height of the second radiating element 52, Н ₀ + 2d - height suspension of the third radiating element 53, H ₀ + 3d the height of the suspension of the fourth radiating element 54, where H ₀ ≤2.5 m for the timing of the meter wavelength range,

, λ is the wavelength, θ _hl is the given glide path angle.

Narrow channel transmitter 2 with narrow channel side frequencies (BF CC) and narrow channel carrier plus side frequencies (LFB) output, wide channel 3 transmitter with wide channel side frequencies (BF CC) and the carrier plus side frequencies of the “wide channel” (NSC ShK) are made as they are, for example, in serial beacons of the SP-90 meter wavelength range produced by the Chelyabinsk Radio Plant “Polet” JSC and operated at civil and aerodromes of jointly based civil and state th Aviation.

Switchgear 4 (FIG. 2) with first 411, second 412, third 413 and fourth 414 inputs and first 421, second 422, third 423 and fourth 424 outputs and an adder (FIG. 3), as will be shown below, can be made based on directional couplers in strip design and calculated according to formulas from well-known directories.

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 radiating elements 51-54 of the antenna array in a one-meter timing. UHF-Yagi antennas, horn antennas that are part of the PRMG-6 stationary beacon, or antennas with narrower radiation patterns in the vertical plane, for example, resonator antennas with a partially transparent surface, can be used in the timing of the decimeter range.

As probes 6, electric dipoles or magnetic dipoles (frames) short in comparison with the wavelength can be used.

As a RGM 8 meter, any serial RGM meter can be used, for example, the landing and navigation signal analyzer ASPN-1, manufactured by the Radio Engineering Systems Scientific and Production Association, Chelyabinsk.

These timing devices are interconnected as follows (Fig. 1). The output of the BCh CC of the transmitter 2 of the narrow channel is connected to the first input 411 of the switchgear, the output of the BCh CC of the transmitter 3 of the wide channel is connected to the second input 412 of the switchgear, the output of the BCH of the transmitter 2 of the narrow channel is connected to the third 413 input of the switchgear, the output of the BCH of the CC of the transmitter 3 a wide channel is connected to the fourth input 414 of the switchgear, each 42Kth (hereinafter K = 1, ..., 4) the output of the switchgear is connected to the input of the 5Kth emitting element, each 6Kth aperture second sensor is connected with 71K-th adder input, and 72K-th output of the adder is connected to 8K-th input meter DDM.

The glide path beacon operates as follows. Signals of the narrow channel 2 transmitter from the narrow channel side frequency output (BC frequency) and the narrow channel carrier plus side frequency output (BC frequency) and wide channel 3 transmitter from the wide channel side frequency output (BC frequency) and output The "carrier plus side frequencies" of the wide channel (NFC HF) are distributed by the device 4 between the four radiating elements 51-54, which are emitted into the surrounding space. The signals from the aperture sensors 61-64 installed in the radiating elements 51-54, respectively, are sent to the inputs of the adder 7, which generates signals for monitoring the timing parameters that carry information about the position of the specified glide path angle and the slope of the glide path. The RGM meter provides processing of the generated signals and an indication of the parameters: "0 RGM UK", "0 RGM ShK", "steepness of the RGM UK" and "steepness of the RGM ShK".

The presented block diagram of the timing (Fig. 1) provides the formation of the outputs of the radiating elements of the amplitude-phase distribution for signals of narrow and wide channels in accordance with the following table 1.

, (коэффициент а далее называется коэффициентом вырезки в диаграмме направленности УК); d₁=d₃=с₂, d₂=d₄=с₃ излучение сигналов УК можно представить как результат излучения двух троек излучающих элементов (ИЭ). В первую тройку следует включить 51-ый ИЭ и 53-ий ИЭ, излучающие синфазные с равной амплитудой сигналы БЧ УК, и расположенный в середине между ними 52-ой ИЭ, излучающий синфазный с ними, равный по амплитуде сигнал НБЧ УК. Во вторую тройку ИЭ следует включить 52-ой ИЭ и 54-ый ИЭ, излучающие синфазные с амплитудой а сигналы БЧ УК, и расположенный в середине между ними 53-ой ИЭ, излучающий синфазный с ними и с амплитудой a сигнал НБЧ УК. При этом сигналы первой и второй троек сдвинуты относительно друг друга по фазе на величину ψ₂-ψ₁.When b ₁ = b ₂ , b ₂ = b ₄ ,

, (the coefficient a is hereinafter referred to as the clipping coefficient in the radiation pattern of the criminal code); d ₁ = d ₃ = s ₂ , d ₂ = d ₄ = s _{3 the} radiation of the UK signals can be represented as the result of the radiation of two triples of radiating elements (IE). The first three should include the 51st IE and 53rd IE, emitting in-phase BC equal-phase signals with equal amplitude, and the 52nd IE located in the middle between them, radiating in-phase with them, equal in amplitude NSC BC signal. The 52nd IE and the 54th IE emitting in-phase BC signals in amplitude and amplitude 53 and the 53rd IE located in the middle between them, radiating in-phase with them and with amplitude a NSC BC signals in the second three should be included. In this case, the signals of the first and second triples are phase shifted relative to each other by ψ ₂ -ψ ₁ .

As shown in patent RU 2429499 for application 200911623/09 dated April 28, 2009, “Glide path beacon (options)” with the indicated amplitude-phase distribution of currents in triples of the IE, the glide path zone remains unchanged, despite the change in the height of the emitters from the underlying surface due to loss snow or melting snow or changes in the reflective properties of the underlying surface.

Here coefficient a is a parameter that regulates the “clipping” in the total radiation pattern. Coefficient a can take a value from "0" (no cutting) to a value of 0.7-0.8 (for 0 < a <0.8 in the case of a perfectly flat underlying surface in the region of small elevation angles a "false" glide path cannot appear) .

If the signals of the second three are out of phase with respect to the signals of the first three, it is possible to adjust (decrease, with increasing a ) the level of the UK signal in the region of small elevation angles and thus significantly reduce the level of irradiation of the terrain folds responsible for glide path curvature when using standard beacons with zero grating.

The radiation patterns in the vertical plane at a = 0.577: F _{CK UK} (θ) for signals CK UK (31), F _{LBK UK} (θ) for signals LBK UK (32) are shown in FIG. 4. The radiation patterns are calculated with the following source data, shown in table 2.

From the consideration of the graphs in FIG. Figure 4 shows that, along with a significant weakening of the field at small elevation angles, which is important for eliminating glide path curvatures, an interference zero appears in the directional zone of the timing _belt in the directional pattern F of the _{NLF CC} (θ) at an angle θ ₁ ≈ 4.5 °, which would be a disadvantage with single-frequency timing.

This disadvantage is eliminated by including in the composition of the timing belt an additional wide-channel transmitter, elements of the microwave path in the switchgear and the emission of the timing signals of the wide channel by the radiating elements 51-54.

As can be seen from table 2, the radiation of HF signals can also be represented as the result of the radiation of two triples of radiating elements (IE). The first three should include the 51st IE and the 53rd IE, emitting in-phase HF signals of common frequency and the 52nd IE located in the middle between them, emitting in-phase signal with them and equal in amplitude to the signal of the low-frequency signal. The 52nd IE and 54th IE, radiating in-phase signals of equal frequency amplitude of the HF and the 53rd IE located in the middle between them, emitting an in-phase signal of the low frequency signals of common mode and equal amplitude, should be included in the second three IEs. Therefore, when the height of the snow cover on the underlying surface changes or its reflective properties change, the position of the zero value in the radiation patterns at the glide path angle will be preserved.

Vertical radiation patterns are shown in FIG. 5: F _{CU CC} (θ) for the CU CC signals (33), F _{CNB SK} (θ) for the CNB CC signals (34).

As can be seen from the consideration of MD charts (Fig. 5) for wide-channel signals, a large level is observed in the MD both at small elevation angles and in the vicinity of 4.5 °. Moreover, at elevation angles below the glide path angle, the signals of the warhead HF and LFH HF are in phase with each other, and above the angle of the glide path are in-phase with each other. This allows you to generate signals so that modulation of the high-frequency signal by a tone signal of 150 Hz prevails below the glide path angle, and above it modulation of the high-frequency signal by a tone signal of 90 Hz prevails. Thus, the dependence of the RGM on the elevation angle over a wide channel by the nature of the predominance of tonal frequencies over each other is identical to the dependence of the RGM on the elevation angle on a narrow channel. This is a significant difference between the operation of the wide channel of the present invention and the operation of the wide channel of analogues in which the RGM is independent of elevation. The magnitude of the RGM in a wide channel of analogues is constant for any elevation. Throughout the entire coverage area, a 150 Hz tone signal prevails over a 90 Hz tone signal.

In FIG. Figure 6 shows the calculated total dependence of the RGM on the elevation angle formed in space while emitting narrow and wide channel signals of the present invention. The calculations of the mentioned dependence are performed according to the exact formulas for calculating the RGM given in the article by Zotov A.V., Voitovich N.I., Zhdanov B.V. "Modeling the work of a dual-frequency instrumental aircraft landing system" in the Bulletin of the South Ural State University, Computer Technologies, Management, Radio Electronics series, 2013, Volume 13, No. 4. - Page 55-69.

As can be seen from the consideration of the graph in FIG. 6, with the simultaneous emission of narrow and wide channel signals in space, a monotonic dependence of the RGM on the elevation angle is formed, which is typical for the operation of analogue beacons.

The switchgear 4 (Fig. 2) with the first 411, second 412, third 413 and fourth 414 inputs and with the first 421, second 422, third 423 and fourth 424 outputs (hereinafter, the switchgear) contains the first 9 (HO1), second 10 (НО2), third 11 (НО3), fourth 12 (НО4), fifth 13 (НО5), and sixth 14 (НО6), directional couplers (НО), first 15, second 16, third 17, and fourth 18 fixed phase shifters on π / 2, first 19, second 20, third 21 and fourth 22 coordinated loads.

, для второго 10 НО и четвертого 12 НО величина коэффициента связи α₂=α₄=β, 0,2<β<0,7, для третьего 11 и пятого 13 НО величина коэффициента связи равна

.Each of the mentioned BUT consists of a first transmission line with the first and third shoulders and a second transmission line with the second and fourth shoulders, the connection between which is determined by the coupling coefficient α _n where n is the number of the BUT, n = 1, ..., 6. For the first 9 BUT and sixth 14 BUT

, for the second 10 BUTs and the fourth 12 BUTs, the coupling coefficient α ₂ = α ₄ = β, 0.2 <β <0.7, for the third 11 and fifth 13 BUTs, the coupling coefficient is

.

These switchgear devices are interconnected as follows. The first input 411 of the switchgear is connected in series with the first shoulder 91 of the first transmission line of the first 9 HO (HO1), the first phase shifter 15, the first shoulder 101 of the first transmission line of the second 10 NO (HO2), the first 111 shoulder of the first transmission line of the third 11 NO (HO3) and the first agreed load 19; the second transmission line of the second 10 NO (HO2) by the arm 102 is connected to the second 20 matched load, and by the arm 104 is connected in series with the second 16 phase shifter, the first output 421 of the switchgear, which is connected to the first 51 radiating element.

The second input 412 of the switchgear is connected in series with the second arm 92 of the second transmission line of the first 9 NO (HO1), the first arm 121 of the first transmission line of the fourth 12 NO (HO4), the second arm 132 of the second transmission line of the fifth 13 NO (HO5) and the third matched load 21; the second transmission line of the fourth 12 HO (HO4) by the second arm 122 is connected to the fourth matched load 22, and the arm 124 is connected in series with the third phase shifter 17, the fourth output 424 of the switchgear, which is connected to the fourth radiating element 54.

The third 413 input of the switchgear is connected in series with the second shoulder 142 of the second transmission line of the sixth 14 HO (HO6), the fourth 18 phase shifter, the first shoulder 131 of the first transmission line of the fifth 13 HO (HO5), the second output 422 of the switchgear, which is connected to the second radiating element 52.

The fourth input 414 of the switchgear is connected in series with the first shoulder 141 of the first transmission line of the sixth 14 HO (HO6), the second shoulder 112 of the second transmission line of the third 11 HO (HO3), the third output 423 of the switchgear, which is connected to the third radiating element 53.

а фаза равна минус 90°; сигнал в плечо n2 при этом не ответвляется.The distribution device operates as follows. When a signal is sent to the first arm n1 of the n-th HO, the first transmission line is the main transmission line, and the second line (with shoulders n2 and n4) is the connected transmission line. We assume that the signal amplitude in the first arm n1 is 1, and the phase is zero, then the signal amplitude in the arm n4 will be α _n and the phase is 0; the signal amplitude in the arm n3 will be equal to

and the phase is minus 90 °; the signal to the arm n2 does not branch out.

далее задерживается на 90° фазовращателем 15, изменяется в а₂раз при ответвлении в НO2, задерживается на 90° фазовращателем 16. В результате (если пренебречь задержками сигнала и потерями сигнала в соединительных кабелях) комплексная амплитуда сигнала БЧ УК на выходе 421 распределительного устройства (на входе ИЭ 51) равна

.The signal of the warhead CC from the input 411 to the input of the radiating element 51 passes along the first line 91-93 of the first 9 BUT, changing by

then it is delayed by 90 ° by the phase shifter 15, it changes by a factor of ₂ when branching into НО2, it is delayed by 90 ° by the phase shifter 16. As a result (if we neglect the signal delays and signal losses in the connecting cables), the complex amplitude of the BC signal at the output 421 of the distribution device ( at the input of IE 51) is equal to

.

Similarly, the complex amplitudes of the BC signal of the CC on the other radiating elements of the antenna array 5 are calculated, as well as the complex amplitudes of the signals of the LF BC, BF HF and LFB HF on all radiating elements 51-54. The values of the complex amplitudes of the signals are presented in the above table 2.

. Каждый из упомянутых НО состоит из первой линии передачи с плечами С1 и С3 и второй линии передачи с плечами С2 и С4, где С - номер НО с коэффициентом связи α_n (n=7, 8, 9, 10), где n - номер в обозначении НО на фиг. 6: НО n. Для первого 23 (НO7) и третьего 25 НО (НO9) коэффициент связи между первой и второй линиями передач равен α₇=α₉=0,707, а для второго (НO8) 24 и четвертого (НО10) 26 НО коэффициент связи между первой и второй линиями передач равен

.The adder 7 (Fig. 3) with the first 711, second 712, third 713 and fourth 714 inputs and with the first 721, second 722, third 723 and fourth 724 outputs (hereinafter adder) contains the first 23 NO (HO7), the second 24 NO ( HO8), third 25 HO (HO9), fourth HO 26 (HO10) and first 27, second 28, third 29 and fourth 30 fixed phase shifters on

. Each of these BUTs consists of a first transmission line with shoulders C1 and C3 and a second transmission line with shoulders C2 and C4, where C is the number of the BUT with the coupling coefficient α _n (n = 7, 8, 9, 10), where n is the number in the designation BUT in FIG. 6: BUT n. For the first 23 (HO7) and third 25 HO (HO9), the coupling coefficient between the first and second transmission lines is α ₇ = α ₉ = 0.707, and for the second (HO8) 24 and the fourth (HO10) 26 HO, the coupling coefficient between the first and second transmission lines equals

.

These devices of the adder 7 are interconnected as follows.

, первым плечом 231 первой линии передачи первого 23 НО (НO7), вторым фиксированным 28 фазовращателем на

, вторым плечом 242 второго 24 НО (НO8).The first input 711 of the adder is connected in series with the first 27 fixed phase shifter on

, the first shoulder 231 of the first transmission line of the first 23 HO (HO7), the second fixed 28 phase shifter on

, the second shoulder 242 of the second 24 HO (HO8).

, первым плечом 251 первой линии передачи третьего 25 НО (НO9), первым плечом 241 второго 24 НО (НO8).The second input 712 of the adder is connected in series with the third 29 fixed phase shifter on

, the first shoulder 251 of the first transmission line of the third 25 HO (HO9), the first shoulder 241 of the second 24 HO (HO8).

The third arm 243 of the second 24 HO is connected to the first output 721 of the adder, the fourth arm 244 of the second 24 HO is connected to the second 722 output of the adder.

The third input 713 of the adder is connected in series with the second shoulder 232 of the second transmission line of the first 23 BUT, the second shoulder 262 of the fourth 26 BUT.

The fourth input 714 of the adder is connected in series with the second arm 252 of the second transmission line of the third 25 BUT, the fourth 30 fixed phase shifter, the first shoulder 261 of the fourth 26 BUT.

The third arm 263 of the fourth 26 HO is connected to the third 723 output of the adder, the fourth arm 264 of the fourth 26 HO is connected to the fourth 724 output of the adder.

The adder operates as follows.

The signals of the warhead CC, NBCH UK, warhead HF, NBCH HK from aperture sensors 61-64 are fed to inputs 711-714, respectively. The signals generated by the adder on the position of the glide path in space and the steepness of the zone are sent to outputs 721-724.

The signal about the position of the glide path line is formed in the same way as in space the signal is formed on the glide path line, i.e. with a value of RGM = 0 on a narrow channel and RGM = 0 on a wide channel. These signals are called "0 RGM UK" and "0 RGM ShK", respectively. Signals containing information about the steepness of the glide path zone are formed in the adder in such a way that information about the steepness of the glide path along the CC is obtained at the output at which the RGM over the wide channel is 0, information about the steepness of the glide path along the CC is received at the output at which the RGM over the narrow equal to the channel. These signals are referred to as “steepness of RGM UK” and “steepness of RGM ShK”, respectively. Thus, the outputs of the adder form the signals "0 RGM UK", "0 RGM ShK", "the steepness of the RGM UK" and "the steepness of the RGM SHK".

(1) является суммой четырех сигналов (2), поступающих с датчиков 61-64, установленных соответственно на четырех излучающих элементах 51-54:Consider, for example, the BC signal at the output 721. The BC signal at the output 721

(1) is the sum of four signals (2) coming from sensors 61-64, installed respectively on four radiating elements 51-54:

- комплексные амплитуды сигналов от соответствующих датчиков. Они определяются величинами АФР, представленными в таблице 1.Where

- complex amplitudes of the signals from the respective sensors. They are determined by the AFR values presented in table 1.

The transmission coefficients S _71n-721 (n = 1, ..., 4) are determined from considering the wave path from the nth sensor to the output 721 in the circuit shown in FIG. 3 (3-6):

As a result, we obtain (7),

.At this output, the control signal "0 RGM UK" is formed, i.e. should be

.

In space on the glide path, the sum of the voltage of the warhead signal from the 51st and 53rd radiating elements included in the first three IEs is zero and the sum of the voltage of the warhead signal from the 52nd and 54th radiating elements included in the second three IE mentioned above is also equal to zero. Therefore, the adder must be constructed so that equalities (9-10) are satisfied:

From which it follows (11-12):

на выходе 721 сумматора равно нулю.Thus, with α ₇ = α ₉ = -3dB, the voltage

the output of the 721 adder is zero.

на выходе сумматора не равно нулю. Следовательно, РГМ УК на выходе равно нулю. Можно показать, что напряжение сигнала НБЧ ШК на выходе 721 равно нулю. Поскольку в окрестности глиссады сигнал НБЧ ШК пренебрежимо мал, то это означает, что по показаниям измерителя РГМ на выходе 721 сумматора определяют изменения в положении глиссады по УК и, стало быть, о положении глиссады, формируемой в результате излучения сигналов УК и ШК в целом. При отклонении комплексной амплитуды тока сигнала БЧ УК в одном из излучающих элементов указанные выше равенства не выполняются, в результате суммарное напряжение сигнала БЧ УК оказывается не равным нулю. Следовательно, по показаниям сигнала БЧ УК на первом выходе сумматора контролируют положение глиссады в пространстве.In the same time

at the output of the adder is not equal to zero. Consequently, the RGM CC at the output is zero. It can be shown that the voltage of the signal of the NFC BF at the output 721 is zero. Since in the vicinity of the glide path, the signal of the LFN CC is negligible, this means that according to the readings of the RGM meter at the output 721 of the adder, changes in the position of the glide path along the CC and, therefore, the position of the glide path formed as a result of the emission of CC and CC signals as a whole are determined. When the complex amplitude of the current signal of the BC AM signal is deviated in one of the emitting elements, the above equalities are not satisfied, as a result, the total voltage of the BC AM signal is not equal to zero. Therefore, according to the testimony of the warhead CC signal at the first output of the adder control the position of the glide path in space.

It can be similarly shown that additionally by performing HO8 and HO10 with a coupling coefficient

the position of the glide path angle set by the wide channel, the slope of the glide path zone along the narrow channel, and the steepness of the zone along the wide channel are controlled.

Practical examples

The calculation was performed and electrodynamic modeling of the switchgear 4, the adder 7 and the radiating element with an aperture sensor was performed, working design documentation was developed and samples of the mentioned devices were made.

The electrodynamic problem is formulated in a strict diffraction statement. The spatio-temporal non-stationary system of Maxwell equations with given initial and boundary conditions is solved numerically in the time domain by the method of finite integrals (Finite Integration Technique, FIT).

Switchgear

The calculation of the switchgear is performed with the following initial data: a = 0.578; β = 0.501.

(-6 дБ)Then

(-6 dB)

α ₂ = α ₆ = β = -6 dB

(-4,76 дБ)

(-4.76 dB)

The results of calculating the required amplitude of the coefficient of signal transmission from the specified input to the given output according to the given ratios, the results of calculating the mentioned coefficient according to the three-dimensional model of the design of the switchgear based on Maxwell equations and the experimental results on the sample of the switchgear at the operating frequency are shown in Table 3.

Adder

The adder is made of four NO and four fixed to 90 phase shifters. The coupling coefficient of HO7 and HO9 is minus 3 dB. The coupling coefficient of HO8 and HO10 is minus 6 dB:

α ₇ = α ₉ = 0.708 α ₈ = α ₁₀ = 0.501

, а при прохождении волны по первой линии НO8 и НO10 волна ослабевает в

раз.Therefore, the attenuation of the wave when passing along the first line of HO7 or HO9 is

, and when the wave passes along the first line of HO8 and HO10, the wave weakens in

time.

равна 0,355. Аналогично вычисленные коэффициенты передачи

(w=1, …, 4; n=1, …,4) представлены в таблице 4. В таблице 4 для сравнения приведены коэффициенты передачи

, полученные в результате моделирования характеристик образца сумматора и результаты измерений коэффициентов передачи

на образце сумматора.On the way from the first input 711 to the first output 721 of the adder, the BC signal is delayed by a phase shifter 27 by 90 °, attenuates 0.708 times when passing along the first line HO7, while delaying by 90 °, it branches off into H08 with a coefficient of 0.501. Thus, the amplitude of the transmission coefficient from the first input 711 to the first output 721

equal to 0.355. Similarly calculated transmission ratios

(w = 1, ..., 4; n = 1, ..., 4) are presented in table 4. In table 4, the transmission coefficients are shown for comparison

obtained as a result of modeling the characteristics of the adder sample and the measurement results of transmission coefficients

on the adder sample.

Tables 5-20 show the results of the calculation of the signal voltages of the BC HF, NBCH UK, HF HF, HF HF at each of the outputs 721 of the adder taking into account the amplitude-phase distribution of the input signals and transfer coefficients of the adder.

Exit 721 ("O RGM UK")

Exit 722 ("About RGM ShK")

Exit 723 ("The Coolness of the Criminal Code")

Exit 724 ("Coolness of the Bar")

равно 0, напряжение НБЧ УК

не равно нулю. Это обстоятельство позволяет по сигналу с амплитудой

и по сигналу с амплитудой

на выходе 721 контролировать положение 0 глиссады по УК.As can be seen from tables 5 and 6, at the output 721 the voltage of the warhead CC

equal to 0, voltage NBCH UK

not equal to zero. This circumstance allows for a signal with amplitude

and on a signal with amplitude

at the exit 721 to control the position 0 of the glide path on the Criminal Code.

By the signals at the output 722, it is possible to control the position of the glide path angle over a wide channel, and by the signals at the outputs 723 and 724 to control the slope of the zone along the CC and CC, respectively.

Radiating Element with Sensor for Timing Antenna

4 samples of the radiating element of the timing antenna array were made. The radiating element of the AR timing is a resonator antenna with a partially transparent surface, made in accordance with the patent of the Russian Federation (Voitovich N.I., Bukharin V.A., Ershov A.V., Repin N.N. Flat resonator antenna (options) / / RF patent for the invention No. 2357337, Russia, IPC H01Q 13/10. - 2007137544/09; claimed October 10, 2007, published May 27, 2009. Bull. No. 15, Priority October 9, 2007 (Russia)).

The aperture sensor is made in the form of a short asymmetric dipole introduced into the inner region of the antenna. Experiments on samples showed that the coupling coefficient of the sensor with the antenna is minus 24 dB.

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 zone of approach of aircraft for landing: at aerodromes in beam-ravine terrain, in hilly and foothill terrain; at aerodromes where the terminal safety strip abruptly breaks off 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 aerodromes listed above, using the timing of the present invention eliminates the need for snow removal or snow packing in the area in front of the lighthouse (in the so-called timing zone A, the dimensions of which are determined by the dimensions of the first 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 (4)

1. Two-frequency glide path beacon containing a narrow channel transmitter with an output of "side frequencies" and an output of "carrier plus side frequencies", an antenna array of four radiating elements mounted on a vertical mast with suspension heights: H ₀ - suspension height of the first radiating element, N ₀ + d suspension height of the second radiating element, Н ₀ + 2d - suspension height of the third radiating element, Н ₀ + 3d suspension height of the fourth radiating element, where H ₀ ≤2.5 m,

, λ is the wavelength, θ _g is the given glide path angle, with each emitting element comprising an aperture control sensor of the emitted signals (hereinafter referred to as an aperture sensor), characterized in that it further comprises a wide channel transmitter with wide channel side outputs and wide channel output carrier plus side frequencies of the "wide channel, switchgear with four inputs and four outputs, an adder with four inputs and four outputs and a modulator of difference in modulation depth with four inputs, while the output is" side the stota of the narrow channel transmitter is connected to the first input of the switchgear, the wideband transmitter side channel output is connected to the second switchgear input, the carrier plus side frequencies of the narrow channel transmitter narrow channel is connected to the third switchgear output, output carrier plus side frequencies of the "wide channel of the wide channel transmitter is connected to the fourth input of the switchgear, each K-th (K = 1, ..., 4) output of the distribution device -keeping connected to the input K of the radiating elements, each aperture sensor K-th radiating element is connected to the K-th adder input and the K-th adder output is connected to the K-th input measuring modulation depth difference. 2. Two-frequency glide path beacon according to claim 1, characterized in that the switchgear contains six directional couplers, four fixed phase shifters on

, four coordinated loads, each directional coupler consisting of a first transmission line with first and third shoulders and a second transmission line with second and fourth shoulders, the connection between the first and second lines is determined by the coupling coefficient α _n (n = 1, ... ,, 4) , for the first and third directional coupler

, where a is a coefficient equal to the ratio of the amplitudes of the signal "carrier plus side frequencies" in the third and second antennas,

; for the second and fourth directional coupler, the value of the coupling coefficient α ₂ = α ₄ = β,

; for the fifth and sixth directional coupler, the coupling coefficient is

; wherein the first input of the switchgear is connected in series with the first shoulder of the first transmission line of the first directional coupler, the first phase shifter on

, the first shoulder of the first transmission line of the second directional coupler, the first shoulder of the first transmission line of the third directional coupler and the first matched load, the second transmission line of the second directional coupler with the third arm is connected to the second matched load, and the fourth arm is connected in series with the second phase shifter on

and the first radiating element; the second input of the switchgear is connected in series with the second shoulder of the second transmission line of the first directional coupler, the first shoulder of the first transmission line of the fourth directional coupler, the second shoulder of the second transmission line of the fifth directional coupler and the third matched load, the second transmission line of the fourth directional coupler with the second arm connected to the fourth matched load, and the fourth arm is connected in series with the third phase shifter on

a fourth output and a fourth radiating element; the third input of the switchgear is connected in series with the second shoulder of the second transmission line of the sixth directional coupler, the fourth phase shifter on

, the first shoulder of the first transmission line of the fifth directional coupler and the second radiating element; the fourth input of the switchgear is connected in series with the first arm of the first transmission line of the sixth directional coupler, the second arm of the second transmission line of the third directional coupler and the third radiating element. 3. Two-frequency glide path beacon according to claim 1, characterized in that the adder with four inputs and four outputs according to claim 1 (hereinafter adder) contains four directional couplers, four fixed phase shifters on

wherein each directional coupler consists of a first transmission line with first and third shoulders and a second transmission line with second and fourth shoulders, for the first and fourth directional couplers, the coupling coefficient χ _n between the first and second transmission lines is χ ₁ = χ ₄ = 0.707, and for the second and third directional couplers, the coupling coefficient between the first and second transmission lines equal

, while the first input of the adder is connected in series with the first fixed phase shifter on

, the first shoulder of the first transmission line of the first directional coupler, the second fixed phase shifter on

, the second shoulder of the second directional coupler; the second input of the adder is connected in series with the third fixed phase shifter on

, the first shoulder of the first transmission line of the third directional coupler, the first shoulder of the second directional coupler; the third arm of the second directional coupler is connected to the first output of the adder; the fourth arm of the second directional coupler is connected to the second output of the adder; the third input of the adder is connected in series with the second shoulder of the second transmission line of the first directional coupler, the second shoulder of the fourth directional coupler; the fourth input of the adder is connected in series with the second shoulder of the second transmission line of the third directional coupler, the fourth fixed phase shifter on

, the first shoulder of the fourth directional coupler; the third arm of the third directional coupler is connected to the third output of the adder; the fourth arm of the fourth directional coupler is connected to the fourth output of the adder.

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