RU2693024C1 - Glide-path transmitter - Google Patents

Abstract

FIELD: radio equipment.

SUBSTANCE: invention relates to radio engineering and can be used in systems for instrumental approach to landing aircraft at aerodromes with high level of snow cover and complex form of terrain. Glide-path transmitter (GPT) format of landing radio beacon group (LRBG) with antenna array (AR) of radiating elements (RE) further comprises a second AR RE, wherein GPT with two AR, spaced apart in height, provides formation of "uninterrupted" glide path without use of clearance channel (not envisaged by format LRBG). In another version GPT some RE second AR combined with RE first AR. Invention provides higher reliability in comparison with two-frequency GPT, since passive microwave devices are used instead of the active device (the passageway transmitter).

EFFECT: high glide path and zone GPT stability.

3 cl, 7 dwg

Description

1. The technical field to which the invention relates.

The invention relates to radio engineering and can be used in the systems of instrumental support for the landing of state aircraft. Glide radio beacons (RMs) of decimeter waves of the landing beacon group format (PRMG), included in the above-mentioned systems, form a glide zone designed to control the aircraft in a vertical plane. Timing in accordance with the present invention allows for instrumental approach of aircraft to land at airfields with a high level of snow cover and folds of the terrain, causing interference of radio waves in the glide path.

2. The level of technology

The first timing belt of the meter wave range with a reference zero is known [G.A. Pakholkov, V.V. Kashinov and others. "Glide radio landing systems". - M .: Transport. - 1982, p. 13], containing a device for forming a total channel, a device for generating a differential channel signal, the first and second antennas separated vertically, the lower antenna being powered by the signals of the total channel, and the upper antenna being powered by differential channel signals. The signal of the total channel is understood as a signal generated by the modulation of high-frequency oscillations with tonal frequencies Ω ₁ and Ω ₂ that are the same in amplitude, while the high-frequency oscillations are in phase with each other. The signals of the difference channel are the signals of the side frequencies generated by modulating high-frequency oscillations with oscillations with frequencies Ω ₁ and Ω ₂ that are equal in amplitude, while high-frequency oscillations have a phase shift of 180 °. The information parameter in the landing systems of the meter wave range is the difference in the modulation depth (RGM) of the emitted signal by oscillations with frequencies Ω ₁ and Ω ₂ . Timing with a reference zero is the simplest type of timing, it has found wide application on the airfields of civil and state aviation.

The first known radio beacon has two significant drawbacks. First, the glide angle depends on the height of the snow cover. The permissible level of snow cover is 20 cm. Secondly, there is a high level of emission of signals at low elevation angles, which causes distortion of the glide path on airfields with elevated folds of terrain in front of the timing antenna.

Known second timing, implemented in the decimeter wavelength range (DCV) [Benin V.M. Zero-zone glide beacon with switching of radiation patterns. // Questions of radio electronics, a series of OT, 1970, vol. 6]. The state-of-the-art broadcasting center with commutation of radiation patterns is a part of the PRMG-76UM radio beacon landing group (PRMG), produced by AO Chelyabinsk Radio Plant Polet and operated on aerodromes of state aviation and on airdromes of joint basing of civil and state aviation.

The second known radio beacon contains a signal conditioning device for the landing system of the PRMG format with the "differential signal" output and the "total signal" output, the first and second antennas located on the vertical mast. At the output of the differential signal of the signal shaping device, signals are generated in the form of alternating radio pulse bursts with a modulation frequency of 1300 and 2100 Hz, while the phases of carrier oscillations of radio pulse bursts with modulation frequencies of 1300 and 2100 Hz differ by 180 degrees. The output "total signal" signals are generated in the form of alternating radio pulse bursts with a modulation frequency of 1300 and 2100 Hz, while the phases of the carrier oscillations of the radio pulse bursts with a modulation frequency of 1300 and 2100 Hz are equal to each other.

и

, где λ - длина волны, θ_гл - угол глиссады.The suspension heights h ₁ and h _{2 of the} first and second antennas relative to the surface of the earth are:

and

where λ is the wavelength, θ _hl is the glide angle.

As a result of commutation in space, two radiation patterns (DNs) are alternately formed: the so-called "upper lobe" and "lower lobe". Switching the power supply circuit of the antenna system with a frequency of 12.5 Hz creates alternate emission of signals with amplitude modulated signal of the form of a square wave with a frequency of 1300 Hz by the upper lobe and with a frequency of 2100 Hz - by the lower lobe. The intersection of the DN “upper lobe” and DN “lower lobe” determines the glide path surface. In the systems of landing decimeter wavelengths, the information parameter is the so-called signal discontinuity coefficient (RS) with modulation frequencies of 2100 and 1300 Hz.

The second known radio beacon has the same two drawbacks as the first known timing. Firstly, the glide path angle depends on the height of the snow cover, the permissible snow cover level is 10 cm. Secondly, the glide path behavior essentially depends on the shape of the terrain in the area where the aircraft approaches the landing site.

Known technical solutions designed to ensure the work of the State Russian Museum on aerodromes with varying levels of snow cover, presented in the author's certificates of the USSR for inventions and patents of the Russian Federation for the invention:

A.S. № 711845. - 2591230. Priority 03.20.78. Register 09.28.79;

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

A.S. No. 1426260. - 4125479. Priority 09/30/86. Register 05.22.88;

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

A.S. No. 287782. - 3195405. Priority 31.03.88. Register 01/02/89);

A.S. No. 1623443. - 4619435 / 24-09, Priority 12/13/88. Register 09/22/90;

A.S. No. 1626884. - №4619434 / 09. Priority 13.12.88. Register 08.10.90;

A.S. No. 1690468. - 4619436/09, Priority 12/13/88. Register 07/08/91;

A.S. No. 1690469. - 4619436/09. Priority 13.12.88. Register 07/08/91;

A.S. No. 1695758. - 4731827/09. Priority 08/22/89. Register 08/01/91;

A.S. №1715060. - 4673557/09. Priority 04/04/89. Register 10.22.91;

A.S. No. 1730923. - 4731828/09, Priority 08/22/89. Register 01/01/92;

A.S. No. 1734471. - 4673558/09. Priority 04/04/89. Register 01/15/92;

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

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

A.S. No. 1802602. - 4873721/09, Priority 11.10.90. Register 09.10.92;

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

A.S. No. 1822265. - 4887243/09, Priority 11/28/90. Register 10/12/92;

A.S. No. 1828278. - 4809235/09, Priority 04/02/90. Register 10/12/92;

The patent of the Russian Federation №21222216. - 94032782, Priority 09/08/94. Register 11/20/98.

The 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) and Australian patent No. 1 545035, Application No. 44640/77, Instrument landing system glide path antenna for drive therefor [Australia # 8121/76, filed 12 Nov. 1976; Int. CL ² G01S 1/18].

Their common drawback is the low level of the emitted signals in the region of the interference minima formed by the total signal in the timing zone. As a result, the specified timing area is not provided.

These two disadvantages are eliminated in the well-known third timing [patent RU 2624263. Dual-frequency glide path beacon on the application 2016122838 of 06/08/2016]. The proposed technical solutions are connected with the use of an additional wide (clearance) channel (Zhdanov B.V., Voitovich N.I. A glide beacon for aerodromes with a high level of snow cover. // 27th International Crimean Conference "Microwave Technology and Telecommunications Technologies (KryMiKo 2017). Sevastopol, November 5-11, 2017: materials of the conference. 8 t. - Moscow, Minsk, Sevastopol, 2017. p. 433-439). The wide channel is provided in the signal format of beacons of the meter wave band (ILS format), however, it is not provided in the format of PRMG signals.

The main problem that manifests itself with an increase in the suspension height of the radiating elements of the timing antenna in connection with an increase in their number is the appearance of additional interference minima in the DN signal of the "side frequencies" and the signal "carrier plus side frequencies" within the range of the beacon. With the use of a wide channel (with its own interference minima), due to the incoherent summation of the signals of the main and wide channels, the minima overlap. As a result, the required timing is provided.

The technical solutions proposed in the claimed patent allow eliminating interference minima in the timing area, ensuring a stable glide path independent of changes in the level and properties of the underlying surface, and create a cut in radiation at low site angles without using an additional wide channel.

The proposed solution to the problem provides output characteristics without the use of a wide (clearance) channel (not provided for in the PRMG format). The proposed solution provides a higher reliability of the timing because instead of the active device (wide channel transmitter), passive elements (antennas, power splitters, phase shifters, combiners) are used, whose reliability is two orders of magnitude higher than the reliability of active electronic devices. The proposed option is less expensive to manufacture and operate the timing.

3. Disclosure of the invention

The technical result of the invention is aimed at improving the stability of the glide angle and providing the timing area when the height of the underlying surface changes due to snow falling or melting or grass growing or when the reflective properties of the underlying surface change due to exposure to meteorological factors. The work of the timing is ensured at the airfields with a high level of snow cover and difficult terrain in the area of landing of the aircraft.

The technical result is achieved by the timing of the PRMG format, which contains the device for generating signals of the landing system of the PRMG format with a differential channel output and a total channel output, the first signal distribution device with a differential channel input, a total channel input and four outputs, the first antenna array with four radiating elements (IE), also additionally contains the first power divider with the first and second output, the second power divider with the first and second output, the second distribution device si with the input of the differential channel, the input of the total channel and four outputs, the first phase shifter by 90 °, the second phase shifter by 90 °, the second AP with four IE.

, λ - длина волны, θ_гл - угол глиссады. ИЭ второй АР размещены на вертикальной мачте с одинаковым смещением всех ИЭ по высоте на некоторую величину относительно высот подвеса ИЭ первой АР. Величина смещения выбирается в пределах от половины вертикального размера ИЭ величины до величины, равной разности величины d и величины смещения ИЭ второй АР относительно ИЭ первой АР.In this case, the IE of the first and second APs are located on the vertical mast. The height of the suspension of IE of the first AR is: H ₀ - the height of the first IE, H ₀ + d - the height of the second IE, H ₀ + 2d - the height of the third IE, H ₀ + 3d - the height of the fourth IE, where H ₀ exceeds approximately 20 cm maximum snow depth in the area where the aerodrome is located,

, λ is the wavelength, θ _hl is the glide path angle. The IE of the second AR is placed on the vertical mast with the same displacement of all of the IE in height by a certain amount relative to the heights of the suspension of the IE of the first AR. The offset value is selected in the range of half the vertical size of the IE value to a value equal to the difference of the d value and the offset value of the second AR relative to that of the first AR.

The values of the transmission coefficients from the inputs of the total and differential channels to the outputs 43-46 of the first signal distribution device are shown in Table 1.

The value of the coefficient a is chosen in the range from 0.4 to 0.75, depending on the nature of the terrain in the area of approach of aircraft for landing.

The values of the transmission coefficients from the inputs of the total and differential channels to the outputs 53-56 of the second signal distribution device are shown in Table 2.

These devices are interconnected as follows. The output of the differential channel of the signal conditioning device is connected in series with the first power divider and through its first output with the differential input of the first signal distribution device. The second output of the first power divider through the first phase shifter at 90 ° is connected to the differential input of the second signal distribution device. The output of the total channel of the signal conditioning device is connected in series with the second power divider and through its first output with the total input of the first signal distribution device. The second output of the second power divider through the second phase shifter at 90 ° is connected to the total input of the second signal distribution device. The outputs of the first signal distributor are connected to the IE of the first AR, respectively. The outputs of the second signal distribution device are connected to the IE of the second AR, respectively.

Setting the amplitude-phase distribution of currents in the first and second ARs in accordance with Table 1 and Table 2, respectively, leads to a weakening of the radiation at low elevation angles, under which are folds of the terrain in the zone of landing of the aircraft for landing, capable of reflecting electromagnetic waves in the region glide paths and thereby bend the glide path. The attenuation of radiation at low elevation angles leads to the formation of a glide path without curvature. Presented in Tables 1-2, PRA provides for the formation of a glide path, the angle of which does not depend on the height of the snow cover.

Powering two APs, spaced apart by height, with high-frequency signals with a phase shift of 90 °, ensures the formation of a so-called “un-boundary” glide zone, i.e. areas in which the level of the radiation pattern in the total signal is sufficient to ensure the range of the timing in the sector of elevation specified by the standards.

In another embodiment, the PRMG timing device contains a signal conditioning system for the landing system of the PRMG format with a differential channel output and a total channel output, a signal distribution device with a differential channel input, a total channel input and four outputs, the first AP with four IEs also contains four power dividers for two directions , each, four phase shifters at 90 °, each, the second AR with four IE. IE first and second AR placed on a vertical mast. The height of their suspension is the same as in the first version of the timing. The values of the transmission coefficients of the signal distribution device are the same as in the first version of the timing. The output of the differential channel of the signal conditioning device of the landing system is connected to the differential input of the signal distribution device. The output of the total channel of the signal conditioning system of the landing system is connected to the total input of the signal distribution device. Each output of the signal distribution device is connected to the corresponding power divider into two directions and through their first outputs with the first AR, respectively, and the second outputs of the two power divisors are sequentially connected to the phase shifters by 90 ° and the second AR, respectively. The values of the transmission coefficients of the signal distribution device are the same as in the first version of the timing.

In the second embodiment, in comparison with the first, only one signal distribution device is used. The second signal distribution device is replaced by simpler four power dividers in two directions and two additional phase shifters by 90 degrees. The second option is less time consuming to manufacture. However, it lost the ability to quickly adjust the coverage area by changing the ratio of the amplitudes of the signals in the first and second ARs. Inoperative timing adjustment due to a change in the signal transmission factors in the above-mentioned four power dividers.

The timing according to the third variant contains a signal shaping device of the landing system with a differential channel output and a total channel output, a first signal distribution device with a differential channel input, a total channel input and four outputs, the first equidistant AR with four IE. It also contains a second signal distribution device with a differential channel input, a total channel input and four outputs, four phase shifters for 90 °, each, three adders with the first and second inputs and one output, each, a second equidistant AP with four IEs. The first IE of the second AR is combined with the second IE of the first AR. The second IE of the second AR is combined with the third IE of the first AR. The third IE of the second AR is combined with the fourth IE of the first AR.

In this case, the output of the differential channel of the signal conditioning system of the landing system is connected in series with the first power divider and through its first output with the differential input of the first signal distribution device. The second output of the first power divider is connected to the differential input of the second signal distribution device. The output of the total channel of the signal conditioning device is connected in series with the second power divider and through its first output with the total input of the first signal distribution device. The second output of the second power divider is connected to the total input of the second signal distribution device. The first, second and third outputs of the first signal distribution device are each connected in series with the first, second and third phasers by 90 °, respectively, with the first input of the first, second and third adders and the first, second and third IEs of the first AR, respectively. The fourth output of the first signal distribution device is connected in series with the fourth phase shifter at 90 ° and the fourth IE of the second AP. The first output of the second signal distribution device is connected to the first radiating element of the first AP. The second, third and fourth outputs of the second signal distribution device are connected in series with the second inputs of the first, second and third adders and with the first, second and third IEs of the second AR.

In the third variant, the number of IE is reduced from 8 to 5. The reduction was made possible by the introduction of simpler adders compared with antennas and two phase shifters. In the third variant of the timing, the maximum displacement of the elements of the second AR with respect to the IE of the first AR is realized. The offset is equal to the distance between the IE in the AR. The third option would require a higher mast for its implementation. This disadvantage is not fundamental, since timing antenna is located far from the runway axis.

The solution of these and other problems is explained further by the text and drawings on the figures.

4. Brief Description of the Drawings

FIG. Figure 1 shows the electrical block diagram of the first variant of the glide path beacon (RM) of the format of the beacon landing group (PRMG) for the instrumental approach of aircraft to land at airfields with a high level of snow cover and complex terrain of the present invention. FIG. 1 adopted the following notation:

1 is a device for forming signals of the landing system (UFSP) with an output of 11 differential channels and an output of 12 total channels,

2 - the first power divider with the first 21 and second 22 output,

3 - the second power divider with the first 31 and the second 32 output,

4 - the first signal distribution device (URS) with the input of 41 differential channels, the input 42 of the total channel and the first 43, the second 44, the third 45 and the fourth 46 output,

5 - the second device of the distribution of signals with the input 51 of the differential channel, the input 52 of the total channel, with the first 53, second 54, third 55 and fourth 56 output,

6 - the first phase shifter at 90 °,

7 - the second phase shifter at 90 °,

8 - the first antenna array (AR) with the first 81, the second 82, the third 83 and the fourth 84 radiating element (IE). The first AR contains two ordered troika IE: the first ordered troika contains 81-83 IE, the second ordered troika contains 82-84 IE. IE 82-83 are common to the first and second triples of IE.

9 - the second AR with the first 91, the second 92, the third 93 and the fourth 94 IE. The second AR, as well as the first, contains two ordered triples of IE: the first ordered triplicate contains 91-93 IE, the second triple contains 92-94 IE. IE 92-93 are common to the first and second ordered triples of IE.

FIG. 2 shows a block diagram of a second version of the PRMG format for providing an instrumental approach for aircraft to land at airfields with a high level of snow cover and difficult terrain according to the present invention. FIG. 2 entered designations:

1 'is a device for forming signals of the landing system with an output 11' of the differential channel and an output 12 'of the total channel,

4 'is a signal distribution device with an input 41' of the differential channel, an input 42 'of the total channel and the first 43', second 44 ', third 45' and fourth 46 'outputs;

101 - the first power divider (DM) in two directions,

102 - the second power divider into two directions,

103 - the third power divider into two directions,

104 - the fourth power divider into two directions,

111 - the first phase shifter at 90 °,

112 second phase shifter at 90 °,

113 - the third phase shifter at 90 °,

114 - the fourth phase shifter at 90 °.

8 'is the first AP with the first 81', the second 82 ', the third 83' and the fourth 84 'IE. The first AR contains two ordered troika IE: the first ordered troika contains 81'-83 'IE, the second ordered troika contains 82'-84' IE. IE 82'-83 'are common to the first and second triples of IE. 9 'is the second AP with the first 91', the second 92 ', the third 93' and the fourth 94 'IE. The second AR, as well as the first, contains two ordered triples of IE: the first ordered troika contains 91'-93 'IE, the second three contains 92'-94' IE. IE 92'-93 'are common to the first and second ordered triples of IE.

FIG. 3 shows the structural electrical circuit of the third option for providing the instrumental approach of aircraft for landing on airfields with a high level of snow cover and difficult terrain of the present invention. FIG. 3 introduced the following notation:

1 "- the device of formation of signals of the landing system with the output of the 11" differential channel and the output 12 "of the total channel,

2 "- the first power divider with the first 21" and the second 22 "output,

3 "- the second power divider with the first 31" and the second 32 "output,

4 "- the first signal distribution device with an input 41" of the differential channel, an input 42 "of the total channel and the first 43", the second 44 ", the third 45" and the fourth 46 "output;

5 "- the second signal distribution device with an input 51" of the differential channel, an input 52 "of the total channel and the first 53", second 54 ", third 55" and fourth 56 "output;

121 - the first phase shifter at 90 °,

122 - second phase shifter at 90 °,

123 - the third phase shifter at 90 °,

124 - fourth phase shifter at 90 °,

131 - the first adder with the first and second input and one output,

132 - the second adder (SU) with the first and second inputs and one output,

133 - the third adder with the first and second input and one output,

81 '' element of the first AR,

82 (91) "" - combined IE: 82 "-th element of the first AR and 91" IE of the second AR,

83 (92) '' - combined IE: 83 '' is the first element of the first AR and 92 '' is the second AR,

84 (93) '' - combined IE: 84 '' -th element of the first AR and 93 '' IE of the second AR.

94 '' second element of the AR.

FIG. 4 shows the diagrams of the DN of the central elements of the first F _1,2 (θ), (401) and the second - 0.5 F _1.3 (θ), (402) of the ordered triples of IE of the first AR, recorded by the sum signal (82nd and 83 - iy IE, respectively). Graph 403 corresponds to a DN with the combined emission of the sum signal by the 82nd and 83rd IEs of the first AR.

FIG. 5 shows the diagrams of the DN of the central elements of the first (501) and second (502) ordered triples of the second AR, powered by the sum signal (92nd and 93rd IE, respectively). Graph 503 corresponds to a DN with the combined emission of the sum signal by the 92nd and 93rd IEs of the second AR.

FIG. 6 shows the diagrams of the DN for the signal of the total channel when the waves of the first (403) AP, the second (503) AP, and jointly (601) the first 8 and the second 9 AR are radiated.

FIG. 7 shows the diagrams of the DN for the signal of the total channel when the waves of the first (701) AP, the second (702) AP and jointly (703) the first 8 and the second 9 AR for the particular case, when the shift between the first IE 8 and the second AR are equal to the distance between IE in each of the mentioned ARs.

5. The implementation of the invention

First option

Referring to FIG. 1, which shows the structural electrical circuit of the first variant of the glide path beacon of the PRMG format for providing an instrumental approach for aircraft to land on airfields with a high level of snow cover and difficult terrain according to the present invention

The timing device contains a signal generation system 1 of the landing system with an output of 11 differential channels and an output of 12 total channels, the first 2 power splitters with the first 21 and second 22 outputs, the second 3 power dividers with the first 31 and second 32 outputs, and the first 4 signals distribution device with an input 41 differential channel, input 42 of total channel and first 43, second 44, third 45 and fourth 46 outputs, second 5 signal distribution device with input 51 of the differential channel, input 52 of total channel and first 53, second 54, third 55 and fourth 56 outputs MI, the first 6 phasers at 90 °, the second 7 phasers at 90 °, the first 8 AP with the first 81, the second 82, the third 83 and the fourth 84 IE, the second 9 AR with the first 91, the second 92, the third 93 and the fourth 94 IE. IE 81-84 and 91-94 are located on the vertical mast.

These devices are interconnected as follows. The output 11 of the differential channel of the landing signal generation device 1 is serially connected to the first 2 power divider and through its first output 21 to the differential 41 input of the first 4 signal distribution devices. The second 22 output of the first power divider 2 through the first 6 phase shifter at 90 ° is connected to the differential 51 input of the second 5 signal distribution device. The output 12 of the total channel of the landing signal generation device 1 is serially connected to the second 3 power divider and through its first output 31 with a total 42 input of the first 4 signal distribution devices. The second 32 output of the second power divider 3 is connected via a second phase shifter by 90 ° to a total 52 input of the second 5 signal distribution device. The outputs 43, 44, 45, 46 of the first 4 signal distribution devices are connected to IEs 81, 82, 83, 84, respectively. The outputs 53, 54,55, 56 of the second 5 signal distribution device are connected to IE 91, 92, 93, 94, respectively.

, λ - длина волны, θ_гл - угол глиссады.The height of the suspension IE 81-84 of the first 8 AR are: H ₀ - the height of the first IE, H ₀ + d - the height of the second IE, H ₀ + 2d - the height of the third IE, H ₀ + 3d - the height of the fourth IE, where H ₀ depending from the maximum height of snow cover at the aerodrome for timing of the Russian Museum, is selected in the range from 0.5 to 1.5 m,

, λ - wavelength, θ _hl - glide angle.

относительно высот подвеса ИЭ первой АР. Величина смещения

выбирается в пределах от половины вертикального размера L ИЭ 81-84 до величины d. Значения коэффициентов передачи суммарного и разностного сигналов на выходы 43-46 первого 4 устройства распределения сигналов приведены в табл.1.IE 91-94 second 9 AR placed on a vertical mast with the same displacement of all IE in height by

relative to the heights of the suspension of the first IE. Offset value

is selected in the range of half the vertical size L IE 81-84 to the value d. The values of the transmission coefficients of the total and differential signals at the outputs 43-46 of the first 4 signal distribution devices are given in table 1.

The value of the coefficient a is chosen in the range from 0.4 to 0.75, depending on the nature of the terrain in the area of approach of aircraft for landing.

The transmission coefficients of the total and differential signals at the outputs 53 -56 for the second signal distribution device are similar to the transmission coefficients for the first signal distribution device (Table 2).

The coefficient b in table 2 is equal to the ratio of signals in the first and second APs (defined by devices 4 and 5 of the signal distribution).

All the above-mentioned devices can be made similarly to the devices implemented in the serial GRM of the PRMG-76UM product manufactured by the Polyet Chelyabinsk Radio Plant and operated on the aerodromes of the state aviation of the Russian Federation.

Timing works as follows. In the device 1 of the signal generation signal, the high-frequency harmonic oscillations are modulated by two alternating sequences of rectangular oscillations: in the form of a "meander" with a frequency of 2100 Hz and with a frequency of 1300 Hz. The change in the passage of oscillations with frequencies of 2100 Hz and 1300 Hz in the device 1 for the generation of landing signals is carried out under the control of a generator with a frequency of 12.5 Hz. During one half cycle of switching (for 0.04 sec.), At outputs 11 and 12, common-mode signals modulated by a square wave with a frequency of 2100 Hz are formed between themselves. During the other switching half-period (within 0.04 sec.), The signal at output 11 is shifted out of phase by 180 ° relative to the phase of the high-frequency oscillation at output 12, as a result, the signals that are modulated by a meander with a frequency of 1300 are formed at outputs 11 and 12 Hz

The signal of the differential channel from the output 11 is fed to the input of the first 2 power splitters, from the first 21 outputs of which is fed to the differential 41 input of the first 4 devices of the distribution of signals. From the second 22 output, the differential signal through the 90 ° phase shifter is fed to the differential 51 input of the second 5 signal distribution device. The signal of the total channel from output 12 is fed to the input of the second 3 power divider, from the first 31 outputs of which is fed to the total 42 input of the first 4 devices of the distribution of signals. From the second 32 output, the total signal through the 90 ° phase shifter is fed to the total input of the second 3 signal distribution devices.

The first 4 signal distributors receive signals with a normalized level equal to 1, and the second 5 signal distributors receive signals with a relative level equal to b, while the inputs 51 and 52 of the signals have an additional phase shift of 90 ° relative to the phase of the signals inputs 41 and 42 of the first signal distribution device. An additional phase shift of 90 ° is obtained by passing through phase shifters 6 and 7 by 90 °.

The first 4 signal distribution device distributes the difference and total signals received by it at outputs 43-46 with amplitudes and phases indicated in Table 1. With the specified amplitudes and phases, signals from outputs 43-46 arrive at the inputs of antennas 81-84, respectively, and emitted into the surrounding space.

The second 5 signal distribution device distributes the difference and total signals received by it at outputs 53-56 with amplitudes and phases as shown in Table 2. With the specified amplitudes and phases, signals from outputs 53-56 arrive at the inputs of antennas 93-96, respectively, and emitted into the surrounding space.

Thus, during one switching half-period (within 0.04 s), signals modulated by a meander with a frequency of 2100 Hz are radiated to the surrounding space with a DN of F ₂₁₀₀ (θ), where θ is the elevation angle. During the other switching half-period (within 0.04 s), signals modulated by a meander with a frequency of 1300 Hz, with a DN of F ₁₃₀₀ (θ), are emitted into the surrounding space.

The elevation angle θ _gl at which the DN levels of F ₂₁₀₀ (θ) F ₁₃₀₀ (θ) are equal to each other F ₂₁₀₀ (θ _hl ) = F ₁₃₀₀ (θ _hl ) is the glide slope angle.

The glide slope angle θ _hl , as was shown earlier (Zhdanov B.V., Voitovich N.I.

Glide beacon for airfields with a high level of snow cover. // 27th International Crimean Conference "Microwave Technology and Telecommunication Technologies" (KriMiKo 2017). Sevastopol, November 5-11, 2017: materials conf. in 8 tons. - Moscow, Minsk, Sevastopol, 2017. P. 433-439), does not depend on the height of the suspension H _{0 of the} lower IE (on the height of the suspension of the entire antenna system) relative to the underlying surface, i.e. from the height of snow cover on the earth's surface. As for the range of the timing, the range is determined by the level of the electric field intensity, i.e. depends on the level of the DN total signal. In the interference minima of the DN when working with one of the APs, the signal may be unacceptably small (in the flight experiment, the aircraft navigation equipment blender does not work). Therefore, we restrict ourselves to analyzing the DN for the total signal.

Let the number m determine the number of AP: m = 1 corresponds to the first AP, m = 2 corresponds to the second AP. The number n determines the sequence number of the IE in the first or second AP when the IE is counted from bottom to top. We introduce the following notation for DN:

- величина смещения ИЭ второй АР относительно ИЭ первой АР с соответствующим номером. Знак плюс означает смещение ИЭ вверх, знак минус - смещение вниз.F _{n, m} (θ) -DH of the n-th IE of the m-th AR; when m = 1, the IE belongs to the first, and when m = 2, the second AR,

- the offset value of the IE of the second AR relative to the IE of the first AR with the corresponding number. The plus sign means the displacement of the IE up, the minus sign indicates the displacement down.

For simplicity, we will assume that IEs are horizontal dipoles located above a perfectly conducting horizontal plane. Then the DN of the n-th IE (n = 1, 2, 3, 4) (the first AR with m = 1 or the IE of the second AR with m = 2) in the vertical plane looks like:

Where:

; λ - длина волны;k is the wave number;

; λ is the wavelength;

H ₀ - the height of the lower suspension (first; n = 1, m = 1) antenna of the first AR;

d is the distance between adjacent elements in the first (second) AP,

θ_гл - угол глиссады;

θ _hl - glide angle;

As an example of the first version of the timing, consider the timing, containing the first 4-element AR, in which the coefficient a = 0.5 (table 1), the second 4-element AR, in which the coefficient a = 0.6 (table 2). Let the coefficient b = 1. λ = 0,312 m. θ _hl = 3 °. The suspension height of the lower antenna H ₀ = 1 m. The IE of the second AR is offset relative to the IE of the first AR with the corresponding number by 0.5 m.

FIG. 4 shows the diagrams NAM:

F _1,2 (θ) -401, -0.5 F _1,3 (θ) -402 F ₅ (θ) = F _1,2 (θ) -0,5 F _1,3 (θ) -403.

The first and second ARs, each, consist of two pairs of ordered triples of IE, containing the total channel IE (central) and located at a distance dor one of the lower IE and one upper IE of the difference channel. In the first AR, those are the first three: 82-IE of the total channel, 81 and 83 IE of the difference channel. The second three: 83-IE total channel, 82 and 84 IE differential channel. In the second AR, those are the first three: 92-IE of the total channel, 91 and 93 IE of the difference channel. The second three: 93-IE total channel, 92 and 94 IE differential channel.

As can be seen from the graphs in FIG. 4 days, the total current signal IE of the first three (82nd IE) F _1.2 (θ) (plot 401) takes a zero value at θ ₁ , = 3.59 °, i.e. in the area of the timing in the vertical plane. The DN of the total signal of the second three (83rd IE) F _1.3 (θ) (plot 402) twice takes a zero value in the timing zone in the vertical plane: with θ ₂ = 2.25 ° and with θ ₃ = 4.50 ° With the combined radiation of the total signal, the IE of the first and second triples of the DN according to the total signal, firstly, has a significantly lower level compared to the radiation level when emitting only the IE of the first triples. With a decrease in the level of NAM, the irradiation of the folds of the terrain decreases, which is required to reduce the curvature of the glide path. However, secondly, as before, the DN (plot 403) takes a zero value within the timing area (for θ = 3.98 °).

FIG. 5 shows the diagrams of DN for IE ordered threes of the second AR:

F _2.2 (θ) -501, -0.6F _2.3 (θ) -502, F ₆ (θ) = F _2.2 (θ) -0.6F _2.3 (θ) -503.

As can be seen from the consideration of the graphs, the behavior of DN IE (graphs 501, 502) in the ordered triples of the second AR is similar to the behavior of BP in the ordered triples of the first AR. With the combined emission of the total signal, the IE of the first and second triples of DN (plot 503) on the total signal at small elevation angles has a significantly lower level compared to the radiation level when emitting only the IE of the first triples. DN also takes a zero value within the operating area of the State Russian Museum (at θ = 3.44 °). It should be noted that in the elevation plane the position of the zero levels in the bottom pattern in the second AR does not coincide with the position of the zero levels in the bottom pattern of the first AR.

FIG. 6 shows the diagrams NAM

F ₅ (θ) -403, F ₆ (θ) -503,

As can be seen from consideration of graph 601 in FIG. 6, when the first AR and the second AR are fed with a high-frequency signal with a phase shift of 90 °, the zero levels in the DN along the total channel disappear (plot 601). NAM has a low level of radiation at low elevation angles, which ensures the timing of work on aerodromes with complex terrain in the area of approach of aircraft for landing. Taking into account the independence of the glide path angle from the height of the antenna suspension, we conclude that the timing of the present invention provides operation on airfields with a high level of snow cover and difficult terrain in the area of approach of aircraft for landing.

Second option

Referring to FIG. 2, which shows the structural electrical circuit of the second version of the timing for the instrumental approach of aircraft to land at aerodromes with a high level of snow cover and difficult terrain of the present invention.

Timing according to the second option contains the device 1 'signal generation system landing format PRMG with the output of 11' differential channel and the output 12 'total channel, the device 4' distribution of signals with the input 41 'of the differential channel, the input 42' of the total channel and the first 43 ', the second 44 ', third 45' and fourth 46 'output, first 101, second 102, third 103 and fourth 104 power dividers in two directions each, first 111, second 112, third 113 and fourth 114 phase shifters at 90 ° each, first 8 AR with four 81'-84 'IE, the second 9 AR with four 91'-94' IE. Images of common IE for the first and second ARs are partially filled. These devices are interconnected as follows. The output 11 'of the differential channel of the landing signal conditioning device 1' is serially connected to the differential 41 'input of the signal distribution device 4'. The output 12 'of the total channel of the signal distribution device 1' is connected to the total 42 'input of the signal distribution device 4'. The outputs 43 ', 44', 45 ', 46' of the signal distribution device 4 'are connected to power dividers 101-104 into two directions and through their first outputs with IE 81', 82 ', 83', 84 ', respectively, and the second the outputs of the power dividers 101-104 are connected in series with the phase shifters 111-114 by 90 ° and IE 91'-94 ', respectively. IE 81'-84 'and 91'-94' are placed on the vertical mast.

The suspension heights of the IE 81'-84 'and 91'-94' are the same as in the first version of the Russian Museum (point 1). The values of the transmission coefficients of the total and differential channel at the outputs 43'-46 'of the device 4' of the distribution of signals are the same as the first version of the timing.

The work of the glide path beacon according to the second variant is similar to the work of the State Russian Museum according to the first variant. The only difference is that the ratio of the amplitudes of the signals in the IE of the second AR and the first AR (coefficient b) is now set by the power dividers 101-104, and not by the power dividers 2 and 3 in FIG. one.

Third option

Referring now to FIG. 3, which shows the structural electrical circuit of the third version of the PRMG format RMG for instrumental approach of aircraft for landing on airfields with a high level of snow cover and the difficult terrain of the present invention. According to the third variant, the glide beacon contains a landing signal shaping device 1 ″ with a 11 ″ differential channel output and a total channel 12 ″ output, a signal distribution device 4 ″ with a differential channel input 41 ″, a total channel input 42 ″ and the first 43 ", the second 44", the third 45 "and the fourth 46" exit, the first 121, the second 122, the third 123 and the fourth 124 phase shifters at 90 ° each, the first 131, the second 132 and the third 133 adders with the first and the second entrances and one exit, each, the first 8 '' AP with four 81 '' - 84 '' IE, the second 9 '' AP with four 91 '' - 94 '' E. The radiating elements 82 "- 84" 'of the first 8 "AR are combined with the IE elements 91" - 93 "of the second AR, respectively.

These devices are interconnected as follows. The output 11 ″ of the differential channel of the landing signal conditioning device 1 ″ is connected in series with the first 2 ″ power splitter and through its first output 21 ″ to the differential 41 ″ input of the first 4 ″ signal distribution device. The second 22 "output of the first power divider 2" is connected to the differential 51 "input of the second 5" device of the signal distribution. The output 12 ″ of the total channel of the landing signal generation device 1 ″ is sequentially connected to the second 3 ″ power splitter and through its first output 31 ″ to the total 42 ″ input of the first 4 ″ signal distribution device. The second 32 "output of the second power divider 3" is connected to the second 52 "input of the second 5" signal distributor, the output 46 "of which is connected in series with the phase shifter 124 and IE 94". The outputs 43 ″, 44 ″, 45 ″ each are connected in series with the corresponding phase shifter 121, 122, 123, with the first input of the adder 133, 132, 131 and IE 81 ″, 82 ″, 83 ″, respectively. The output 53 ″ of the second 5 ″ signal distribution device is connected to IE 81 ". The outputs 54 ″, 55 ″, 56 ″ of the second 5 ″ signal distribution device are connected in series with the second inputs of adders 133, 132, 131 and IE 91 ″, 92 ", 93", respectively.

The timing of the third option is similar to the timing of the first option.

The resulting DN (Fig. 7) obtained by quadrature summation of the signals of the total channel emitted by the first AR (plot 701) and the second AR (plot 702) is shown in FIG. 9 (plot 703). As can be seen from the review of schedule 703 DN, a high level in the DN is observed in the entire timing area.

(9(d=1,5 м) выше, чем при смещении на 0,5 м, что более выгодно.The timing of the third option provides work on the airfields with a high level of snow cover and difficult terrain in the area of approach of the aircraft to land according to the present invention (timing). The level of DN on the total channel when the second AR is shifted by distance

(9 (d = 1.5 m) is higher than at a displacement of 0.5 m, which is more profitable.

However, this would require a mast of 1 m higher.

Claims (5)

1. Glide radio beacon containing a signal conditioning device for a landing system with a differential channel output and a total channel output, a first signal distribution device with a differential channel input, a total channel input and four outputs, a first antenna array with four radiating elements mounted on a vertical mast with heights suspension: ₀ H - height of the first radiating element, H ₀ + d - the height of the second radiating element, H ₀ + 2d - the height of the third radiating element, H ₀ + 3d - the height of the fourth izluchayuscheg element, where H ₀ is greater than the height of the snow cover,

, λ - wavelength, θ _hl - glide angle, characterized in that it further comprises a first power divider with first and second outputs, a second power divider with first and second outputs, a second signal distribution device with a differential channel input, a total channel input and four outputs, a first phase shifter by 90 °, a second phase shifter by 90 °, the second antenna array with four radiating elements placed on a vertical mast with the same displacement of all radiating elements in height by a certain amount relative to the heights of the radiator e the first antenna array, the offset value is selected from half the vertical size of the radiating elements of the first antenna array to a value equal to the difference of the distance between the radiating elements of the antenna array and said half of the vertical size, while the output of the differential channel of the signal-shaping device is sequentially connected to the first divider power and through its first output - with a differential input of the first signal distribution device, the second output of the first power divider through the first phase shifter at 90 ° is connected to the differential input of the second signal distributor, the output of the total channel of the signal conditioning device is sequentially connected to the second power divider and through its first output to the total input of the first signal distributor, the second output of the second power divider through the second phase shifter at 90 ° is connected to the total input of the second signal distribution device, the outputs of the first signal distribution device are connected to the emitting ementami first array antenna, respectively, the outputs of the second signal distribution device connected to the radiating elements of the second array antenna, respectively. 2. Glide radio beacon according to the second variant, comprising a landing signal conditioning device with a differential channel output and a total channel output, a signal distribution device with a differential channel input, a total channel input and four outputs, the first antenna array with four radiating elements located on a vertical mast with suspension heights: H ₀ - height of the first radiating element, H ₀ + d - height of the second radiating element, H ₀ + 2d - height of the third radiating element, H ₀ + 3d - height of the fourth of radiating element, where H ₀ exceeds the height of the snow cover,

, λ - wavelength, θ _hl - glide angle, characterized in that it additionally contains first, second, third and fourth power dividers into two directions each, first, second, third and fourth phasers by 90 ° each, second antenna array with four radiating elements placed on a vertical mast with the same displacement of all radiating elements with a height of a certain value relative to the suspension heights of the radiating elements of the first antenna array; the amount of displacement is selected from half the vertical size of the radiating elements of the first the antenna array to a value equal to the difference of the distance between the radiating elements of the antenna array and said half of the vertical size, and the output of the differential channel of the signal conditioning system of the landing radio array beacon (PRMG) format is connected to the differential input of the signal distribution device, the output of the total channel of the signal conditioning device landing system format PRMG connected to the total input of the device signal distribution; the outputs of the signal distribution device are connected to power dividers in two directions and, through their first outputs, to the radiating elements of the first antenna array, respectively, and the second outputs of the power dividers are sequentially connected to phase shifters by 90 ° and the radiating elements of the second antenna array, respectively. 3. Glide radio beacon of the third option, containing a signal conditioning device for the landing system with a differential channel output and a total channel output, the first signal distribution device with a differential channel input, a total channel input and four outputs, the first antenna array with four radiating elements placed on the vertical mast with suspension heights: H ₀ - height of the first radiating element, H ₀ + d - height of the second radiating element, H ₀ + 2d - height of the third radiating element, H ₀ + 3d - height of four of the radiating element, where H ₀ exceeds the height of the snow cover,

, λ - wavelength, θ _hl - glide path angle, characterized in that it additionally contains a second signal distribution device with a differential channel input, a total channel input and four outputs, four 90 ° phase shifters, three adders with the first and second inputs and one output each, the second equidistant antenna array with the first, second, third and fourth radiating elements placed on the vertical mast above each other in ascending order of their numbers; wherein the first radiating element of the second antenna array is aligned with the second radiating element of the first antenna array, the second radiating element of the second antenna array is aligned with the third radiating element of the first antenna array, the third radiating element of the second antenna array is aligned with the fourth radiating element of the first antenna array; the output of the differential channel of the signal conditioning system of the landing system of the landing radiobeacon group (PRMG) is sequentially connected to the first power divider and through its first output to the differential input of the first signal distribution device; The second output of the first power divider is connected to the differential input of the second signal distributor, the output of the total channel of the signal conditioning device of the fitment is sequentially connected to the second power divider and through its first output to the total input of the first signal distributor, the second output of the second power divider is connected to the total input the second signal distributor, the first output of the first signal distributor connected in series with the first phase shifter the fourth radiating element of the second antenna array, the second, third and fourth outputs of the first signal distribution device are each connected in series with the second, third and fourth phasers, the first input of the first, second and third adders, and the first, second and third radiating elements of the first antenna array, respectively ; The first output of the second signal distribution device is connected to the first radiating element of the first antenna array, the second, third and fourth outputs of the second signal distribution device are connected in series with the second inputs of the third, second and third adders and with the first, second and third radiating elements of the second antenna array.

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