RU2695316C2 - Method for adjusting information parameter of course-glide path beacons and its implementation device (embodiments) - Google Patents

Abstract

FIELD: physics.SUBSTANCE: invention relates to aerodrome radio engineering systems for providing approach of aircraft for landing. Technical result is achieved by introducing into HRB or GPB a meter or decimetre wavelength range with a signal generation and formation device (SGFD) with first and second outputs and antenna with first and second inputs of additionally controlled directional coupler and adder. Dual-range HRB also includes a second SGFD and two frequency-separating devices.EFFECT: technical result is adjustment of the information parameter of course-glide path beacons, in particular combination with high accuracy of course line, formed by heading radio beacon (HRB) of aircraft landing system with direction of axis of runway, combination of two course lines with direction of runway axis at operation of spacecraft at frequencies in two ranges simultaneously, setting with high accuracy angle of glide path with constant height of aerial suspension of glide path beacon (GPB).6 cl, 4 dwg

Description

A method for adjusting the information parameter of heading-glide path beacons and devices for its implementation (options).

Technical field

The invention relates to aerodrome radio engineering systems for aircraft approach, in particular, to directional and glide path beacons (CRM) of instrumental aircraft landing systems with the signal format ILS and PRMG.

State of the art

The main means of providing instrumental approach of civil aviation aircraft for landing and landing are radio beacon landing systems (SP) of the meter wavelength format ILS (Instrument Landing System); for state aircraft, the main means are beacon systems for decimeter wave landing of the format of the landing beacon group (PRMG) [G. Pakholkov and others. Goniometric radio engineering landing systems. - M .: Transport, 1982. - 159.] 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 in the development of ILS and PRMG 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 radio beacon joint venture includes a directional radio beacon (CRM), a glide path radio beacon (GRM) and on-board equipment (BA).

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 .

KRM is installed on the continuation of the axis of the runway (VII), on the side opposite to the side of the aircraft landing. The ILS KRM antenna emits electromagnetic waves into the surrounding space in the frequency range 108-112 MHz, modulated in amplitude by the signals of tonal frequencies ƒ ₁ = 90 Hz, ƒ ₂ = 150 Hz. The KRM PRMG antenna emits electromagnetic waves into the surrounding space in the decimeter wavelength range of 927.5-932.4 MHz, modulated by waveforms of meander waves with a frequency of ƒ ₁ = 1300 Hz and ƒ ₂ = 2100 Hz. The surface on which the difference in modulation depths (RGM) in the SP of meter waves or the coefficient of audibility in the SP of decimeter waves of signals ƒ ₁ and ƒ ₂ is equal to zero, is a vertical plane passing through the axis of the IIW.

The glide path beacon (GRM) is installed at a distance of about 300 m from the end of the VII from the side of the aircraft approaching and is offset from the axis of the VII by a certain distance (120-180 m). The timing antenna of meter waves (MB) emits electromagnetic waves into the surrounding space in the frequency range from 328.6 to 335.4 MHz [3, 60], modulated by signals with frequencies of 90 and 150 Hz. The decimeter wave (DTSV) timing antenna emits electromagnetic waves into the surrounding space in the frequency range 962–966.9 MHz [3, 60], modulated by waveforms of meander waves with a frequency of ƒ ₁ = 1300 Hz and ƒ ₂ = 2100 Hz.

The surface on which the difference between the modulation depths of the RF signals by the 90 and 150 Hz tones is zero, is a cone, the apex of which is at the base of the antennas. The axis of the cone is vertical, and the generatrix is tilted by a given angle relative to the surface of the Earth (surface of the glide path). Above the surface of the glide path, a signal with a modulation depth of the carrier tonal frequency of 90 Hz prevails, and lower with a modulation depth of the carrier tonal frequency of 150 Hz.

The intersection of the heading plane and the surface of the glide path sets in space a line for the aircraft to land, called the glide path. On-board equipment indicates the deviation of the aircraft from the glide path, its readings are used to make a decision by the pilot or autopilot to adjust the flight path of the aircraft.

The first two-frequency directional radio beacon of the ILS format instrument landing support system is known, which is presented in patent US 4032920 E.J. Martin (Two-Frequency Instrument Landing System with Integral Monitor, IPC: G01S 1/16, published 28.06.1977), containing:

- a device for generating and generating a signal (CFS) of a narrow channel with two outputs, a “carrier plus side frequencies” (LF) signal is generated at the first output, a signal containing only “side frequencies” (BF) is generated at the second output;

- an antenna array containing a number of pairs of radiating elements located on opposite sides relative to the continuation of the axis of the runway, with the first and second entrance.

Known for the second two-frequency directional radio beacon format ILS [SP-90, exchange rate beacon (RMK). Technical description ICRV.461512.019TO, NIIIT-RTS, 1996-1999].

The well-known second two-frequency KPM contains a CC transmitter with an output of the CC of the CC and the output of the NSC of the CC, a linear array of 8 pairs of radiating elements located on opposite sides relative to the continuation of the axis of the runway, with the first and second input.

The simplest known timing is the well-known timing zero reference. It includes two antennas, the lower antenna being located at a height half that of the upper antenna. The lower antenna emits an LFB signal; the upper antenna emits an LF signal.

Known timing belt format ILS. [SP-90, glide path radio beacon (RMG). Technical description ICRV.461512.020TO, NIIIT-RTS, 1996-1999], comprising a narrow channel transmitter with an output “side frequencies” of a narrow channel and an output “carrier plus side frequencies” of a narrow channel, a linear antenna array of type M of three radiating elements located on a vertical mast, with two inputs: an input for LFB signals and an input for LF signals.

Known CRM format PRMG, operating in the decimeter wavelength range [G.A. Pakholkov, V.V. Kashinov et al. "Goniometric radio engineering landing systems." - M .: Transport.- 1982, p. 18] containing a UGFS with first and second outputs with first and second signals, respectively, and an antenna with first and second inputs.

The well-known timing of the PRMG format, operating in the decimeter wavelength range with a reference zero [G.A. Pakholkov, V.V. Kashinov et al. "Goniometric radio engineering landing systems." - M .: Transport. - 1982, p. 18], containing the PFG signal with the first and second outputs, the first and second antennas spaced vertically, the lower antenna being powered by the first signal and the upper antenna being fed by the second signal. The first signal is understood to mean the signal formed by modulating high-frequency oscillations with meanders with frequencies of 2100 Hz and 1300 Hz, identical in amplitude, while the oscillations are in phase with each other. The second signal means the signal generated by modulating high-frequency oscillations with meanders with frequencies of 2100 Hz and 1300 Hz, identical in amplitude, while high-frequency oscillations have a phase shift of 180 °.

The well-known CRM and timing can be represented functionally in the form of two devices connected to each other: UGFS with first and second outputs and antennas with first and second inputs. The high-frequency signal, amplitude-modulated by two signals of tone frequencies, comes to the first output of the UVSP. Moreover, the higher and lower spectral components of the modulated signal have an initial phase of oscillations that coincides with the initial phase of carrier oscillations. The second output also receives a high-frequency signal that is also amplitude-modulated by two tone frequency signals. However, the initial phase of the oscillations of the spectral components due to the modulation of one tone frequency differs from the initial phase of the oscillations of the spectral components due to the modulation of another tone frequency by 180 °. When the first signal is applied to the first input of the antenna, electromagnetic waves are emitted into the surrounding space with the formation of a radiation pattern with one main lobe. This DN is further referred to as total DN. When a second signal is applied to the second input of the antenna, electromagnetic waves are emitted into the surrounding space with the formation of a beam with two main lobes. This DN we further call the difference type DN.

The authors are not aware of an analogue of a dual-band directional radio beacon, which would operate at two frequencies far apart from each other while simultaneously forming independent course lines in the direction of the VII axis. CRM with narrow and wide channels cannot be considered as an analog, since the mentioned CRM forms a course line only on a narrow channel. However, it is easy to imagine two SRMs independent of each other, each of which has its own antenna attached to the axis of the VII, and serving alternately decreasing aircraft at different frequencies. Here is such a device, consisting of two independent from each other CRM, can conditionally be presented as an analogue of the dual-band CRM proposed below.

In the ILS and PRMG beacons, different carrier frequency ranges, different amplitude modulation depths, and different tone signals are used. However, these differences in the signals are not fundamental, do not affect the essence of the present invention.

All known CRMs have a common drawback. When installing CRM at the aerodrome, it is often necessary to correct the angular position of the heading line, that is, (essentially) the position of the zero level of the differential antenna beam. This occurs, for example, with errors in the positioning of the positions for placing the bases of the supports of the radiating elements of the KRM antenna array, due to the deviation of the amplitude-phase current distribution in the antenna array of the KRM antenna from the ideal distribution. In existing CRM, with small errors, correction is performed by mechanical rotation of the CRM antenna. Sometimes such a procedure may be difficult or even impossible. For example, the KRS antenna of the ILS landing system is a linear array of 12-26 radiating elements from 24 m to 52 m long, rigidly mounted on a concrete foundation and practically does not have the possibility of mechanical rotation. There are known cases when it was necessary to destroy the foundation and create it again with adjusted positions for the radiating elements of the antenna array.

The lack of options for non-mechanical angular displacement of the zero level of the bottom of the antenna of the Raman antenna causes certain difficulties in introducing landing systems at aerodromes and during their operation.

In addition, there is a need to ensure, in the decimeter wavelength range, the specification of the heading line simultaneously at two operating frequencies from two widely spaced frequency ranges. In this regard, when the CRM operates on one antenna, the problem of combining two course lines with the axis of the runway arises. The fact is that for a number of technological reasons it is not possible to provide an identical amplitude-phase current distribution in the radiating elements of the antenna array in a wide frequency range. When the current distribution is not identical, the position of the zero levels in the DN, which determine the position of the course line, turns out to be different at different frequencies. In this regard, the problem arises of adjusting the position of the course line, at least at one of the operating frequencies.

All known timing have a common drawback, which is as follows.

As you know, the glide path angle is determined by the height of the antenna suspension relative to the underlying surface. When calculating the suspension height of the antennas, we proceed from the assumption that the timing is placed on a flat surface that extends to infinity in all directions,

The real situation at airfields is such that the shape of the underlying surface differs significantly from the ideal. As a result, it becomes necessary to adjust the height of the antenna suspension. This is detected during flight timing adjustment. Then, to change the height of the antenna suspension, it is necessary to interrupt the laboratory aircraft flights and resume them after setting the correct antenna heights. In addition, when checking the operation. This procedure can be repeated several times. In connection with these difficulties, it becomes necessary to adjust the angle of the glide path without changing the height of the antenna suspension.

In addition, it is difficult to verify the operation of the automatic control system of the CRM and the timing, which is performed by shifting the course line and glide path from the nominal position to the alarm of the device for monitoring the position of the course line and glide path ("zero accident"). At the same time, the ground-based engineering and technical personnel of the joint venture changes the suspension height of the glide path antennas GRM MB and GRM DCV, mechanically rotates the antenna CRM DT | V and changes the operating mode of the CRM MB.

After this check, the SRM and the timing are returned to their original position corresponding to the normal operating conditions of the beacons.

This check is associated with a significant waste of flying time.

The aim of the present invention is to solve these problems in a more efficient way compared to moving antennas, namely using the method of adjusting the information parameter of beacons and the device for its implementation, as proposed below.

Disclosure of invention

The technical result of the invention is the adjustment of the information parameter of the beacons, in particular, combining with high accuracy the course line formed by the CRM of the meter or decimeter wavelength range with the direction of the runway axis, combining with the direction of the runway axis of two course lines when the CRM is operating at two frequencies simultaneously, setting with high accuracy of the glide path formed by the timing of the meter or decimeter wavelength range, at a given angle with constant height of the suspension of the timing antennas.

The group of inventions presented below is united by one general idea, which is explained in the method for adjusting an information parameter in space described below. In this case, the beacon contains a UHFS with first and second outputs and an antenna with first and second inputs, and the signal at the first output, which is the first signal, is modulated in amplitude by two tone frequency signals so that all high-frequency spectral components have an initial phase of oscillation equal to the initial phase carrier oscillation, the signal at the second output, which is the second signal, is modulated in amplitude by two signals of the same tone frequencies so that the initial phase of the high-frequency spectral components with one tone hour the total modulation is equal to the initial phase of the carrier wave, and the initial phase of the high-frequency spectral components with a different modulation frequency differs from the initial phase of the carrier wave by 180 °; characterized in that the signal of the second output is partially branched, the unbranched signal of the second output is fed to the second input of the antenna with the formation of a difference radiation pattern with two main lobes in space, the branch from the second output and the signal from the first output are jointly fed to the first input of the antenna with formation in space total radiation pattern with one main lobe, changing the level of the branch signal, set the value of the information parameter to the desired position.

Technically, this result is achieved by introducing an additionally adjustable directional coupler (BUT) with an input, first and second outputs, and an adder with first and second inputs and output into a well-known CRM or GRM. In this case, the first output of the UHFS is connected in series with the first input of the adder and with the first input of the antenna, and the second output of the UHFS is connected in series with the input of the adjustable directional coupler and the second input of the antenna, the first output of the NO connected to the second input of the adder.

The introduction of an additionally adjustable directional coupler with an input, first and second outputs, and an adder with first and second inputs and outputs into the directional beacon and connecting them in the beacon as described above allows us to solve the problem of accurately combining the course line of a single-frequency course beacon or a narrow channel of a two-frequency course beacon with the direction of the runway.

Introduction to the directional radio beacon of an additional second device for generating and generating signals, an adjustable directional coupler with an input, first and second outputs, a first frequency separation device with first and second inputs and an output, and a second frequency separation device with a first and second inputs and their output connection in a beacon as described below allows us to solve the problem of accurately combining two course lines formed at different, far-spaced operating frequencies of two a directional radio beacon with the direction of the runway.

The introduction of a directional coupler with an input, first and second outputs and an adder with first and second inputs and outputs into the glide path beacon and their connection in the beacon as described above allows us to solve the problem of accurately setting the glide path angle of a single-frequency beacon or narrow channel of a two-frequency glide beacon.

The solution to the problem of adjusting the position of the heading line as applied to the directional radio beacon allows eliminating the mechanical turn of the KRM antenna or the execution of a new foundation if the radiating elements of the antenna array of the KRM antenna cannot be eliminated by mechanical rotation of the antenna in order to align the course line with the direction of the runway axis, and reduce the volume of flight measurements when commissioning the CRM.

The solution to the problem of adjusting the position of the heading line in relation to the dual-band heading beacon allows eliminating the option of two ASMs with two antennas, the first of which provides the ASM at the operating frequency in the first range, and the second antenna at the operating frequency in the second frequency range.

The solution to the problem of adjusting the position of the glide path as applied to the glide path beacon eliminates the repeated attempts to set the antenna suspension heights in order to form the glide path angle predetermined for a given aerodrome in a single-frequency beacon or in a narrow channel of a two-frequency timing. Using the adjustment, the glide path angle is set with high accuracy. The result is achieved in a more economical way.

A brief description of the drawings.

In FIG. 1 is a block diagram of devices for adjusting an information parameter generated by a beacon in accordance with the present invention. In FIG. 1 designation introduced:

1 - a device for generating and generating signals (UFFS),

2 - antenna

3 - adjustable directional coupler (BUT),

4 - adder (SU).

In FIG. _Figure 2 shows the unnormalized total 5 F _nbf (ϕ) antenna and differential 6 F _bch (ϕ) antenna formed by a 17-element antenna array when applying signals to the first and second inputs of the antenna, respectively, when the voltage coupling coefficient of voltage distribution K = 0.

In FIG. 3. shows the dependences of the RGM (ϕ) for some values of the coupling coefficient of the NO in the voltage K of an adjustable directional coupler: 7 (K = -0.2), 8 (K = -0.1) 9 (K = 0), 10 (K = 0.1), 11 (K = 0.2).

In FIG. 4 is a functional diagram of a dual-band course PRMG beacon with alignment of the course line with the axis of the runway in accordance with the present invention. In FIG. 4, the following notation is introduced:

50 - the second UFFS,

60 - the first frequency separation device,

70 is a second frequency separation device.

The implementation of the invention

An example implementation of a method for adjusting the information parameter of beacons The following are closely interconnected method and five devices that form a single general inventive concept.

Turning to FIG. 1, which shows a block diagram of devices for implementing the named method in accordance with the present invention.

The method of adjusting the information parameter is that the information parameter is formed by a device 1 for generating and generating signals with the first and second outputs 11 and 12 and antenna 2 with the first 21 and second 22 inputs, and the signal at the first output of the UHFS, which is the first signal, is modulated by the amplitude of the two signals of the tone frequencies so that all high-frequency spectral components have an initial phase of oscillation equal to the initial phase of the carrier wave, the signal at the second output, which is the second signal, (second hn) are modulated in amplitude by two signals of the same tone frequencies so that the initial phase of the high-frequency spectral components with one tone modulation frequency is equal to the initial phase of the carrier wave, and the initial phases of high-frequency spectral components with a different modulation frequency differ from the initial phase of carrier oscillations by 180 ° , characterized in that the second signal is partially branched, the unbranched second signal is fed to the second input of the antenna 22 with the formation of a radiation pattern in space ostnogo form, the first and the second branched signals together is fed to the first input of the antenna 21 to form a space pattern of the total species, altering the level of the branched signal set value information parameter in the desired position.

Five devices that implement the aforementioned method of the present invention are described below. The first device is designed to combine the course line formed by a single-frequency or two-frequency directional radio beacon of the landing system of a meter wavelength range of the ILS format with the axis of the runway. The second device is designed to combine the course line formed by the directional beacon of the landing system of the format of the landing beacon group of the decimeter wavelength range with the axis of the runway. The third device is designed to perform alignment of the course line with the axis of the runway in a dual-band directional beacon format PRMG.

The fourth device is designed to adjust the angle of the glide path formed by the glide path beacon meter wavelength range. The fifth device is designed to adjust the angle of the glide path formed by the glide path beacon of the decimeter wavelength range.

First device

Turning again to FIG. 1. Let now in FIG. 1 shows an ILM of a meter wavelength range of ILS format with alignment of the course line with the axis of the runway of the present invention.

The heading beacon contains a UGFS with first 11 and second 12 outputs, antenna 2 with first 21 and second 22 inputs, HO 3 with an input and first 31 and second 32 outputs, an adder 4 with first 41 and second 42 inputs and output.

The mentioned devices are made in the same way as they are performed in serial beacons, for example, in the landing system SP-90 manufactured by Chelyabinsk Radio Plant "Polet".

Presented in FIG. 1 device are interconnected as follows. The first 11 output of the UHFS is connected in series with the first 41 input of the adder 4 and with the first 21 input of the antenna, and the second 12 output of the UHFS is connected in series with HO 3 and the second 22 input of the antenna, the first 31 output of HO is connected to the second 42 input of the adder.

The first device operates as follows. Device 1 generates and generates on the first 11 output the first signal modulated in amplitude by two signals of tone frequencies ƒ ₁ and ƒ ₂ , called the signal "carrier plus side frequencies" (LF) U _nb (t):

Where:

t is the time

m is the modulation depth,

ω ₀ - carrier frequency,

ψ ₀ is the initial phase of carrier oscillations,

Ω ₁ = 2πƒ ₁ , Ω ₂ = 2πƒ ₂

and at the second 12 output, the second signal, amplitude-balanced in amplitude by two signals of the same tone frequencies ƒ ₁ and ƒ ₂ U _bf (t), called the “side frequencies” ( _BF ) signal:

- коэффициент, равный отношению амплитуд напряжений сигналов с угловыми частотами Ω₁ и Ω₂ модуляции в каналах БЧ и НБЧ в одночастотном радиомаяке или узкого канала в двух частотном радиомаяке на входе антенны (величиной коэффициента

регулируют крутизну зоны УК).

- a coefficient equal to the ratio of the amplitudes of the voltage signals with angular frequencies Ω ₁ and Ω ₂ modulation in the channels of the warhead and low frequency in a single frequency beacon or a narrow channel in two frequency beacon at the input of the antenna (the value of the coefficient

regulate the steepness of the UK zone).

Based on the formula for the product of two cosines, from (1) it follows:

As can be seen from (3), all five high-frequency spectral components of the LFB signal in (3) have an initial phase of oscillations ψ ₀ equal to the initial phase of the carrier oscillation.

From (2) it follows:

As can be seen from (4), the high-frequency spectral components with a tonal modulation frequency of ƒ ₁ and the high-frequency spectral components with a tonal modulation frequency of имеют ₂ have a difference of the initial oscillation phases equal to 180 °.

In this case, the first 11 output of the UHFS is connected in series with the first 41 input of the adder 4 and with the first 21 input of the antenna, and the second 12 output of the UHFS is connected in series with the adjustable directional coupler 3 and the second 22 input of the antenna, the first 31 output of the NO connected to the second 42 input of the adder.

The first signal from the output of 11 UGFS 1 is sequentially fed to the input of the adder 4, to the first 21 input of the antenna and is radiated into the surrounding space with the formation of a radiation pattern of the total form F _nbch (ϕ) (F _nbch (-ϕ) = F _nbch (ϕ)).

The second signal from the second 12 output of the device 1 generating and generating signals is fed to the input of BUT. BUT with an adjustable coupling coefficient for voltage K partially branches the first signal to output 31. The unbranched second signal from output 32 enters the second antenna input 21 and is radiated into the surrounding space with the formation of a radiation pattern of the differential form F _nbc (ϕ) (F _nbc (-ϕ ) = - F _nbch (ϕ)).

A branched second signal with an amplitude of K, where K is the voltage coupling coefficient of the output voltage, from the output 31 of the voltage input goes to the second 42 input of the adder.

с результирующей

ДН:The branched second and unbranched second signals together form in the surrounding space the resulting signal warhead

with the resulting

DN:

Where:

- результирующая ДН для сигнала БЧ.

- the resulting pattern for the warhead signal.

In FIG. _Figure 2 shows the _unnormalized total F _nbch (ϕ) of DN 5 and the differential F _bch (ϕ) of DN 6 formed by a 17-element antenna array of the Raman antenna.

So, when signals arrive at the first 21 input, the antenna 1 forms in space the total beam pattern with one main lobe. Upon receipt of signals at the second 22 input, the antenna 1 forms a differential beam with two main lobes.

The information parameter of the beacon of the meter wavelength range is the difference between the depths of the RGM modulation by the carrier tone signals ƒ ₁ and ƒ ₂ , determined by the ratio of the amplitude of the warhead signal to the amplitude of the LFB signal. In the case under consideration, the non-normalized MD for the warhead signal depends on the parameter K: F _bch (ϕ, K)

Let us be interested in some value of the dependent variable of the RGM, which we denote by the letter C ₀ . The value ϕ _{cm of the} independent variable ϕ, at which the RGM assumes a value equal to C ₀ , can be found from the solution of the transcendental equation:

двумя членами ее разложения в ряд Маклорена в окрестности точки ϕ=0:The position of the course line (RGM = 0) with a high degree of approximation can be found by presenting the function

two terms of its expansion in the Maclaurin series in a neighborhood of the point ϕ = 0:

Given that F _bch (0) = 0 we get:

When K << 1

При этом смещение Δϕ линии курса оказывается величиной, прямо пропорциональной

и обратно пропорциональной крутизне S_РГМ зоны КРМ:When graphing the dependence of the RGM (ϕ, K) with a given parameter K, the graph of the function of the RGM (ϕ, 0) shifts along the axis of the RGM parallel to itself by an amount

In this case, the shift Δϕ of the course line turns out to be a value directly proportional

and inversely proportional to the steepness S _RGM zone CRM:

Where:

In accordance with the requirements of ICAO standards, the steepness of zone S of the _RGM set out at the CRM must be such as to ensure that on the threshold of the runway the right (left) half-sector width is 52.5 m [Note 1 in paragraph 3.1.3.7.3 Appendix 10 to Convention on International Civil Aviation. Aviation telecommunications. Volume 1. Radio navigation aids. ICAO, Montreal (Canada), 2006. - 616 p.]. Thus, the set value S of the _RGM depends on the distance between the CRM and the threshold of the runway, i.e. from the distance D between the KRM antenna and the end face of the runway on the side opposite to the side of the aircraft approach, and the length L of the runway. At the same time, on the right (left) part of the hemisphere, the RGM value should be 0.0775.

So, for example, with a distance between the KRM antenna and the runway threshold (D + L = 980 + 2500) m equal to 3480 m, the nominal width of the right (as well as the left) part of the hemisphere is 0.864 °, and the slope of zone S of the _RGM is

In FIG. _Fig. 2 shows the unnormalized total 5 F _nbch (ϕ) _days , differential 6 _days F _Fbch (ϕ), formed by a 17-element antenna array, corresponding to K = 0.

In FIG. Figure 3 shows the dependences of the RGM (ϕ, K) for some values of K: 7 (K = -02), 8 (K = -0.1) 9 (K = 0), 10 (K = 0.1), 11 ( K = 0.2).

As a result of the input to input 21, along with the first signal of the branched second signal, a shift of the zero level of the RGM along the ϕ axis is observed. The magnitude of the offset Δϕ is determined by the sign and amplitude of the parameter K, that is, by the fraction and phase of the branch part of the signal from the second 12 output of the PFS coming to the first 21 input of the antenna.

The coefficients K = ± 0.1 corresponds to the offset Δϕ≈ ± 0.25 °. The coefficients K = ± 0.2 corresponds to the offset Δϕ≈ ± 0.5 °.

Thus, by adjusting the level of the branch signal by changing the coupling coefficient K BUT, the value of the information parameter is set to the desired position.

Second device

Assume now that in FIG. 1 shows a directional radio beacon in the format of a landing beacon group of the decimeter wavelength range with the alignment of the course line with the direction of the axis of the runway of the present invention.

The decimeter range directional beacon contains the same functional devices as the meter range directional beacon, however, implemented in the decimeter wavelength range.

The mentioned devices are made in the same way as they are carried out in serial beacons, for example, in the PRMG-76UM landing system manufactured by Chelyabinsk Radio Plant "Polet" and operated at state airfields.

The compound shown in FIG. 1 of the devices to each other is described above in the first embodiment of the devices of the present invention.

Course PRMG radio beacon works as follows. Device 1 operates under the control of a generator with a switching frequency ƒ _k equal to 12.5 Hz. [The block diagram and operation of the device 1 for generating and generating signals are discussed in our patent application for invention No. 2016115278/07 (024039) of 04/19/2016].

At the first output 11 of device 1, a high-frequency signal U ₁ (t) is generated, which during the first half-cycle of the signal of the control generator corresponding to 0.04 sec. Is modulated by a packet of meanders with a frequency of 2100 Hz U ₁₁ (t):

and during the second half-cycle, corresponding to the subsequent 0.04 seconds, it is modulated by a packet of meanders with a frequency of 1300 Hz U ₁₂ (t):

In this way,

Where:

- функция коммутации пачек меандров с частотой 2100 Гц (1300 Гц),

- the function of switching packs of meanders with a frequency of 2100 Hz (1300 Hz),

In the implemented RMC format PRMG:

τ = 35 ms is the duration of the worker. control generator interval

T _to = 80 ms - the switching period,

Ω _k = 2πƒ _k ,

- функция модуляции меандром с частотой 2100 Гц (1300 Гц).

- modulation function meander with a frequency of 2100 Hz (1300 Hz).

When substituting (18), (19) and (20) in (17) and termwise multiplying the terms, there are spectral components of the signal at the output 11 of device 1.

At the second 12 output of device 1, a high-frequency signal U ₂ (t) is generated, which during the first half-cycle of the control generator corresponding to 0.04 sec. Is modulated by a packet of meanders with a frequency of 2100 Hz, and during the second half-period corresponding to the subsequent 0.04 sec. ., is modulated by a packet of meanders with a frequency of 1300 Hz, and during the second half-cycle due to the passage of a high-frequency signal through the half-wave phase shifter of device 1 (not shown in Fig. 1), its phase is shifted by 180 °.

The minus sign in front of the second term in square brackets is due to a phase shift of the high-frequency signal by 180 ° during the passage of a packet of meanders with a frequency of 1300 Hz. Since, according to the Euler formula, -1 = e ^iπ , then, the minus sign in formula (18) means a 180 ° phase shift of the low-frequency oscillation in phase. So, a comparison of relations (17) and (21) shows that the spectral components due to the meander with a modulation frequency of 2100 Hz at outputs 11 and 12 have an initial phase of oscillation equal to the initial phase of carrier oscillations, and the initial phase of oscillation of the spectral components due to the meander with a modulation frequency of 1300 Hz, at outputs 11 and 12 it differs from each other by 180 °.

The first signal from the output 11 of the UGFS 1 is sequentially fed to the input of the adder 4, to the first 21 input of the antenna and radiated into the surrounding space with the formation of a radiation pattern of the total form F _nbch (ϕ).

The second signal from the second 12 output of the device 1 generating and generating signals is fed to the input of BUT. BUT with an adjustable voltage coupling coefficient K partially branches the second signal to output 31. The unbranched second signal from output 32 enters the second antenna input 21 and is radiated into the surrounding space with the formation of a radiation pattern of the differential form F _nbc (ϕ).

The information parameter of the PRMG format beacon is the coefficient of audibility of cattle signals (ϕ), determined by the ratio;

где

Where

- напряженность электрического поля волны, излученной при поступлении сигнала на первый (второй) вход.

- the electric field strength of the wave radiated upon receipt of the signal at the first (second) input.

Having performed the approximate transformations of relation (19), similarly to the transformations in the “First device” section, with regard to the operation of the CRM of the PRMG format with adjustment of the information parameter of the course-glide path beacons, we again come to formula (9).

By adjusting the level of the branch signal by changing the coupling coefficient K BUT, the course line is combined with the direction of the runway axis.

Third device

Turning now to FIG. 4, which shows a dual-band course PRMG beacon with the alignment of the course line with the axis of the runway.

The PRMG dual-band directional radio beacon (Fig. 4) of the present invention contains the first 1 and second UFFS, for example, two of the aforementioned PRMG 76UM landing radio beacon heading devices manufactured by CRZ Polet JSC or similar, dual-band directional antenna 2 with the first 21 input and second 22 input, the first 60 and second 70 frequency separation devices with first and second output and output, each.

Presented in FIG. 4 devices are interconnected as follows. The first output 11 of the first 1 PFFS is connected in series with the first 41 inputs of the control system, the first 601 input of the switchgear 60 and the first 21 input of the antenna. The second 12 output of the UHFS is connected in series with the input of an adjustable directional coupler, with the first 701 input of the second 70 CGR and with the second 22 input of the antenna 2. The first 31 output of the NO connected to the second 42 input of the SU 4. The first 501 output of the second UHFS is connected to the second 602 input of the first 70 CIA. The second output 502 of the second 50 PFFS is connected to the second 702 input of the second 70 CIA.

All of the above devices in the two-band CRM of the PRMG format proposed by the present invention can be made similar to those used in the serial production of Chelyabinsk Radio Plant "Flight" of the CRM product PRMG-76U.

Presented dual-band directional beacon operates as follows. Using the first 1 PFFS, high-frequency oscillations are generated at one of the operating frequencies of the first range and the first signal and the second signals of the first range are formed from them. Using the second 50 UHFS, high-frequency oscillations are generated at one of the operating frequencies of the second range and the first signal and the second signals of the second range are formed from them. The first signal and the second signal of the second range through the ACI 60 and 70 are fed to the first 21 and 22 inputs of the antenna 2 and, as a result of radiation, form a heading line in space at a frequency of the second range.

The first signal of the first UHFS through the control system and the first CRO arrives at the first 21 antenna input.

The first signal of the first range, unbranched by an adjustable directional coupler, is supplied to the first 21 antenna input through the control system and the first HMI 60.

The branched first signal through the second 70 IACs is fed to the second 22 input of the antenna. The emitted signals of the first range form in space the line of the course at the frequency of the first range.

The antenna mounted on the extension of the runway axis is oriented so that the course line formed at the operating frequency of the second range is directed in the direction of the runway axis. To combine the course line formed at the operating frequency of the first range with the direction of the runway axis, the method and devices for its implementation according to paragraph 3 of the present invention are used.

The necessary phase relations for specifying the sign of K are established by selecting the length of the connecting feeder between the first output of the adjustable directional coupler and the second input of the adder. For operational adjustment, you can use BUT or an adder with adjustable gear ratios.

Thus, choosing the amplitude and sign of the parameter K, the angular position of the resulting MD and, accordingly, the angular position of the heading line are shifted without mechanical rotation of the antenna.

Fourth device

As you know, in a two-frequency timing, the glide path angle is determined by narrow channel signals. Wide channel signals form a range below the lower hemisphere of the glide path. In the vicinity of the glide path angle, the wide channel signals are negligible. Therefore, the adjustment of the glide path angle is performed by affecting the signals of only a narrow channel.

Turning again to FIG. 1. Assume now that in FIG. 1 is a block diagram of a narrow channel dual-band timing or a block diagram of a "zero zone" timing with a glide path angle adjustment.

The glide path beacon contains 1 narrow-channel UHFS with the first 11 and second 12 outputs, antenna 2 with the first 21 and second 22 inputs, NO 3 directed with the input and the first 31 and second 32 outputs, SU 4 with the first 41 and second 42 inputs and outputs.

The aforementioned devices are made in the same way as they are carried out in serial glide-slope beacons, for example, in the flight system SP-90 manufactured by Chelyabinsk Radio Plant “Polet” and operated at civil aerodromes.

Presented in FIG. 1, the devices are interconnected as described in paragraph 2. The operation of a timing belt with an adjustable glide path angle is similar to that of an ASM with combining the heading line formed by the directional radio beacon of the ILS format wavelength meter landing system with the axis of the runway. At the first 11 output of the UFGS, an LFB signal is generated. At the second 12 output, a warhead signal is generated. The unbroken signal of the warhead is fed to the second 22 input of the antenna. The branched warhead signal and the LFB signal are jointly supplied to the first input of the antenna.

In a glide path “zero zone” beacon, the first input of the antenna is the input of the lower (reference) antenna, the second input is the input of the upper antenna.

Selecting the amplitude and sign of the parameter K, the angular position of the resulting beam and, accordingly, the angular position of the glide path are shifted by the method without changing the height of the antenna suspension.

Fifth device

Turning again to FIG. 1. Assume now that in FIG. 1 shows a block diagram of a timing belt of the PRMG format with glide path angle adjustment. The glide path beacon contains a signal generating device 1 with first 11 and second 12 outputs, antenna 2 with first 21 and second 22 inputs, HO 3 with input and first 31 and second 32 outputs, SU 4 with first 41 and second 42 inputs and output. The mentioned devices are made in the same way as they are performed in serial glide slope beacons, for example, in the flight system PRMG-76UM manufactured by Chelyabinsk Radio Plant "Polet" and operated at state airfields.

Presented in FIG. 1 devices are interconnected as described in paragraph 2.

Timing with an adjustable glide path angle in the decimeter wavelength range is similar to timing with an adjustable glide path angle in a meter wavelength range. The first signal is formed at the first 11 output of the UFGS. A second signal is generated at the second 12 output. The unbranched second signal is fed to the second 22 input of the antenna. The branched second signal and the first signal are jointly supplied to the first 21 input of the antenna.

At the first output 11 of device 1, a high-frequency signal U ₁ (t) is generated, which during the first half-period of the control generator signal corresponding to 0.04 sec. Is modulated by a meander packet with a frequency of 2100 Hz, and during the second half-period corresponding to the subsequent 0.04 sec., modulated by a packet of meanders with a frequency of 1300 Hz.

At the second 12 output of UGFS 1, a high-frequency signal U ₂ (t) is generated, which during the first half-period of the control generator, corresponding to 0.04 sec., Is modulated by a packet of meanders with a frequency of 2100 Hz, and during the second half-period, corresponding to the subsequent 0.04 sec. ., is modulated by a packet of meanders with a frequency of 1300 Hz, and during the second half-cycle due to the passage of a high-frequency signal through the phase shifter of device 1 (not shown in Fig. 1), its phase is shifted by 180 °. The first signal from the first 11 output of UGFS 1 is sequentially fed to the input of the control system and to the first 21 input of the antenna with the formation in the space of the radiation pattern of the total form F _nbc (ϕ).

The branched part of the second signal from the output 31 goes to the second input 42 of the control system 4. The second signal is emitted by the antenna 2 into the surrounding space with the formation in space of the resulting radiation pattern of the difference form

Selecting the amplitude and sign of the parameter K, the angular position of the zero level of the resulting beam and, accordingly, the angular position of the glide path are shifted without changing the height of the antenna suspension.

Claims (6)

1. The method of adjusting the information parameter of the course-glide path beacons, the information parameter is formed by a device for generating and generating signals with first and second outputs and an antenna with first and second inputs, the signal at the first output being the first signal being modulated in amplitude by two tone signals frequencies so that all high-frequency spectral components have an initial phase of oscillation equal to the initial phase of the carrier oscillation, the signal at the second output, which is the second signal, modules the amplitude of the two signals of the same tone frequencies so that the initial phase of the high-frequency spectral components with one tonal modulation frequency is equal to the initial phase of the carrier wave, and the initial phase of the high-frequency spectral components with a different tonal modulation frequency differs from the initial phase of carrier oscillations by 180 °, the fact that the second signal is partially branched, the non-branched second signal is fed to the second input of the antenna with the formation of a spatial radiation pattern with two I main petals, the second and the first branched signals together is fed to the first input of the antenna in space to form the total beam pattern with a main lobe, changing the level of the branched signal set value information parameter in the desired position. 2. Heading beacon ILS format landing system, comprising a device for generating and generating signals with first and second outputs and an antenna with first and second inputs, and the signal at the first output is modulated in amplitude by the signals of two tone frequencies ƒ ₁ and ƒ ₂ so that the initial phase the spectral components ƒ ₀ -ƒ ₁ , ƒ ₀ -ƒ ₂ , ƒ ₀ , ƒ ₀ + ƒ ₁ , ƒ ₀ + ƒ ₂ is equal to the initial phase of the carrier wave ƒ ₀ , the signal at the second output is modulated in amplitude by two signals of the same tone frequencies ƒ ₁ and ƒ ₂ so that the high-frequency spectral components with od тон ₀ -ƒ ₁ , ƒ ₀ + ƒ ₁ have an initial phase frequency equal to the carrier phase, and the initial phase of oscillations of high-frequency spectral components with a different modulation tone frequency ƒ ₀ -ƒ ₂ , ƒ ₀ + ƒ ₂ differs from the initial phase carrier 180 °; characterized in that it further comprises an adjustable directional coupler with an input and first and second outputs, an adder with first and second inputs and an output, the first output of the device generating and generating a signal in series connected to the first input of the adder and the first input of the antenna, the second output of the generating device and signal generation is connected to the input of an adjustable directional coupler, the first output of which is connected to the second input of the adder, and the second output is connected to the second input of the antenna us. 3. A directional radio beacon in the format of a landing beacon group, comprising a signal generation and generation device with first and second outputs and an antenna with first and second inputs, wherein a signal is generated at the first output of the signal generation and generation device, which during the first half-period corresponding to 0, 04 sec, modulated by a packet of meanders with a frequency of 2100 Hz, and during the second half-cycle corresponding to the subsequent 0.04 sec, modulated by a packet of meanders with a frequency of 1300 Hz, at the second output of the device a high-frequency signal, which during the first half-period of the control generator, corresponding to 0.04 seconds, was modulated by a packet of meanders with a frequency of 2100 Hz, and during the second half-period corresponding to the subsequent 0.04 seconds, was modulated by a packet of meanders with a frequency of 1300 Hz, and during the second half-cycle, its phase is shifted 180 °, characterized in that it further comprises an adjustable directional coupler with an input and first and second outputs, an adder with first and second inputs, the first output of the generating device and generating a signal is connected in series with the first input of the adder and with the first input of the antenna, the second output of the device for generating and generating a signal is connected to the input of the adjustable directional coupler, the first output of which is connected to the second input of the adder, the second output of the adjustable directional coupler is connected to the second input of the antenna. 4. A directional radio beacon in the format of a landing beacon group, comprising a first device for generating and generating signals at a first carrier frequency with a first and second output, an antenna with first and second inputs, while at the first output of the device for generating and generating a signal, a signal is generated that during the first the half period corresponding to 0.04 seconds is modulated by a packet of meanders with a frequency of 2100 Hz, and during the second half period corresponding to a subsequent 0.04 seconds, it is modulated by a packet of meanders with a frequency of 1300 Hz, per W A high-frequency signal is generated at the device’s rum output, which is modulated by a meander packet with a frequency of 2100 Hz during the first half-period of the control generator, corresponding to 0.04 sec, and modulated by a meander packet with a frequency of 1300 Hz during the second half-period corresponding to the next 0.04 sec, moreover, during the second half-cycle, its phase is shifted by 180 °, characterized in that it further comprises an adjustable directional coupler and an adder, a second device for generating and generating signals on the second carrier frequency with the first and second outputs, the first and second frequency separation devices with first and second inputs and outputs, each, and the signals at the first and second outputs are similar to the signals at the first and second outputs of the first device for generating and generating signals, while the first output of the first device generating and generating signals is connected in series with the input of the adder, the first input of the first frequency separation device and the first input of the antenna, the second output of the first generating device and forms signal conditioning is connected in series with the input of an adjustable directional coupler, with the first input of the second frequency separation device and with the second input of the antenna, the first output of the adjustable directional coupler is connected with the second input of the adder, the first output of the second signal generation and generation device is connected with the second input of the first frequency separation device , the second output of the second device for generating and generating signals is connected to the first input of the second device. 5. Glide path beacon meter wavelength range, containing a device for generating and generating signals with first and second outputs and an antenna with first and second input, and the signal at the first output is modulated in amplitude by the signals of two tone frequencies ƒ ₁ and ƒ ₂ so that the initial phase of the spectral components ƒ ₀ -ƒ ₁ , ƒ ₀ -ƒ ₂ , ƒ ₀ , ƒ ₀ + ƒ ₁ , ƒ ₀ + ƒ ₂ is equal to the initial phase of the carrier wave ƒ ₀ , the signal at the second output is modulated in amplitude by two signals of the same tone frequencies ƒ ₁ and ƒ ₂ so that the high-frequency spectral components with about discharge tone modulation frequency ƒ ₀ -ƒ _1, ƒ ₀ + ƒ ₁ are the initial phase equal to the phase of the carrier, and the initial phase of the high-frequency spectral components of oscillations with different tone modulation frequency ƒ ₀ -ƒ _2, ƒ ₀ + ƒ ₂ differs from the initial phase carrier vibrations of 180 °; characterized in that it further comprises an adjustable directional coupler with an input, first and second outputs, an adder with first and second inputs and an output, the first output of the signal generation and generation device being connected in series with the first input of the adder and with the first input of the antenna, the second output of the generating device and signal generation is connected to the input of an adjustable directional coupler, the first output of which is connected to the second input of the adder, the second output of an adjustable directional coupler Applicants have coupled to the second input of the antenna. 6. Glide path beacon format of the landing beacon group, comprising a device for generating and generating signals with first and second outputs and an antenna with first and second inputs, while at the first output of the device for generating and generating signals, a format signal of the landing beacon group is generated, which during the first half-cycle corresponding to 0.04 seconds was modulated by a packet of meanders with a frequency of 2100 Hz, and during the second half-period corresponding to the subsequent 0.04 seconds, it was modulated by a packet of meanders with a frequency 1300 Hz, a high-frequency signal is generated at the second output of the device, which is modulated by a meander packet with a frequency of 2100 Hz during the first half-cycle of the control generator, corresponding to 0.04 seconds, and is modulated by a meander packet with a second half-period corresponding to a subsequent 0.04 sec. frequency 1300 Hz, and during the second half-cycle the phase of the carrier is shifted by 180 °, characterized in that it further comprises an adjustable directional coupler with an input, first and second outputs, an adder with first and second inputs and an output, wherein the first output of the signal generating and generating device is connected in series with the first input of the adder and with the first input of the antenna, the second output of the generating and generating device is connected to the input of the adjustable directional coupler, the first output of which is connected to the second input of the adder, and the second output of the adjustable directional coupler connected to the second input of the antenna.

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