RU2710604C1 - Method of providing electromagnetic compatibility of radioelectronic equipment mounted on a mobile object - Google Patents

Abstract

FIELD: radio equipment.SUBSTANCE: invention relates to radio engineering and specifically to technical means of providing electromagnetic compatibility (EMC) of radioelectronic equipment (REE) located on a mobile object (MO). Technical result is achieved by the following sequence of actions: preliminary developing radiators for newly introduced means into REE of MO; calculating the ideal Q-factor of the radiator proper without the presence of the object housing; emitters are successively installed in permitted places on PO housing; measuring in each of the places the ideal Q-factor of the radiator in the system with the object body; calculating coefficient kaircraft body effects at the n-th installation point for emitters of an arbitrary type; storing measured values kand ranking them; finally emitter is installed in place, where value of kmaximally.EFFECT: technical result when using the disclosed method is expansion of its application area and provision of EMC of REE conditions installed on the MO.1 cl, 3 dwg

Description

The invention relates to radio engineering, and in particular to technical means for ensuring electromagnetic compatibility (EMC) of electronic equipment (RES) located on a moving object (software) (soil, railway, ships, aircraft, etc.), due to the optimal placement of the emitter introduced into the RES of the new radio facility. The method is mainly intended to achieve EMC onboard RES installed on aircraft (LA).

A known method for evaluating the EMC of onboard equipment as part of an aircraft in the frequency range from 10 kHz to 400 MHz according to patent RU No. 2497282 2012. An analogous method makes it possible to evaluate the possibility of EMC of onboard RESs when a new tool is introduced into the RES equipment. The method consists in performing the following actions: sequentially turn on the radio transmitters of the onboard radio electronic equipment, evaluate the operability of the onboard equipment before and after turning on the radio noise, measure the induced interference currents by an induction measuring current sensor, use the spectrum analyzer to measure the interference voltage level in the electric circuit taking into account the transient impedance of the induced current.

The disadvantage of this method is the low reliability of the assessment of EMC, because when it is implemented, the influence of the object’s case on the input parameters of the emitter at the place of its installation on the object’s body is not taken into account.

The “Method for ensuring electromagnetic compatibility of a communication system” is also known according to patent RU No. 2271067, 2004. An analogous method is intended to provide an EMC communication system, primarily a mobile radio communication system, working with other radio electronic equipment. In the known method: measure the group effect of the transmitters of the communication system on the receivers of other RES, then from the entire set of transmitters identify a group of transmitters that can operate simultaneously in a given frequency channel, identify for each frequency channel and fix the set of frequency channels from this range, and when the operation of the communication system, the operating frequency of the transmitter is selected from among a fixed set of frequencies suitable for EMC conditions.

A disadvantage of the known technical solution is the relatively low reliability of the evaluation of the EMC of a communication system with the mutual movement of mobile communications.

The closest analogue (prototype) in its technical essence to the claimed method is a method of providing EMC RES located on an aircraft by installing a radiator of a new radio facility introduced into the onboard RES in authorized places that take into account design and operational limitations, which provide more the effective influence of the aircraft’s hull on achieving the required parameters of the aircraft emitter-hull system, which affect the conditions for achieving EMR RES. See book: Reznikov GB Aircraft antennas, Moscow: Soviet Radio, 1962, p. 112-114.

(см. с. 112-142 упомянутой книги Г.Б. Резникова); устанавливают излучатель в выбранном месте с наибольшим значением

.The following sequence of actions is envisaged in the nearest tax: first, taking into account design and operational limitations, a set of N≥2 places on the aircraft’s body is allowed, which are allowed to install an emitter and radio means in them; sequentially in each n-th allowed place, where n = 1, 2, ... N, set the emitter of the newly introduced radio; measure the electrical parameters of the emitter in a system with an aircraft body, and the elongation coefficient of the emitter is used as a parameter

(see p. 112-142 of the mentioned book by G. B. Reznikov); install the emitter in the selected location with the highest value

.

The disadvantage of the prototype is a narrow scope, because with it, it is possible to study only electric type emitters (asymmetric vibrator, capacitive loop, cap emitters, etc.), because for magnetic type emitters (frame, inductive loop, groove, shunt vibrator), this parameter is unacceptable; in addition, the elongation coefficient takes into account only the magnitude of the current in the emitter, which is not the basis for an energy (power) reliable estimate of the parameter indicating a positive or negative effect of the aircraft body on fulfilling the EMC requirements and the feasibility of installing the emitter in this place.

The technical result in the implementation of the claimed method is to expand the scope of its application, i.e. for both electric and magnetic type radiators and achieving a more reliable assessment of the conditions for fulfilling the EMC requirements of onboard RES by reducing the concentration of reactive electromagnetic field associated with the emitter, the main source of spurious interference induced at the inputs of other RES on board the aircraft.

This goal is achieved by the fact that in the known method of providing EMC of onboard RES located on a moving object (PA), mainly on an aircraft, which consists in determining a set of N≥2 places on the aircraft housing that are allowed taking into account structural and / or operational of restrictions for installation of emitters in these places, measured in the n-th place, where n = 1, 2, ... N, the electrical parameters of each of the emitters in the system with the aircraft housing, pre-measure the complex input impedance Z _n = R _n + jX _n , where R _n , X _n - respectively the active and reactive components of the input resistance Z _{n of an} emitter of electric or magnetic type, chosen for their installation on an aircraft and measured in the absence of an aircraft housing.

и

соответственно излучателей электрического и магнитного типа, а после установки излучателя в n-ном разрешенном месте на корпусе ЛА в качестве электрического параметра излучателя в системе с корпусом ЛА измеряют идеальную добротность соответственно излучателя электрического

и магнитного

типа в присутствии корпуса ЛА. Причем измеряют

и

непосредственно на входе излучателя при отключенном от входа излучателя фидерном тракте.From the measured values of R _n , X _n calculate the ideal figure of merit

and

respectively, emitters of electric and magnetic type, and after installing the emitter in the n-th authorized place on the aircraft’s body as the electric parameter of the radiator in the system with the aircraft’s body, the ideal quality factor of the electric radiator is measured

and magnetic

type in the presence of the aircraft body. Moreover, they measure

and

directly at the input of the emitter when the feeder path is disconnected from the input of the emitter.

и магнитного

типа.Then calculate the coefficient k _{n of the} influence of the aircraft body at the n-th installation site of the electric emitter

and magnetic

type.

и соответствующие им тип излучателя запоминают. А после завершения вычислений k_n по всем N их значения ранжируют.All measured values

and the corresponding type of emitter is stored. And after the completion of calculations k _n for all N, their values are ranked.

Finally, an emitter of the corresponding type is installed in a permitted place on the aircraft body, in which of all the calculated values, the value of k _{n is} maximum.

вычисляют по формуле Q_Σ0=|X_n|/R_n.Ideal Q factors of emitters

calculated by the formula Q _Σ0 = | X _n | / R _n .

Thanks to a new set of essential features in the claimed method, based on measurements of electrical parameters in terms of quality factors, it is possible to more accurately take into account the influence of the object’s body at the installation sites of emitters of an arbitrary type of newly introduced radio means in which the energy concentration of the reactive electromagnetic field associated with the emitter is minimal and, therefore, ceteris paribus, it will form interference to a minimum extent, affecting the remaining RES, i.e. conditions for fulfilling the EMC requirements for onboard RES In addition, the assessment of the parameters of the emitter in terms of quality factor is acceptable to an emitter of an arbitrary type: electric and magnetic.

The claimed technical solution is illustrated by drawings, which show:

in FIG. 1 is a drawing illustrating placement of electric type emitters in permitted places on the aircraft body;

in FIG. 2 is a drawing explaining the placement of magnetic type emitters in permitted places on the aircraft body;

in FIG. 3 - tables 1 and 2 with the results of experimental measurements.

The implementation of the claimed method is explained as follows.

The mounted emitter on the aircraft body, like any other electrodynamic system, is characterized by the general equation of energy balance (see, for example, the book: Muravyov, Yu.K. Antenna devices for radio communications. Leningrad: VAS, 1973, p. 8-9):

- комплексная мощность, затрачиваемая сторонним источником;here

- integrated power consumed by a third-party source;

P _A = P _Σ + P _P - active power dissipated by the antenna system;

P _Σ is the power spent on creating the radiation field;

R _P - the power of irrevocable heat loss in the structural elements of the antenna and its environment;

ω is the circular frequency;

и

- усредненная за период энергия связанного с излучателем реактивного электрического поля и связанного реактивного магнитного поля.

and

- the energy averaged over the period associated with the emitter of the reactive electric field and the associated reactive magnetic field.

и магнитного

реактивных полей в системе излучатель-корпус ЛА будет иметь место баланс их энергий в среднем за период.In the case of equality of the energies of the bound electric

and magnetic

reactive fields in the system of the radiator-body of the aircraft will have a balance of their energies on average over the period.

This indicates a potentially minimal concentration of the reactive field associated with the emitter in the near field and, as a result, minimization of spurious interference to other RES.

или

баланс в электродинамической системе (1) нарушен и резко возрастает в ближней зоне энергия связанного реактивного поля, усредненного за период. В этом случае излучатель (систему излучатель-корпус ПО) относят соответственно к излучателям электрического

или излучателям магнитного

типа.Under the conditions

or

the balance in the electrodynamic system (1) is broken and the energy of the bound reactive field averaged over the period sharply increases in the near zone. In this case, the emitter (the system of the emitter-case software) is assigned respectively to the emitters of the electric

or magnetic emitters

type.

For further analysis of the possibility of providing EMC RES along with other means (frequency, time, spatial separation, the use of filters, etc.), the concepts used in the claimed method are: ideal Q factor of the emitter Q _Σ0 in the absence of influence of the aircraft body and ideal Q factor Q _Σn of the emitter system -the aircraft hull when the emitter is installed in the n-th authorized place on the aircraft hull.

излучателя много меньше длины рабочей волны λ, т.е.

Q_Σ0 излучателя произвольного типа можно вычислить по формуле Q_Σ0=|X_n|/R_n.In the case when the largest geometric size

emitter is much less than the wavelength λ, i.e.

Q _{Σ0 of} an arbitrary type emitter can be calculated by the formula Q _Σ0 = | X _n | / R _n .

The value of Q _Σn in any place in the n-th place on the aircraft can be measured, for example, by a Q-meter - Q-meter or other similar device.

Based on the preliminary observations stated, the implementation process of the claimed method is reduced to the following sequence of actions:

1. Based on the presented structural and / or operational limitations, determined by the overall dimensions, layout, aerodynamic constraints, etc., an electrical circuit and design of the arbitrary type of emitters proper are developed to minimize their ideal quality factor Q _Σ0 .

и

через соответствующие им входные сопротивления:2. Calculate the ideal quality factor

and

through the corresponding input impedances:

where, the indices "e" and "m" indicate that the parameter belongs to the emitter of the electric and magnetic type, respectively.

, соответствует условию

где λ длина рабочей волны излучателя.Expressions (2) are all the more valid, the closer the largest linear size of the emitter

meets the condition

where λ is the working wavelength of the emitter.

3. Install sequentially designed emitters in the permitted places on the aircraft body. In FIG. Figure 1 shows five permitted locations for the installation of electric type emitters (unbalanced vibrators), i.e. N ^e = 5. In FIG. 2 - four permitted places for installing magnetic type emitters (grooved), i.e. N ^m = 4.

или магнитного

типа в n-ном месте в присутствии корпуса ЛА. Для получения более точных измерений за счет исключения искажающего влияния тепловых потерь в фидерном тракте, органах настройки и согласования, фидерный тракт отключают от входа излучателя, а измерения

и

проводят путем подключения Q-метра непосредственно к входу излучателя.4. Measure, for example, using a quality factor meter (Q-meter) of the type “KV-1” (No. 3651) or another similar device, the ideal quality factor of the system: an electric emitter

or magnetic

type in the n-th place in the presence of the aircraft body. To obtain more accurate measurements by eliminating the distorting effect of heat loss in the feeder path, tuning and matching organs, the feeder path is disconnected from the input of the emitter, and measurements

and

carried out by connecting a Q-meter directly to the input of the emitter.

и магнитного типа

по формулам:5. Calculate the coefficient k _{n of the} influence of the aircraft body at the n-th installation site of the electric emitter

and magnetic type

according to the formulas:

6. All calculated values of k _n and the corresponding types of emitters are stored (see Fig. 3).

7. The stored values of k _n are ranked (Fig. 3).

или

.8. The final choice of the type of emitter and the place of its installation is determined on the basis of reaching the highest value for this type of emitter in this place

or

.

или магнитного типа

максимальное значение k_n достигается выбором места установки излучателя и его типа, при которых минимальное значение приобретает идеальная добротность

системы излучатель-корпус объекта. Это однозначно указывает на снижение в ближней зоне связанного реактивного поля, создающего в ближней зоне помехи другим РЭС, входящим в состав бортового комплекса РЭС (см. например, книгу: Муравьев Ю.К. Антенные устройства для радиосвязи. Ленинград: ВАС, 1973, с. 9-10).As follows from formula (3) for a fixed value of ideal quality factor of electric type emitters

or magnetic type

the maximum value of k _{n is} achieved by choosing the installation location of the emitter and its type, at which the minimum value acquires the ideal quality factor

system emitter-body of the object. This unambiguously indicates a decrease in the near zone of the associated reactive field, which creates interferences in the near zone with other RES included in the onboard complex of the RES (see, for example, the book: Muravyov, Yu.K. Antenna devices for radio communications. Leningrad: VAS, 1973, p. . 9-10).

To verify the validity of the conclusions made, experimental measurements were carried out on mock-ups of TU-154 (Fig. 1) and AN-8 (Fig. 2) aircraft, made on a scale of 1:10, taking into account the observance of the principle of electrodynamic similarity.

The measurements were carried out in the frequency range 1.0 ... 2.0 GHz for an electric type emitter, which was located in 5 permitted places and magnetic type - in 4 allowed places (Fig. 1 and 2).

The measurement results shown in Tables 1 and 2 provide the basis for the following conclusions:

1. The coefficient k _{n of the} influence of the housing on the electrical parameters of the emitter in the system with the housing of the object substantially depends on the installation location of the emitter.

2. At the point of attaining the highest value of k _{n, the} ideal figure of merit of the object emitter-body system is minimal, which indicates a decrease in the concentration of the energy of the associated reactive field averaged over a period in the near field and, consequently, a decrease in the level of interference that interferes with other elements of the radio-electronic complex of the airborne complex.

3. The most acceptable, from the point of view of providing EMC RES, is for an emitter of electric type the places on the aircraft’s hull designated Nos. 4 and 5, where k ^e = (1.40 ÷ 1.48) is maximum at all frequencies (Fig. 1, Table 1). For a magnetic type emitter, the best place is No. 1 (Fig. 2), in which k ^m = (1.73 ÷ 1.78) at all frequencies.

4. Reflected in the claims a new set of essential features, confirmed by the results of experimental verification, indicates the possibility of achieving the formulated technical result when implementing the claimed technical solution.

Claims (2)

1. The way to ensure electromagnetic compatibility (EMC) of electronic equipment (RES), located on a moving object (software), mainly on an aircraft (LA), which consists in the fact that they determine the set of N≥2 places on the body of the aircraft, allowed taking into account design and / or operational restrictions for installing the emitters in these places are measured at the nth place, where n = 1, 2, ... N , the electrical parameters of each of the emitters in the system with the aircraft’s hull, characterized in that the complex input copro ivlenie Z _n = R _n + j x _n, where R _n, X _n - respectively the active and reactive components of the input impedance Z _n emitters electric or magnetic type, chosen for their installation on the aircraft, measured in the absence of the aircraft body, the measured values of R _n , X _n calculate ideal Q factors

respectively, emitters of electric and magnetic type, and after installing the emitter in the nth allowed place on the aircraft’s body as the electric parameter of the radiator in the system with the aircraft’s body, the ideal quality factor of the electric radiator is measured

and magnetic

type in the presence of the body of the aircraft, and measure

directly at the input of the emitter when the feeder path is disconnected from the input of the emitter, and then the coefficient k _{n of the} influence of the aircraft housing at the nth installation site of the electric emitter is calculated

and magnetic

type, remember

after which all the stored values of k _n are ranked, and the emitter of the corresponding type is finally installed in a permitted place on the aircraft body, in which of all the calculated values, the value of k _{n is} maximum. 2. The method according to p. 1, characterized in that the ideal quality factor of the electric emitter

and magnetic

type calculated by the formulas:

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