RU2593911C1 - Method of generating signal to control fighter in horizontal plane in its short-range guidance at clustered air target - Google Patents

Abstract

FIELD: radio control.

SUBSTANCE: invention relates to radio control and can be used in radio electronic systems of radio control in short-range guidance of a fighter at the best, predicted intercept point, at a clustered air target (CAT) with additional creation of a condition for providing required linear resolution of targets in the cluster in the fighter on-board radar due to the effect of radar antenna aperture synthesis.

EFFECT: technical result is: in the process of guiding a fighter in the horizontal plane at a clustered air target (CAT) in the best predicted intercept point to create the conditions for providing the on-board radar system (ORS) with the required linear resolution of targets in the cluster basing on the synthesis aperture radar (SAR) effect.

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Description

The invention relates to the field of radio control and can be used in electronic electronic radio control systems (REU) with close guidance of the fighter to the most advantageous anticipated meeting point at a group air target (MCC) with the additional creation of conditions to ensure the required linear resolution of targets in a group in an airborne radar station ) fighter due to the effect of radar synthesis aperture (SAR) antenna.

There is a method of generating a fighter control signal in the horizontal plane when it is pointed at the most advantageous anticipated meeting point on a single air target, according to which the mismatch parameter Δχ _g in the horizontal plane is determined as

Where

_r χ and χ _zm - respectively the actual and the desired angles feedforward longitudinal fighter flight in the horizontal plane;

ψ _and and ψ _um - respectively, the actual and required flight rates of the fighter;

ε _g - the angle of the bearing of the target in the horizontal plane [1].

The disadvantage of this method of generating a fighter control signal in the horizontal plane when it is pointing to the most advantageous anticipated meeting point is the inability to provide such guidance of the fighter to a group air target, which would create an additional condition for ensuring the required linear resolution of targets in the group in the fighter’s radar station when it is aimed at MCC.

There is a method of generating a fighter control signal in a horizontal plane when it is near pointing at a group of air targets at the most advantageous anticipated meeting point, which consists in generating a fighter control signal in a horizontal plane Δ _g from a range at which the fighter is launched from its missile to a range , upon reaching which the fighter launched from his side of the missile will meet with the goal, in accordance with the expression

Where

to ₁ is the coefficient of proportionality;

φ _g - the current value of the most advantageous lead angle in the horizontal plane;

D - range to group air targets;

ω _g - the angular velocity of rotation of the line of sight "fighter - group air target" in the horizontal plane;

V _sbl - the approach speed of a fighter with a group air target;

V _p and t _p are the speed and time of flight of the rocket, respectively [2].

The disadvantage of this method of generating a fighter control signal in the horizontal plane is the impossibility of using it to provide such close guidance of the fighter to a group air target in accordance with the method that is optimal according to the criterion of the minimum local quality functional when flying the fighter to the most advantageous anticipated meeting point, which would additionally create condition and to ensure the required linear resolution of targets in the group in the fighter radar based on the PC A antenna effect.

The purpose of the invention is the process of close guidance of a fighter in a horizontal plane at a group air target at the most advantageous anticipated meeting point in accordance with a method optimal for the criterion of minimum local quality functional, to additionally create a condition for ensuring in its radar station the required linear resolution of targets in the group based on the effect SAR antenna.

управления истребителем формируется в соответствии выражениемThis goal is achieved by the fact that in the method of generating a control signal of a fighter in a horizontal plane when it is near pointing at a group air target, which consists in the fact that from a range upon reaching which the fighter launches missiles from its side to a range upon reaching which the fighter a missile launched from its side will meet with a target, a fighter control signal is generated in accordance with expression (4), and from the capture range of the MCC onboard radar station to escort along range, speed, angular coordinates and their derivatives, to a range at which a fighter launches a rocket, signal $${\Delta }_R^{*}$$

fighter control is formed in accordance with the expression

Where

kΔφ is the dynamic gain;

скорости полета истребителя;w - penalty factor for the accuracy of tracking the current value of the angle between the line of sight "fighter - group air target" and the vector

fighter flight speed;

k - penalty coefficient by the value of the control signal

скорости полета истребителя от линии визирования «истребитель - групповая воздушная цель»;φ _Tr - the required angle of the deviation of the vector

the speed of the fighter from the line of sight "fighter - group air target";

ΔL is the required linear resolution of the goals in the group;

V _GVTs and V _and - respectively, the longitudinal components of the flight speeds of a group air target and a fighter;

скорости полета групповой воздушной цели;q is the angle between the line of sight "fighter - group air target" and the vector

group air target flight speeds;

λ and Δf are, respectively, the working wavelength of the onboard radar station of the fighter and the bandwidth of the narrow-band Doppler filter in the speed meter of the onboard radar station.

New features with significant differences are:

1. The formation in accordance with expressions (6), (7) and (8) of the fighter control signal in the horizontal plane when it is guided from the capture range of the MCC by the airborne radar station to tracking along the range, speed, angular coordinates and their derivatives, to the range upon reaching which the fighter launches a rocket from its side, in accordance with the method that is optimal according to the criterion of minimum local quality functional to ensure the required linear resolution of targets in its fighter radar PPE based on the effect of SAR antenna.

2. The consistent use of two methods for generating fighter control signals in the horizontal plane when it is guided close to the most advantageous anticipated meeting point in accordance with the method that is optimal by the criterion of the minimum local quality functional with the additional creation of conditions for providing the required linear resolution of targets in the fighter radar, defined by expression (6), and further, with close guidance of the fighter also at the most advantageous anticipated meeting point, emogo expression (4).

These signs have significant differences, because in known methods are not found.

The use of new features will make it possible to generate such a control signal for the fighter, which, firstly, during the near guidance of the fighter to the most advantageous anticipated meeting point in the horizontal plane at the MCC in accordance with the method that is optimal by the criterion of minimum local quality functional, will additionally create a condition for ensuring Fighter radar of the required linear resolution of targets in a group based on the SAR effect of the antenna and, secondly, it will provide guidance to the most advantageous fighter chku meeting for the successful launch of the assigned to defeat the purpose of the composition of their group.

(формула (6) описания изобретения) с их связями.In fig. Figure 1 shows the dynamic structural diagram of a RESU fighter with its close guidance in a horizontal plane, explaining the proposed method of generating a control signal of a fighter in cooperation with the known [2] (page 343, Figure 15.5 - elements of the RESU: kinematic link, formula (15.27) on page 341; goniometer; fighter control signal shaper Δ _g , formula (4) of the description of the invention); signal generator Δ _{p of} trajectory roll control, formula (15.30) on page 342); automatic control system (ACS); control object (fighter) with their connections), which additionally includes a calculator of the required angle of deviation of the fighter’s flight speed vector from the fighter-group air target line of sight (formula (8) of the description of the invention), commutator, fighter control signal generator

(formula (6) of the description of the invention) with their relations.

Figure 2 shows the geometry of the mutual movement of the fighter and the group of air targets, consisting of two targets, C1 and C2.

Figures 3 and 4 show the results of modeling an electric fighter with a proposed method for generating a control signal.

The method of generating a fighter control signal in the horizontal plane when it is near pointing at a group air target as part of a RESU loop is implemented as follows (Figure 1).

скорости полета ГВЦ, в соответствии с выражением (8) вычисляется требуемый угол φ_тр между линией визирования «истребитель - групповая воздушная цель» и вектором

скорости полета истребителя, который (угол φ_тр) необходимо постоянно поддерживать в процессе его ближнего наведения в наивыгоднейшую упрежденную точку встречи на ГВЦ по методу, оптимальному по критерию минимума локального функционала качества при его полете для дополнительного создания условия для обеспечения в БРЛС истребителя требуемого линейного разрешения ΔL целей в группе на основе эффекта РСА антенны. Значение этого угла φ_тр поступает (рисунок 1) на вход формирователя 4 сигнала управления истребителем, куда также поступают значения угла φ_г, скорости сближения V_cбл истребителя с ГВЦ и отношение весовых коэффициентов w/k. В результате на выходе формирователя 4 в соответствии с выражением (6) формируется сигнал управления

истребителем в горизонтальной плоскости, который поступает на вход коммутатора 5, куда дополнительно поступают значения (рисунок 2) дальности Д_пр, при достижении которой истребителем осуществляется пуск с его борта ракеты по назначенной для атаки цели из состава группы, дальности Д_з, дальности окончания ближнего наведения Д_он (дальности, при достижении которой истребителем пущенная с его борта ракета встретится с назначенной для атаки целью из состава группы), (рисунок 1) сигнал управления Δ_г истребителем в горизонтальной плоскости, формируемый на выходе формирователя 6 сигнала управления истребителем в соответствии с выражением (4) на основе поступающих на его входы сигналов φ_г, угловой скорости ω_г вращения линии визирования «истребитель - групповая воздушная цель» в горизонтальной плоскости, дальности Д_пр и скорости сближения V_cбл. На выходе коммутатора 5 первоначально, при выполнении условия Д_з>Д_пр, формируется сигнал управления

истребителем в горизонтальной плоскости, который поступает на вход формирователя 7 сигнала траекторного управления истребителем по крену, куда также поступает текущее значение крена истребителя с выхода динамического звена 8, описывающего объект управления (истребитель). В результате на выходе формирователя 7 формируется сигнал Δ_р траекторного управления истребителем в горизонтальной плоскости ([2], страница 342, формула (15.30) для обеспечения его ближнего наведения в наивыгоднейшую упрежденную точку встречи на ГВЦ по методу, оптимальному по критерию минимума локального функционала качества с дополнительным созданием условия для обеспечения в БРЛС истребителя требуемого линейного разрешения ΔL целей в группе на основе эффекта РСА антенны. На основе сигнала Δ_р в САУ 9 вырабатывается сигнал δ_э управления элеронами истребителя 8 для его управления в горизонтальной плоскости. Собственное поперечное ускорение J_г и курс Ψ истребителя с выхода динамического звена, описывающего истребитель 8, поступают на входы кинематического звена 1, замыкая тем самым контур ближнего наведения истребителя в горизонтальной плоскости в наивыгоднейшую упрежденную точку встречи с дополнительным созданием условия для обеспечения в его БРЛС требуемого линейного разрешения ΔL целей в группе на основе эффекта РСА антенны. Для обеспечения устойчивости и управляемости работы РЭСУ истребителем в САУ 9 вводится корректирующий сигнал ω_х.With the help of kinematic link 1 (Figure 1), the phase coordinates of the fighter’s own flight (lateral acceleration J _g and fighter _{heading связь} ) are _{connected to the} GVC (lateral acceleration J _fcc ) in the horizontal plane. As a result, the values of the angle ε _{g of the} bearing of the HVC and the current value of the most advantageous lead angle φ _g in the horizontal plane are received at the inputs of the protractor 2 (Figure 2). The calculator 3 (Figure 1) based on the received at its inputs values of distance D _of the capture MCC-board radar for range tracking, speed, angular coordinates and their derivatives, the speed of convergence V _cbl fighter with GVC, the radial component V of speed _and flight fighter , (Figure 2) the values of the required linear resolution ΔL of the targets in the group and the angle q between the line of sight “fighter - group air target” and the vector

MCC flight speed, in accordance with expression (8), the required angle φ _tr between the line of sight "fighter - group air target" and the vector

the fighter’s flight speed, which (angle φ _tr ) must be constantly maintained during its close guidance to the most advantageous anticipated meeting point at the MCC using the method that is optimal by the criterion of the minimum local quality functional during its flight to additionally create conditions for ensuring the required linear resolution in the fighter radar ΔL targets in the group based on the PCA antenna effect. The value of this angle φ _tr arrives (Figure 1) at the input of the fighter control signal _generator 4, which also includes the values of the angle φ _g , the approach speed V _{cb of the} fighter from the MCC and the ratio of weight coefficients w / k. As a result, at the output of the shaper 4, in accordance with expression (6), a control signal is generated

the fighter in the horizontal plane, which enters the input of the switch 5, which additionally receives the values (Figure 2) of the range D _pr , upon reaching which the fighter launches a rocket from its side at the designated target for the attack from the group, range D _s , and the end range of the near guidance D _he (the range at which the fighter missile launched from its side will meet the designated target for attack from the group), (Figure 1) control signal Δ _f fighter in the horizontal plane, ph adjustable at the output of the shaper 6 of the fighter control signal in accordance with expression (4) based on the signals φ _g , angular velocity ω _{g of the} rotation of the sight line “fighter - group air target” in the horizontal plane, range D _pr and approach speed V _cbl. At the output of the switch 5 initially, when the condition D _s > D _pr is satisfied, a control signal is generated

fighter in the horizontal plane, which enters the input of the shaper 7 of the fighter trajectory control signal along the roll, which also receives the current value of the fighter roll from the output of the dynamic link 8 describing the control object (fighter). As a result, at the output of the shaper 7 a signal Δ _{r of} the fighter trajectory control is generated in the horizontal plane ([2], page 342, formula (15.30) to ensure its close guidance to the most advantageous anticipated meeting point at the MCC using the method optimal by the criterion of the minimum local quality functional with the additional conditions for the creation of a radar fighter desired linear resolution ΔL purposes in the group based on the effect SAR antenna. on the basis of the signal Δ _p in ACS 9 produces a control signal δ _e e ronami fighter 8 for its control in the horizontal plane. The proper lateral acceleration J _r and Ψ fighter rate from the output of the dynamic link describing fighter 8 are applied to inputs of the kinematic unit 1, thus closing the loop passing guidance fighter aircraft in the horizontal plane in the most advantageous feedforward meeting point with the additional creation of conditions to ensure in its radar station the required linear resolution ΔL of targets in the group based on the SAR antenna effect. To ensure the stability and controllability of the RESU fighter in the ACS 9, a correction signal ω _x is introduced.

When the fighter (Figure 2) reaches the missile launch range (D _s = D _pr ) at the output of the switch 5 (Figure 1), the fighter control signal Δ _g (expression (4) is generated, as a result of which the trajectory control signal is generated at the output of the former 7 horizontal roll fighter, translating it into close guidance only at the most advantageous anticipated meeting point.

что приведет к размыканию контура ближнего наведения истребителя и выходу его из процесса ближнего наведения (выходу из атаки).Upon reaching fighter range (Figure 2), above which occur meeting fired from its bead missiles assigned to the attack order of the group (the condition D _s = D _it), to switch the output 5 (Figure 2) will not be generated no of two control signals Δ _g or

which will lead to the opening of the fighter’s close guidance loop and its exit from the near guidance process (exit from the attack).

In order to assess the operability of the proposed method for generating a fighter control signal, it was simulated as part of a dynamic structural diagram of a fighter jet in a horizontal plane. During the simulation, the following initial data were adopted (Figure 2):

the number of goals in the group - 2;

the required linear resolution of targets in the group ΔL = 150 m;

initial range to the MCC D (0) = 250 km;

radial component of the flight speed V MCC _MCC = 300 m / s;

the radial component of the fighter’s flight speed V _and = 300 m / s;

скорости полета ГВЦ q (0)=0 град.; рабочая длина волны БРЛС истребителя λ=3 см;initial angle between the line of sight "fighter - group air target" and the vector

GVC flight speed q (0) = 0 deg .; working wavelength of radar fighter λ = 3 cm;

the bandwidth of the narrow-band Doppler filter in the channel for measuring the approach speed of a fighter with a MCC Δf = 10 Hz;

ratio of penalty factors -

скорости полета истребителя от линии визирования «истребитель - групповая воздушная цель», при этом обеспечивается (рисунок 4) требуемое линейное разрешение целей в группе ΔL=150 м.As a result of the simulation, it was found that by the 15th second of the fighter’s close guidance (Figure 3), using the electronic control system with the method for generating the fighter control signal introduced into it, the required vector deflection angle φ _tr

the fighter’s flight speed from the line of sight “fighter is a group air target”, while ensuring (Figure 4) the required linear resolution of targets in the group ΔL = 150 m

Thus, the proposed method of generating a fighter control signal in the horizontal plane when it is near pointing at a group of air targets at the most advantageous anticipated meeting point in accordance with the method that is optimal by the criterion of minimum local quality functional will additionally create a condition for providing the required linear resolution in its radar goals in the group based on the effect of radar synthesis of the antenna aperture.

Information sources

1. Radio-electronic systems for navigation, aiming and armament control of aircraft. T. 2. The use of aircraft electronic systems in solving combat and navigation tasks / Ed. M.S. Yarlykova. - M .: Radio engineering, 2012 (page 104, formula (2.44), (analog).

2. Aircraft radio control systems. T. 2. Radio-electronic homing systems / Ed. A.I. Kanaschenkova and V.I. Merkulova. - M .: "Radio Engineering", 2003 (page 18, formula (7.6); page 20, formula (7.16), (prototype).

Claims (1)

The method of generating a fighter control signal in the horizontal plane when it is near pointing at a group air target, which consists in generating a signal $${\Delta }_R$$

fighter control in a horizontal plane from a range at which the fighter launches a rocket from its side, to a range at which the fighter launches a missile launched from its side with a target, in accordance with the expression

Where

to _i is the coefficient of proportionality;
φ _g - the current value of the most advantageous lead angle in the horizontal plane;
D - range to group air targets;
ω _g - the angular velocity of rotation of the line of sight "fighter - group air target" in the horizontal plane;
V _sbl - the approach speed of a fighter with a group air target;
V _p and t _p respectively the speed and time of flight of the rocket,
characterized in that from the capture range of a group of airborne targets by an airborne radar station for tracking in range, speed, angular coordinates and their derivatives, to a range at which the fighter launches a missile from its side, a signal $${\Delta }_R^{*}$$

fighter control is determined by the expression

Where

k _Δφ is the dynamic gain;
w - penalty factor for the accuracy of tracking the current value of the angle between the line of sight "fighter - group air target" and the vector

fighter flight speed;
k is the penalty coefficient by the value of the control signal;
φ _Tr - the required angle of the deviation of the vector

the speed of the fighter from the line of sight "fighter - group air target";
ΔL is the required linear resolution of the goals in the group;
V _GVTs and V _and - respectively, the longitudinal components of the flight speeds of a group air target and a fighter;
q is the angle between the line of sight "fighter - group air target" and the vector

group air target flight speeds;
λ and Δf are, respectively, the working wavelength of the onboard radar station of the fighter and the bandwidth of the narrow-band Doppler filter in the speed meter of the onboard radar station.

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