RU2220397C1 - Method for guidance of flight vehicles on ground targets at semi-active synthesizing of antenna aperture - Google Patents

Abstract

FIELD: systems of flight vehicle homing on ground targets. SUBSTANCE: measured on the flight vehicle of the receiving site are the values of the rate of its closure to the target, angular velocity of the target sighting line and the lateral acceleration of the flight vehicle of the receiving site providing the best accuracy of homing to the target. The control signal is produced on their basis. The value of angular velocity of the target sighting line is transmitted from receiving site flight vehicle to the transmitting site flight vehicle. Measured on board the transmitting site flight vehicle are the distance from it to the ground target, angular velocity of the target sighting line and the lateral acceleration, on the basis of which the value of the required angular velocity of the target sighting line is computed, providing the preset value of linear resolution of the receiving site radar in angle. On the basis of the computed required angular velocity of the target sighting line, measured values of the distance to the target, angular velocity of the target sighting line and the lateral acceleration of the transmitting sight flight vehicle the control signal of the transmitting site flight vehicle is produced. In compliance with the produced control signals the control of the flight vehicles of the receiving and transmitting sites is accomplished respectively. EFFECT: enhanced accuracy of guidance, enhanced guidance range and secrecy of guidance. 2 dwg

Description

 The invention relates to systems for homing aircraft (LA) for ground targets, using radar stations with the synthesis of antenna aperture (SAA) and Doppler beam sharpening (DOL) of an antenna to measure the coordinates of targets.

 In these systems, guidance effectiveness is equally strongly dependent on both the accuracy of measurements of the coordinates of the targets and the method of pointing the aircraft at them. In this regard, the guidance system for this purpose should provide such a trajectory of the induced aircraft, which ensures high accuracy of measurements of the coordinates of the ground target and high accuracy of guidance.

 Among the well-known radar meters for coordinates of ground targets, the most effective are radars with SAA, which allow in any weather conditions to obtain high detail images of the earth's surface, approaching photo images [1-3], and, as a result, to make high-precision measurements of target coordinates. In connection with the foregoing, the most effective guidance methods are those that allow the use of radar with SAA or DOL on a guided LA.

Currently, the antenna aperture synthesis methods are most widely used in active homing systems for air-to-surface missiles and attack aircraft operating on ground targets [1–4, 6–8]. However, the following disadvantages are inherent in active homing systems [4]:
1. In such systems, to ensure the required detail of the image of the earth's surface when using SAA, the flight path of the induced aircraft should be fundamentally curved, which negatively affects the accuracy of aiming and leads to a loss of range up to 15%.

 2. The short range of the active guidance system due to the low power of the transmitter installed on the induced aircraft.

 3. Low stealth guidance process, predetermined by the radiation of the transmitter induced aircraft.

 In connection with the noted drawbacks, the use of semi-active homing systems for aircraft with the synthesis of antenna apertures on them is very promising [3, 9]. In these homing systems, two aircraft are used, which form two movable positions: a transmitting and a receiving one, and the receiving position is induced almost directly along the straight path to the target. Each of the moving positions is equipped with its own radar, which form a bistatic radar system [10].

 The specificity of semi-active CAA is that high linear resolution of targets in the radar of the receiving position is achieved through specially organized movement of the aircraft of the transmitting position when the aircraft moves of the receiving position directly in the direction of the target [3, p. 278].

 In rocket technology, the semi-active homing method is used quite widely, but when aiming at air targets. Moreover, for the formation of the trajectory control parameter of the rocket, as a rule, various varieties of the proportional guidance method are used, and the DOL or CAA mode is implemented in its radar. Illumination of the target is provided by the radar of the fighter, the control system of which should provide such a trajectory of its movement that the guided missile and the target should always be within the solid angle, the value of which is determined by the width of the radiation pattern of the radar antenna.

 There is a method of simultaneous guidance of an air-to-air missile and a fighter’s flight to the most advantageous meeting point with a target [5, p.238; 11, p. 96]. With a uniform and rectilinear movement of the target, the fighter and the rocket after launch also move rectilinearly and evenly. With ideal homing missiles in such conditions, the angular velocity of the line of sight of the missile target is zero. With this method of semi-active homing missiles and the specified condition for the movement of the target is not required to change the flight path of the fighter.

 Continuous or discrete-continuous signals are used as target illumination signals when pointing air-to-air missiles [5, p. 237, 312; 11, p. 84]. The selection of target signals in missile radar is carried out against the background of reflections from the earth's surface using a narrow-band Doppler filter. When pointing at an approaching target, reflections from the earth's surface do not affect the functioning of the radar, since the speed of approach to the target is greater than the speed of approach to the ground. When attacking a target in catch-up courses, the frequency spectrum of the signals reflected from it falls into the region of the spectrum of the signal coming from the earth's surface along the side lobes of the antenna pattern, which lie below the main lobe. As a rule, in the passband of a narrow-band Doppler filter, the target signal exceeds in power the signal reflected from the earth's surface. Therefore, in catch-up courses, it is also possible to measure the speed of approach, angular coordinates and their derivatives with respect to time.

 However, this method of semi-active homing, as well as other methods of semi-active homing at air targets, cannot be used when aiming at slow-moving ground targets. This is explained by the fact that with this method of pointing to a ground target, the spectrum of the signal reflected from it is located in the region corresponding to reflections from the earth's surface in the direction of the main lobe of the radar antenna radiation pattern. In addition, when aiming at a fixed ground target, the lead angle is fundamentally small, since it is only necessary to parry the rocket drift caused by the wind. As a result, the linear resolution in the angular coordinate drops sharply, which leads to an increase in the power of the signal reflected from the earth's surface passing through the narrow-band Doppler filter, compared with the case of large lead angles.

 Summarizing the aforesaid, it can be argued that to obtain a high linear resolution of a ground target during semi-active synthesis of the antenna aperture during the movement of the aircraft of the receiving position directly to the target is possible only due to a specially organized movement of the aircraft of the transmitting position. In this case, the choice of the trajectory of the aircraft in the receiving position minimizes guidance errors, in particular the miss, and the movement of the aircraft in the transmitting position is optimized based on the required linear resolution in the radar of the receiving position [3, p. 278].

To clarify what has been said, we will consider a possible version of the operation of the air-to-surface missile guidance system for a semi-active synthesis of the antenna aperture and give the main dependences of the linear azimuth resolution on the application conditions. Suppose that on an airplane located at point O _c (Fig. 1) at a distance D _c from a fixed target O _c and moving at a speed V _c at an angle φ _c to it, a backlight signal with a wavelength λ is generated, which is received after reflection from the target on a rocket located at the point O _p at a distance D _p from the target and moving with speed V _p at an angle φ _p to it.

В зависимости от точности аппроксимации частоты f_дрр (2), могут быть получены различные формулы, связывающие между собой требуемое разрешение Δl_т с условиями применения самолета и ракеты, определяемыми конкретными значениями V_c, φ_c, V_p, φ_p. Рассмотрим наиболее простой случай, который базируется на аппроксимации частоты f_дрр рядом Тейлора с использованием линейных членов разложения. При таких условиях

где было учтено равенство (1).The Doppler frequency of the signal f _drc reflected from the target and received on the rocket is determined by the ratio
f _other = (V _c cosφ _c + V _p cosφ _p ) / λ. (1)
In turn, the Doppler frequency of the signal f _drr reflected from the point O _{rr of the} earth’s surface, remote from the target at a distance of O _c O _rr , equal to the required linear resolution Δl _t , can be calculated by the formula

Depending on the accuracy of the approximation of the frequency f _drr (2), various formulas can be obtained that relate the required resolution Δl _t to each other with the conditions of use of the aircraft and the rocket, determined by the specific values of V _c , φ _c , V _p , φ _p . Let us consider the simplest case, which is based on approximating the frequency f _drp by the Taylor series using linear expansion terms. Under such conditions

where equality (1) was taken into account.

где

и

- угловые скорости линии визирования цели в горизонтальной плоскости соответственно с самолета и с ракеты. Из выражения (4) можно получить, что требуемое разрешение Δl_т на ракете, определяемое соотношением

зависит от длины волны λ сигнала подсвета цели, полосы пропускания ΔF приемника ракеты и динамики взаимного перемещения самолета и ракеты относительно цели, определяемой ω_гc и ω_гp. В свою очередь из выражения (5) следует, что для получения на ракете требуемого разрешения Δl_т, самолет должен перемещаться таким образом, чтобы угловая скорость линии визирования ω_гc удовлетворяла требованию

где ω_гт - требуемое значение угловой скорости линии визирования цели.In order to resolve the points O _c and O _pp , the passband of the rocket receiver ΔF should not exceed the value

Where

and

- the angular velocity of the line of sight of the target in the horizontal plane, respectively, from an airplane and from a rocket. From expression (4) it can be obtained that the required resolution Δl _t on the rocket, determined by the ratio

depends on the wavelength λ of the target illumination signal, the passband ΔF of the rocket receiver, and the dynamics of the mutual movement of the aircraft and the rocket relative to the target determined by ω _gc and ω _gp . In turn, it follows from expression (5) that, in order to obtain the required resolution Δl _t on a rocket, the aircraft must move in such a way that the angular velocity of the line of sight ω _gc satisfies the requirement

where ω _rm is the required value of the angular velocity of the line of sight of the target.

Из известных способов наведения летательных аппаратов на наземные цели с синтезированием апертуры антенны наиболее близким аналогом (прототипом) является способ самонаведения, описанный в литературе [4], который в горизонтальной плоскости характеризуется следующим алгоритмом траекторного управления:

где Δ_г - сигнал управления ЛА в горизонтальной плоскости;

- требуемое значение угловой скорости вращения линии визирования цели ω_г, при котором обеспечивается требуемое линейное разрешение цели по углу в горизонтальной плоскости Δl_т; Д_н - значение дальности до цели в начале наведения; Д_к - известное значение дальности окончания наведения, зависящее от типа наводимого ЛА; V_cб - значение скорости сближения ЛА с целью; j_г - значение поперечного ускорения ЛА в горизонтальной плоскости; к_уст - коэффициент, определяющий точность наведения и стабилизацию линейного разрешения по углу в горизонтальной плоскости; λ - длина волны РЛС; ΔF - полоса пропускания приемника РЛС.It can be seen from expression (6) that the trajectory of the aircraft is determined by the required resolution Δl _t , the passband ΔF of the missile receiver, the wavelength λ of the target illumination signal and the dynamics of the relative movement of the missile relative to the target determined by ω _{gp /} , and therefore the law of missile guidance. To implement the desired trajectory of the aircraft, it is necessary to transmit the value of the angular velocity ω _{gp of} the target line of sight to it from the rocket. When using the rocket method of proportional guidance to a stationary ground target, when ω _gp ≈ 0, the aircraft moves along a trajectory that corresponds to the condition

Of the known methods of pointing aircraft to ground targets with the synthesis of the antenna aperture, the closest analogue (prototype) is the homing method described in the literature [4], which in the horizontal plane is characterized by the following trajectory control algorithm:

where Δ _g is the control signal of the aircraft in the horizontal plane;

- the desired value of the angular velocity of rotation of the line of sight of the target ω _g , which provides the required linear resolution of the target in the angle in the horizontal plane Δl _t ; D _n - the value of the distance to the target at the beginning of the guidance; D _to - the known value of the range of the end of guidance, depending on the type of induced aircraft; V _cb is the value of the approach speed of the aircraft with the target; j _g - the value of the transverse acceleration of the aircraft in the horizontal plane; to _mouth - a coefficient that determines the accuracy of guidance and stabilization of the linear resolution of the angle in the horizontal plane; λ is the radar wavelength; ΔF is the bandwidth of the radar receiver.

за счет минимизации ω_г. В формуле (10) Д - текущая дальность от ЛА до цели.This trajectory control algorithm simultaneously provides both the required linear resolution in azimuth due to the use of ω _gt (9) and the minimization of the current miss [5, p. 183]

by minimizing ω _g . In the formula (10), D is the current range from the aircraft to the target.

However, due to the fact that the active homing system is used in the homing system presented in [4], the following drawbacks are inherent in it: 1) to ensure the required image detail of the earth’s surface
when using CAA, the flight path of a missile aimed at a target should fundamentally be curved, which reduces the accuracy of guidance and leads to loss of range; 2) a short range due to the low power of the rocket transmitter.

 Thus, the objective of the invention is the provision of high-precision guidance of missiles at slow moving ground targets along trajectories close to straight, and increasing the range of the guidance system. In addition, the implementation of the proposed invention will improve the secrecy of the guidance system.

 The task is achieved in that it provides simultaneous guidance of two aircraft: the aircraft of the transmitting position (aircraft) and the aircraft of the receiving position (rocket). In this case, the rocket’s movement will be carried out almost along a straight line trajectory with a minimum current miss, and the aircraft’s motion will be carried out along the trajectory in which the CAA or DOL mode is implemented in the missile’s radar.

его сближения с целью и угловую скорость

линии визирования цели в горизонтальной плоскости. Измеряют поперечное ускорение

ЛА приемной позиции в горизонтальной плоскости. Формируют сигнал управления Δ_гр ЛА приемной позиции в горизонтальной плоскости по закону

где Д_н - значение дальности до цели в начале наведения; Д_к - известное значение дальности окончания наведения, зависящее от типа ЛА приемной позиции.The claimed method of pointing aircraft to ground targets with semi-active SAA is carried out in the following order. From the radar of the transmitting station’s radar, target illumination signals are emitted. Based on the signals reflected from the target, the speed values are measured at the aircraft of the receiving position

its proximity with the target and angular velocity

line of sight of the target in the horizontal plane. Lateral acceleration

LA receiving position in the horizontal plane. Form a control signal Δ _gr LA of the receiving position in the horizontal plane according to the law

where D _n - the value of the distance to the target at the beginning of the guidance; D _to - the known value of the range of the end of guidance, depending on the type of aircraft receiving position.

линии визирования цели.From the LA of the receiving position, the measured value of the angular velocity is transmitted along the data line to the LA of the transmitting position

target line of sight.

от него до наземной цели и угловую скорость

линии визирования цели. Измеряют поперечное ускорение

ЛА передающей позиции в горизонтальной плоскости. Рассчитывают значение требуемой угловой скорости ω_гт линии визирования цели по формуле

где λ - длина волны сигнала подсвета цели, ΔF - полоса пропускания приемника РЛС приемной позиции, Δl_т - требуемое значение линейного разрешения РЛС приемной позиции по углу.Based on the signals reflected from the target on board the transmitting aircraft, the range is measured.

from it to a ground target and angular velocity

target line of sight. Lateral acceleration

Aircraft transmitting position in the horizontal plane. The value of the required angular velocity ω _{gt of the} line of sight of the target is calculated by the formula

where λ is the wavelength of the target illumination signal, ΔF is the passband of the radar receiver of the receiving position, Δl _t is the required linear resolution of the radar of the receiving position in the angle.

где q_ω - постоянный коэффициент.A control signal Δ _{gf of the} aircraft of the transmitting position in the horizontal plane is generated in accordance with the formula

where q _ω is a constant coefficient.

In accordance with the control signals Δ _gp (11) and Δ _gc (13) control the aircraft respectively receiving and transmitting positions.

обратно пропорционально дальности до цели, что предопределяет повышение чувствительности сигнала управления Δ_гc к несоответствию Δ_гт и

на малых дальностях ЛА передающей позиции от цели.In the control signal (13): ω _rm - determines the required value of the angular velocity of the line of sight of the target, providing a given linear resolution of the angle Δl _tr in the horizontal plane in the radar of the receiving position; weight factor value

inversely proportional to the distance to the target, which determines the increase in the sensitivity of the control signal Δ _gc to the discrepancy Δ _gt and

at short ranges of the aircraft transmitting position from the target.

From the expressions (11) - (13) it follows that, compared with the control signal (8) of the prototype, the control signal of the aircraft of the receiving position is characterized by the absence of the term ω _rm , taking into account the need to stabilize the required linear resolution Δl _{t of the} radar of the receiving position in angle, and provides only minimization of the current miss (10). In turn, the control signal of the aircraft of the transmitting position (13) differs from (8) by the presence of an additional term that takes into account the angular velocity ω _{gp of} the target line of sight from the aircraft of the receiving position and another weighting factor when generating the required angular velocity ω _gt (12) of the target line of sight .

 Figure 1 explains the geometric relationship between the coordinates of the absolute and relative motion of aircraft and ground targets in the horizontal plane.

In FIG. 2 presents a simplified block diagram of a possible variant of a semi-active aircraft guidance system for ground targets that implements the proposed guidance method, where:
1 - aircraft transmitting position;
2 - accelerometer aircraft transmitting position;
3 - calculator control signals aircraft transmitting position;
4 - range meter radar aircraft transmitting position;
5 - transmitter radar aircraft transmitting position;
6 - control system of the aircraft transmitting position;
7 - protractor radar LA transmitting position;
8 - receiver radar aircraft transmitting position;
9 - antenna radar aircraft transmitting position;
10 - the goal;
11 - a receiving antenna of a data line;
12 - receiver data line;
13 - calculator of the required value of the angular velocity of the line of sight of the target;
14 - antenna radar LA receiving position;
15 - transmitting antenna of a data line;
16 - transmitter data line;
17 - protractor radar LA receiving position;
18 - receiver radar LA receiving position;
19 - accelerometer LA receiving position;
20 - aircraft receiving position;
21 - control system of the aircraft receiving position;
22 - calculator control signals of the aircraft receiving position;
23 - speed meter radar LA receiving position.

 2, dashed lines show communications by radio signals.

 Note. The principles of constructing radar transmitting and receiving positions and their structural schemes for various operating modes of the SAA are described in detail in the literature [1-3, 10]. Extensive literature is devoted to the principles of constructing data transmission lines, in particular [12]. In connection with the foregoing, the presented structural diagram of the functioning of the guidance system is given in a simplified form.

 The claimed method of pointing aircraft to ground targets with semi-active SAA is as follows.

линии визирования цели и подают ее в привод антенны РЛС ЛА приемной позиции 14, доворачивающий ее в направлении цели.The high-frequency signal generated in the transmitter of the radar of the LA of the transmitting position 5, is transmitted through the antenna system of the radar of the LA of the transmitting position 9 in the direction of the target 10. The signal received from the target 10, received by the radar antenna of the LA of the receiving position 14, is input to the radar receiver of the LA of the receiving position 18, where there is a selection of the signal reflected from the target, against the background of noise, in particular, due to narrow-band Doppler filtering when using the CA antenna mode. From the output of the radar receiver of the LA of the receiving position 18, the signal is fed to the input of the protractor of the radar of the LA of the receiving position 17, in which the angular velocity is measured

line of sight of the target and feed it into the drive of the radar antenna of the aircraft of the receiving position 14, turning it in the direction of the target.

линии визирования цели подают в вычислитель сигналов управления ЛА приемной позиции 22 и в передатчик линии передачи данных 16 для модуляции его сигнала, излучаемого затем передающей антенной линии передачи данных 15 в направлении ЛА передающей позиции.In addition, the measured value of the angular velocity

the target line of sight is fed to the transmitter of the control signals of the aircraft of the receiving position 22 and to the transmitter of the data line 16 to modulate its signal, which is then emitted by the transmitting antenna of the data line 15 in the direction of the aircraft of the transmitting position.

ЛА приемной позиции с целью, которую затем подают в вычислитель сигналов управления ЛА приемной позиции 22, куда одновременно из акселерометра ЛА приемной позиции 19 подают измеренное значение поперечного ускорения

ЛА приемной позиции в горизонтальной плоскости. В вычислителе сигналов управления ЛА приемной позиции 22 на основе измеренных значений

а также заранее введенных значений дальностей начала Д_н и окончания Д_н наведения в соответствии с формулой (4) формируют сигнал управления Δ_гр, подаваемый в систему управления ЛА приемной позиции 21, которая отклоняет рулевые органы ЛА приемной позиции 20, обеспечивая его полет по траектории, минимизирующей текущий промах.In addition, the signal from the output of the radar receiver of the LA of the receiving position 18 is fed to the radar speed meter of the LA of the receiving position 23, in which the approach speed is measured on its basis

LA of the receiving position for the purpose, which is then fed to the calculator of the control signals of the LA of the receiving position 22, where simultaneously from the accelerometer of the LA of the receiving position 19 serves the measured value of the transverse acceleration

LA receiving position in the horizontal plane. In the calculator of the control signals of the aircraft of the receiving position 22 based on the measured values

as well as the previously entered values of the ranges of the beginning of D _n and the end of D _n guidance in accordance with formula (4) form a control signal Δ _gr fed to the control system of the aircraft of the receiving position 21, which rejects the steering organs of the aircraft of the receiving position 20, ensuring its flight along the trajectory minimizing the current miss.

и подают ее в вычислитель сигналов управления ЛА передающей позиции 3.At the same time, the signals reflected from the target 10 are received by the antenna system of the radar of the aircraft of the transmitting position 9 and fed to the receiver of the radar of the aircraft of the transmitting position 8, in which the frequency selection of the signals of the target occurs. The signals from the output of the receiver of the radar of the aircraft of the transmitting position 8 are fed to the input of the range meter of the radar of the aircraft of the transmitting position 4, in which the distance to the target is measured on their basis

and submit it to the transmitter control signals of the aircraft transmitting position 3.

линии визирования цели, подаваемые в вычислитель сигналов управления ЛА передающей позиции 3, куда из акселерометра ЛА передающей позиции 2 подают измеренные значения поперечного ускорения

ЛА передающей позиции в горизонтальной плоскости.At the same time, signals from the receiver of the radar of the aircraft of the transmitting position 8 are supplied to the protractor of the radar of the aircraft of the transmitting position 7, in which signals are generated to control the position of the antenna system of the radar of the aircraft of the transmitting position 9 and the measured values of the angular velocity

target sighting lines supplied to the LA control signal transmitter of the transmitting position 3, to which the measured values of lateral acceleration are fed from the accelerometer of the LA of the transmitting position 2

Aircraft transmitting position in the horizontal plane.

The calculator of the required value of the angular velocity of the line of sight 13 based on the previously entered values of the passband ΔF of the radar receiver of the receiving position, the required linear resolution Δl _{t of the} radar of the receiving position by the horizontal angle and wavelength λ determines the required value of the angular velocity ω _{rm of the} line of sight in accordance with by the formula (5), which is fed to the calculator of the control signals of the aircraft of the transmitting position 3, where, in accordance with the formula (6), the control signal Δ _{gf of the} aircraft of the transmitting position is calculated horizontally ntal plane. In the control system of the aircraft of the transmitting position 6, the generated control signal Δ _g in the horizontal plane is converted to the corresponding control actions, which lead to the deviation of the steering organs of the aircraft of the transmitting position. As a result, the aircraft of the transmitting position moves along such a trajectory at which the CA antenna mode is implemented in the radar of the receiving position.

 The claimed method of guidance of aircraft does not impose any restrictions on the magnitude of the transverse accelerations and angular velocities of the line of sight of both aircraft, as well as the elemental base and the speed of the computers.

 The use of the invention will ensure the trajectory of the aircraft in the receiving position with a minimum current miss and the trajectory of the aircraft in the transmitting position, in which the CAA mode is provided in the radar of the receiving position. This will ensure high-precision guidance of the aircraft receiving position on small sized inactive ground targets along a trajectory close to straight. In addition, the implementation of the proposed invention can improve stealth guidance and increase the range of the guidance system.

Sources of information
1. Antipov V. N., Isaev S. A., Lavrov A. A., Merkulov V. I. Multifunctional fighter radar systems. - M .: Military Publishing, 1994.

 2. Radar stations with digital synthesis of the antenna aperture / Ed. V.G. Goryainova. - M .: Radio and communications. 1988.

 3. Gerasimov A.A., Koltyshev E.E. et al. Radiovision / Ed. G.S. Kondratenkova. - M.: VVIA them. prof. NOT. Zhukovsky, 1997.

 4. Kurilkin V.V., Merkulov V.I., Vikulov O.V., Shuklin A.I. The method of proportional homing of aircraft to ground objects. Patent RU 2148235.

 5. Merkulov V.I., Lepin V.N. Aircraft radio control systems, part 1, part 2. - M .: Radio and communications, 1997.

 6. Merkulov V.I., Kurilkin V.V., Shuklin A.I. Algorithm for trajectory control of an air-to-surface missile using synthesis of an antenna aperture. Patent RU 2164654.

 7. Merkulov V.I., Kurilkin V.V., Sablin V.N., Shuklin A.I. Algorithm for proportional homing of air-to-surface missiles with aperture synthesis. - Radio Engineering, 2000, 7, pp. 47-54.

 8. Merkulov V.I., Kurilkin V.V., Shuklin A.I. Air-to-surface missile trajectory control algorithm using antenna aperture synthesis. - Radio Engineering, 2000, 3, pp. 69-75.

 9. Antipov V. N. Resolution of semi-active radars with synthesized aperture. - Radio Engineering, 1987, 5, pp. 66-68.

 10. Chernyak B. C. Multiposition radar. - M .: Radio and communications, 1993.

 11. Maksimov M.V., Gorgonov G.I. Electronic homing systems. - M.: Radio and Communications, 1982.

 12. Aircraft radio control systems, part 3, part 4. V.I. Merkulov, Chernov B.C. et al. / Ed. IN AND. Merkulova. - M.: Radio and Communications, 1998.

Claims (1)

A method of pointing aircraft at ground targets during semi-active synthesis of the antenna aperture, which consists in the fact that using the radar station of the aircraft (transmitting position) radiate target illumination signals, based on the signals reflected from the target at the receiving position LA, the speed values are measured

its proximity with the target and angular velocity

line of sight of the target with the aircraft in the horizontal plane, measure lateral acceleration

LA of the receiving position in the horizontal plane, form the control signal Δ _gr LA of the receiving position in the horizontal plane according to the law

where D _n - the value of the distance to the target at the beginning of the guidance; D _to - the known value of the range of the end of guidance, depending on the type of aircraft receiving position, from the LA of the receiving position, the measured value of the angular velocity is transmitted to the LA of the transmitting position

the line of sight of the target, based on the signals reflected from the target on board the aircraft transmitting position, measure the range

from it to a ground target and angular velocity

target line of sight, measure lateral acceleration

LA of the transmitting position in the horizontal plane, the value of the required angular velocity ω _{g of} the target line of sight is calculated according to the formula

where λ is the wavelength of the target illumination signal; ΔF is the bandwidth of the radar receiver of the receiving position; Δ1 _t - the required value of the linear resolution of the radar receiving position in the corner, form the control signal Δ _{gs of the} aircraft of the transmitting position in the horizontal plane in accordance with the formula

where qω is a constant coefficient, in accordance with the control signals Δ _gr and Δ _gs control the aircraft respectively receiving and transmitting positions.

Images