RU2117902C1 - Method of target indication by direction for system of guidance of controlled object - Google Patents

Abstract

FIELD: methods of target indication by direction for systems of guidance of controlled objects of air-surface class. SUBSTANCE: method includes measurement in some point out of target of target coordinates relative to this point, determination of latitude and longitude of this point, calculation of elevation of this point above sea level, latitude and longitude and elevation above sea level of the target location point. In calculation of elevations, use is made of digital map of the target location region and this point; transmission of latitude, longitude and target elevation to controlled object where latitude and longitude of the controlled object carrier are determined; measurement of carrier flight elevation, angles of orientation of its longitudinal axis and angle of orientation of sight axis of system of guidance of controlled object carrier in horizontal and vertical planes; calculation of controlled object carrier elevation above sea level with use of digital map of region in which flight route of controlled object carrier runs, angles of orientation of vector of distance; controlled object carrier - target, and also angles of orientation of sight axis of controlled object guidance system relative to vector of carrier to target distance in the specified above planes, and sight of controlled object guidance system is turned towards reduction of angles the last indicated, down to their zero values. EFFECT: increased distance between controlled object carrier and target at the moment of completion of target indication by direction of guidance system of controlled object in cases of action of aircraft carrier of controlled object against small-size ground targets. 3 dwg

Description

 The invention relates to methods of targeting in the direction of the guidance system of a managed object (UO) and can be used to create new and modernize existing targeting systems in the direction of guidance systems of controlled objects of the class "air - surface".

 A known method of targeting in the direction of the homing system UO [1], which consists in the fact that on the media UO pre-set UO so that the longitudinal axis is collinear to the longitudinal axis of the media UO, and the field of view of the homing system homing UO previously rigidly oriented along its longitudinal axis, on the UO carrier, the target is detected and recognized, radiation from the target is received, angles are measured in the vertical and horizontal planes between the longitudinal axis of the UO carrier and the direction from which the received radiation from the target comes , and deploy the carrier of the UO in the vertical and horizontal planes in the direction of decreasing these angles to zero values. The disadvantage of this method is the large time required for target designation of the homing system of UO, due to the rotation of the media UO, with significant inertia.

There is also a method of targeting in the direction of the homing system UO [2], which consists in the fact that the UO is pre-installed on the UO carrier so that the longitudinal axis of the UO is collinear to the longitudinal axis of its carrier, the target is detected and recognized, radiation from the target is received, angles A are measured _vn and A _gn, respectively, in the vertical and horizontal planes between the longitudinal axis of the UO carrier and the direction from which the received radiation arrives, and the angles A _in and A _go are measured in the UO, respectively, in the vertical and horizontal planes x between the longitudinal axis of the UO and the axis of the sight of the homing system of the UO, calculate on the carrier of the UO radiation the differences of the angles A _gn and A _go and the difference of the angles A _vn and A _in and unfold the sight of the homing UO system, respectively, in horizontal and vertical planes in the direction of reducing these differences zero values. The disadvantage of this method is the relatively small range of target designation for optical homing UO under the action of aircraft carriers UO for small ground targets.

 The prototype of the invention should be considered a targeting method in the direction of the homing system UO (2), a common feature of which with the claimed invention is that it unfolds the sight of the guidance system UO in vertical and horizontal planes in the direction of decreasing the corresponding angles to their zero values.

In addition, in the prototype on the carrier UO pre-set UO so that the longitudinal axis of the UO is collinear to the longitudinal axis of its carrier, detect and identify the target, receive radiation from the target, measure the angles A _ext and A _n respectively in the vertical and horizontal planes between the longitudinal axis of the carrier RO and the direction from which the received radiation arrives from the target, and angles A _in and A _go are measured on the DO, respectively, in the vertical and horizontal planes between the longitudinal axis of the GO and the axis of the sight of the guidance system of the GO and calculate a medium angle values and difference A _corolla A and the difference _in the angles A and A _{th rH.}

 The disadvantage of the prototype is the relatively small range to the target at which the target designation is performed in the direction of the optical sight of the guidance system under the action of aircraft carriers of the defense on small ground targets. This is due to the fact that in the prototype target designation in the direction of the guidance system is carried out after the detection and identification of the target by the crew of the aircraft carrier UO. Visual detection and identification of a small-sized target by the crew of a UO carrier is possible at ranges of about 3. ..5 km to the target. Therefore, by the time the target designation is carried out in the direction, the UO carrier will be in the range of the target’s air defense systems and will most likely be hit by them. The use of the UO carrier by the crew when searching for a target of optical devices having a large increase and allowing to increase the range of detection and recognition of the target, but having a narrow field of view in this connection, will increase the search time of the target on the carrier, due to the need to examine a large spatial angle with a narrow field of view such a device. Since the aircraft carrier approaches it in the process of searching for a target, in this case too, by the time target designation in the direction of the guidance system of the targeting system is completed, the targeting vehicle will be at a short distance to the target, entering the range of its air defense systems.

 The aim of the invention is to eliminate this drawback of the prototype, namely increasing the distance between the carrier of the MA and the target at the time of the end of target designation in the direction of the sight of the guidance system of the MA under the action of the aircraft carrier MA on small ground targets.

 This goal is achieved as follows. At a certain point AND outside the target, the geographical coordinates of this point are determined and the coordinates of the target relative to this point are measured. According to this information, the latitude, longitude and altitude above the sea level of the target location are calculated at point And and these coordinates of the target are transmitted to the UO carrier via a radio channel. On this medium, the latitude and longitude of its location are determined, the altitude of its flight above the terrain is measured, and the altitude of its location above sea level is calculated. According to this information, the angles of orientation of the range vector of the target — the carrier — are calculated on the UO carrier relative to the horizontal plane passing through the target and relative to the geographic meridian. On the UO carrier, the orientation angle of its longitudinal axis relative to the magnetic meridian in the horizontal plane and relative to the local vertical is measured. In addition, the angles of deviation of the axis of the visor of the guidance system of the MA from the longitudinal axis of the carrier in horizontal and vertical planes are measured on the UO carrier. According to this information, the deflection angles in the horizontal and vertical planes of the axis of the sight of the sighting system of the sighting system from the range vector, the target is the support carrier, and the sight of the sighting system of the sighting system in these planes is reduced to reduce these angles to zero.

 Thus, targeting in the direction of the visor of the guidance system of the MA is carried out without detecting the target by the crew of the aircraft carrier of the MA and, therefore, can be carried out at ranges to the target significantly exceeding the range of its detection by this crew.

вектор дальности между точками Ц и И и его проекция на плоскость ГП;

прямоугольная система координат, расположенная в плоскости ГП, начало которой находится в точке Ц, ось

направлена по касательной к географическому меридиану, проходящему через цель, а ось

направлена по касательной к географической параллели, проходящей через цель; θ_ц - угол превышения цели относительно точки И; С-Ю - направление магнитного меридиана в точках И и О'; Δ_и,Δ_o - значения углов магнитного склонения в точках И и О' соответственно; К_ци - значение магнитного азимута цели относительно точки И; х_ци- проекция вектора

на ось

; У_ци - проекция вектора

на ось

;

вектор дальности между УО и целью и его проекция на плоскость ГП; х_оц, y_оц - координаты точки О' в системе координат

Н_ц, Н_и, Н_ро, Н_о - высоты соответственно точек Ц, И, О' и О над уровнем моря;

орт продольной оси носителя УО и проекция этого орта на плоскость ГП;

- орт оси визира системы наведения УО и проекция этого орта на плоскость ГП; А_гоц - угол ориентации вектора

относительно направления

; К_мн - магнитный азимут продольной оси носителя УО; А_воц - угол ориентации вектора

относительно плоскости ГП; В_ов - угол ориентации продольной оси носителя УО в вертикальной плоскости; В_лв, А_лв - углы ориентации орта

относительно орта

соответственно в вертикальной и горизонтальной плоскостях; В_вц, А_вц - углы ориентации орта

относительно вектора

соответственно в вертикальной и горизонтальной плоскостях.The essence of the proposed method is illustrated by the circuits shown in FIG. 1, 2 and in FIG. 3. In FIG. 1.2 shows the positions of the MA and the target at the current time t of target designation in the direction of the guidance system of the MA in horizontal (Fig. 1) and vertical (Fig. 2) planes. In FIG. 1, 2 are indicated: UM - sea level; C - the location of the target; GP - the horizontal plane passing through point Ts; O, O '- the point at which the UO is located, and the projection of this point on the surface of the earth; And, And 'is the point at which the radio transmitter is located, and its projection onto the GP plane;

the distance vector between the points C and I and its projection on the plane of the GP;

a rectangular coordinate system located in the plane of the GP, the beginning of which is at point C, the axis

is directed along the tangent to the geographic meridian passing through the target, and the axis

directed tangent to a geographic parallel passing through the target; θ _c - the angle of excess of the target relative to the point And; C-S — direction of the magnetic meridian at points I and O '; Δ _and , Δ _o are the values of the angles of magnetic declination at points And and O ', respectively; To _qi - the value of the magnetic azimuth of the target relative to the point And; x _qi - vector projection

on the axis

; U _qi - vector projection

on the axis

;

the distance vector between the MA and the target and its projection onto the GP plane; x _sc , y _sc - coordinates of the point O 'in the coordinate system

N _c , N _and , N _ro , N _o - the heights of the points C, I, O 'and O, respectively, above sea level;

the unit vector of the longitudinal axis of the UO carrier and the projection of this unit vector on the GP plane;

- the orth of the axis of the visor of the guidance system UO and the projection of this unit vector on the plane of the GP; And _goz is the orientation angle of the vector

regarding direction

; To _mn - magnetic azimuth of the longitudinal axis of the carrier UO; And _VOC - the orientation angle of the vector

relative to the plane of the GP; In _ov - the angle of orientation of the longitudinal axis of the media in the vertical plane; In _lv , And _lv - orientation angles of the unit vector

regarding orth

respectively in the vertical and horizontal planes; _ВЦ , А _ВЦ - _orth orientation angles

relative to the vector

respectively in the vertical and horizontal planes.

In FIG. 3 is a structural diagram of a possible embodiment of a device that implements the proposed method of target designation in the direction of the guidance system UO. The dashed lines are the elements of the device located at the point And and on the media UO. In each element having more than one input or output, the numbers indicate the numbers of the corresponding inputs and outputs. In FIG. 3 marked: 1 - receiver of satellite navigation system (PSSN); 2 - range finder; 3 - magnetic compass (MK); 4 - calculator; 5 - radio transmitter (RP); 6 - a radio receiver; 7 - the receiver of the satellite navigation system located on the carrier UO (PSSN NUO); 8 - radio altimeter (RV); 9 - a magnetic compass located on the carrier UO (MK NUO); 10 - goniometer device (UE); 11 - three-stage gyroscope (PC); 12 - the computer located on the media UO (VNUO); 13 - drive rotation of the sight of the guidance system UO (PPV); ψ _and , λ _and are the latitude and longitude of the point And shown in FIG. 12; TsK1 - a digital map of the area where the points Ts and I are located; ψ _C , λ _C - - latitude and longitude of the target location; ψ _o , λ _o - - latitude and longitude of the point O (Fig. 1, 2); TsK2 - a digital map of the area in which the flight path of the carrier UO. The remaining notation in FIG. 3 are the same as in FIG. 12.

и высоту Н_ц(t) над уровнем моря точки Ц, в которой находится цель в момент времени t, по следующему алгоритму

H_и(t) = H_и(ψ_и(t),λ_и(t)), (3)
H_ц(t) = H_ц(ψ_ц(t),λ_ц(t)), (4)

где
H_и(ψ_и(t),λ_и(t)),H_ц(ψ_ц(t),λ_ц(t)) - однотипные алгоритмы вычисления высоты точки на цифровой карте по известным значениям широты и долготы этой точки;
а, е - большая полуось и эксцентриситет референц-эллипсоида, значения которых известны.The essence of the proposed method is as follows. At the point And outside the target (Fig. 1, 2), at the current time t of the target designation, the distance D (t) from the point And to the target is measured and the magnetic azimuth K _qi (t) of the target relative to point I. In addition, at the point And determine the latitude ψ _and (t) and longitude λ _and (t) of this point. The values of D (t), K _qi (t), ψ _and (t), λ _and (t) are entered into the computer located at point I. In the same computer, the digital map CK1 of the location area of the point And and the target is preliminarily introduced. Using the coordinates ψ _and (t), λ _and (t) and a digital map in this calculator, calculate the height Ni (t) of the And point above sea level and the angle of magnetic declination Δ _and (t) at the point I. In addition, they calculate latitude ψ _q (t), longitude

and the height N _c (t) above sea level of the point C, where the target is located at time t, according to the following algorithm

H _and (t) = H _and (ψ _and (t), λ _and (t)), (3)
H _c (t) = H _c (ψ _c (t), λ _c (t)), (4)

Where
H _and (ψ _and (t), λ _and (t)), H _c (ψ _c (t), λ _c (t)) - the same type of algorithms for calculating the height of a point on a digital map from known values of the latitude and longitude of this point;
a, e - semi-major axis and eccentricity of the reference ellipsoid, the values of which are known.

а по долготе

где ψ_max, ψ_min - - максимальная и минимальная широта района, перенесенного на цифровую карту, а λ_max, λ_min - максимальная и минимальная долгота этого района. По введенным в вычислитель значениям широты ψ_и и долготы λ_и точки И вычисляют те две пары значений аргументов матрицы, внутри которых находятся введенные значения ψ_и и λ_и
ψ_к≤ ψ_и≤ ψ_к+1,
λ_l≤ λ_и≤ λ_l+1,
где
ψ_к= φ_min+K•Δψ,
ψ_к+1= φ_min+(K+1)•Δψ,
λ_l= λ_min+l•Δλ,
λ_l+1= λ_min+(l+1)•Δλ.
Используя значения высот Н_kl, Н_(к+1)l, Н_{(k+1) (l+1)}, соответствующие полученным парам значений аргументов матрицы.Since algorithms (3) and (4) are of the same type, it suffices to consider the essence of one of them, for example, algorithm (3). In the digital map of CC1, information about the terrain of the area where the points C and I are located is contained in the DEM stored in the memory of the calculator, each element
H _ij (i = 1,2 ..., n; j = 1,2, ..., m)
which is above sea level a terrain point having latitude ψ _i and longitude λ _j . The discreteness of this matrix is latitude

and in longitude

where ψ _max , ψ _min - is the maximum and minimum latitude of the area transferred to the digital map, and λ _max , λ _min - the maximum and minimum longitude of this area. The latitude ψ _and longitude λ _{and the} point And entered into the calculator calculate the two pairs of values of the matrix arguments inside which the entered values ψ _and and λ _and
ψ _k ≤ ψ _and ≤ ψ _{k + 1} ,
λ _l ≤ λ _and ≤ λ _{l + 1} ,
Where
ψ _k = φ _min + K • Δψ,
ψ _{to + 1} = φ _min + (K + 1) • Δψ,
λ _l = λ _min + l • Δλ,
λ _{l + 1} = λ _min + (l + 1) • Δλ.
Using the values of the heights Н _kl , Н _{(к + 1) l} , Н _{(k + 1) (l + 1)} , corresponding to the obtained pairs of values of the matrix arguments.

где

По подобному алгоритму вычисляют и высоту H_ц(t) (4) по входным данным ψ_ц(t),λ_ц(t).
Полученные координаты цели ψ_ц(t),λ_ц(t), H_ц(t) с помощью радиопередатчика, находящегося в точке И, передают на носитель УО, где принимают излучение этого передатчика и в результате обработки принятого излучения радиопередатчика получают эти координаты цели, которые вводят в вычислитель, установленный на носитель УО. В навигационной системе носителя УО вычисляют широту ψ_o(t) и долготу λ_o(t) точки О, в которой находится носитель УО в рассматриваемый момент времени t. Кроме того, на носителе УО измеряют высоту H_ор(t) полета УО. Эти значения вводят в вычислитель носителя УО, куда предварительно вводят цифровую карту ЦК2 района, в котором проходит маршрут полета носителя УО. По введенной информации в вычислителе носителя УО вычисляют координаты положения носителя УО относительно цели по следующему алгоритму

X_оц(t) = [ψ_o(t)-ψ_ц(t)]•R_з(ψ_o), (14)

ΔH_оц(t) = H_o(t)-H_ц(t), (16)
H_o(t) = H_op(t) + H_po(t), (17)
H_po(t) = H_po(ψ_o(t),λ_o(t)), (18)

где
H_poψ_o(t),λ_o(t)) - алгоритм, подобный рассмотренному выше алгоритму (9);
a=b=0
при
х_оц(t)

0, У_оц(t)

0,
a=b=1 при х_оц(t)< 0, У_оц(t)

0,
a=1, b=0 при х_оц(t) < 0, У_оц(t)<0,
a=b=2 при х_оц(t)

0, У_оц(t) < 0.ψ _k , λ _l ;
ψ _{k + 1} , λ _l ;
ψ _k , λ _{l + 1} ;
ψ _{k + 1} , λ _{l + 1} ,
and considering the change in height between these values linear, we get

Where

Using a similar algorithm, the height H _c (t) (4) is also calculated from the input data ψ _c (t), λ _c (t).
The obtained coordinates of the target ψ _c (t), λ _c (t), H _c (t) are transmitted to the UO carrier using the radio transmitter located at point I, where the radiation from this transmitter is received and, as a result of processing the received radiation from the radio transmitter, these target coordinates are received that are entered into the computer installed on the media UO. In the navigation system of the UO carrier, the latitude ψ _o (t) and the longitude λ _o (t) of the point O at which the UO carrier is located at the considered time t are calculated. In addition, on the carrier UO measure the height H _op (t) flight UO. These values are entered into the calculator of the UO carrier, where the digital map of the Central Control Commission 2 of the region in which the flight path of the UO carrier passes is entered. According to the entered information in the media calculator UO calculate the coordinates of the position of the media UO relative to the target according to the following algorithm

X _sc (t) = [ψ _o (t) -ψ _c (t)] • R _s (ψ _o ), (14)

ΔH _sc (t) = H _o (t) -H _c (t), (16)
H _o (t) = H _op (t) + H _po (t), (17)
H _po (t) = H _po (ψ _o (t), λ _o (t)), (18)

Where
H _po ψ _o (t), λ _o (t)) is an algorithm similar to the above algorithm (9);
a = b = 0
at
x _sc (t)

0, y _ots (t)

0
a = b = 1 for x _ots (t) <0, y _ots (t)

0
a = 1, b = 0 for x _ots (t) <0, Y _ots (t) <0,
a = b = 2 for x _ots (t)

0, _Voc (t) <0.

Using a magnetic compass mounted on the MA carrier, measure the magnetic azimuth K _mn (t) of the longitudinal axis of the MA carrier, and using an angle gauge measure the angle A _lv (t) in the horizontal plane between the axis of the sighting system of the MA guidance system and the longitudinal axis of the MA carrier, as well as the angle B _lv in the vertical plane between these directions.

Using this information, the orientation angle A _sc (t) of the orientation in the horizontal plane of the range vector of the target carrier UO is calculated
A _sc (t) = A _sc (t) + Δ _o -K _pl (t) (21)
and
angle А _ВЦ (t) in the horizontal plane between the distance vector, the target is the carrier of the MA and the axis of the sight of the guidance system of the MA
A _bc (t) = A _sc (t) - A _lv (t)
Where
Δ _o - the angle of magnetic declination at point 0, calculated on the media UO according to the digital map CK2, entered into its calculator. In the process of targeting in the direction in the horizontal plane, deploy the visor of the guidance system of the UO in the direction of decreasing the angle A of the _ax (t) (22) to a zero value at which the axis of this sight will be aimed at the target.

In the vertical plane on the MA carrier, with the help of a three-stage gyroscope, the angle В _{o of the} orientation of the longitudinal axis of the _MA carrier relative to the horizontal plane is measured and the angle of the _NC orientation in the vertical plane of the range vector is _{measured, the MA} carrier is the target relative to the longitudinal axis of this carrier
In _nts (t) = In _s (t) - And _VOTs (t)
as well as the angle _ВЦ between the distance vector, the carrier of the MA - target and the axis of the sight of the guidance system of the MA in this plane
_ВЦ (t) = В _нЦ (t) - В _лв (t)
In the process of target designation in the direction in the vertical plane, deploy the sight of the guidance system of the VO in the direction of decreasing the angle В _ВЦ (24) to its zero value, at which the axis of this sight will be aimed at the target in the considered plane.

 Thus, the proposed method allows both in horizontal and vertical planes to direct the sight of the guidance system of the UO to the target, regardless of the distance between the UO carrier and the target. Therefore, for targeting in the direction of the guidance system of the UO by the proposed method, preliminary detection of the target by the crew of the UO carrier, as required in the prototype, is not necessary. This provides a significantly higher than in the prototype, the value of the distance between the carrier of the MA and the target at the time of detection of the target by the guidance system of the MA, which makes it possible to use the MA without entering its carrier in the coverage area of the air defense system of the target.

 A device that implements the proposed method of targeting in the direction of the guidance system UO, includes elements located at point And outside the target, and elements mounted on the media UO. At point And there are PSSN 1, range finder 2, MK 3, calculator 4 and RP 5, the first and second outputs of PSSN 1 are connected respectively to the first and second inputs of the calculator 4, the output of the range finder 2 is connected to the third input of the calculator 4, the output of MK 3 is connected with the fourth input of the calculator 4, the first, second and third outputs of which are connected respectively with the first, second and third inputs of RP 5.

 A radio receiver 6, PSSN NUO 7, RV 8, MK NUO 9, UU 10, PK 11, VNUO 12 and PPV 13 are installed on the UO carrier, and the first, second and third outputs of the radio receiver 6 are connected respectively with the third, fourth and fifth inputs of VNUO 12 , the first and second outputs of the PSSN NUO 7 are connected respectively with the first and second inputs of the VNOO 12, the output of the PB 8 is connected with the sixth input of the VNOO 12, the output of the MK NUO 9 is connected with the seventh input of the VNOO 12, the first and second outputs of UUO 12 are connected with the eighth and the ninth inputs of VNUO 12, the output of PC 11 is connected to the tenth input of VNUO 12, the first and second outputs of which are connected respectively to the first and second inputs 13 PPV.

This device works as follows. Preliminary, i.e. prior to target designation, a predetermined digital map of CK1 is supplied to the fifth input of calculator 4 and this information is stored in calculator 4. Also, a predetermined digital map of district CK2 is fed to the eleventh input of VNOO 12, in which the flight path of the UO carrier passes, and this information is stored in VNOO 12. PSSN 1, range finder 2, MK 3, calculator 4 and RP 5 are set at point And outside the target. PSSN 1 receives radio signals emitted by artificial Earth satellites that are part of the satellite navigation system, and based on these radio signals calculate the latitude ψ _and and longitude λ _and point I. The values ψ _and and λ _and from the outputs of the PSSN 1 are fed to the corresponding inputs of the calculator 4 and remember in it. Using a range finder 2, measure the distance D between the target and point And and from the output of the range finder 2, the measured value D is supplied to the third input of the calculator 4. Using MK 3, the magnetic azimuth K _{qi of the} target is measured relative to point I and the output value MK 3 is fed the measured value K _q to the fourth input of the calculator 4. Using the information supplied to its inputs, in the calculator 4 in accordance with the algorithm (1) ... (9) calculate the latitude ψ _c ,, longitude λ _{c =} and the height H _{c of} the target location. These coordinates from the corresponding outputs of the calculator 4 are fed to the corresponding inputs of the RP 5, with which information about the values of these coordinates is radiated into space. Radio receiver 6 receives this radiation from RP 5 and processes it, as a result of which at the corresponding outputs of radio receiver 6 they obtain the values of these target coordinates, which are fed to the corresponding inputs of VNUO 12. PSSN NUO 7 receives radio signals emitted by artificial Earth satellites, which are part of the satellite system navigation, and calculates the latitude ψ _o and longitude λ _{o of the} point 0, in which the media is located. Value ψ _o, λ _o from respective outputs 7 PRSPs HMD fed to the respective inputs 12. With VNUO PB 8 _op measured height H, which is output from the RV 8 is supplied to the sixth input 12. With VNUO MK HMD magnetic bearing 9 is measured K _mn , which from the output of MK NUO 9 is fed to the seventh input of VNUO 12. Using UU 10, the values of angles A _lv and B _lv are measured, which from the corresponding outputs of UU 10 are fed to the eighth and ninth inputs of VNUO 12. Using PC 11, the angle B is measured _s , which from the output of PC 11 is fed to the tenth input of VNUO 12. Using the information received th at its inputs, in VNUO 12 in accordance with the algorithm (9) ... (24) calculate the values of the angles В _ВЦ , А _{вц of} the orientation angles in the vertical and horizontal planes of the axis of the sight of the guidance system of the UO. The values of these angles from the corresponding outputs of the VNUO 12 are fed to the corresponding inputs of the PPV 13, which turns the sight to reduce these angles to their zero values, at which the axis of the sight will be aimed at the target.

Sources of information:
1. Maksimov MV, Gorgonov GI, Radio-electronic homing systems. M .: Radio and communication, 1982, p. 48.

 2. Lazarev L.P. Optoelectronic devices for guidance of aircraft., M.: Mechanical Engineering, 1984, p. 182.

Claims (1)

The method of targeting in the direction of the guidance system of the managed object, which consists in deploying the sight of the guidance system of the controlled object in vertical and horizontal planes in the direction of decreasing the corresponding angles to their zero values, characterized in that they measure the distance D between the target and some point outside the target and the magnetic azimuth K _{q of the} target relative to this point, determine the latitude ψ _and and longitude λ _and this point, enter the values D, K _qi , ψ _and , λ _and into the calculator installed in the region of this point, in which first enter a digital map of the target location area and this point, calculate the latitude ψ _c , longitude λ _c and the height H _c above sea level of the target location and transmit these coordinates of the target over the air to the carrier of the managed object, determine the latitude ψ _o on this medium and longitude λ _o of its location, is measured height H _op its flight over the terrain, the magnetic azimuth K _plural longitudinal axis of the vehicle and the orientation angle in _s this axis in the vertical plane, and angles a and B _{lv lv} orientation respectively in a vertically second and horizontal axis reticle guidance system controlled object relative to the longitudinal axis of its carrier is introduced values ψ _n, λ _n, H _n, H _op, ψ _o, λ _o, K _pl, B _s, B _lv and A _lv calculator carrier controlled object, where previously introduced digital map of the area in which the flight route extends carrier controlled object is calculated on the carrier orientation angles in the vertical and horizontal vector distance carrier - the purpose and the angles a _CC, B _CC orientation in the horizontal and vertical axes in planes zira guidance system controlled object relative to the vector distance carrier - target zero values which provide guidance when turning reticle system managed object.

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