RU2079109C1 - Complex target indication system - Google Patents

Abstract

FIELD: aviation instrument engineering. SUBSTANCE: the system uses an aircraft coordinate and angles sensor, target polar coordinates sensor, two coordinate converters, two summing units, target speed generating unit, switching unit, storage unit, target sighting angle generating unit, target range generating unit, delay unit. EFFECT: enhanced effectiveness. 4 dwg

Description

 The invention relates to aircraft instrumentation, and in particular to target designation systems providing aiming parameters on-board aiming and guidance systems.

 Known target designation systems described in the books of P. Davydov "Aviation Radar", M. Transport. 1984 year

 Lazareva L.P. "Infrared and light devices for homing aircraft" M. Engineering, 1970. Fedosova EA "Designing guidance systems", M. Mechanical Engineering, 1975. Mubarakshina R.V. "Integrated guidance of aircraft and separable means", M. Mashinostroenie, 1990, which describes the systems of integrated target designation using radio and optical means for locating targets and means of navigation of an aircraft (LA). The closest in technical essence is the system described in the aforementioned book of R.V. Mubarakshin on page 10. This system, selected as a prototype, contains a goniometer-rangefinder target coordinate sensor relative to the aircraft-DCC, an aircraft coordinate sensor-DCS, a coordinate converter PC1 and a unit for generating components of the target velocity component BFSC. This system ensures the formation and delivery to consumers of target coordinates and components of the target’s speed based on data on the coordinates and angles of the aircraft, measured by the DCS, and relative polar coordinates of the target, measured by the DCC of the range D and the angle of sight of target A.

 However, in case of failures (malfunctions) by signal A or signal D, the system becomes inoperative, which is a disadvantage of the prototype.

 The technical result of the proposed solution is to ensure the operability of the system in case of failures (malfunctions) of the sensor of the polar coordinates of the target DCC in range or in the angle of sight of the target.

 The technical result is achieved by the fact that in a complex targeting system containing a coordinate sensor and angles of the aircraft, a sensor of polar coordinates of the target, a first coordinate converter, a first summing unit, a target speed generating unit, the first and second inputs of which the first and second outputs of the first summing unit are connected , the first fourth inputs of which are connected, respectively, the first and second outputs of the coordinate sensor and the angles of the aircraft, the first and second outputs of the coordinate transformer, the first input of which the third output of the coordinate sensor and the angles of the plane is connected, which disconnects by inserting a switching unit, a memory unit, a second coordinate converter, a second summing unit, a target angle forming unit, a target range forming unit, a delay unit, and the first sixth block inputs switching connected respectively the first fourth outputs of the sensor of the polar coordinates of the target, the output of the block forming the angle of sight of the target and the output of the block forming the range of the target, and the first and second outputs of the switching block connected respectively to the second and third inputs of the first coordinate transformer, the first and second outputs of the target velocity generating unit, the third and fourth outputs of the target polar coordinate sensor are connected to the first fourth inputs of the memory block, the first and second outputs are connected respectively to the first third inputs of the second coordinate transducer block of memory and the fourth output of the sensor coordinates and angles of the aircraft, the first third. The inputs of the second summing unit are connected, respectively, the first output of the target polar coordinate sensor, the third and fourth outputs of the coordinate and angle sensor of the aircraft, the output of the second summing unit and the second output of the target polar coordinate sensor, respectively, are connected to the first and fifth outputs of the formation unit the target’s range are connected, respectively, the fifth output of the coordinate sensor and target angles, the first and second outputs of the second coordinate converter, the output of the second summing unit and the first output of the delay unit, the third, fourth and fifth outputs of the coordinate sensor and the angles of the aircraft, the first and second outputs of the second coordinate converter, the second output of the delay unit and the second output of the target’s polar coordinate sensor are connected to the first seventh inputs of the block for creating target viewing angles, the unit for forming the angle of sight of the target is made on four quadrants, four adders, two division blocks, a multiplication block, an arcsine shaper, an arctangent shaper, a shaper, rnya square, said first squarer, a first adder, the first block division arcsine generator are connected in series; a third adder, a second division unit, an arctangent shaper are connected in series; the second quadrator, fourth adder, square root shaper, multiplication unit are connected in series, the output of the third quadrator is connected to the second input of the first adder, the fourth quadrator is connected between the output of the third adder and the other input of the fourth adder, the output of the fourth adder is connected to the third input of the first adder, block output multiplication is connected to another input of the first division block, the output of the arctangent former is connected to the second input of the second adder, the first seventh inputs of the forming block The viewing angles of the target are connected respectively to the third input of the second adder, one and the other inputs of the third adder, to the input of the second quadrator combined with another input of the second division unit, to the fourth input of the second adder, to the input of the third quadrator and to the input of the first quadrator, combined with another input of the multiplication block, and the output of the second adder is connected to the output of the block forming the angle of sight of the target; the target range forming unit is made on two adders, a coordinate transformer, a sine shaper, a division block, the fifth adder, a coordinate transducer, a third division block being connected in series, a sixth adder and a sine shaper connected in series, and the sine shaper output connected to another input of the third division block whose output is connected to another input of the third division block, the output of which is connected to the output of the target range formation unit, the first fifth of which inputs are connected us respectively to one and the other inputs of the fifth adder, the second input of the coordinate converter to one and the other input of the sixth adder connected to a third input of the coordinate converter.

где V модуль путевой скорости самолета; V_цs, V_цz - составляющие путевой скорости цели соответственно спроектированные на оси С₁С₄ и С₃Ц₀.In FIG. 1 shows a block diagram of a device containing: 1 coordinate sensor and angles of a DCS aircraft, 2 sensor of polar coordinates of the DEC target, 3 - the first coordinate converter PK1, 4 first summation unit BS1, 5 - block for generating the target speed BFSSC, 6 switching unit BC, 7 BP memory unit, 8 second coordinate converter PK2, 9 second BS2 summation unit, 10 target BFUVC target angle formation unit, 11 BFDC target range formation unit, 12 base delay unit; in FIG. 2 in the HOW plane, the position of the target (C) relative to the aircraft (C ₁ ), where it is indicated: X _c , Y _c the target coordinates in the reference (terrestrial) coordinate system of the HOW, with the target position (C ₁ ) in the current time t, X _c , Y _{c the} coordinates of the aircraft (C ₁ ) in the reference coordinate system at the current time t, X _c0 , Y _{c0 the} coordinates of the target (C ₀ ) at the previous point in time, which is "τ" short from the current one; X _с0 , Y _с0 coordinates of the aircraft (С ₀ ) at the moment of time (t-τ) C _o C ₁ С ₀ С ₁ trajectory of the aircraft, close to the straight line during the time "τ"; C ₀ C _{1 the} trajectory of the target, close to the line during the time "τ"; С ₁ Ц ₁ Д distance from the aircraft to the target at time t С ₀ Ц ₀ Д ₀ distance from the aircraft to the target at time (t-τ) ;; X ₁ C ₁ Y ₁ coordinate system associated with the aircraft; Φ, Φ _{o the} angles between the line of movement and the direction to the target at time t, (t-τ) ;; α angle between the line of the trajectory and the axis Y ₁ parallel to Y (angle of the trajectory of the aircraft); And the angle between the longitudinal axis of the aircraft (C ₀ C) and the axis Y ₁ (angle of sight of the target); j is the angle between the longitudinal axis of the aircraft (C ₀ C) and the axis X ₁ ; parallel to X; C ₄ C ₁ , C ₃ C ₀ lateral deviation of the target from the trajectory of the aircraft, respectively, at time t and (t-τ); With ₀ With _{4 the} direction of the helicopter speed of the aircraft V; C ₀ C ₁ direction of the target velocity vector V _c . In FIG. 3 is a block diagram of a BFUVTs11, comprising: 13 first quadrator KV1, 14 - first adder C1, 15 first dividing unit BD1, 16 arsenic generator FAS, 17 second adder C2, 18 third adder C3, 19 second division unit BD2, 20 arctangent generator FAT 21 second KV2 quadrator; 22 fourth C4 adder; 23 square FKK root shaper; 24 BU multiplication block; 25 third KV3 quadrator; 26 fourth KV4 quadrator; in FIG. 4 is a block diagram of BFDC12, comprising: 127 fifth adder C5, 28 - coordinate converter PC, 29 third division block BD3, 30 sixth adder C6, 31 sine shaper FS; in FIG. 3 and 4 adders C1 C6 are blocks of algebraic summation, performing arithmetic operations of summing and subtracting input signals. In accordance with FIG. 2, the following relations hold:

where V is the module of the ground speed of the aircraft; V _cs , V _cz are the components of the target speed of the target, respectively designed on the axis C ₁ C ₄ and C ₃ C ₀ .

где

ДКС1 измеряет координаты местоположения самолета X_с, Y_с, угол ψ, угол наклона траектории a и модуль путевой скорости V. С первого и второго выходов ДКС1 сигналы X_с, Y_с поступают на первый и второй входы БС1, с третьего выхода ДКС1 сигнал угла j поступает на первый вход ПК1 (3), на второй вход БС2 (9) и на первый вход БФУВЦ10, с четвертого выхода ДКС1 сигнал угла a поступает на второй вход БФУВЦ10 и на третий входы ПК2 (8) и БС2 (9), с пятого выхода ДКС1 сигнал V поступает на первый вход БФДЦ11 и на третий вход БФУВЦ10.V _cs = V _cx cosα-V _cu sinα, V _cz = V _cx sinα-V _cu cosα (4)
V _cx , V _{cy the} components of the target speed of the target on the x and y axis, respectively,

Where

DKS1 measures the coordinates of the aircraft location X _s , Y _s , angle ψ, the angle of inclination of the trajectory a and the ground speed module V. From the first and second outputs of DKS1, the signals X _s , Y _s go to the first and second inputs of BS1, from the third output of DKS1, the angle signal j goes to the first input of PC1 (3), to the second input of BS2 (9) and to the first input of BFUVTs10, from the fourth output of DKS1, the angle signal a goes to the second input of BFUVTs10 and to the third inputs of PC2 (8) and BS2 (9), s the fifth output of DKS1, the V signal is fed to the first input of BFDTs11 and the third input of BFUVTs10.

DCC2 measures the polar coordinates of the target relative to the plane, the angle of sight of target A and the distance to target D. Signal A from the first output of DCC2 is fed to the first input of BC6 and to the first input of BS2 (9), signal D from the second output of DCC2 goes to the second input of BC6, to the second input БЗ12 and to the seventh output of БФУВЦ10, the pink DCC2 failure signal at angle A (U ₁ ) from the third output of DCC2 goes to the third input of BC6 and to the third input BP7, a single DCC2 failure signal from range D from the fourth output of DCC2 goes to the fourth input BK6 and the fourth entrance of BP7. The fifth and sixth inputs of BK6, respectively, from the outputs of BFUVTS10 and BFDTS11 receive signals A _to and D _to .

BK6 is made on two relays, one relay connects the first input of BK6 (signal A) to its first output when DKTs2 is working in angle A (And ₁₀ ) and connects the fifth input of BK6 (signal A _to ) to its first output when DKTs2 is in angle A (And ₁ And ₁₀ ); another relay connects the second input BK6 (Signal D) to its second output when DKTs2 is operational in range D (And ₂ 0) and connects the sixth input BK6 (signal D _to ) to its second output. Thus, when DCC2 is fully operational (And ₁ = 0, And ₂ = 0) from the first and second outputs of BK6, signals A and D are received respectively at the second and third inputs of PC1 (3), which converts the polar coordinates A, D into linear coordinates
x _cs = x _c - x _c = Dsinβ, y _cc = y _c - y _c = Dcosβ,
here β = 90 ^° -ψ - A in accordance with dependence (3).

BS1 is made on two adders (performing algebraic summation), on the first adder a signal is generated of the coordinate of the target location X _c X _cs + X _s , which from the first output of BS1 is fed to the first input of BFSC5, a signal of coordinate Y _c Y _{c cs} + Y is generated on the second adder _s , which from the second output BS1 enters the second input BFSST5.

который с первого выхода БФСЦ5 поступает на первый вход БП7, на другой дифференциаторе формируется сигнал составляющей скорости цели

который со второго выхода БФСЦ5 поступает на второй вход БП7, БП7 выполнен на двух запоминающих устройствах, одно и другое запоминающее устройство при И₁ 0 и И₂ 0 на третьем и четвертом входах БП7 пропускают сигналы V_цх и V_цу соответственно на первый и второй выходы БП7 и, соответственно, при И₁ И₁₀ или И₂ И₂₀ (отказы ДКЦ2 по сигналам А или Д) на выходах БП7 будут запомненные сигналы V_цхз, V_цуз, которые с первого и второго выходов БП7 поступают соответственно на первый и второй ПК2 (8), в котором по поступившим сигналам формируются сигналы составляющих скорости цели в соответствии с зависимостью (4)
V_цs= V_цxcosα - V_цysinα, V_цz= V_цxsinα + V_цycosα
которые соответственно с первого и второго выходов ПК2(8) поступают на второй и третий входы БФДЦ11 и на четвертый и пятый входы БФУВЦ10.BFSST5 is made on two differentiators performing the differentiation operation. On one differentiator, a signal of the target velocity component is formed

which from the first output of BFSC5 goes to the first input of BP7, a signal of the target velocity component is formed on another differentiator

which from the second output of BFSC5 goes to the second input of BP7, BP7 is made on two storage devices, one and the other storage device with And ₁ 0 and And ₂ 0 at the third and fourth inputs of BP7 pass the signals V _cx and V _cu respectively to the first and second outputs BP7 and, accordingly, with I ₁ AND ₁₀ or I ₂ AND ₂₀ (failures of DCC2 by signals A or D) at the outputs of BP7 there will be stored signals V _cc , V of the _center , which from the first and second outputs of BP7 are received respectively at the first and second PC2 (8), in which the signals form x target speed according to the relation (4)
V _cs = V _cx cosα - V _cs sinα, V _cz = V _cx sinα + V _cos cosα
which, respectively, from the first and second outputs of PC2 (8) go to the second and third inputs of BFDC11 and to the fourth and fifth inputs of BFUVTS10.

In BS2 (9), which performs algebraic summation operations, a signal Φ = A - 90 ^° + ψ + α is formed that implements dependence (2), which, from the output of BC2 (9), goes to the first input of B312 and to the fourth input of BFDC11.

BZ12 is made on two delay devices, a signal Φ _o = Φ (t-τ) is generated on the first delay device, which from the first output of BZ12 is fed to the fifth input of BFDC11, a signal D _o = D (t-τ) is generated on the second delay device which from the second input BZ12 enters the sixth input of BFUVTS10.

, поступающий на другой вход БУ24, где формируется сигнал "2Д•d", поступающий на один вход БД1(15); в С1(14) формируется сигнал f = D $\genfrac{}{}{0ex}{}{\text{2}}{\text{o}}$ -D²-d² поступающий на другой вход БД1(15), где формируется сигнал

поступающий на вход ФАС16, где формируется сигнал

поступающий на первый вход С2(17); в БД2(19) формируется сигнал

поступающий на вход ФАТ20, где формируется сигнал arctgθ, поступающий на второй вход С2(17), на третий и четвертый входы которого соответственно с первого и второго входов БФУВУ10 поступают сигналы j и α, в С2(17) формируется, реализующий зависимости (6) и (1) сигнал

поступающий на выход БФУВЦ10.In case of a failure of DCC2 by signal A (AND ₁ AND ₁₀ at the third output of DCC2), V _CHC and V _{DC are stored in BP7} , respectively, are formed in PC2
V _ts5 = V _tsx3 cosα-V _tsy3 sinα, V _yts = V _tsx sinα + V _tsy cosα,
arriving at the fourth and fifth inputs of BFUVTs10, in which (see figure 3):
the seventh input (signal D) is connected to one input of the BU24 and to the input of KB1 (13), where the signal "D ² " is formed, which arrives at the first input C1 (14);
the sixth input (signal D ₀ ) is connected to input KB3 (25), where signal D is generated $\genfrac{}{}{0ex}{}{\text{2}}{\text{o}}$ entering the second input C1 (14);
the third input (signal V) and the fourth input (signal V _cs ) are connected to one and the other inputs C3 (18), which generates a signal (V _cs V), which arrives at one input of the DB2 (19) and at the input of KB4 (26), where the signal (V _cs V) ^{2 is formed} , which arrives at one input C4 (22);
the fifth input (signal V _cz ) is connected to another input of DB2 (19) and to input KV2 (21), where signal V is generated $\genfrac{}{}{0ex}{}{\text{2}}{\text{cz}}$ arriving at another input C4 (22), where the signal d ² = (V _cs -V) ² + V is formed $\genfrac{}{}{0ex}{}{\text{2}}{\text{cz}}$ entering the third input C1 (14) and the input FKK (23), where the signal is formed

arriving at another input of БУ24, where the signal "2D • d" is generated, arriving at one input of БД1 (15); in C1 (14) a signal f = D $\genfrac{}{}{0ex}{}{\text{2}}{\text{o}}$ -D ² -d ² arriving at another input of BD1 (15), where a signal is generated

arriving at the input of FAS16, where the signal is formed

arriving at the first input C2 (17); in BD2 (19) a signal is formed

arriving at the input of FAT20, where the arctgθ signal is generated, arriving at the second input of C2 (17), the third and fourth inputs of which, respectively, from the first and second inputs of BFUVU10 receive signals j and α, which is formed in C2 (17), which implements dependencies (6) and (1) a signal

arriving at the output of BFUVTs10.

From the output of BFUVTs10, the signal "Ak" goes to the fifth input of VK6, in which, respectively, with the signal And ₁ And ₁₀ at the third input (DCC2 failure by signal A), the signal "Ak" will be at the first output.

, поступающий на выход БФДЦ11.In case of failure of DCC2 by the signal D (AND ₂ AND ₂₀ on the fourth output of DCC2), V _cxz and V _{cc are stored in BP7} , respectively, from one and the other outputs of PC2 (8), the signals V _cs = V _cx3 cosα-V _cs sinα, V _cz = V _cx3 sinα-V _cy3 cosα, arriving at the second and third inputs of BFDC11, in which (see Fig. 4):
the first (V signal) and second (V _cs signal) inputs are connected to one and the other C5 inputs (27), where a signal (V _cs -V) is generated, which arrives at the first PC input (28), the second and third inputs of which signals V _cz and Φ _o from the third and fifth inputs of BFDTS11; in PC28, a signal V ₁ = V _cz cosΦ _o - (V _cs -V) sinΦ _{o is} generated, which arrives at one input of DB3 (29);
the fourth (signal Φ) and fifth (signal v _o ) inputs of the BFDC11 are connected to one and the other inputs C6 (30), where a signal (Φ _o -Φ) is generated and fed to the input FS31, where a signal sin (Φ _o -Φ) is generated, arriving at the other input of the BD3 (29), where the signal implementing the dependence (5) is formed

entering the output of BFDTS11.

From the output of BFDTS11, the signal D _to arriving at the sixth input of BK6, in which, respectively, with And _{2 20} at the fourth input (failure of the DCC2 by signal D), the signal D _to will be at the second output.

Thus, when DC 2 _fails , by signal D or signal A, signals D _k or A _k are generated, which ensures the formation and delivery to consumers of the parameters X _c , Y _c , V _xc , V _yc , and therefore the system is operational in case of signal failures (malfunctions) D or signals A.

Claims (1)

 An integrated target designation system comprising an aircraft coordinate and angle sensor, a target polar coordinate sensor, a first coordinate converter, a first summing unit, a target speed generating unit, the first and second inputs of which are connected to the first and second outputs of the first summing unit, to the first fourth inputs of which respectively, the first and second outputs of the coordinate sensor and the angles of the aircraft, the first and second outputs of the coordinate converter, the first input of which is connected to the third output of the coordinate sensor and the airplane’s head, characterized in that a switching unit, a memory unit, a second coordinate converter, a second summing unit, a target sight angle forming unit, a target range forming unit, a delay unit are introduced into the first sixth inputs of the switching unit, respectively, the first fourth outputs are connected sensor of polar coordinates of the target, the output of the block forming the angle of sight of the target and the output of the block forming the range of the target, and the first and second outputs of the switching unit are connected respectively to the second and third the inputs of the first coordinate transducer, the first and second outputs of the target velocity forming unit, the third and fourth outputs of the target polar coordinate sensor are connected to the first fourth inputs of the memory block, the first and second outputs of the memory block and the fourth output are connected to the first third inputs of the second coordinate transducer the coordinates and angles of the aircraft, the first output of the target’s polar coordinates sensor, the third and the fourth are connected respectively to the first third inputs of the second summing unit the first outputs of the coordinate unit and the angles of the aircraft, the output of the second summing unit and the second output of the sensor of the polar coordinates of the target, respectively, are connected to the first and second inputs of the delay unit, the fifth output of the sensor of forming the range of the target is connected respectively to the fifth output of the sensor of coordinates and angles, the first and second the outputs of the second coordinate transformer, the output of the second summing unit and the first output of the delay unit, to the first seventh inputs of the target sight angle forming unit are connected respectively Actually the third, fourth and fifth outputs of the coordinate and angle sensor of the aircraft, the first and second outputs of the second coordinate transformer, the second output of the delay unit and the second output of the target’s polar coordinate sensor, while the block of forming the target’s viewing angle is made on four quadrants, four adders, two blocks division, multiplication block, shaper of arcsine, shaper of arctangent, shaper of square root, the first quadrator, first adder, first block of division, shaper of arcsine The third adder, the second division unit, the arctangent generator are connected in series, the second quadrator, the fourth adder, the square root generator, the multiplication unit are connected in series, the output of the third quadrator is connected to the second input of the first adder, the fourth quadrator is connected between the output of the third adder and the other input the fourth adder, the output of the fourth adder is connected to the third input of the first adder, the output of the multiplication unit is connected to another input of the first division unit, the output the arctangent shaper is connected to the second input of the second adder, the first seventh inputs of the target sight angle forming unit are connected respectively to the third input of the second adder, one and the other inputs of the third adder, to the input of the second quadrator, combined with the other input of the second division unit, to the fourth input of the second adder , the input of the third quadrator and the input of the first quadrator, combined with another input of the multiplication unit, and the output of the second adder is connected to the output of the angle forming unit In order to achieve the goal, the target range forming unit is made on two adders, a coordinate transformer, a sine shaper, a division block, the fifth adder, coordinate transformer, and the third division block being connected in series, the sixth adder and sine shaper connected in series, and the sine shaper output connected to another input the third division block, the output of which is connected to the output of the target range formation unit, the first fifth inputs of which are connected respectively to one and the other inputs of the fifth sum torus, the second input of the coordinate transformer, one and the other inputs of the sixth adder, connected to the third input of the coordinate transformer.

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