RU2251656C1 - Airborne complex of controlling adjustable aerial bomb with laser feathered homing head, fulfilled according to the scheme duck - Google Patents

Abstract

FIELD: aviation technique.

SUBSTANCE: airborne complex of controlling adjustable aerial bomb fulfilled according to the scheme “duck”, provides self-guidance of the bomb without roll stabilization with the help of a passive laser homing head with feathered stabilization. In the airborne complex there is a four-quadrant photoreceiver which serves as a receiver of a laser signal reflected by the target. Signals of each quadrant get to inputs of electronic devices through liminal schemes cutting off the photoreceiver noises, impulse amplifiers, analogue amplifiers. The electronic devices provide procedure of allocating targets for all aerial bombs with passive homing heads used simultaneously during an attack on different targets by aircraft-carriers. It is realized with the help of assignment of a special code and inputting into the airborne complex of an amplitude summing unit, of five high-amplitude detectors, analogue calculator, analogue switch, amplifier, analogue-numeric transformer, leveling device, of three numeric-analogue transformers, special calculator.

EFFECT: Realization in the airborne complex of the procedure of allocating targets substantially increases effectiveness of the complex since it provides combat mission of one or several aircraft-carriers against different scattered targets.

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Description

The invention can be used in aeronautical engineering for delivering combat load with increased accuracy E _quo = 4 ... 7 m in a wide range of applications in terms of bomb height and speed, when the target distribution mode is implemented in the on-board complex, which ensures simultaneous operation of several illuminated lasers goals.

Known on-board complex corrected roll stabilized with a television homing head (Application 93044583/11 from 04.16.93, RF patent No. 2058011, Bull. No. 10 from 04/10/96).

The following procedures are implemented in the onboard complex of a roll-stable corrected aircraft with a television homing head of the connections already existing in existing corrected devices and new units: storing in the processing field of the current television signal as a reference, highlighting significant contrasting landmarks in this field, performing correlation processing of current and reference television signals; formation based on the results of correlation processing is discriminatory the second characteristic, determining with this characteristic the angular displacement of the current television image of the target relative to the reference one, generating for the triaxial gyrostabilizer, on which the television camera is mounted, control signals that return the optical axis of the television camera to the center of the target chosen by the operator, determining the magnitude of the unscaling between the current television image and reference, rewriting (when exceeding the size of the unscaled preset threshold value) tech of the target’s television image as a new reference. The airborne complex increases the efficiency of corrected aircraft, expands the zones and conditions for the reset of these devices, increases the accuracy of homing of aircraft for low-contrast and non-contrast targets, and increases the noise immunity of the aircraft to organized interference.

However, in this airborne complex, the target distribution mode is not implemented, which does not provide volley discharge of homing bombs while the carrier aircraft is operating for several purposes.

Airborne airborne weapons systems of the USA and Western European countries with laser, television and thermal imaging heads are known (Foreign Science and Technology News. Aviation Weapon Systems No. 1, 1987, pp. 1-24).

Airborne systems of the specified aircraft weapons include a radiation-signal receiver, an optical system, an electronic computing device and steering controls for aircraft weapons.

All these onboard control systems have the disadvantage that they do not have a target distribution mode, which does not allow for simultaneous operation of the carrier aircraft for several purposes.

The control systems for duck bombs with a laser homing head with a radiation-signal weather vane (the PAVEWAY I and PAVEWAY II series of laser bombs) are best known abroad.

A series of laser bombs of the PAVEWAY I type includes GBU 10 / B, GBU 10 A / B, GBU 11 A / B, GBU 12 A / B.

The PAVEWAY II laser bomb series includes GBU 10 E / V, GBU 10 F / B, GBU 12 D / B, GBU 12 E / B, GBU 16 V / V, GBU 16 C / V.

These bombs are distinguished by their caliber (diameter), type of combat load, the presence or absence of retractable stabilizing feathers.

All of the aforementioned aerial bombs are made according to the “duck” aerodynamic scheme, are equipped with a weather vane laser radiation receiver and have an onboard control complex that is identical in structure and composition (see V. Dmitriev. New Guided Aerial Bombs. Foreign Military Review, 1985, No. 7, p. 42 )

The airborne control systems for the laser bombs PAVEWAY I and PAVEWAY II are made almost completely identical and contain a sequentially connected “radiation-signal” converter with an optical system, a signal detector, an electronic computing device that generates control signals to the steering organs with aerodynamic rudders made according to the “duck” scheme "

In the on-board control system of American laser bombs made according to the “duck” scheme, the target distribution system is not implemented, that is, if there are several signals reflected by various targets in the field of view of the photodetector of the laser radiation, the on-board complex cannot determine “their” target among them and, thus, it becomes impossible to simultaneously operate one or several aircraft in one place for several purposes, which significantly reduces the possibility of using laser weapons. This is a very significant drawback of such airborne control systems.

Closest to the proposed on-board aircraft bomb control system designed according to the “duck” scheme with a laser homing head is the on-board complex of the PAVEWAY I. air bomb (see V. Dmitriev. New Guided Aerial Bombs. Foreign Military Review, 1985, No. 7, p. 42).

The PAVEWAY I airborne bomb control system uses a photodetector divided into four quadrants as a receiver of reflected laser radiation.

The signals from these quadrants are fed through threshold devices that cut off the internal noise of the photodetector, to pulse amplifiers, and then to analog amplifiers.

Signals from opposite quadrants are then compared in a subtraction circuit where an error signal is generated. The error signal then goes to the steering gear, controlling the aerodynamic rudders made according to the “duck” scheme of its channel.

At the same time, the aerodynamic steering wheels on the laser bomb are located in front according to the “X” pattern.

Error signals generated by oppositely located quadrants are processed by their pair of aerodynamic rudders so that the center of the quadrants of the weather-stabilized vane photodetector during bomb control coincides with the received laser signal reflected from the target.

Since the reflecting properties of the target, the transparency of the atmosphere vary quite widely, in addition, in the process of homing a laser bomb, the distance to the target changes, the amplitude of the reflected signal received by the photodetector varies over a wide range.

To stabilize the level of the received signal in the on-board complex prototype, automatic gain control is implemented. To do this, from the output of the threshold devices of all channels, the signals are fed to the adder, the output of which controls an element with an adjustable characteristic, which, in turn, changes the gain of the pulse amplifiers of all channels.

The expected technical result consists in the creation of such an on-board complex for controlling an aerial bomb (made according to the “duck” scheme with a laser weather vane GOS), which provides a target distribution mode that allows organizing simultaneous operation of several laser bombs in the target area for various purposes.

To solve this problem, an on-board control complex containing sequentially connected quadrants of a laser photodetector, threshold devices, pulse and analog amplifiers, an adder and an element with an adjustable characteristic, difference schemes and steering drives of aerodynamic rudders made according to the “duck” circuit at the output of analog amplifiers , introduced an amplitude adder, five peak detectors, an analog calculator, an analog switch, an amplifier, an analog-to-digital converter (ADC), a comparative e device, three digital-to-analog converters (DACs), a special computer built on a programmable logic integrated circuit (FPGA), with four detector outputs connected to the four inputs of the analog adder and to the inputs of the first, second, third, and fourth peak detectors, respectively, and the output of the analog adder connected to the inputs of the analog computer, the fifth peak detector and the first input of the summing device, the first output of the analog computer is connected to the sixth input of the analog switch , the second output of the analog computer is connected to the seventh input of the analog switch, the outputs of the first, second, third, fourth and fifth peak detectors are connected to the first, second, third, fourth and fifth inputs of the analog switch, respectively, the output of the analog switch through the amplifier and ADC is connected to the first the input of the special calculator, the first output of the special calculator is connected to the second input of the amplifier, the second input of the special calculator is connected to the output of the comparator, the second input of which is through the first AP is connected to the second output spetcvychislitelej, the third input of which serves the purpose of original data, third and fourth outputs spetcvychislitelej through the second and third DAC respectively connected to the inputs of steering actuators aerodynamic control surfaces, performed in a "weft".

Figure 1 shows the functional diagram of the onboard control system of the corrected aircraft bomb made according to the "duck" scheme with a laser vane homing head selected as a prototype, and the functional diagram of the control complex of the aircraft of the corrected aircraft bomb proposed in the invention.

Figure 2 shows the functional diagram of the proposed invention, the control complex of the corrected aircraft bomb, made according to the scheme "duck", with a laser vane homing head and providing a target distribution mode when working with multiple laser bombs on spaced targets.

On-board complex prototype contains (figure 1):

- four quadrant photodetectors (1, 2, 3, 4) reflected by the target of laser radiation;

- two signal subtraction devices (19, 20);

- steering drive aerodynamic rudders made according to the scheme "duck", (21), (22).

The on-board complex prototype (figure 1) works as follows.

The aircraft carrier bomb enters the target area. With the help of an aircraft sighting and navigation complex (PRNK), the pilot detects a target, imposes an aiming crosshair on the target. PRNK is transferred to the auto tracking mode of the selected target. The laser rangefinder-illuminator of the carrier aircraft begins to highlight the selected target.

The PRNA calculator determines the drop point of an aerial bomb with a laser homing vane.

Using a combat button, the pilot removes all the fuses to reset the bomb.

The command to reset the bomb produces a calculator PRNK.

This moment corresponds to the discharge point at which the photodetector of the on-board complex (quadrants 1, 2, 3, 4) on the trajectory of the autonomous flight of an air bomb is most likely to capture the reflected laser signal at the maximum distance from the target.

For this, four identical photosensitive elements (1, 2, 3, 4) are placed behind the lens of the vane laser homing head (LGSN) in the image plane. The laser spot reflected from the target hits either all the quadrants of the photodetector, or only part of them.

Aerial bombs made according to the “duck” scheme with a laser weather vane seeker are not stabilized along the roll during an autonomous flight to the target.

Therefore, the control signals to the aerodynamic steering wheels, made according to the “duck” scheme, are formed taking into account the lack of stabilization of the aerial bomb along the roll.

In this case, error signals along the control channels are formed as the voltage difference coming from opposite sites of the photodetector (1 and 3; 2 and 4, see figure 1).

The error signal generated by the difference circuit 20, is fed to the steering gear RP ₂ (22), which controls one pair of aerodynamic rudders made according to the aerodynamic scheme "duck". (The rudders are located on the aerial bomb in front of the bomb according to the “X” pattern).

Moreover, during the flight of the bomb, the laser signal reflected from the target in the process of eliminating the error signal is transferred to the center of the photodetector quadrants.

Similarly, an error signal is generated for the steering gear RP ₁ (21, FIG. 1), which controls the second pair of aerodynamic rudders.

In this case, the signal from quadrant 2 is input to the difference circuit 19.

The second input of the differential circuit 19 comes from quadrant 4.

The error signal from the output of the differential circuit 19 is fed to the steering gear RP ₁ (21), which controls the second pair of aerodynamic rudders made according to the aerodynamic scheme "duck".

While processing the mismatch signal, the aerial bomb “brings” the received, reflected from the target, laser signal to the center of the quadrants, which ensures that the bomb hits the target.

The similar control principle of a corrected aircraft bomb with a laser vane seeker, which is not stabilized along the roll, is quite stable and provides the required accuracy of pointing at a target illuminated by a laser emitter.

However, the on-board prototype system, made in accordance with figure 1, is not able to provide a target distribution system, that is, if there are several signals reflected from different targets in the field of view of the photodetector, to determine “their” target, which makes it impossible for one or several carrier planes in one place for several spaced targets.

This significantly narrows the possibility of using adjustable duck bombs with a laser weather vane.

The proposed airborne control system of an aerial bomb made according to the “duck” scheme with a laser vane seeker is presented in FIG. 2.

It contains four quadrant photodetectors (1, 2, 3, 4) of the laser radiation reflected by the target, four threshold detector devices (5, 6, 7, 8), four pulse amplifiers (9,10,11,12), four signal amplifiers ( 15,16,17,18), the adder of the output signals from the quadrants of the photodetector (13), an element with an adjustment characteristic for organizing automatic gain control (14).

At the output of amplifiers 15, 16, 17, 18, an amplitude adder 23, five peak detectors (PD) (25, 26, 27, 28, 29), an analog computer (24), an analog switch (AK) (30), an amplifier ( 31), an ADC (32), a comparator (34), three digital-to-analog converters (33, 36, 37), a special computer built on an FPGA (35) (BMK on-board microcomputer), and the outputs of amplifiers (15, 16, 17, 18) are connected respectively to the four inputs of the amplitude adder 23 and to the inputs of the first, second, third and fourth peak detectors 25, 26, 27, 28, respectively, and the output of the amplitude the ummator is connected to the inputs of the analog calculator 24, the peak detector 29 and to the first input of the comparator, the first output of the analog calculator is connected to the sixth input of the analog switch, the second output of the analog calculator is connected to the seventh input of the analog switch, the outputs of the peak detectors 25, 26, 27, 28 , 29 are connected to the first, second, third, fourth and fifth inputs of the analog switch 30, respectively, the output of the analog switch 30 through the amplifier 31 and the ADC 32 is connected to the first input Jelya 35, the first output of the special calculator 35 is connected to the second input of the amplifier (31), the second input of the special calculator 35 is connected to the output of the comparator 34, the second input of which through the DAC 33 is connected to the second output of the special calculator 35, to the third input of which the initial data about the target are supplied ( code “m”), the third and fourth outputs of the special calculator 35 through the DAC 36 and DAC 37 are respectively connected to the inputs of the steering drives RP ₁ and RP ₂ , controlling the aerodynamic rudders made according to the “duck” scheme.

The process of aiming and dropping a corrected aerial bomb made according to the “duck” scheme with a laser vane seeker, receiving the laser signal reflected by the target, fully corresponds to the operation of the onboard control complex - the prototype.

The efficiency of the proposed airborne complex is enhanced by the fact that threshold devices 5, 6, 7, 8 cut off the internal noise of photodetectors (1, 2, 3, 4).

To amplify the signals from the output of the threshold devices 5, 6, 7, 8 enter through pulse amplifiers 9, 10, 11, 12, included in the automatic gain control circuit, to the amplifier stages 15, 16, 17, 18.

The power of the reflected signals falling on the quadrants 1, 2, 3, 4 of the photodetector can vary widely depending on the range, transparency of the atmosphere, reflecting the properties of the target.

This power also changes in the process of reducing the distance to the target when aiming an air bomb at the target.

To protect the elements of the amplifier path from saturation in the proposed on-board control complex, a cascade of automatic gain control is used (13, 14, 9, 10, 11, 12).

The signal at the input to element 14 should not depend on the mismatch, therefore, it is summed from all quadrants 1, 2, 3, 4 in the adder 13 and is fed to element 14, which has an adjustment characteristic.

The output of element 14 controls the amplification of cascades 9, 10, 11, 12.

At the same time, equipment 23 ... 37 additionally introduced into the on-board complex to ensure target distribution works as follows.

подается на аналоговый вычислитель 24, определяющий характеристики uΣ и

. Полученное среднее значение (uΣ ) и среднее по модулю отклонение (

) оцифровываются и вводятся через входы 7 и 6 в спецвычислитель 35, который производит вычисление порога. Спецвычислитель 35 вычисляет порог:Electric signals in the form of short voltage pulses, following with a large duty cycle from the output of amplifiers 15, 16, 17, 18 through four channels, are fed to the input of the amplitude adder 23. The amplitude adder 23 calculates the sum of the values u ₁ ... u ₄ (voltage at the outputs amplifiers 15, 16, 17, 18). Received Total Signal

fed to an analog computer 24, which determines the characteristics of uΣ and

. The obtained mean value (uΣ) and the average deviation modulo (

) are digitized and input through inputs 7 and 6 to special computer 35, which performs the calculation of the threshold. Special calculator 35 calculates a threshold:

.Threshold =

.

The threshold code is issued through the 2 output of the special calculator 35 to the DAC 33, which allows the comparator 34 to record the excess of the threshold total from the output of the amplitude adder 23 and thus perform pulse selection by amplitude.

In addition, the signals from the output of amplifiers 15, 16, 17, 18 (via four channels) and the signal from the output of the amplitude adder 23, through the peak detectors 25, 26, 27, 28, are fed to the input of the analog switch 30, where they are also stored by the commands the special calculator 35 through the amplifier 31 and the ADC 35 are fed to the input of the special calculator 35. The special calculator 35 from all the received pulses from the output of the amplitude adder 23 selects the pulses that are received in accordance with the code sequence recorded in the memory of the special calculator 35 through input 3 (code “m”) . A code sequence is necessary in order to provide a target allocation mode.

The coding of the probe pulse sequence should provide:

a) that the law of changing the interval between successive pulses is not repeated in any sequence;

c) so that at two intervals (three received pulses), provided that the coding law and numerical values of four parameters are entered into the special calculator 35, it is possible to determine the sequence number from the given coding law and calculate the moment of arrival of the next pulse from the sequence number and the value of the last interval.

The above requirements are satisfied by the coding law described by the expression:

where: A _i is the current value of the numerical sequence of the coding law;

A _{i + 1} - the calculated value of the numerical coding sequence;

a is the initial parameter of the sequence;

b is the final parameter of the sequence;

m is the sequence number;

r is the period of the clock frequency.

The values of the numerical values of the four parameters (a, b, m, r) are set to input 3 of the special calculator 35 and the backlight station at the same time upon receipt of input data before performing the task.

The ability to change the numerical values of the parameters in the law of coding immediately before the task significantly complicates the enemy’s formulation of active interference, since in this case, during an attack, the time of which, as a rule, does not exceed one minute, it is necessary to solve an equation with four unknowns, which is the task practically unsolvable.

Introduction to the proposed airborne control complex of elements 5 ... 37 distinguishes the proposed airborne control complex from the considered prototype, since the proposed airborne control complex allows for the implementation of the target distribution mode in the bomb, which makes it possible to organize simultaneous operation of carrier aircraft for several purposes.

Claims (1)

On-board control system for a corrected duck aircraft with a laser vane homing head containing four quadrants of photodetectors of laser reflected radiation, two steering gears, each of which is designed to control two aerodynamic rudders made according to the duck the fact that it is equipped with four threshold detectors, four pulse amplifiers, four analog amplifiers, an adder, an output connected to an element with adjustable a characteristic that changes, depending on changes in range, transparency of the atmosphere, reflecting target properties, the gain of pulse amplifiers, an amplitude adder, five peak detectors, an analog calculator, an analog switch, an amplifier, an analog-to-digital converter, a comparing device, three digital-to-analog converters, a special calculator, moreover, each quadrant through a threshold detector and a pulse amplifier is connected to an analog amplifier, the outputs of all threshold detectors in are connected to the inputs of the adder, the four outputs of the analog amplifiers are connected to the four inputs of the amplitude adder and to the inputs of the first, second, third and fourth peak detectors, respectively, and the output of the amplitude adder is connected to the inputs of the analog computer, the fifth peak detector and the first input of the comparison device, the first the output of the analog computer is connected to the sixth input of the analog switch, the second output of the analog computer is connected to the seventh input of the analog switch, the output of the first , the second, third, fourth and fifth peak detectors are connected to the first, second, third, fourth and fifth inputs of the analog switch, respectively, the output of the analog switch through the amplifier and the analog-to-digital converter is connected to the first input of the special calculator, the first output of the special calculator is connected to the second input of the amplifier and the eighth input of the analog switch, the second input of the special computer is connected to the output of the comparator, the second input of which is connected via a digital-to-analog converter n spetcvychislitelej to the second output, the third input of which serves the purpose of original data, third and fourth outputs spetcvychislitelej through digital to analog converter are connected respectively to the inputs of steering actuators aerodynamic control surfaces, formed in a "weft".

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