UA125827C2 - Infrared target seeking device "tsd-203t" - Google Patents

Abstract

The invention relates to missilery, namely to target seeking devices with enhanced sensivity and protection against natural noises and jamming of intermediate range missile. An infrared target seeker comprises a casing, a protective cover, a base, a stabilizer consisting of drive having a gimbal, two angular velocity sensors, a platform controller consisting of a programmable logic matrix with an integrated calculator and two power amplifiers, two reducers consisting of a motor-reducer and an angle sensor, and an image device consisting of a frame, a lens system and a thermal imaging device comprising a video controller, an infrared matrix photoreceiver with a cooling system and an analog-to-digital converter comprising a processing unit, and electronic bay having an interface device, a numerical calculation unit having a primary processing unit, a target image identification unit and unit for calculation of trajectory of target and other objects in sight, a connector unit and power supply unit. The programmable logic matrix with the integrated calculator is additionally comprises an operational module for compensation of sensor installation inaccuracy providing decreasing the design requirements to the accuracy of production and installation of angle sensors and angular velocity sensors therein, this excludes restructuring the entire target seeker after replacement of the drive with a new one. The analog-to-digital converter is additionally comprises an operational module for compensation of the distortion of the photoreceiving device elements, providing a view formation in conditions of changing in the accumulation time. The numerical calculation unit is additionally comprises an operational module for predicting and correcting the target trajectory, providing improvement of the missile’s interference immunity against natural noises and jamming. The technical result of the disclosed invention is in enhancement of the noise-proof features.

Description

improving the immunity of the missile against natural and artificial interference. The technical result of the claimed invention achieved by this invention is an increase in immunity. and Infrared homing head un and SN ko aka B I

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The invention relates to missile technology, in particular to thermal, i.e., infrared homing heads of the R-27T medium-range air-to-air missile with increased sensitivity and protection against natural and artificial interference, namely, to the GeNn-203T infrared homing head.

A thermal homing head of a missile insensitive to infrared pulsating interference (1) is known, which includes, in particular, one photoreceptor placed separately from the photoreceptors that are placed on the rotating rotor of the coordinator.

The disadvantage of this warhead is its use for short-range anti-aircraft missile systems, which does not meet the characteristics of medium-range air-to-air missiles.

The second analogue refers to anti-aircraft missile guidance systems (2), which have steering drives and amplifiers, a signal threshold transmission unit, a digital optical camera and a digital infrared camera and an electronic key.

The disadvantage of the second analogue is that the control of this system refers to missiles in the visible, and not in the infrared ranges.

The third analogue is the homing head |Z)|, which has a gyro-coordinator, which includes a four-plane radiation receiver and control windings, amplifiers, an adder and a timer.

The third analogue controls artillery shells and guided missiles intended for artillery, not air missiles.

The fourth analog includes the passive infrared homing head of the I4Y rotating missile, which contains a lens that is optically connected to a sequentially connected cooling linear matrix of photosensitive elements, an electronic switch, an analog-to-digital converter, an operational memory device, a target selector and amplifier, three-stage corrective gyroscope.

The disadvantages of the fourth analogue are the limitation of its functional capabilities, namely insufficient distribution capacity in the process of detecting and accompanying the target before the launch of the missile, and non-compliance with the characteristics of an air-to-air missile.

The closest technical solution, both in substance and in terms of tasks, is what is being solved

Zo is chosen as the closest analogue, there is an infrared homing head in the source |5|, which has a casing, a cap, a base, a stabilizer consisting of a motor that has a gimbal, an angular velocity sensor, a platform controller, which includes two power amplifiers, two reducers, which consist of a motor-reducer and an angle sensor, and an image device, which includes a frame, a lens and a thermal imaging device, which contains a video controller, an infrared matrix photoreceiver with a cooling system, and an analog-to-digital converter, which consists of of the processing unit, and the electronic compartment, which has a matching device, a numerical calculation unit, which has a primary processing unit, a target image identification unit and a unit for calculating the trajectory of the target and other objects in the field of view, a connector unit, and a power supply unit. This closest analogue refers to the infrared homing head of the Z36T model.

The limitation of its functionality in accordance with modern requirements for infrared homing heads is also considered a drawback of the closest analogue.

The basis of the claimed invention is the task of obtaining a relatively inexpensive design of an infrared homing head and increasing the level of its functional capabilities in accordance with modern requirements for an air-to-air medium-range missile.

The task is solved due to the fact that the "GSN-203T1" infrared homing head contains an operational module for compensation of the inaccuracy of sensor installation, an operational module for compensating the unevenness of the elements of the photo-receiving device, and an operational module for predicting and correcting the target's trajectory.

The essence of the invention of the GSN-203T infrared homing head, which has a casing, a cap, a base, a stabilizer consisting of a motor that has a gimbal, two angular velocity sensors, a platform controller, which includes a programmable logic matrix with an integrated computer and two power amplifier, two reducers consisting of a motor-reducer and an angle sensor, and an image device, which includes a frame, a lens and a thermal imaging device, which contains a video controller, an infrared matrix photoreceiver with a cooling system and an analog-to-digital converter, consisting of a processing unit, and an electronic compartment that has a matching device, a numerical calculation unit that has a primary processing unit, a target image identification unit and a calculation unit for the trajectory of the target and other objects in the field of view, a connector unit, a unit power supply, consists in the fact that the programmable logic matrix with an integrated computer additionally contains an operating module for compensation of net points the ability to install sensors, which ensures a reduction in the design requirements for manufacturing accuracy and the installation of angle sensors and angular velocity sensors in it, which excludes the rebuilding of the entire homing head after replacing this actuator with a new one, the analog-to-digital converter additionally contains an operational module for compensating the unevenness of the elements of the photo-receiving device, which ensures the formation of the image of the field of view in the conditions of changes in the accumulation time, and the numerical calculation unit additionally contains an operational module for predicting and correcting the target trajectory, which ensures the improvement of the missile's immunity against natural and artificial interference.

The technical result of the claimed invention is achieved by using: - a system of electronic adjustment of the angle sensors and angular velocity sensors in it, - a system of electronic correction of the unevenness of the elements of the photo-receiving device operating under conditions of change in the accumulation time, - a system of electronic correction of the target trajectory and prediction on based on correlation analysis and target image identification for anti-missile defense, which operate in automatic mode with an optimal set of operations.

Thanks to the specified operational modules, the following technical characteristics have been obtained: - target capture range at an altitude of 10,000 km - 28-70 km, - capture field - 5 1.5, - target tracking angle - - 60 degrees, - tracking angular speed - at least 40 degrees/s, - the accuracy of the angles of the actuator is measured up to 1 minute.

Thus, the claimed infrared homing head "GSN-203T" meets the criterion of the invention "novelty".

Figure 1 shows the block diagram of the GSN-2031 infrared homing head, where: 1 - casing, 2 - cap, C - base, 4 - stabilizer: 4.1 - image device: 4.1.1 - frame, 4.1.2 - device thermal imaging: 4.1.2.1 - video controller, 4.1.2.2 - analog-to-digital converter: 4.1.2.2.1 - processing unit, 4.1.2.2.2 - operational module for compensation of unevenness of elements

From the photo-receiving device, 4.1.2.3 - infrared matrix photo-receiver with a cooling system, 4.1.3 - lens; 4.2 - engine: 4.2.1 - gimbal, 4.2.2 - angular velocity sensor, 4.2.3 - platform controller: 4.2.3.1 - programmable logic matrix with an integrated calculator, 4.2.3.2 operational module for compensation of sensor installation inaccuracy, 4.2.3.3 - power amplifier, 4.2.4 - reducer: 4.2.4.1 - motor-reducer, 4.2.4.2 - angle sensor; 5 - electronic compartment: 5.1 - matching device, 5.2 - numerical calculation unit: 5.2.1 - primary processing unit, 5.2.2 - target image identification unit. 5.2.3 - unit for calculating the trajectory of the target and other objects in the field of view, 5.2.4 - operational module for forecasting and correcting the trajectory of the target; 5.3 - connector unit, 5.4 - power supply unit. The block diagram of the driver of the infrared homing head "GSN-203T" is given in Fig. 2, a block diagram of the device for imaging the driver of the infrared homing head "GSN-203T" - fig. 3, block diagram of the compartment of the electronic infrared homing head "GSN-203T" - Fig. 4, where: mon connection is compound; her connection is functional.

Infrared homing head "GSN-203T", which is shown in Fig. 1, reacts to the thermal radiation of the target and performs the following functions: - captures and accompanies the target at any time of the day; - generates a control signal for aiming the missile at the target; - provides this signal to the executive mechanism of the control system.

At the same time, the signals from the imaging device (4.1) and the actuator (4.2) are transmitted to the numerical calculation unit (5.2), where the calculation of the necessary parameters and their prediction and correction are performed to obtain the direction to the target and transmit it through the matching device (5.1) to the missile P -27T.

According to the block diagram in Fig. 2 of the image device, first the lens (4.3.1) projects the image of the field of view onto the focal point of the infrared matrix photoreceiver with a cooling system (4.1.2.3), which converts optical signals into electrical signals and transmits the video to the controller (4.1.2.1), which forms an infrared image of the field of view on the operational module for compensation of the unevenness of the elements of the photo-receiving device (4.1.2.2.2) and on the processing unit (4.1.2.2.1) of the analog-to-digital converter (4.1.2.2).

The principle of operation of the GSN-203T infrared homing head actuator (see Fig. 3) boils down to the fact that the programmable logic matrix with an integrated computer (4.2.3.1) of the platform controller (4.2.3) reads the indicators of the angle sensors (4.2.4.2 ) and angular velocity sensors (4.2.2), and the operating module for compensation of the inaccuracy of the sensor installation (4.2.3.2) calculates the necessary corrections of the sensor data and subsequently, depending on the operating mode of this actuator, generates signals on the power amplifier (4.2.3.3), which are necessary to set the cardan frames in the specified position using the reducer (4.2.4).

At the same time, the operating module for compensation of the inaccuracy of sensor installation automatically monitors sensor data errors.

The operation of the electronic compartment: the power supply unit (5.4) forms the necessary power supply voltages for each of the nodes of the electronic compartment, and its operation begins after supplying the power supply voltage to the matching device (5.1), where the adaptation of internal signals to the missile interface is carried out

R-27T. The numerical calculation unit (5.2) performs digital processing of analog signals and determines the direction of the target. At the same time, correlation analysis is used as a method of processing statistical data, which measures the closeness of the relationship between two or more variables. The target trajectory prediction and correction operational module (5.2.4) makes corrections in the calculation of obtaining trajectory coordinates and predicts its movement. The block of connectors (5.3) looks like a single board with appropriate connectors for each of the specified nodes.

Therefore, when using the specified operational modules, an increase in the level of functionality of the GSN-203T infrared homing head is achieved with its relatively inexpensive design.

Sources of information: 1. Patent of the Russian Federation Mo 2419060, published: 05/20/2011 - analog. 2. Patent of the Russian Federation No. 2400690, published: 09/27/2010 - analog. 3. Patent of the Russian Federation Mo 2415375, published: 03/27/2011 - analog. 4. Patent of the Russian Federation Mo 2197709, published: 27.03.2003 - analogue. 5. Thermal head of homing pores

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Claims (5)

DISCLOSURE OF THE INVENTION An infrared homing head having a casing, a cap, a base, a stabilizer consisting of a motor having a gimbal, two angular velocity sensors, a platform controller comprising a programmable logic matrix with an integrated calculator and two power amplifiers, two reducers , which consist of a motor-reducer and an angle sensor, and an image device, which includes a frame, a lens and a thermal imaging device containing a video controller, an infrared matrix photoreceiver with a cooling system and an analog-to-digital converter consisting of a processing unit , and the electronic compartment, which has a matching device, a numerical calculation unit, which has a primary processing unit, a target image identification unit and a target trajectory calculation unit and other objects in the field of view, a connector unit, a power supply unit, which is distinguished by that the programmable logic matrix with an integrated calculator additionally contains an operating module for inaccuracy compensation installation of sensors, made with the possibility of reducing the design requirements for manufacturing accuracy and installation of angle sensors and angular velocity sensors in it, which excludes the rebuilding of the entire homing head after replacing this actuator with a new one, the analog-to-digital converter additionally contains an operating module for compensation of the unevenness of the elements of the photo-receiving device, made with the possibility of forming an image of the field of view in the conditions of a change in the accumulation time, and the numerical calculation unit additionally contains an operational module for predicting and correcting the trajectory of the target, to improve the immunity of the missile against natural and artificial interference. and Iikfranerve homing head and un and "SMT" and I Bakma ol and MM ooo ooo OO pnya t x 1 rn nnya she i pomnlnnannnnnnnnn now! 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