RU2315944C1 - Method for cocking of guided missile on-board system and device for its realization - Google Patents

Abstract

FIELD: military equipment, in particular, systems of guided weapon and rocketry with homing heads, applicable in artillery guided missiles with homing heads.

SUBSTANCE: at development, test of guided missiles, as well as in combat conditions in case of an incorrect exit to operation of the homing head the flight of the guided missile in the terminal trajectory leg will proceed without homing guidance, as a result, the fall point will be poorly predicted. Such a situation will result in an enhanced danger of the guided missile, since at tests the guided missile may come out of the zone of authorized operations, as well as in a destruction of awn objectives in combat conditions. According to the invention, at a missile take-off the clockwork mechanism of the missile control system is started, the an-board equipment power supply battery is cocked, the inertial gyroscope is uncaged. On expiration of time t1 set in the clockwork mechanism the homing head power supply batteries are cocked. At an exit to the operating mode of one of the homing head power supply batteries the nose unit is jettisoned, thereby opening the entrance pupil of the homing head on expiration of time t2 set in the clockwork mechanism. The parameters of the homing head are registered, compared with the preset values, at a negative result of the comparison of the registered parameters the control signal of reduction in the vertical coordinate of the control actuator is normalized, which provides an urgent bringing of the guided missile to the ground surface, time t2 is set as a time sufficient for bringing the homing head to the operating condition and yield of its parameters to the preset made after cocking of the homing head power supply batteries, but less than the time of the expected target lock-on.

EFFECT: prevented emergency situation, enhanced safety of use of the guided missiles.

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Description

The invention relates to military equipment, namely to guided weapon systems and missile technology with homing heads (GOS), and can be used in artillery guided missiles with GOS.

A known method of cocking onboard systems of a guided projectile, selected for the prototype, which consists in the fact that when the rocket starts under the influence of barrel overload, the clockwork mechanism of the rocket control system is launched, after the time set in the clockwork expires, the gyroscope is inertial and a battery for the onboard equipment is charged, cocking the batteries of the seeker, when entering the mode of one of the batteries of the seeker, they shoot the nasal block, opening the entrance pupil of the seeker, Russian Federation patent 2191984, registered It was completed on October 27, 2002, IPC 7 F42В 15/01 [1].

This method is implemented using a device for cocking on-board systems of a guided projectile selected for the prototype, containing a clockwork, homing head, inertial gyroscope, power supply, consisting of a power supply for on-board equipment and GOS power batteries, bow unit, "I" circuit, " OR, a steering drive (RP) and a steering drive control signal generator, consisting of power amplifiers that generate a control current from control signals issued by the GOS for each of the vertical and horizontal control channels, the clockwork output being connected to the inertial gyro cocking input and the power battery charging input of the power supply on-board equipment, the steering input is connected to the steering drive control signal output, the bow input is connected to the output of one of the GSN power supply batteries of the power supply, the first the input of the AND circuit is connected to the output of the inertial gyroscope, and the second input is connected to the second output of the GOS, the output of the AND circuit is connected to the second input of the OR circuit, the first input of which is connected to GOS tim output, and an output - to the input of a power amplifier driver steering actuator control signal [1].

The disadvantage of the data of the method and device is that in the event of an incorrect entry into the operation mode of the GOS, the flight of the guided missile in the final section of the trajectory will occur without homing, as a result of which the point of incidence will be poorly predictable. Such a situation will lead to an increased danger of a guided missile during its development, since a guided missile can leave the zone of permitted operations during missile tests, as well as damage to its objects in combat conditions.

The objective of the proposed group of inventions is to prevent the specified emergency, increasing safety when using guided missiles.

The problem is achieved in that in the method of charging the onboard systems of the guided missile, which consists in the fact that at the start of the rocket the clockwork mechanism of the rocket control system is started, the power supply of the onboard equipment is cocked, the gyroscope is inertial, after the time t1 set in the clockwork, the batteries are charged homing heads (GOS), when entering the mode of one of the GOS power batteries, the nasal block is fired, opening the entrance pupil of the GOS, after it is installed in the watch’s fur At the low of the time t2, the GSN parameters are recorded, compared with the given values, if the parameters recorded are negative, the steering wheel generates a control signal for decreasing the vertical coordinate of the steering wheel control channel, which provides an emergency reduction of the guided missile to the surface of the earth, and the time t2 is set as time sufficient to bring the seeker into working condition and its parameters to return to the specified mode after charging the seeker power batteries, but less time tim expected target capture; into a guided missile, including a clock mechanism, homing head, inertial gyroscope, a power supply unit containing an on-board equipment power supply and GSN power supply, a bow unit, an “I” circuit, a steering gear driver and a steering gear, the first output of the clockwork being connected with a cocking input of the inertial gyroscope and a cocking input of the battery of the power supply of the onboard equipment of the power supply, and a second output - with a cocking input of the batteries of the GOS power supply of the power supply, with the output of one the input of the bow block is input, the input of the steering gear is connected to the output of the steering drive control signal generator, the parameter control unit, the first and second switches and the reduction command driver are additionally introduced, the input of the parameter control block being connected to the first output of the GOS and the output to the first input of the circuit “I”, the second input of which is connected to the third output of the clock mechanism, the first input of the first switch is connected to the output of the inertial gyroscope, the second input of the first switch is connected to the third output of the GOS, the third input the first switch - with the second output ("Capture") of the GOS, and the output of the first switch is connected to the first input of the second switch, the second input of which is connected to the output of the shaper reduction command, the third input of the second switch is connected to the output of the circuit "I", the output of the second switch is connected with the input of the driver control signal generator.

The positive effect is ensured by the fact that in the method of charging the onboard systems of the guided missile and the device for its implementation at time t2, which is longer than the charging time of the GOS power battery t1, but less than the expected target acquisition time t ₃ , they automatically monitor the readiness of the GOS for operation by registering and comparing with the given values of its parameters. At this stage, with the on-board operation mode of the on-board control systems, they are charged up and entered the battery mode of the power supply unit, the GOS is brought to an operational state and its parameters, if the GOS is functioning normally, correspond to the set values. After capturing the target, the GOS gives control signals to the RP control channels, therefore, in the event of a failure of the GOS, incorrect control signals will be generated and further flight of the guided missile can lead to an emergency. To increase the safety of guided missile launches after the time t2 set in the clock mechanism, the parameters of the seeker are recorded, and they are compared with the set values. If the control result is negative, to terminate the uncontrolled flight of the rocket, a control signal for decreasing along the vertical coordinate of the RP control channel is generated, thereby providing an emergency reduction of the guided missile to the surface of the earth. To implement the above operations, a control unit for parameters, the first and second switches and the shaper of the descent command were additionally introduced into the guided missile.

This technical solution is illustrated by graphic materials.

Figure 1 shows a block diagram of a guided missile in which the proposed method is implemented.

Figure 2 shows an example circuit diagram of the switch.

The guided missile block diagram includes:

1 - clockwork (FM);

2 - GOS;

3 - inertial gyroscope (GI);

4 - power supply unit (PSU);

5 - nasal block (BN);

6 - parameter control unit (BKP);

7 - scheme "And";

8 - the first switch;

9 - shaper command reduction;

10 - the second switch;

11 - driver control signal driver;

12 - steering gear (RP).

The device operates as follows.

When a guided missile is launched, for example, under the influence of a starting overload, a clock mechanism (1) starts, in which the time is pre-set: t0 is the start time, t1 is the charging time of the power supply batteries of the power supply unit (4), t2 is the time sufficient to bring the power supply unit into working condition and the output of its parameters to the specified mode after charging its power batteries, but less time than the expected target capture.

At time t0, the clock mechanism (1) generates a high-level pulse, which from its first output goes to the electric igniters of the inertial gyroscope (3) and the power supply battery of the onboard equipment of the power supply unit (4). In this case, the inertial gyroscope is opened (3) and the onboard equipment power battery enters the mode, the output of which supplies voltage to the electronic components of the onboard equipment of the guided missile and RP (12), the electronic blocks are set to their initial state.

In the initial state, at the second and third outputs of the clock mechanism (1) there are low level signals, at the second input of the "And" circuit (7) connected to the third output of the clock mechanism (1), a low level is active, therefore, from the output of the "And" circuit (7) the low level goes to the third control input of the second switch (10), while the output of the second switch (10) is connected to its first input, providing RP control (12) by control signals from an inertial gyroscope (3) at a low signal level with exit 2 ("Capture") of the seeker to capture the target or GOS (2) at a high signal level from output 2 ("Capture") of the GOS after the target is captured.

The control signal from the output of the inertial gyroscope (3) is fed to the first input of the first switch (8), at the second input of which the control signal from the third output of the GOS (2) acts. At the third input of the first switch (8), the switch control signal from the second output (“Capture”) of the GOS (2) is active, the low level of which switches to the output of the first switch (8) with its first input and captures the control signals from the gyro output before capturing the target inertial (3) through the block (8) to the first input of the second switch (10) and from its output to the input of the driver signal shaper drive (11), and from its output to the input of the RP (12).

At time t1, the clock mechanism (1) at the second output generates a high-level pulse, which is supplied to the electric igniters of the batteries of the GOS power supply unit (4). These batteries enter the mode and under the influence of the voltage of one of the batteries of the seeker, an electric igniter of the nasal block (5) is cocked and the last fires off, opening the entrance pupil of the seeker (2) to receive input signals reflected from the target. When the GOOS batteries enter the operating mode from the first GOOS output (2), the signals that determine its parameters are fed to the input of the parameter monitoring unit (6), in which they are compared with the set values. When the parameters of the GOS are required at the output of the parameter control unit (6), a low voltage level is formed, which is supplied to the first input of the "And" circuit (7). In case of failure of the seeker (2), a high voltage level is formed at the output of the parameter control unit (6).

At time t2, the clock mechanism (1) at the third output generates a high-level pulse, which is fed to the second input of the AND circuit (7). If at the moment and at the first input of the circuit "And" (7) there is a high level, i.e. a GSN failure occurred, a high voltage level from the output of the “And” circuit (7) goes to the third control input of the second switch (10) and switches it by connecting the output of the reduction command driver (9) to the drive control driver (11). RP (12), fulfilling the reduction command received from the output of the driver of the control signals of the drive (11) to its input, provides an emergency reduction of the guided missile to the surface of the earth.

When the target is captured at the output 2 (“Capture”) of the GOS (2), a high level is formed that goes to the input 3 of the first switch (8) and commutes its output with input 2, which provides RP control by the control signals from output 3 (control channel) of the GOS (2).

Blocks 1, 2, 3, 4, 5, 7, 11, 12 can be performed, for example, similarly to the prototype [1]. In particular, the driver of the steering drive control signals (11) can be performed, for example, similarly to the prototype [1] on power amplifiers, which generate a control current for the steering wheels of the RP from control signals issued by the GOS.

The generator of the reduction command (9) can be performed, for example, as a constant voltage source on the 142EN5A chip with a stabilized output voltage of +5 V. The parameter control unit (6) is a general controller and can be executed, for example, on a single-chip microcomputer 1830BE51 .

Switches (8), (10) are bipolar. An example circuit design of such a switch is shown in figure 2. The switch (1) is implemented on the inverter (2), for example, on one of the elements of the MS 164LN1, and two single-pole switches (3) and (4), for example on the elements of the MS K176KT1. The inputs 1 and 2 of the switch (1) are the inputs of the unipolar switches (3) and (4), the outputs of which are combined and form the output of the switch (1).

So that the output of the switch (1) is closed with input 1 and open with input 2 at a low level ("0") at control input 3, open with input 1 and is closed with input 2 at a high level ("1") at control input 3 , input 3 of the switch (1) is connected to the input of the signal transmission permit switch 4 and the input of the inverter (2), the output of which is connected to the input of the signal transmission switch (3).

Thus, the proposed method for cocking the onboard systems of a guided missile and a device for its implementation automate monitoring of the parameters of the GOS and its readiness for operation, they allow to stop uncontrolled flight of the rocket in the event of a failure of the GOS, which prevents unforeseen emergency situations, increases the safety of tests and the use of guided missiles.

Claims (2)

1. A method of generating rocket control signals, including starting the clockwork of the rocket control system at rocket launch, charging the onboard power supply battery, snapping the inertial gyroscope, charging the homing head power battery after the time t1 set in the clockwork, shooting the nose unit entering the mode of one of the batteries of the GOS, opening the entrance pupil of the GSP, characterized in that after the time set in the clock mechanism t2> t1, the parameters G SN, compare them with the set values and, if the registered parameters are negatively compared on the steering wheel controls, they generate a control signal for decreasing the vertical coordinate of the steering wheel control channel to provide emergency guidance of the guided missile to the earth’s surface, and t2 is set as the time sufficient to bring the GOS into working condition and the output of its parameters to the specified mode after charging the batteries of the GOS, but less time than the expected target capture. 2. Guided missile, including clockwork, homing, inertial gyroscope, power supply unit containing power supply for on-board equipment and GOS power supply, bow unit, I circuit, steering driver and steering gear driver, the first output of the clockwork connected to the input of the charging of the inertial gyroscope and the input of charging of the battery of the power supply of the on-board equipment of the power supply, and the second output is connected to the input of charging of the batteries of the power of the GOS power supply unit, with the output of one of which is connected the input of the nose block, the input of the steering gear is connected to the output of the steering driver control signal generator, characterized in that it further includes a parameter control unit, first and second switches and a reduction command driver, the input of the parameter control unit being connected to the first output of the GOS, and the output is with the first input of the And circuit, the second input of which is connected to the third output of the clock mechanism, the first input of the first switch is connected to the output of the inertial gyroscope, the second input of the first switch is connected to the GOS output, the third input of the first switch with the second output is the “Capture” of the GOS, and the output of the first switch is connected to the first input of the second switch, the second input of which is connected to the output of the reduction command generator, the third input of the second switch is connected to the output of the “AND” circuit , the output of the second switch is connected to the input of the driver control signal generator.

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