The guidance system managed projectile and the pulse shaper

 

(57) Abstract:

The invention relates to the field of weapons, particularly artillery managed shells with laser homing head. The technical result of the invention is to improve the accuracy of targeting and is achieved by the fact that the guidance system managed projectile contains the steering actuator, the gyro inertial and homing head that includes functional elements, including the element OR, with corresponding connections, the output "Capture" which is connected to the first input of the first element And through the inverter from the first input of the second element And the second inputs of which are connected respectively with the second and third outputs of the gyro inertial. The output of the first element And is connected to the input of "Compensation" of the homing head, and with a third input of the first element OR the second input is connected to the first output of the gyro inertial, and its output to the input of the first amplifier, the output of the second element And is connected to a second input of the second element OR. The output of the second element OR is connected to the input of the second amplifier, the outputs of the first, second, third and fourth amplifiers connected to the first inputs of the fourth input of the gyro inertial and power supply on-Board equipment. Entered the third element And the pulse shaper, the first, second, third and fourth inputs of which are connected respectively to the outputs of the "-Y "+Y "+Z" and "Z" of the homing head, the fifth input is connected to the output of the third element And the first and second outputs connected to first inputs of the first and second elements respectively, and third and fourth inputs connected respectively to the inputs of the third and fourth amplifiers, the first input of the third element And is connected to the output element OR the homing head, and the second input - output "Capture" of the homing head. The pulse shaper includes an input bus, the first element And the first input of which is connected to the input bus, the second element And the generator of clock pulses, the first pulse counter, bus synchronization, and output bus. Entered the second pulse counter, a persistent storage device (ROM) and elements, And the total number of which corresponds to the number of output generated signals. And bus synchronization connected with the input set to the source position of the first pulse counter and the counting input of the second pulse counter, the information outputs of which are connected with the first groupshow, a counting input connected to the generator output clock pulses. The second output of the ROM is connected to the enable input of the second pulse counter, and the first output to the second inputs of all the elements, And the first inputs of which are connected to the input bus and the outputs are connected to the output bus. 2 C. p. F.-ly, 4 Il.

The invention relates to the field of weapons, particularly artillery managed shells with laser homing head.

Known guidance system managed projectile [1], containing the gyro inertial (GI), the steering actuator (RP) and the homing head (GOS) including a photodetector, amplifier relay and linear servo systems, the threshold device relay and linear servo systems, a scheme OR schemes total differential processing, peak detectors, the adder, the selector, the shaper output signals, a scheme of rationing, a logic circuit, a power amplifier, the PWM amplifier-rectifier elements, the windings of the correction coils and the winding weight compensation with corresponding connections, output "Capture" which is connected to the first input of the first element And through an inverter to the first input of the second element And the second inputs of which snan input "Compensation" of the GOS and the third input of the first element OR the second input is connected to the first output of the gyro inertial, and its output to the input of the first amplifier, the output of the second element And is connected to a second input of the second element OR the output of the second element OR is connected to the input of the second amplifier, the outputs of the homing head "-Y" and "+Y" is connected with the first inputs of the first and second elements OR, respectively, the outputs of the homing head "+Z" and "Z" are connected with inputs of the third and fourth amplifiers, respectively, the outputs of the first, second, the third and fourth amplifiers connected to the first inputs of the first, second, third and fourth control windings of the steering actuator, the second inputs of which are connected to the input of the gyro inertial and power supply on-Board equipment.

A significant drawback of this system is that at the initial moment homing, the choice of the initial blunder, due to errors of training and technical scattering, when the penalty is a maximum value, with the homing head is starting to get the maximum amount of commands that, when the steering actuator, affect is at rest in the system documentation is ical damping on site management of 0.05-0.1 and the maximum development teams control the magnitude of the overshoot of the projectile in the angles of attack and slip in consequence of the response to the control signal can reach 100%, and the amplitude of the projectile in the angles of attack and slip, depending on the combinations of the design tolerances for the elements of the airframe, may exceed the maximum allowable value (as defined field of view GOS), which reduces the accuracy of the guidance, and in some cases to failure of the guidance process in consequence of missing the target GOS.

Known shaper pulses [2], comprising a reversible counter, summing input connected to the output of the first element matches the first input connected to the first input of the second element of coincidence, the output of which is connected to the subtractive input of the reversible pulse counter, the second input - output bus and direct RS trigger, R is the input connected to the output of the pulse shaper, the bus clock pulses, the input bus, bus synchronization, the inverter, the element OR the output of which is connected to the input of the pulse shaper, the output of which is connected to the reset input of reversible counter pulses, output retransfer of which is connected to the first input of the OR element, a second input connected through an inverter to the third input of the second element matches and directly from the input bus and a second input s output RS - flip-flop, S - input of which is connected to bus synchronization.

The disadvantage of this device is that if you bind output pulses to sync it lacks the ability to change the duration of the output pulses with respect to the input. At the same time, often in automatic control systems in the initial moment of time (the beginning of the segment management) system error control the maximum and the Executive body of the management system receives the maximum command, leading to high speed impact on the control system, which can lead to failure of the control circuit and the excitation system. Therefore, in such systems at high operating errors in the initial moment of time during the transition process should be submitted to the Executive body system signal varying according to a certain law, for example, by linearly increasing from the minimum acceptable to the value defined by the duration of the input signal, and at the end time of transition of the input signal should be held in Executive body unchanged. Thus in order to avoid phase shifts in the signal forming the middle of the control pulses is not the debtor is giving precision-guided guided projectiles. This is achieved by the fact that at the initial moment homing, defined by the transition process, the team with the GOS on the steering actuator are not on a straight line, and their duration varies during the transition process according to a certain law, for example, by linearly increasing from the minimum value to the value defined by the duration of the input signal, and at the end time of transition of the input signal passes to the steering actuator without changes. Thus in order to avoid phase shifts in the signal forming the middle of the control pulses does not change its temporary position.

The problem is solved in that in the guidance system managed projectile containing the steering actuator, the gyro inertial and homing head that includes functional elements, including the element OR, with corresponding connections, the output "Capture" which is connected to the first input of the first element And through an inverter to the first input of the second element And the second inputs of which are connected respectively with the second and third outputs of the gyro inertial, the output of the first element And is connected to the input of "Compensation" of the homing head and the third input Pervov of the first amplifier, the output of the second element And is connected with the second input of the second element OR the output of the second element OR is connected to the input of the second amplifier, the outputs of the first, second, third and fourth amplifiers connected to the first inputs of the first, second, third and fourth control windings of the steering actuator, the second inputs of which are connected to the fourth input of the gyro inertial and power supply on-Board equipment, entered the third element And the pulse shaper, the first, second, third and fourth inputs of which are connected respectively to the outputs of Y "+Y" The "+Z" and "Z" of the homing head, the fifth input is connected to the output of the third element And the first and second outputs connected to first inputs of the first and second elements respectively, and third and fourth inputs connected respectively to the inputs of the third and fourth amplifiers, the first input of the third element And is connected to the output element OR the homing head, and the second input - output "Capture" of the homing head;

and shaper pulses containing the input bus, the first element And the first input of which is connected to the input bus, the second element And the oscillator clock impul the Noah memory (ROM) and elements, And, the total number of which corresponds to the number of output generated signals, and bus synchronization connected with the input set to the source position of the first pulse counter and the counting input of the second pulse counter, the information outputs of which are connected with the first group addresses the ROM, the second group of addresses which is connected to the information output of the first pulse counter, a counting input connected to the output of the clock generator pulses, the second output of the ROM is connected to the enable input of the second pulse counter, and the first output to the second inputs of all the elements, And the first inputs of which are connected to the input bus and the outputs are connected to the output bus.

In Fig.1 shows a block diagram of the proposed system, and Fig.2 and Fig.3 is a diagram explaining the operation of the system; Fig.4 is an example of executing a pulse shaper, where:

1 - the seeker containing photodetector 19, the relay amplifiers and linear tracking systems 20 and 22, the threshold device relay and linear tracking systems 21 and 28, scheme OR 23, schemes total differential processing 24 and 27, the peak detector 25, an adder 26, the selector 29, the shaper output signals 30, scheme norminate correction coils 36 and 37, the winding weight compensation 38 with corresponding connections are made, for example, as in the prototype, 2 - gyro inertial with modular sensor performed, for example, as in the prototype, 3 - wheel drive, 5 - shaper pulses, performed, for example, as shown in Fig.4, 6 item NO, 7, 8, 4 is the first, second and third elements And, 9, 10, the first and second elements OR, 11, 12, 13, 14 - the first, second, third and fourth amplifiers, 15, 16, 17, 18 to the control winding of the autopilot.

The "Capture" GOS 1 is connected to the first input of the first element And 7 and through the inverter 6 to the first input of the second element And 8, the second inputs of which are connected respectively with the second and third outputs of the gyro inertial 2, the output of the first element And 7 is connected to the input of "Compensation" GOS 1 and the third input of the first element OR 9, a second input connected to the first output of the gyro inertial 2, and its output to the input of the first amplifier 11, the output of the second element And 8 is connected to a second input of the second item OR 10, the output of the second OR element 10 is connected to the input of the second amplifier 12, the outputs of the first 11, second 12 and third 13 and fourth 14 power amplifiers connected to the first inputs of the first 1 is ω gyro inertial 2 and the power source on-Board equipment, the first, second, third and fourth inputs of the pulse shaper 5 are connected respectively to the outputs of the "-Y "+Y" +Z" and "Z" GOS 1, the fifth input of the pulse shaper 5 is connected to the output of the third element And 4, the first and second outputs connected to first inputs of the first 9 and second 10 items OR respectively, and third and fourth inputs connected respectively to the inputs of the third 12 and fourth 13 of the power amplifier, the first input of the third element And is connected to the output element OR the homing head, and the second input is connected with output "Capture" of the homing head.

Does the guidance system as follows.

The shot is made and the projectile flies along a ballistic trajectory. At the clearing point of the trajectory nazarethroad and spins the rotor of the gyroscope inertial 2, go to battery mode power on-Board equipment and GOS 1, detached block the nose, opens the entrance pupil of the GOS.

At approach of the projectile to the target and receiving a reflected from the target pulses of laser radiation GOS generates signal "Capture", which, on entering the first input of the first element And 7, allows the passage of pulses from the first and second output GI 2 to the input of "Compensation" is camping pulses, the total length of which is approximately equal to half the period of rotation of the projectile.

Under the influence of this signal axis GOS will tend to unfold in a vertical plane down and GOS will be generated signal, compensating the effect of precession caused by the signal from the inertial gyroscope, the output signal of the GOS in the process of target tracking will be the following:

< / BR>
where f is the function defined by the direction-finding characteristic CLO, e is the angular velocity of the line "projectile-target", - the angular velocity of precession of the head under the action signal "Compensation" with gyroscope inertial.

This signal is the source for pulse shaping steering autopilot (signals produced by the GOS on the +Y, -Y, +Z, -Z). In the initial guidance, when the initial maximum penalty, the outputs of the +Y, -Y, +Z, -Z GOS 1 produced maximum value of the command (Fig.2B), the middle of which is rigidly attached to the pulses illuminate the target, i.e. to the signal IP.I (Fig.2A) generated by the relay or linear sites FPU and coming from the output element OR 23 GOS. These pulses are received at the first input of the third e is W ill result to the fifth input of the pulse shaper 5. Starting with the first signal IP. I coming after signal Capture, the pulse shaper 5 begins to form temporary "gates" of variable duration during the whole time of transition for each input signal, adopted by the GOS (Fig. 2B). Moreover, the duration of temporary "gate" formed by the first input pulse, corresponds to the minimum duration of control signals generated by the GOS on the +Y, -Y, +Z, -Z, and subsequently can increase any law, for example, linearly increasing, in which the duration of temporary "gates" to each input pulse is increased, for example, to the same constant value while linearly increasing the law to the value corresponding to the maximum duration of the command, and the middle temporal "gate" strictly corresponds to the middle of the control commands generated by the GOS. If the penalty was the maximum, the input command (Fig.2B) are limited in duration and duration determined by the duration of the temporary "gates" (Fig.2B), increases gradually to the maximum value, and if the amount of the penalty was negligible (Fig.2G), and the length of the part of the control commands determined by the expression (1) buuuuut through temporary "gates" without limitation (Fig.2D). At the end of the transition process the input commands are passed through the pulse shaper without changes.

Control command +Y and-Y passing through the pulse shaper 5, with its first and second outputs are received at the first inputs of the first 9 and second 10 circuits, OR where they are summed with the signals compensate for the weight coming on their second and third inputs from the gyro inertial 2. From outputs of the first 9 and second 10 circuits OR control signals received through the first 11 and second 12 amps of power for the first 15 and second 16 of the control winding of the steering actuator 3. Command control +Z and-Z 3-and 4 outputs of the pulse shaper 5, passing through the third 13 and fourth 14 amplifiers, proceed accordingly on 17 third and fourth winding 18 of the steering 3.

Under the action of these signals is the deviation of the rudders, and as a result there is a reduction of misalignment between the axis of the projectile and the optical axis of the GOS. So it is the guidance of the projectile on the target, and a transition section is provided not stepped effect on the airframe, and smooth.

T. O. , due to the fact that at the beginning of the plot homing entering commands on the steering actuator is provided pig. 3) relative to its center of mass in a transitional area guidance, and thereby increases the accuracy of aiming, eliminating the violation of the guidance process arising at angles of oscillation longitudinal axis of the projectile, exceeding the maximum permissible value.

In Fig. 4 shows a block diagram of the pulse shaper 39 - bus synchronization (input 5), 40 - input bus (inputs 1,2,3,4,...,N), 41 - clock, a 42 - first pulse counter, 43 - second pulse counter, 44 - persistent storage device, 45 - schema And 46 - output bus (outputs 1,2,3,4,...,N).

The input bus 40 is connected with the first inputs of all the elements And 45, bus synchronization 39 is connected to the input of the original position of the first pulse counter 42 and the counting input of the second pulse counter 43, the information outputs of which are connected with the first group addresses the ROM 44, the second group of addresses which is connected to the information output of the first pulse counter 42, a counting input connected to the output of the generator of clock pulses 41, the second output of the ROM 44 is connected to the enable input of the second pulse counter 43, and the first output to the second input elements And 45, which outputs soejima, for example 561 series, and a storage device on RT, or implemented on a micro-computer, for example, type VI.

Before putting on the scheme is programming the ROM.

For example, if the repetition period of the input pulses is equal to 50 MS. Duration of the input signal can vary from 0 to 50 MS, the sync pulse is linked to the formation of the control commands, and the command (input), the middle, is formed relative to the center between two adjacent clock pulses. When it is necessary to ensure, for example, the ramp-up pulse at the output of the device 10 to 50 MS in a period of time determined, for example, nine pulses of the input signal, the accuracy formation of the output signals should not be worse than 1 MS.

On the basis of the required accuracy, defined period of pulses of the clock generator, it should be no more than 1 MS.

Is programming a ROM based on the following considerations. The high-order part of the address ROM determines the number of the input pulse, because the counter 42 considers the input pulses and the Junior signal to generate an output signal, because the counter 43 is the instantaneous value of the time between the second zero, in the following 10 memory - logical unit and forth from 30 to 50 memory cell is a logical zero. Next to the second pulse (high-order part of the ROM) in the memory cell 0 through 18 is written logic zero, from 19 to 32 logical unit and from 33 to 50 is a logical zero.

The device operates as follows.

When power is forced zeroing of the counter 43 and the first output of the ROM is a logical zero.

Upon receipt of the sync bus synchronization 39 counter 43 increases your status on the unit, and the counter 42 is reset to zero. During the first 20 MS after twenty cycles of the clock generator on the first output of the ROM is present, the signal is a logical zero, and if at this time on the input bus signals are present, they do not pass on the output bus through the elements And 45. Over the next 10 MS (ten oscillator periods) at the first output of the ROM is the signal of the logic unit, and if the input bus is the signals, they are part of the output device. And the next time on the first release of the ROM signal is a logical zero, which prohibits the passage of the input signals (if any) on the output bus of the device.

PR is its state per unit) and the input signal can pass to the output device only in the time interval from 18 to 32 MS after receipt of the sync pulse. Etc. When entering the ninth pulse at the second output of the ROM appears to signal a logical unit that prevents further operation of the counter 43, and the first output of the ROM signal of the logic unit will always be present, regardless of the state of her younger addresses, and so on. after the ninth pulse of the input signals will be output bus devices without changes.

T. O. , introduction to the shaper pulses of the second pulse counter and ROM allows you to create output signals from the input according to the law, defined by the user.

Sources of information

1. "152-mm shot OF(VOP) with high-explosive controlled projectile OF and charge 1 (reduced variable charge). Technical description and operating instructions OF.00.00.000 (VOF.00.00.000)". M , Military publishing house. 1990, S. 39-64.

2. A. C. 1626348 from 07.02.1991,, N 03 To 5/04.

1. The guidance system managed projectile containing the steering actuator, the gyro inertial and the homing head, item, OR shaping the pulses, the phase of which is determined by the phase of the pulses illuminate the target, the output "capture" of the homing head is connected to the first input of the first element And through an inverter with gyro inertial, the output of the first element And is connected to the input of "Compensation" of the homing head, and with a third input of the first element OR the second input is connected to the first output of the gyro inertial, and its output to the input of the first amplifier, the output of the second element And is connected to a second input of the second element OR the output of the second element OR is connected to the input of the second amplifier, the outputs of the first, second, third and fourth amplifiers connected to the first inputs of the first, second, third and fourth control windings of the steering actuator, the second inputs of which are connected to the fourth input of the gyro inertial and power supply on-Board equipment, characterized in that it introduced the third element And the pulse shaper, the first, second, third and fourth inputs of which are connected respectively to the outputs-Y, +Y, +Z and-Z homing head, the fifth input is connected to the output of the third element And the first and second outputs connected to first inputs of the first and second elements respectively, and third and fourth inputs connected respectively to the inputs of the third and fourth amplifiers, the first input of the third element And is connected to vyhoda. Shaper pulses containing the input bus, the first element And the first input of which is connected to the input bus, the second element And the generator of clock pulses, the first pulse counter, bus synchronization, and output bus, characterized in that it introduced a second pulse counter, a persistent storage device (ROM) and elements, And the total number of which corresponds to the number of output generated signals, and bus synchronization connected with the input set to the source position of the first pulse counter and the counting input of the second pulse counter, the information outputs of which are connected with the first group addresses the ROM the second group of addresses which is connected to the information output of the first pulse counter, a counting input connected to the output of the clock generator pulses, the second output of the ROM is connected to the enable input of the second pulse counter, and the first output to the second inputs of all the elements, And the first inputs of which are connected to the input bus and the outputs are connected to the output bus.

 

Same patents:

The invention relates to techniques for microwave, namely, high-frequency pulsed microwave devices, such as radars

Deploying converter // 2153764
The invention relates to the field of automation and can be used for control of technological processes

The pulse extender // 2137293
The invention relates to a pulse technique

The invention relates to switching devices and may find application in systems management, monitoring, measuring, computing devices, communication devices in different industries

The invention relates to the field of pulse technique

The invention relates to radio communications and can be used to identify signals
The invention relates to rocket technology, particularly to a method of missile guidance in the event of an emergency in flight to improve the safety of objects on the ground within the area of potential fall of emergency rocket or its fragments

The invention relates to rocket technology and can be used in weapons systems remote-controlled missiles

The invention relates to the field of weapons, particularly artillery managed shells with laser homing head

The invention relates to the field of managed artillery ammunition

The invention relates to defense systems, in particular to the guided missiles and projectiles

The invention relates to the field of weapons, particularly artillery managed shells with laser homing head

The invention relates to the field of development of missile guidance systems and can be used in the complexes of anti-tank missiles and missiles

The invention relates to the field of rocketry

The invention relates to defense systems, managed missiles and shells

The invention relates to the field of control systems for rotating the roll angle of the missile airframe was designed as an aerodynamic configuration "duck"

Guided missile // 2244897

FIELD: armament, in particular, guided missiles.

SUBSTANCE: the guided missile has a body with on-board systems, frame with drive shafts made with journals, with air vanes hinge-installed in their end face grooves for folding in the body and fixation in the unfolded position. The guided missile is provided with control-surface deflection transducers and a printed circuit board secured through an insulator on the front end face of the frame and connected by means of a bundled conductor to the on-board systems of the guided missile.

EFFECT: reduced spread in the value of the sweep angle of the air vanes in the process of manufacture.

2 dwg

FIELD: guided missiles, in particular, their control actuators.

SUBSTANCE: the control surfaces are connected by means of a half-axle, in which a central hole is made along the missile longitudinal axis, alkane holes are made perpendicularly to the longitudinal axis for installation of the axles of the control surfaces. The half-axle has components for coupling to the actuation cylinders.

EFFECT: enhanced efficiency of armor-piercing capacity of the missile.

4 cl, 2 dwg

Up!