RU2169344C1 - Remote-control blasting devices for jet projectiles of salvo-fire systems - Google Patents

Abstract

FIELD: military equipment, in particular, remote-control explosive devices for salvo-fire systems jet projectiles with cassette or separated warheads. SUBSTANCE: for taking into account the deviation of the actual parameters of projectile motion from the design ones and correction of the preset time of remote actuation the remote-control explosive device uses an accelerometer and a computer realizing the correction algorithm, taking into account the projectile velocity in a fixed point of the trajectory, the coefficient and functional introduced in the pre-launch procedure. At projectile launching signals corresponding to the projectile axial acceleration start arriving at the computer input. In a fixed point the computer determines the projectile velocity and realizes the preset algorithm. To prevent the influence of deviation of the accelerometer parameters (initial frequency f_o) caused by prolonged storage, dependence of f_o on temperature and other factors, an automatic frequency control (AFC) unit is introduced in the correction unit. This unit has a frequency subtraction circuit, the first and second frequency dividers, controllable frequency divider, flip-flop and an additional oscillator. Besides, the electronic time device has a correcting signal analysis unit, which keeps up with the fact that the total number of correction pulses would not exceed the maximum allowable value. EFFECT: enhanced accuracy of deployment or separation of the warhead in range. 3 cl, 3 dwg

Description

 The invention relates to the field of military equipment, and more specifically to remote explosive devices (TLD) for shells of multiple launch rocket systems with cluster or detachable warheads.

 Known remote explosive devices that provide ammunition at a given point in the flight path after counting the time set by remote equipment from ground equipment (US patent N 3520254, CL 102 - 70.2; N 3686633, CL 340 - 168, N 3646326, CL 235 - 92 BC; N 3788524, class 235-92 PL; N 4424745, class 102-215, German patent 3301040, F 42 C 11/06).

 Known electronic remote fuse according to the patent of Germany 3301040 F 42 C 11/06, containing a generator and a pulse counter, the input of information about which the required time of action of a remote fuse is carried out before firing the installation of a pulse counter. The specified device is the closest to the proposed. It is selected as a prototype.

 The disadvantage when using the known TLDs is the low accuracy of ensuring the disclosure or separation of warheads in range, due to the deviation of the actual parameters of the projectile on the trajectory from the calculated ones.

 The aim of the invention is to eliminate the disadvantage by taking into account the deviation of the actual parameters of the projectile movement on the trajectory from the calculated ones and the correction of the time of remote action installed from ground equipment after the shot.

 This goal is achieved by introducing an accelerometer and a computing device into the TLD that implements a correction algorithm that takes into account the velocity of the projectile at a fixed point on the trajectory, the coefficient and functionality introduced during prelaunch preparation.

 Errors arising due to technological variations in the accelerometer parameters and changes in the initial frequency of the accelerometer when using an accelerometer with a frequency output are proposed to be eliminated by introducing an automatic frequency adjustment circuit.

 Ensuring high reliability of the fuse is achieved by introducing into the electronic temporary device unit analysis of corrective signals.

 A functional diagram of an electronic remote fuse is shown in FIG. 1.

 It consists of a correction unit 1, an electronic temporary device 2, connected to the input 3 of the actuator (IM). Correction block 1 consists of an accelerometer 4 and a computing device 5. The electronic temporary device 2 consists of a generator 6 and a reverse pulse counter 7.

 The output 8 of the accelerometer 4 is connected to the first input 9 of the computing device 5. The second input 10 of the computing device 5 is connected to the first control output 11 of the electronic remote explosive device.

 The first output 12 of the computing device 5 of the correction unit 1 is connected to the first summing input 13 of the reverse pulse counter 7 of the electronic temporary device 2.

 The second output 14 of the computing device 5 of the correction unit 1 is connected to the subtracting input 15 of the reverse pulse counter 7 of the electronic temporary device 2.

 The second summing input 16 of the reversible pulse counter 7 is connected to the output of the generator 6 of the electronic temporary device 2, and the installation input 17 of the said pulse counter 7 is connected to the second control terminal 18 of the electronic remote explosive device.

 The output of the reverse counter 7 of the electronic temporary device 2 is connected to input 3 (MI).

 The accelerometer 4 at its output 8 generates a signal corresponding to the axial acceleration of the V projectile.

The computing device 5 of the correction unit 1 implements the following algorithm
ΔT = Ф-KV, (1)
where ΔT is the time correction generated by the computing device 5;
V is the velocity of the projectile at a fixed point in the trajectory, determined by the integration of the signals of the V accelerometer 4;
K, F - coefficient and functional, respectively, entered into the computing device 5 by the first output 11 of the remote fuse during prelaunch preparation from ground-based remote input equipment.

 Coefficient K takes into account the effect of deviations from the nominal value of the velocity of the projectile at a fixed point on the trajectory on the desired change in the duration of the action.

 The functional Ф is numerically equal to the value providing a zero value Δ T at the nominal (calculated) value of the velocity of the projectile at a fixed point on the trajectory.

 The device operates as follows.

When prelaunching (before launching the projectile) from ground-based remote input equipment at the first output 11 of the remote explosive device, the coefficient K and the functional Ф are fed into it, received in the computing device 5 of the correction unit 1, and on the second output 18 the calculated distance of the remote action T _calculated , arriving at the installation input 17 of the reversible pulse counter 7 of the electronic temporary device 2.

Setting the required time of remote action T _uc can be carried out by any known method: the number of pulses, a parallel code, a time interval, etc.

When the projectile is launched, from the accelerometer 4 of the correction unit 1, signals corresponding to the axial acceleration of the V projectile begin to arrive. These signals from the output 8 of the accelerometer 4 are fed to the input 9 of the computing device 5, which implements their integration. At a fixed point on the trajectory, computing device 5 determines the velocity of the projectile V and implements the algorithm in accordance with expression (1). Depending on the sign obtained, the output signal of the computing device 5 is generated either at terminal 12 (- ΔT), or at terminal 14 (+ ΔT), then either to summing 13 or subtracting 15 the input of the reverse pulse counter 7. As a result, the temporary device 2 generates an output command through the action time T _d equal to:
T _d = T _calc ± ΔT.
When generating signals ΔT in the form of pulses N _ΔT and entering the calculated time T _count also in the form of the number of pulses N _{T count the} time of remote action will be determined by the expression:
T _d = (N _Tcal ± N _ΔT ) T _g ,
where T _g is the pulse period of the generator 6.

 The output signal from the output 19 of the temporary device 2 is fed to input 3 (MI), the operation of which provides the necessary action of the projectile. Depending on the type of warhead used, this can be the opening of a cluster warhead or the separation of the warhead and the opening of the parachute system.

 Thanks to the used correction of the set operating time, the accuracy in range at which the head is opened or separated is significantly increased.

 When using the ideal accelerometer 4, its output signal must be equal to zero before the projectile is launched. However, due to the technological spread, possible accelerometer 4 parameters during long-term storage, and changes in the ambient temperature, the initial signal of the accelerometer 4 can significantly differ from zero.

 On the accelerometer 4, in addition to the axial component of the acceleration of the projectile on the flight path, the component of gravity also depends on the angle of fire. This component gives an additional signal from the output of the accelerometer 4 to the launch of the projectile on the launcher, increasing the deviation from the zero value of the initial signal of the accelerometer 4.

 When using frequency accelerometers constructed according to a non-differential scheme, obtaining a zero signal of the accelerometer (output frequency is zero) is difficult.

 You can use differential frequency accelerometers containing 2 channels, in one of which, under the action of positive acceleration, the output frequency increases, and in the other decreases, and the output signal of the accelerometer is formed as the difference of the output frequencies of the channels. In this case, the desire to obtain the same frequencies in both channels in the absence of acceleration can lead to an undesirable phenomenon of frequency capture, which leads to the fact that the frequency of one of the channels becomes equal to the frequency of the other even under the action of some acceleration, which leads to an additional error.

 To eliminate this phenomenon, it is necessary to distribute the channel frequencies and, as a result of this, have a non-zero initial value of the output frequency of the accelerometer 4. You can of course take into account the value of the initial output frequency of the accelerometer 4 in the algorithm implemented by computing device 5 by introducing correction factors, but take into account temperature changes the initial frequency of the accelerometer 4, and even more so, its departure during long-term storage is difficult, which leads to an error in the operation of the correction unit 1.

 You can eliminate this drawback by introducing an automatic frequency adjustment block (AFC) into the correction block. This is shown in FIG. 2.

 To a correction unit 1, comprising an accelerometer 4 and a computing device 5, in accordance with FIG. 2, AFC block 20 is introduced. This block consists of a circuit for subtracting frequencies 21, first 22, and second 23 frequency dividers, a controlled frequency divider 24, trigger 25, and additional generator 26.

 The frequency output of the accelerometer 4 is connected to the first input (+) 27 of the subtraction circuit 21 and to the counting input (C) 28 of the first frequency divider 22, the enable input 29 of which is connected to the output 30 of the trigger 25 connected by the synchronization input 31 to the enable input 32 of the second frequency divider 23 and the output 33 of the first frequency divider 22. The output 34 of the second frequency divider 23 is connected to the input 35 of the recording of the controlled frequency divider 24, the output 36 of which is connected to the second input 37 of the frequency subtraction circuit 21.

 AFC works as follows. In the initial state during pre-launch preparation, the “Reset” signal keeps the frequency dividers 22, 23, the controlled frequency divider 24 and trigger 25 in the initial state. Auto-tuning starts when the “Reset” signal is removed, while the first frequency divider 22 starts counting pulses from the output of the accelerometer 4 . Since all this is carried out before the launch of the projectile, the frequency at the output of the accelerometer 4 is equal to the initial difference frequency.

где n - номер разряда первого делителя частоты 22,
f₀ - начальная частота акселерометра 4.At the output 33 of the first frequency divider 22, an impulse is formed with a duration T _a equal to

where n is the number of the discharge of the first frequency divider 22,
f ₀ - the initial frequency of the accelerometer 4.

This pulse is fed to the enable input 32 of the second frequency divider 23, which during this pulse divides the frequency of the additional generator 26 by 2 ⁿ . The pulses from this frequency divider 23 are fed to the installation input 35 of the controlled frequency divider 24, made in such a way that its division ratio is equal to the number of pulses received at the installation input 35.

 Thus, during the duration of this pulse, M pulses are supplied from the output 33 of the first frequency divider 22 to the controlled frequency divider 24 and its division coefficient is set equal to the indicated received number of pulses M.

где f_гд - частота импульсов дополнительного генератора 26.Wherein

where f _gd is the pulse frequency of the additional generator 26.

где f_гд - частота импульсов дополнительного генератора 26.After the end of the pulse from the output 33 of the first frequency divider 22, the output 36 of the controlled frequency divider 24 generates pulses with a frequency f _AFC equal to

where f _gd is the pulse frequency of the additional generator 26.

 After the end of the pulse from the output 33 of the first frequency divider 22 at its trailing edge (slice) supplied to the synchronizing input 31 of the trigger 25, the latter switches. The signal from its output 30, entering the resolution input 29 of the first frequency divider 22, prohibits further pulse counting from the output of the accelerometer 4 by this frequency divider 22.

Before the projectile is launched, the initial frequency f = f _{0 is} received from the accelerometer 4 to the first input 27 of the subtraction circuit 21, and the signal from the output 36 of the controlled frequency divider 24 with the frequency f _AFC = f _{0 is} received from the accelerometer 4. The frequency at the output 38 of the frequency subtraction circuit 21, equal to the difference in the frequencies supplied to its inputs 27 and 37, is zero, which should correspond to a stationary projectile, since the acceleration of the projectile is zero.

After the launch of the projectile on the flight path from the signal frequency from the output of the accelerometer 4, the subtraction circuit 21 reduces it by the value of f _AFC = f ₀ . Thus, the input 9 of the computing device 5 receives a signal strictly corresponding to the acceleration of the projectile V, regardless of the initial frequency of the accelerometer 4.

Due to the introduction of correction block 1 of the AFC unit 20, consisting of a subtraction circuit 21, two frequency dividers 22, 23, a controlled frequency divider 24, a trigger 25 and an additional generator 26 with the corresponding connections, the influence of instability and technological spread of the initial signal of the accelerometer 4 on accuracy of operation, and also ensures the accuracy of the explosive device at different pointing angles, since the measurement of the initial signal f _{0 of the} accelerometer 4 of the sensor occurs immediately before launch, that is, angle of guidance.

 Correction block 1 is a more complex device compared to electronic temporary device 2 due to the fact that it includes a precision device - an accelerometer 4. In this regard, the reliability of correction block 1 is lower than the reliability of electronic temporary device 2. Failure of correction block 1 or its incorrect operation leads to an incorrect countdown, i.e. to parametric failure.

 The elimination of this drawback is achieved by introducing the correction signal analysis unit into the electronic temporary device 2.

 A functional diagram of an electronic temporary device with an analysis unit is shown in FIG. 3.

 The electronic temporary device 2 consists of a master oscillator 6, a reverse pulse counter 7, a pulse counter 39, a counter of corrective pulses 28, two keys 41, 42, a switch 43 and a summing block 44 of corrective pulses.

 The reversible counter 7 and the pulse counter 39 are connected in parallel.

 The summing input 16 of the reverse pulse counter 7 and the input 45 of the pulse counter 39 are connected to the output of the generator 6. The outputs 46 and 47 of these counters are connected via a switch 43 to the output 19 of the electronic temporary device 2. The correction input is ΔT (decreasing the duration of the action) through the first key 41 connected to the second summing input 13 of the reversible pulse counter 7 and the first input 49 of the summing unit 44 of the correcting pulses. Correction input 50 + ΔT (increase in operating time) through the second switch 42 is connected to the subtracting input 15 of the reverse pulse counter 7 and the second input 51 of the block of summing correction pulses, the output of which is connected to the input of the counter of correcting pulses 40, while the output of the counter of control pulses 40 is connected with control inputs of keys 41, 42 and switch 43.

 The capacity of the counter corrective pulses 40 is equal to the maximum allowable number N of correction pulses.

 The control terminal 18 of the electronic remote fuse is connected to the input 17 of the reversible pulse counter 7 and the installation input 52 of the pulse counter 39.

 The operation of the electronic temporary device 2 is as follows.

When installing the equipment remote from the ground during prelaunch input at terminal 18 to the electronic device 2 is temporarily introduced calculus required time T _{w ill} remote actions supplied to the adjusting inputs 17 and 52 of the reversible pulse counter 7 and the pulse counter 39.

 When the projectile is launched, the generator 6 is started and the pulses from its output go to the summing input 16 of the reversible pulse counter 7 and the counting input 45 of the pulse counter 39. Correction pulses, if necessary, change the action time to the correction inputs 48 and 50 - ΔT, + ΔT from the block corrections 20, through the keys 41, 42 are respectively supplied to the summing 13 and subtracting 15 inputs of the reverse pulse counter 7. At the same time, the indicated pulses, being summed by the summing block of the correcting pulses 44, are received at the counter input correctly pulsating pulses 40.

 If the total number of correction pulses does not exceed the maximum allowable correction value N, corresponding to the capacity of the counter of correcting pulses 40, the signal does not appear at the output of the latter and the output of the reverse counter of pulses 7 through the switch 43 is connected to the output of the temporary device 2. When filling the reverse counter 7 on it an output signal appears, through the switch 43 coming to the output of the electronic temporary device 2. The electronic temporary device 2 at the same time counts The determined time of action taking into account corrective impulses.

If the total number of correction pulses exceeds the maximum allowable correction value N, corresponding to the capacity of the counter of correcting pulses 40, the last one is filled and a signal appears at its output, closing the keys 41 and 42 at the control inputs and changing the state of the switch 43. Now it turns out to the output of the electronic temporary device 2 connected counter 39, a signal at the output of which 47 is generated after a time T _inc without taking into account the correction signals.

 Thus, if the number of correction pulses does not exceed the permissible value, then the electronic temporary device 2 counts the time of action taking into account the correction. Otherwise, the remote operation time set by the ground equipment is counted.

 This does not lead to a failure in case of incorrect functioning of the correction unit, i.e. improves the reliability of a remote fuse.

Claims (3)

1. A remote explosive device for shells of multiple launch rocket systems containing an electronic temporary device, the output of which is connected to an actuator, including a generator and a pulse counter, the installation input of which is connected to the installation input of the remote explosive device, and a correction unit, characterized in that the unit correction is made in the form of an accelerometer with a computing device connected to its output, generating a signal ΔT for correction after a shot set webbings action temporary electronic device according to the following algorithm
ΔT = Ф - КV,
where V is the velocity of the projectile at a fixed point in the trajectory, determined by the integration of the accelerometer signal;
K, F are the coefficient and functional, respectively, entered into the computing device of the remote explosive device during the prelaunch preparation of ground-based remote input equipment and taking into account (coefficient K) the effect of deviations from the nominal value of the projectile velocity at a fixed point on the trajectory on the required change in the distance of the remote action, numerically equal to ( functional Ф) to a value providing ΔT = 0 with a tabular value of the velocity of the projectile at a fixed point on the trajectory,
and the pulse counter of the electronic temporary device is reversible, its first summing input is connected to the first output of the computing device, corresponding to a decrease in the required action time, and the second is to the output of the generator, the subtracting input of the said counter is connected to the second output of the computing device, corresponding to an increase in the action time, and installation input - to the input input of the calculated value of the duration of the action of the remote explosive device associated with prelaunch training with ground-based remote input equipment.  2. The device according to claim 1, characterized in that in the correction unit between the accelerometer and the computing device, an automatic frequency control unit is introduced containing the first and second frequency dividers, a controlled frequency divider, a subtraction circuit, an additional generator and a trigger, the accelerometer output being connected to the first input of the subtraction circuit and the counting input of the first frequency divider, and its enable input is connected to the output of the trigger, the synchronization input of which is connected to the output of the first frequency divider and connected to the input resolution of the second frequency divider, a second frequency divider output coupled to an input record managed frequency divider, the counting input of which is connected to the counting input of the second frequency divider and the output of the additional generator, and an output - to a second input of the subtractor, the output of which is connected to the input of a computing device.  3. The device according to claim 1 and 2, characterized in that a correctional pulse analysis unit is introduced into the electronic temporary device, consisting of a correction pulse counter and a correction pulse summation unit, a pulse counter, two keys connected between the correction inputs of the electronic temporary device and the inputs a reversible pulse counter and a pulse counter, a counting input connected to the output of the generator, and the installation input to the input input of the calculated time of the remote fuse, and also a switch connected between the outputs of the reversible pulse counter, pulse counter and the output of the electronic temporary device, the control outputs of the switch and two keys are connected to the output of the counter of correcting pulses, the input connected to the output of the summing pulse summing unit, the inputs of which are connected to the outputs of the keys, while the capacitance counter corrective pulses equal to the maximum allowable number of correction pulses.

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