RU2579321C1 - Detonation commands retarder of ballistic type - Google Patents

Abstract

FIELD: aviation; weapons and ammunition.

SUBSTANCE: invention relates to systems of onboard pyroautomation of aircrafts and may be used in explosive devices. Retarder detonation commands of ballistic type comprises cylindrical housing with metal hammer-like piston, a propellant active charge and main passive charge of detonating explosive arranged on both sides of the striker, and initiating device for triggering detonation in the explosive substance. Propellant active charge is made in form of detonating extended charge piece and is arranged in pre-piston chamber of cylindrical case. Main passive charge is made in form of detonating extended charge piece in metal shell and arranged in behind-piston chamber of cylindrical body with formation of controlled gap between the ends of striker pin and main passive charge. Initiator is docked with propellant active charge and is in form of standard explosive, or fuse, or explosive device arranged outside the cylindrical case.

EFFECT: higher efficiency and reliability of onboard automation systems of aircrafts owing to formation of accurate time delays, required order of detonation commands and blocking false and unauthorised signals.

3 cl, 2 dwg

Description

The invention relates to on-board pyroautomatics of aircraft (rocket, space, aviation and special equipment) and can be used to create the necessary time intervals (decelerations, delays, settings), providing a given sequence of detonation circuit elements. It can also be used in the design of fuses and explosive devices of means of destruction and ammunition for various purposes, as well as in industrial initiation systems.

Retarders (or retarding devices) are traditionally used in the design of fuses and explosive devices of various types of ammunition, as well as in blasting in delayed-action initiating devices, incendiary and electric tubes, pyrotechnic relays, etc.

Known inhibitors of detonation teams in the form of pressed or cast checkers or columns of blasting explosives (explosives), explosive compositions or explosive compositions. They are successfully used in the construction of a number of fuses, explosive devices, systems of initiation of almost instantaneous action (with decelerations from a few microseconds to a millisecond) by including them in the explosive circuits of the above devices and systems [1]. The disadvantage of such moderators is a rather narrow range of variation of extremely short delay times (due to the high detonation velocities of the explosives used (7-8 km / s or more), which virtually eliminates the possibility of getting on board the real overall mass characteristics of the devices of the aircraft (in the on-board system for wiring detonation commands) delays of the millisecond range. Non-electric, known and widely used in explosive, working on the same principle e explosive charge initiation systems with a detonating cord (including traditional cords in filament braids and with or without plastic coatings, detonating elongated charges in metal shells, shell-free elastite and plasticite charges in the form of cords and tapes, initiation systems with low-energy pulse conductors like NONEL etc.) [2, 4], which allow one to obtain practically any delay times, also cannot be used on board aircraft (LA) due to the large extent of detonating cords, the length nnyh charges and significant shock wave loads acting on the surrounding components, units, scientific and service equipment, when triggered.

Known gas-dynamic moderators of detonation teams used in fuses, for example, to small-caliber shells. In these designs, the teams are slowed down due to the outflow of gases (products of the combustion of powder or pyrotechnic charge) through a system of calibrated openings, channels and expansion chambers. As in the previous case, such devices allow obtaining stable delays only in the microsecond time interval [1].

Known mechanical and electromechanical moderators of detonation commands. They are used in the construction of, for example, time and tachometric contact fuses, in long-range cocking mechanisms of air bombs [1]. Their disadvantages are insufficiently high reliability indicators and the accuracy of setting time delays, the bulkiness of structures, the consumption of additional electricity, long delay times (tens of seconds, minutes and even hours).

Partially the above disadvantages are eliminated in the design of electric moderators, in which the deceleration time is determined by the charging time of the electrolytic capacitor, which gives a signal to detonate the explosive charge [1]. At the same time, the accuracy of setting the time delays is increased, the mass-dimensional characteristics of the deceleration devices are improved in comparison with the previous analogues, however, the reliability of such devices remains insufficient (electric breakdowns of capacitors are possible), either an autonomous power supply or a tap from the aircraft onboard cable network is required.

Pyrotechnic moderators are known and extremely widely used in practice, using charges of fast or slowly burning explosive materials in their designs: smoke powder, small-gas pyrotechnic compositions in the form of extruded columns of different heights, rings, “spirals” pressed into rotary massive disks (pyrotechnic retardants with arc channels with unilateral and bilateral placement of channels), or in the form of fire-resistant cords in a thread or metal sheath. Pyrotechnic moderators are included in the design of the overwhelming majority of contact mechanical fuses, remote fuses and tubes, incendiary and electric ignition tubes, initiating means (detonator caps and electric detonators) of short-delayed and delayed action [1 ÷ 4].

The disadvantages of almost all pyrotechnic devices used in detonator caps and electric detonators (ED), fuses (explosive devices), as well as in a number of other pyrodevices, for example, pyro cutters, cartridge opening mechanisms, etc. [5], are a significant dependence of the pyrotechnic burning rate compositions from external pressure and the initial temperature of the charge (although not as strong as that of gunpowder), from the density of the press-in, the height of the column (or the length of the ring), from the material of the shell into which the composition is pressed, its geometrical dimensions, the power source of ignition, combustion chamber design, etc .. The vast majority of pyrotechnic composition burns from the exposed surface only at a residual pressure of 10 mm Hg. st .; with a further increase in the degree of vacuum, combustion attenuation occurs, which inevitably leads to a failure of the device. These shortcomings reduce the reliability of such deceleration devices, in general, are the reasons for unacceptably large variations in the times of their operation (for example, with delay times of 15 to 100 ms for short-delayed domestic ED type EDK3-P (-PM; -PMK), ED-3-N ; ED-1-3-T; ED-24 the spread of the deceleration time can reach ± (12 ... 50)%). In addition, the maximum burning rate of pyrotechnic retarders (or quick-burning low-gas compositions), achieved to date, is about 500 mm / s [6]. To ensure a time delay of the millisecond range, the height of the pressing of the pyro-composition should be in the range of 0.5 ... 5.0 mm, which is technologically difficult. In addition to the above, when using pyrotechnic moderators in the detonation circuits of wiring systems, additional devices are needed that convert the detonation pulse first into a firing pulse, and then back - the firing pulse into a detonation one.

In development of the pyrotechnic method of slowing down detonation commands, in recent years, sealed retarding modules have been developed, which are steel bushings (caps) with an outer diameter of 6.2 mm and a height of 10 to 50 mm, into which small-gas retarding compositions are pressed (quickly or slowly burning), igniter-sealing composition and, if necessary, end charge, providing either the required output fire pulse of the retardation module, or the formation of the required amount of gaseous combustion products - a working fluid for piston-type pyrotechnic devices, or the transition from combustion to detonation, or the closure of electrical contacts by electrically conductive combustion products, etc. [6]. Ignition-sealing composition after its combustion forms a glassy gas-tight slag cork that can withstand gas pressures up to several tens of megapascals. In this case, the low-gas retarder burns in a sealed volume and therefore its burning rate is practically independent (or weakly dependent) on the ambient pressure. The advantages of retardation modules in comparison with the previous analogues are the simplicity of design and the short time required to set the specified time intervals, higher accuracy of issuing commands by sealing the modules during the combustion of special ignition-sealing compounds. However, all the other disadvantages listed above, inherent in pyrotechnic moderators, remain. Thus, the upper values of the temperature coefficient _kt of the burning rate for fast-burning low-gas trains can reach twenty percent, which can hardly be considered satisfactory for most on-board automation systems of such aircraft as spacecraft and rocket blocks.

Known electronic moderators of detonation teams based on specialized large intengral microcircuits (their other name is firmly fixed - microchips) used in some modern electronic devices, remote and distance contact explosive devices (WU) [2]. The main element of these moderators is an electronic temporary device that provides high accuracy for counting the set time (with an error of a fraction of a percent) without the use of precision elements in the master oscillator of a special electronic explosive device or remote control equipment for launching a projectile (rocket). In addition to the high accuracy of programming time intervals, the advantages of electronic ED and VU are increased safety with respect to stray currents of any origin, the impossibility of unauthorized operation from any current source, except for a special explosive device (or remote control equipment), moreover, one with an established security code identical to setting the electronic circuit in the ED (or VU), as well as the ability to automatically check the status of the electric blast network and blocks blasting process in case of failure to fulfill the conditions of reliability. Electronic ED and VU, despite the above indisputable advantages over devices with pyrotechnic slowdown nodes, are also inherent in significant disadvantages. These include the insufficiently high resistance of microchips to powerful ionizing radiation, the need to include power supplies in the device design (either capacitor, charged from bulky and massive explosive devices or remote control equipment, or thermal with an electrolyte melted from an additional pyrotechnic device). In addition, there is currently no domestic industrial base for the production of microchips, as a result of which the cost of electronic ED and VU remains extremely high.

Known detonating device for conducting perforated blasting in deep wells, allowing to initiate detonation of heat-resistant explosives without initiating explosives (without a standard low-voltage means of detonation: electric detonator or detonator capsule) [7]. The device consists of a cylindrical metal case, inside of which there is a heat-resistant propelling charge (active charge), sensitive to thermal effects and easily ignited by the built-in initiating means (electric igniter (in the description - the outdated concept of “electric igniter”) or incandescent wire), a metal piston ( short cylinder-roller) and the main charge of the blasting explosive (passive charge) in the form of two press-fits of different densities. The principle of operation of the detonating device is as follows. During rapid combustion or explosion of a composition (potassium picrate, magnesium picrate or a mixture of picrate and potassium perchlorate) in a propellant charge, the piston starts to move under the influence of the combustion products pressure (in the device it acts as a striker). When a piston strikes a layer of a passive charge of a low-density blasting explosive, a powerful initiating shock wave is created in the latter, which causes detonation of a high-density charge.

This device by technical nature is the closest to the claimed.

The known closest to the claimed device has several advantages compared with the above analogues. It is distinguished by its simplicity of design and high reliability of action, which is confirmed by the sufficient depth to date of studying such sections of explosion physics as “Sensitivity of explosives to mechanical stress”, “Conditions for the transition of an initiating shock wave to detonation,” “Detonation in explosive charges under the influence of high-speed compact drummers ”and others [8]. Another indisputable advantage of this detonating device is the wide temperature range of its operation, because there are no initiating explosives in it, and propelling (active) and main (passive) charges are made of heat-resistant blasting explosives. The output parameters of the device are very slightly affected by environmental parameters (pressure, temperature). However, this advantage can be realized, in our opinion, only if the propellant charge is not ignited by an electric igniter or an incandescent wire followed by burning in parallel layers, but explode (when either explosive combustion or low-speed or full detonation modes are realized ) And for this, the indicated means of initiation must be with exploding incandescent bridges operating from a high-voltage source of an electric signal. The latter, due to their, as a rule, large masses and dimensions, may not be applicable on a number of aircraft; primarily on spacecraft. When using the device from low-voltage on-board current sources, the process of heating the explosive layer of the propellant charge near the incandescent bridge with its subsequent ignition, and from it the entire propellant charge will depend on the environmental parameters. The response time of the device will be from a few milliseconds to tens of milliseconds; the scatter of the response time will be of the same order. This factor limits and even eliminates the use of this device in airborne aircraft pyroautomatics systems. Due to the placement in the closest to the claimed known device of the passive charge of the blasting explosive practically close to the piston in this design can be realized only fairly small (tens of microseconds) deceleration times. In addition, the design of the device does not allow them to change, i.e. set the required settings immediately before use.

The task to which the claimed invention is directed is to develop a simple, reliable, reasonably safe, accurate, not requiring additional consumption of electric energy, resistant to all factors of outer space detonation moderator - a device for creating the necessary time intervals, providing a given sequence of detonation elements circuits and explosive logic on-board pyroautomatics, expanding the scope of application closest to the claimed zvestna device.

In the implementation of the invention, the task is solved by achieving a technical result, which consists in increasing the efficiency and reliability of on-board automation systems of aircraft by forming accurate time delays, ensuring the required sequence of detonation commands and blocking false and unauthorized signals.

The specified technical result is achieved by the fact that the propellant charge is made in the form of a cut-off of a detonating elongated charge (ДУЗа) in a metal (aluminum, copper, steel, etc.) shell, or an extended charge in a polymer (polyvinyl chloride, fluoroplastic, polyethylene, etc.) shell, or a charge without a shell (for example, an elastite in the form of a cord or tape) inserted into the device’s body into a pre-piston charging chamber. In the inventive device performs the function of an active charge. A segment of a detonating elongated charge was also used as the main charge of the blasting explosive (passive charge), but only in a metal shell inserted into the device’s body on the opposite side of the piston — into the piston chamber so that the gap between the ends of the piston and the remote sensing device was variable. The initiation of detonation in a propellant (active) charge is carried out by an initiating device in the form of any standard means of detonation (a capsule — a detonator, an electric or light detonator, an explosive cartridge), or a fuse or explosive device (contact, non-contact, remote, etc.) placed outside device enclosures.

For greater compactness of the device, intended for significant times of slowing down detonation (from several hundred milliseconds to several seconds), its body can be made in the form of a pipe bent or twisted into a spiral. In this case, a metal ball or a short cylinder (roller) with a spherical or animated frontal part can be used as a piston (striker).

The invention is illustrated by drawings, which depict:

in FIG. 1 is a variant of the proposed device that implements a deceleration time from several tens of microseconds to several tens of milliseconds;

in FIG. 2 - a variant of the proposed device for long slowdown times (hundreds of milliseconds - seconds).

Here 1 is the case;

2 - pre-piston chamber;

3 - firing pin (piston - in Fig. 1 or ball in Fig. 2);

4 - piston chamber;

5 - passive (main) charge;

6 - active (propelling) charge;

7 - initiating device.

The proposed device is used and operates as follows. When a command signal is sent to the initiating device 7, it is triggered, as a result of which the detonation process is initiated in the active (propelling) charge 6. The detonation products of the propelling charge flowing into the pre-piston chamber 2 create pressure in it, which, acting on the firing pin (a piston, ball or roller with a spherical or animated frontal part) 3, set the latter in motion and accelerate it to a certain speed. Moving in the piston chamber 4, the firing pin 3 acts on the passive, main charge 5, which is a detonating elongated charge in a metal shell. The use of remote sensing as a passive charge in a metal shell is due to two main reasons. Firstly, since the inventive device is intended for use in on-board aircraft pyroautomatics systems, it is intended to use both active and passive charges of elongated small-caliber charges (with an outer diameter of up to 5 mm); In this case, the question of reducing the critical parameters of the initiation of detonation in such charges under their end-shock loading is urgently raised. In this regard, preference should be given specifically to charges in the metal shell, since a decrease in the time of chemical transformations in the zone of chemical reactions due to an increase in the lifetime of high pressures and temperatures, as well as the transition of the unloading wave from the shock-compressed shell material to the explosive charge substance and its leading action on explosives will inevitably lead to a decrease in the critical parameters of initiation, which is extremely important for ensuring the operability of the inventive device with a high degree of reliability. Secondly, charges in metal shells have rigidity, which is also necessary to ensure the process of initiation of detonation in them by the impact of a fast-flying body. The slowdown time of the detonation command using the inventive device will be the sum of the time the active (propellant) charge detonation flows into the pre-piston chamber, the time the pressure rises in it to a value at which there will be a disruption from the place of the striker, its acceleration to some constant approximation) of speed, time of movement of the striker on the piston chamber and time of transitional processes in the explosive charge of the passive charge until steady detonation. The current level of development of explosion physics and internal ballistics allows us to solve this problem in an analytical form. A decisive contribution to the integral deceleration time will be made by the movement time of the striker (piston of Fig. 1 or the ball of Fig. 2) in the piston chamber. By pushing (or pushing) a passive charge (ДУЗ) inside the device’s case, one can also vary the deceleration time (decreasing it or increasing it accordingly).

Additionally, the claimed device can perform the functions of an explosive diode in explosive logic circuits of an aircraft. This is explained as follows. If the passive charge 5 is accidentally triggered by a false signal, its detonation products will fill the piston chamber 4. The pressure created by them, due to its significant geometrical dimensions, will not reach the value that is necessary for driving the hammer-drum 3. As a result, the device exits system, but a false command will not work.

The application of the invention allows to obtain with a high degree of reliability, increased security and with sufficient accuracy the guaranteed delays of detonation commands, especially the millisecond range, regardless of environmental factors and without additional energy consumption. The scope and functionality of the device are expanding.

Information sources

1. Means of destruction and ammunition: Textbook / L.V. Babkin, V.A. Veldakov, E.F. Gryaznov and others. Under the general. ed. V.V. Selivanova. - M: Publishing house of MSTU. N.E. Bauman, 2008.

2. Graevsky M.M. Handbook of electric explosive explosive charges. Ed. 2nd rev. and additional - M.: Rendezvous - AM, 2000.

3. Karpov P.P. Igniter Caps and Detonator Caps / Ed. P.F. Bubnova - L .: Publishing house Art. Academy of the Red Army Dzerzhinsky, 1935.

4. Engineering ammunition. Guidance on material and application. Prince 1. - M: Military Publishing, 1976.

5. Auxiliary systems of rocket and space technology / Ed. I.V. Tishunina. - M .: Publishing house "Mir", 1970.

6. Design of automatic spacecraft for basic scientific research: Monograph / Comp. V.V. Efanov; Ed. V.V. Khartova, V.V. Efanova, K.M. Pichkhadze: In 3 volumes T. 1; 3. - M .: Publishing house MAI-PRINT, 2013, 2014.

7. The USSR AS 163132, IPC E21B, C06C. Detonating device / Baum F.A., Derzhavets A.S.- No. 836138 / 22-3; declared 05/15/63; publ. 06/22/64. Bull. No. 12.

8. Explosion Physics / Ed. L.P. Orlenko. - Ed. 3rd, revised. - B2 t. T1. - M: FIZMATLIT, 2002.

Claims (3)

1. A ballistic-type detonation command moderator comprising a cylindrical body with a metal striker in the form of a piston placed inside it, a propelling active charge and the main passive charge of a blasting explosive placed on both sides of the striker, and an initiating detonation excitation device in an explosive substance, characterized in that the propellant active charge is made in the form of a segment of a detonating elongated charge and placed in the pre-piston chamber of a cylindrical body, and about The main passive charge is made in the form of a segment of a detonating elongated charge in a metal shell, which is placed in the piston chamber of the cylindrical body with the formation of an adjustable gap between the ends of the striker and main passive charge, and the initiating device is docked with a propelling active charge and made in the form of a standard blasting device or a fuse or fuse placed outside the cylindrical body. 2. The moderator according to claim 1, characterized in that the cylindrical body has a curved shape. 3. The retarder according to claim 1, characterized in that the firing pin is in the form of a ball or roller with a spherical or animated frontal part.

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