RU2541595C1 - Safety device for aircraft onboard automatics detonation circuits - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: proposed device comprises case with through cylindrical bore stopped by pressure cover from one side and by end plug with internal piston from opposite side. Transfer detonator charge features U-like shape and is composed of two radial channels in the piston body and axial channel communicating the later and accommodating explosive composition embedded and/or fitted therein. Booster charges are arranged on both ends of transfer charge. One boss of the device case accommodates electric fuse and transfer charge end device for transfer of detonation commands while cotter pin is fitted in another boss. Retainer is fitted in through holes made in the walls of the case and piston to retain both by pre-compressed cylindrical spring fitted in piston blind chamber on piston one side. Spacing between electric fuse and transfer charge end element complies with that between radial channels of said charge. End plug to be screwed in device case serves to adjust the piston stroke.

EFFECT: higher reliability, multi-purpose applications, simplified design, better manufacturability, reusable feature.

2 cl, 1 dwg

Description

The invention relates to devices and automation systems using the energy of high-energy condensed systems (explosives and explosive compositions, gunpowders, solid fuels and pyrotechnic compositions), and can be used at space rocket, aviation and special equipment to solve the problem of blocking detonation circuits from traction stray currents, leakage currents from the onboard cable network, charges of static electricity, high-frequency electromagnetic radiation, lightning discharges, etc. learning signals, as well as unauthorized influences on objects of technology.

There are known designs of a large number of safety mechanisms of fuses and explosive devices (VU) of contact, remote, non-contact, command, inertial action for various types of artillery shells and mines, warheads of guided and unguided missiles, aviation, naval, engineering ammunition, grenades, etc. . (Means of destruction and ammunition, 2008; Kozlov V.I., 2012). Being components of shock mechanisms and fire (more correctly, fire and detonation) circuits of almost all mechanical and electromechanical fuses and safety devices of safety and semi-safety types, these mechanisms are constructed constructively according to one scheme.

A detonator capsule (CD) or a transfer charge (PZ) is mounted in a movable engine, a rotary disk, or in a rotary sleeve of a safety detonating device (PDU) or a capsule isolation mechanism (MIC). Moreover, in the initial unbroken state, the axes of the igniter caps (KV) -PZ-KD or KD-detonator are not combined; the fire chain is open. When cocking the fuse, the locking devices break down and the engine, rotary disk or sleeve are rotated so that the axes of all elements of the fire chain coincide; the fire chain closes. The movable engine, rotary disc or sleeve are driven by a coil spring, wound during assembly. The disadvantage of such safety mechanisms is the inclusion of spiral springs (and in the long-range cocking mechanisms of remote control units - clock mechanisms) that are in a twisted state for a long time. Possible defects of the spring tape can lead to its mechanical destruction (breakage), which will lead to malfunction of the cocking unit and the failure of the PM and the fuse or fuse. In addition, the removal of locking devices in such PMs is carried out either due to inertial forces (when a shell, grenade, torpedo, rocket, etc. accelerates in the barrel, torpedo installation, on the guide (or in the rocket container), or under the action centrifugal forces during the spin of the projectile in the channel of the rifled gun, which practically makes it impossible to use such devices on board the spacecraft and units flying in space or in a very rarefied atmosphere.

The so-called safety and launching devices are known and widely used in objects of rocket, space and aviation technology - PPU (Auxiliary systems of rocket and space technology, 1970; Zagorsky V.K., 2011), designed to exclude the possibility of premature (accidental or unauthorized) triggering of airborne pyrotechnic, pyromechanical, detonation devices and systems, as well as to ensure their reliable activation by command (signal) from the onboard control system according to the sequence diagram or with Of the earth. In terms of purpose, principle of operation and the main structural elements, the PUFs are similar to the above-mentioned safety mechanisms of fuses and fuses (especially mechanical PUFs with tape springs). The vast majority of PPU is made according to the so-called "rotary" scheme. A blocking rotor (in fuses and a VU - a moving engine), which plays the role of a fuse when it rotates around the axis, closes or opens the fire chain (ignition or detonation). The disadvantages of PUFs of the "rotary" type are associated with the complexity, cumbersomeness and insufficiently high reliability of the drives used: mechanical, electromechanical, inertial or using environmental parameters. So, the rotation of the locking rotor in the PPU with a mechanical drive is carried out using an exhaust cord, a cam mechanism, a rod with reciprocating movement (an additional mechanism for moving the rod is required!) Or a bellows drive (a source of a working fluid in the form of a cylinder with compressed gas or a gas generator with shutoff valves and remote control devices, etc.). In PPU with an electromechanical drive, the rotation of the locking rotor is carried out using a DC motor with high torque (often used in addition to the gearbox), a crank-spring mechanism connected to the splined shaft of the engine directly or through the gearbox. In addition to the large masses and dimensions of PUFs with an electromechanical drive, they require additional large energy consumption for the electric motor. In addition, the device is quite complex, has a large number of rubbing, rotating parts. PUFs with an inertial drive or a drive that uses environmental parameters, as a disadvantage, have a very limited area of their application on aircraft: only when launching (launching) rockets or when landing descent vehicles (payload) on Earth or other planets. In addition, the design of these PUFs includes additional sensitive devices, for example, a barometric relay, as well as additional power sources, electric motors, massive platforms, cut-off safety pins, twisted tape springs, etc. All this limits the possibility of using the PUF of these types on board such aircraft as spacecraft and missile units.

Electronic PUFs are very promising; they are small in size, weight, low power consumption. However, to date, the required level of radiation-thermal resistance of the used microchips, their failure-free operation in conditions of powerful electromagnetic fields, and microwave signals have not been ensured.

A known design of self-liquidator with a “pyroelectric” drive of single-use supersonic flying targets that fires at the end of a target’s flight if it is not damaged from the air or from the ground. (Auxiliary systems of rocket and space technology, 1970, p.204-208, Fig.6.8, 6.9). Structurally, self-liquidator consists of a housing, inside of which there is a piston with a safety shutter, in the body of which two through channels are drilled perpendicular to the axis. Detonators (transfer charges) are pressed into the channels. The damper is designed to protect against the possible initiation of detonation in a blasting explosive charge (explosive charge) in case of accidental operation of electric detonators, at least even one of two. In cross section, the piston has the shape of a flattened circle. From spontaneous movement of the piston and the flap holds a coil spring and a safety pin, removed manually before starting the target. A thin-walled metal cup with a charge of explosive devices in the form of several pressed pieces is mounted on the case. On the opposite side of the case, exactly opposite the charge of the explosive explosive devices, the initiating means are placed - electric detonators, called the outdated term "electric fuses" (in accordance with the "Terminology of electric blasting" recommended by the Interdepartmental Commission for Explosive Affairs (1976), the term is not allowed to be used). To move the piston with a safety flap to the starting position (circuit closure of electric detonators-detonators-charge of explosive devices), a bellows actuator with a pyrotechnic element is installed in its end part. Self-liquidator works as follows. When the target is separated from the carrier aircraft, the on-board power system supplies inrush current to the bellows drive. The gaseous products of combustion of the pyrotechnic element or the powder charge fill the bellows and stretch it, overcoming the resistance of the holding coil spring, move the piston with a shutter and set the detonators strictly in the gap between the electric detonators and the charge of explosive devices. In this case, the detonation circuit is closed. As a result of plastic deformation of the bellows (when stretching it), the piston is held in the starting position.

When an electric signal is applied to electric detonators, the latter are triggered, detonators are initiated, and the latter transmit a detonation pulse to the charge of the explosive detonators and undermine it.

This known device is the closest to the proposed by the number of similar features and the problem to be solved, and is taken as a prototype.

In this known device, in comparison with the previous ones, a reduction in weight and size characteristics and energy consumption is achieved due to the absence of electric motors (solenoids, electromagnets), inertial mechanisms, cam, gear mechanisms, pushing rods, gearboxes, a certain increase in reliability is also achieved by replacing the tape spring with a cylindrical twisted , and a blocking rotating rotor on a piston with translational motion. A disadvantage of the known closest to the proposed device is the difficulty in providing a given high level of reliability due to the use of a pyrotechnic bellows drive in its design. It is very difficult to ensure uniform operation of the bellows (moving to the same length with the same developmental effort) even in one batch and even when using technically pure compressed gas from the same source (cylinder, for example) as a working fluid. The reason for this lies in significant variations in the physicomechanical parameters of the material of the bellows and in the permissible deviations of the thickness of its wall.

In addition to this, the source of the working fluid for the bellows is the combustion products of the pyrotechnic composition (or powder charge), for which indicators such as combustion rate, composition of the combustion products, volume of gaseous products, and their pressure strongly depend on environmental parameters (mainly, pressure and temperature).

A detonation circuit built in one line (electric detonators-detonators-charge BVV) necessitates the use of an additional unit in the device design - a safety shutter.

The shape of the piston (flattened cylinder) and, accordingly, the holes inside the housing require application in the manufacture of expensive and inefficient milling operations.

In addition, the known closest to the proposed device is disposable; repeated, or even repeated, use of any components and parts is excluded due to the complete destruction of the device when it is triggered.

The technical solution according to the invention is aimed at achieving a technical result, which consists in eliminating the above disadvantages, namely:

- to increase the reliability of the device;

- in achieving the versatility of the device in relation to aircraft of any classes, in maintaining operability in any areas of their flights (trajectories), regardless of environmental parameters and disturbances;

- in reducing the cost and improving the manufacturability of the device;

- the possibility of reuse of the main components and parts of the device.

To achieve the technical result, the device according to the invention, like the above known closest to it, contains a housing with a through hole in which a piston with a transfer charge detonator (in the closest known two of them; called detonators) is mounted, twisted spring, electric detonator (in the closest known there are two; the name is given outdated - electric fuses).

Unlike the closest known in the device according to the invention, the housing has an internal cavity - a through hole of a cylindrical shape of one (constant) diameter along the entire length of the housing. On both ends of the case there are threaded connections; on the one hand, with a clamping cap, which serves for a preloaded cylindrical spring; on the other hand, with an end cap restricting the stroke of the piston. On the outer side of the housing, tides are placed on its lateral surface, in one of which two adjacent cavities with threaded seats for the electric detonator and for the end element of the charge-translator of detonation commands are made. At another tide, a detonation check is mounted, the latch of which in the initial state of the device is inserted into the through holes in the walls of the housing and piston and keeps the latter from spontaneous movement. The piston of the device has a cylindrical shape and is made in the same diameter as the hole inside the housing. On the side surface of the piston, annular compression grooves are made. At one end, the piston has a closed (blind) cavity with a cylindrical coil spring located in it and a compressed clamping cover. The transfer charge detonator located in the piston has a U-shape and is made in the form of two radial channels interconnected by an axial channel. An explosive compound (explosive composition) is pressed into the channels (or filled). The distance between the radial channels of the transfer charge-detonator corresponds to the distance between the electric detonator and the charge-translator of the detonation commands. This form of transfer charge eliminates the safety flap mounted on the piston.

The transfer charge detonator is equipped with end amplification charges, which are small press-ins (or fillings) of the explosive composition (or composition) with higher explosive and technical characteristics than the main transfer charge detonator. This allows the use of relatively low explosive compositions (or compositions) for the equipment of the latter, upon detonation of which the piston itself and the device body remain intact. For repeated use of the device, re-equipping of the transfer charge-detonator and replacement of the electric detonator, charge-translator of detonation commands and detonation checks (which, by the way, also provides for multiple re-equipping) are required.

Placing a coil spring compressed in the piston cavity during assembly of the device by the pressure cap allows using the energy of the compressed spring to move the piston in order to close the detonation circuit, while eliminating the pyrotechnic bellows drive.

Placing a threaded end plug in the device’s housing allows you to limit (control) the piston stroke and precisely set it to a position in which the radial channels of the transfer charge-detonator will be combined with the electric detonator and the charge-translator of detonation commands.

Placing detonation checks on the device’s body allows you to quickly and reliably remove the mechanical connection between the body and the piston.

The use in the design of the device components and pyroautomatics equipped only with explosives (compositions) and explosive compositions, the rejection of gunpowder, pyrotechnic compositions eliminates the influence of environmental parameters and disturbances on the stability (uniformity) of the device. Thus, the considered features contribute to improving the reliability of the device, achieving the versatility of the device in relation to aircraft of any classes, maintaining operability in any areas of their flights (trajectories) regardless of environmental parameters and disturbances, lowering costs, and improving the manufacturability of individual units and parts , and the device as a whole, as well as the possibility of its repeated use for a series of tests.

The invention is illustrated in the drawing, which shows an example of a device explaining the essence of the proposed solution, where:

1 - housing;

2 - the piston;

3 - detonation check;

4 - coil spring;

5 - pressure cap;

6 - a clamp;

7 - transfer charge detonator;

8 - terminal amplification charge;

9 - end cap;

10 - electric detonator;

11 - charge-translator of detonation commands.

The above device operates as follows. When a command (electric signal) is supplied from the on-board control system by a sequence diagram or remotely from the Earth (or air) to the detonation check initiation device 3, it is triggered, as a result of which the latch 6 is sunk into the check case and disengages from the piston 2. Under the action the force of the coil spring 4 the piston 2 is moved all the way into the end cap 9. The spring 4 at this position of the piston 2 remains in a pressed state and does not allow the piston to spontaneously move in the opposite direction ui. The radial channels of the transfer charge-detonator 7 were set strictly against the electric detonator 10 and the charge-translator of the detonation commands 11. The device closed the detonation circuit (in the starting position or in the cocked state). When an electric pulse is applied to the incandescent bridges of the detonator 10, the latter is triggered and initiates the detonation of the transfer charge-detonator 7. The detonation pulse, amplified by the end amplification charge 8, excites detonation in the charge-translator of detonation commands 11, through which it is transmitted to the multiplier (splitter) of detonation commands, and from it - bridgeless actuators (burst bolts, knock locks, push rods, checks, etc.).

The reliability of the device in terms of guaranteed non-closure of the detonation circuit during the passage of false commands, exposure to spurious signals of both natural and man-made nature is confirmed by the following circumstances. When a false (spurious) signal arrives at the electric detonator 10, it can trigger into the piston volume, since the detonation pin 3 did not work, and the latch 6 reliably holds the piston 2 in its original position. The detonation circuit is open.

If a false (spurious) signal arrives at the means for initiating detonation checks 3 (similar to a bridge type electric detonator or electric detonating device - EDU), it can also trigger. It will activate check 3; the retainer 6 disengages from the piston 2; the latter as a result of its movement will close the detonation chain. But since in this situation the command for the operation of the electric detonator 10 will not follow from the control system, the circuit will remain closed, but detonation will not follow. And finally, the third case, in which a false (spurious) signal was received by both electric detonators: pos.10 and pos.3. In this case, they will work almost instantly and simultaneously (the time and the spread of the response time of the bridge electric detonators and EDU used in the on-board pyroautomatics is tens of microseconds). During this period of time, the piston 2 will not have time to move to the starting position and close the detonation circuit. The total time from the supply of an electric signal to the detonation pin to the installation of the piston 2 in the starting position (cocking time of the device) is tenths of a second or even several seconds.

Information sources

1. Means of destruction and ammunition: Textbook / A.V. Babkin, V.A. Veldanov, E.F. Gryaznov and others. Under the general. ed. V.V. Selivanova. - M.: Publishing House of MSTU. N.E. Bauman, 2008 .-- S.843-953.

2. Kozlov V.I. Design features of explosive devices for ammunition of the barrel artillery // URL: http: //technomag.http: //edu.ru/doc/452053.htm [Electronic resource], (accessed 08.08.2012).

3. Auxiliary systems of rocket and space technology / Ed. I.V. Tishunina. - M.: Mir Publishing House, 1970. - S.185-215.

4. Zagarskikh V.I. Explosives and pyroautomatics: Textbook. allowance. Part 2. M .: MO RF, 2011.

Claims (2)

1. A device for protecting detonation circuits of on-board automation of aircraft, including a housing with a through hole and a piston installed in it, in the body of which there is a channel with a transfer charge-detonator pressed into it and / or embedded in it, a coil coil spring and an electric detonator mounted in the device’s body characterized in that the housing has a through hole of a cylindrical shape of constant diameter along the entire length of the housing with an installed piston, and on the outer wall of the housing in one of the tides The electric detonator and the end device of the charge-translator of detonation commands are placed, a detonation check is installed on another tide, the latch of which is inserted into the holes in the walls of the body and piston in the place of a closed cavity formed by cylindrical blind axial drilling made in the piston and the pressure cap, which is previously placed compressed spring; the transfer charge-detonator has a U-shape and is made in the form of two radial channels and an axial channel connecting them, and the distance between the radial channels corresponds to the distance between the electric detonator and the end element of the charge-translator. 2. The device according to claim 1, characterized in that the transfer charge-detonator is equipped with end amplifying charges made of explosive composition and / or explosive composition with increased initiating ability and susceptibility to detonation.