RU2703580C1 - Aviation detonating fuze - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to fuses of free fall aerial bombs (AB) and is intended for safe operation and application of AB. It can be used for formation of cocking command of aircraft fuse on the basis of physical factors arising after separation of AB from carrier and when it is in free fall. Device comprises a housing with an electric trigger consisting of a contact assembly for connection to a power supply of the carrier, a conductive bundle and an electrical filter connected to the input of the power supply, a magnetometer unit, magnetic induction module calculation unit, angular position calculation unit, magnetic induction gradient calculation unit, cocking command generation unit, safety-actuating mechanism and target sensor. Output of the magnetometer unit is connected to the inputs of the magnetic induction module calculation unit, the angular position calculation unit, the magnetic induction gradient calculation unit, which outputs are connected to the cocking command generation unit connected to the safety-actuating mechanism, the actuating input of which is connected to the target sensor output.

EFFECT: higher safety of AB operation and use.

1 cl, 1 dwg

Description

The invention relates to technical devices that provide for the activation of free-fall aircraft bombs (AB), in particular to aircraft fuses.

Known aircraft fuses with electric starting devices ("Aircraft ammunition" edited by V.A. Kuznetsov, publication "VVIA named after prof. N.E. Zhukovsky", 1968, p. 382), consisting of an electric igniter and a conductive tourniquet. When the battery is separated from the aircraft, a current pulse is supplied to the electric igniter through a conductive bundle from the aircraft power source, which leads to the operation of the electric igniter and the launch of the pyrotechnic long-range cocking mechanism.

The disadvantage of this technical solution is the low safety of the fuse in conditions of exposure to electromagnetic fields of high power due to the possible operation of the electric igniter from induced currents, which requires the introduction of an additional stage of fuse protection.

Known aircraft fuse (patent RU No. 2399869 publ. 20.03.2010, IPC F42C 14/16) containing a metal casing with an electric starting device consisting of a conductive tourniquet with a contact node, a cocking unit with an electric igniter, an electric filter connecting an electric igniter and a conductive tourniquet .

Known aircraft fuse (patent RU No. 2592934, publ. 06/27/2016, IPC F42C 14/16), comprising a housing, a cocking unit with an electric igniter and a moderator, an electric harness with a contact node, an electric filter connected between the electric harness and the electric igniter.

The safety of operation of these fuses when exposed to electromagnetic fields is ensured by the presence of an electric filter connected between the electric harness and the electric igniter.

The disadvantage of these fuses is the possibility of their arbitrary cocking in case of accidental disruption from the bomb holder and applying an electric current pulse to the contact node, causing the electric igniter to fire and, accordingly, the irreversible cocking of the fuse, precluding its further use.

The objective of the invention is to increase the safety of operation and use of the fuse, including as part of the battery.

The technical result of the invention is to prevent uncontrolled cocking of the fuse and to increase the safety of operation and use of batteries.

The problem is solved due to the fact that the aircraft fuse contains a housing with an electric starting device, consisting of a contact node for connecting to the power source of the carrier, conductive harness and an electric filter connected to the input start of the power source, magnetometer unit, angular position calculation unit, unit magnetic induction module calculation, magnetic induction gradient calculation unit, cocking command formation unit, safety-actuator and target sensor, p and the output of the magnetometer unit is connected to the inputs of the calculation unit of the magnetic induction module unit calculating the angular position and calculation unit of the magnetic induction gradient, the outputs of which are connected to the block forming arming command, connected to the slam-actuator executive input of which is connected to the output target sensor.

The introduction of the magnetometer block, the magnetic induction module calculation unit, the angular position calculation unit, and the magnetic induction gradient calculation unit into the aircraft fuse makes it possible to register the following physical factors that occur after the battery is separated from the carrier:

- reduction of the magnetic induction module after separation of the battery from the magnetic mass of the carrier;

- a change in the angle between the longitudinal axis of the AB and the induction vector of the Earth's magnetic field in the process of free fall of the AB;

- the presence of the gradient of the magnetic field of the Earth when AB approaches the earth's surface.

The introduction of a cocking team formation unit into an aircraft fuse ensures that the PIM is cocked in the presence of the three listed physical factors. Thus, the introduction of an additional AB protection stage is ensured, based on a physical principle that is different from the principle implemented with an electric starting device.

The invention is illustrated in the drawing, which shows a structural diagram of an aircraft fuse.

In the drawing are indicated:

1 - contact node;

2 - conductive harness;

3 - electric filter;

4 - power source;

5 - block magnetometers;

6 - block calculation module of the magnetic induction;

7 - block calculating the angular position;

8 - block calculation of the gradient of magnetic induction;

9 - block formation team cocking;

10 - safety-actuating mechanism;

11 - target sensor.

Works aircraft fuse as follows. At the time of separation of the battery from the carrier, a current pulse from the carrier's power source is supplied to the contact node 1. Through a conductive tourniquet 2 and an electric filter 3, a current pulse is supplied to the start input of the power source 4.

Further, using the magnetometer unit 5 and the calculation unit of the magnetic induction module 6, a decrease in the magnitude of the magnetic induction module relative to its initial value is recorded until it is separated from the carrier. In this case, an electric signal is input to the input of the cocking team formation unit 9.

Then, using the block for calculating the angular position 7, the initial value of the angle between the longitudinal axis AB and the induction vector of the Earth's magnetic field is determined. When the specified angle changes during the free fall of the battery relative to its initial value, a second electrical signal is supplied to the cocking command generation unit 9.

In the presence of the gradient of the magnetic field induction of the Earth, perceived by the magnetometer unit 5 with a free fall of AB and its approach to the earth's surface, a third electrical signal is received from the magnetic induction gradient calculation unit 8 to the cocking command generation unit 9.

After the arrival of the sequence of the three indicated signals, the cocking command generation unit 9 cockes the safety-executive mechanism 10. Upon receipt of the executive command from the target sensor 11, the safety-executive mechanism 10 is triggered and the battery is undermined.

The proposed technical solution allows introducing an additional fuse protection stage based on the principle of magnetometry in addition to the electric principle and eliminates its charging in the event of an accidental disruption from the bomb holder and the supply of an electric current pulse to the fuse's electric starting device.

The technical result of the invention is the prevention of uncontrolled cocking of the fuse and improving the safety of operation and use of batteries.

Claims (1)

An aircraft fuse, characterized in that it comprises a housing with an electric starting device, consisting of a contact node for connecting a carrier, a conductive cable and an electric filter connected to the starting input of the power source, a magnetometer unit, an angular position calculation unit, a magnetic module calculation unit induction, magnetic induction gradient calculation unit, cocking command generation unit, safety-executive mechanism and target sensor, while the output of the unit magnetometers are connected to the inputs of the magnetic induction module calculation unit, the angular position calculation unit, and the magnetic induction gradient calculation unit, the outputs of which are connected to the cocking command generation unit connected to the safety-executive mechanism, the executive input of which is connected to the output of the target sensor.

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