RU2818146C1 - Pyrotechnic cartridges ejection device - Google Patents

Abstract

FIELD: military equipment.

SUBSTANCE: invention relates to military equipment and can be used to protect aircraft (AC) from guided missiles. Device for ejection of pyrotechnic cartridges contains housing and contact modules installed on it and assemblies of attachment to AC frame. Housing is rigidly fixed on the AC and has a semi-circular box shape. On its curvilinear surface there are guides with locking rings. Attachment assemblies of additional ejection devices are installed on the housing, and inside the housing there is an electronic module for generating a pulse for actuation of pyrotechnic cartridges, which receives signals from computing devices of the on-board complex of AC, with three outputs. Increased reliability of the device for ejection of pyrotechnic cartridges is achieved due to exclusion of mechanisms ensuring rotation of the housing of the device in the direction of flight of the attacking missile.

EFFECT: higher efficiency of AC protection against guided missiles by ensuring that the required type of pyrotechnic cartridges is fired in the direction of flight of the attacking missile.

1 cl, 2 dwg

Description

The invention relates to the field of military technology and can be used to protect an aircraft from guided missiles.

The closest in technical essence to the claimed invention is a passive interference emission device, which contains a box-shaped body with attachment points for replaceable cassettes and a contact module for triggering pyrotechnic cartridges. The body is installed in a frame with the possibility of rotation in one plane, and the frame is connected to the fuselage of the aircraft with the possibility of rotation in a plane perpendicular to the plane of rotation of the body. Additionally, housing and frame rotation angle sensors, housing and frame rotation mechanisms, as well as a control unit have been introduced. The outputs of the housing and frame rotation angle sensors are connected to the first and second inputs of the control unit, respectively, the first and second outputs of the control unit are connected to the housing and frame rotation mechanisms, respectively, and the third output is connected to the input of the contact module. [Patent RU No. 2664254 C1, IPC F41H 11/02, F41G 3/22, F41B 4/00, 05/27/2017].

The disadvantage of this device is the low efficiency of protecting the defended aircraft from guided missiles and a decrease in the reliability of the ejection device itself due to the need to rotate the body of the device to ensure the shooting of pyrotechnic cartridges into the target area of space, which entails an increase in the response time of the ejection device to a threat in the form of high-speed guided missiles, and the use of gear motors, potentiometric sensors for determining the angle of rotation and a control unit, respectively, as a mechanism for rotating the body of the device.

From the RF patent No. 2517549 C1, MPK F41H 1/02, 03/05/2013, a technical solution is known relating to a passive interference emission device, which contains a box-shaped housing rigidly mounted on the aircraft with an electronic pulse generation module installed on it for triggering interference cartridges and attachment points for replaceable cassettes, an electrical impulse transmission device for triggering jammer cartridges, guide devices for jammer cartridges. The device for transmitting an electrical impulse for triggering jamming cartridges is made in the form of a set of replaceable contact modules with contact units containing three spring-loaded contacts and providing electromechanical contact with the corresponding jamming cartridge, while the number and location of each contact node in the replaceable contact module corresponds to the number and location of jamming cartridges in a replaceable cassette.

From US patent No. 4063485, IPC F41F 3/00, 1966, a technical solution is known relating to a jamming system for protecting aircraft from homing missiles, containing, in particular, a unit for ejecting pyrotechnic charges that create passive interference. The specified block includes a load-bearing beam made in the form of a body electrically connected to the side of the aircraft; the housing is divided into sections equipped with an electrical means for igniting the charge and guides, with each section designed to accommodate a multi-charged replaceable cassette with the possibility of removal, containing installation places for placing charges in them, and the installation places are made in the form of guide launch tubes.

From US patent No. 5400690, IPC F41F 3/042, 1994, a technical solution is known relating to a multi-charge receiver of pyrotechnic cartridges, which is a housing with slots for placing pyrotechnic cartridges, in which pyrotechnic units are mounted and electrical ignition devices are placed.

From the RF patent No. 99610, MPK F41H 11/02, 2010, a technical solution is known relating to the ejection unit, which is designed for comprehensive protection of aircraft from guided missiles in passive jamming devices, the principle of operation of which is based on the shooting of jamming cartridges that create directional jamming interference for homing missiles in order to “blind” them and divert them from the trajectory of destruction of the aircraft. The said ejection unit contains a box-shaped body rigidly fixed to the aircraft, a removable cassette installed in the body, made in the form of a frame, while the mounting locations for jamming cartridges in the cassette are formed by the walls of holes made in the upper and bottom parts of the cassette, respectively, and forming guides for jamming cartridges, cartridge clamps relative to the body. The means for supplying a pulse for triggering the jamming cartridge is made in the form of a contact group located on the lower part of the housing and interacting with the electronic pulse distributor, each contact of which is spring-loaded and interacts with the corresponding jamming cartridge, while the cassette is completely placed inside the beam.

All of the above devices have a housing, replaceable cassettes for loading pyrotechnic cartridges into them, and devices for transmitting an electrical impulse for firing (shooting) pyrotechnic cartridges. In this case, all axes of the barrels in the cassettes are directed in one direction and perpendicular to the base of the cassette and the body of the device.

The technical result of the invention is to increase the efficiency of protecting an aircraft from guided missiles by ensuring that the required type of pyrotechnic cartridges is fired in the direction of flight of the attacking missile. Increased reliability of the device for ejecting pyrotechnic cartridges is achieved by eliminating the mechanisms that ensure the rotation of the device body in the direction of flight of the attacking missile.

Figure 1 shows a drawing explaining the essence of the invention, where 1 - housing, 2 - guide devices, 3 - contact modules, 4 - retaining rings, 5 - electronic pulse generation module, 6 - attachment points to the aircraft frame, 7 - attachment points additional ejection devices. Figure 2 shows a block diagram of the invention, where 3 - contact modules, 5 - electronic pulse generation module, 8 - aircraft power supply system, 9 - control panel, 10 - multiplex data transmission channel, 11 - blocking unit and checks, 12 - computing devices of the on-board defense complex of the aircraft, 13 - pyrotechnic cartridges.

The ejection device for pyrotechnic cartridges consists of a semicircular box-shaped body 1, guide devices 2 (32 pieces) located on the curved surface of the body 1, attachment points to the aircraft frame 6 and attachment points for additional ejection devices 7. The guide devices 2 are designed as barrels and have locking rings 4 and contact modules 3. Contact modules 3 are electromechanical and serve to determine the type of pyrotechnic cartridges 13 and their operation. The guide devices 2 are permanently connected to the body 1, as a result of which the charging/discharging of pyrotechnic cartridges 13 is carried out from the outside of the guide devices 2 with fixation by means of retaining rings 4 located at the base of the guide devices 2. On the body 1 there are attachment points to the frame of the aircraft 6 and attachment points for additional ejection devices 7, allowing to increase the consumable ammunition of pyrotechnic cartridges 13. The housing 1 contains an electronic pulse generation module 5. Its first output is connected to the power supply system of the aircraft 8. The second output of the electronic pulse generation module 5 is connected to the control panel 9 located in the cockpit of the aircraft, through a multi-complex data transmission channel 10. The third output of the electronic pulse generation module is connected to the blocking and check block 11.

The pyrotechnic cartridge ejection device operates as follows. Before turning on the device for ejecting pyrotechnic cartridges, pyrotechnic cartridges 13 of the required type and quantity are inserted into the guide devices 2 and are fixed with retaining rings 4. When the device for ejecting pyrotechnic cartridges is turned on, power is supplied from the power supply system of the aircraft 8 to the control panel 9 and the electronic pulse generation module 5. Electronic The pulse generation module 5, through contact modules 3, polls the presence and type of pyrotechnic cartridges 13 located in each guide device 2. The received information is transmitted via a multiplex data transmission channel 10 to the control panel 9. After this, power is supplied from the power supply system of the aircraft 8 to blocking block and checks 11. The latter transmits to the electronic pulse generation module 5 information about the presence/absence of blocking that prevents the shooting of pyrotechnic cartridges 13. The on-board defense complex of the aircraft detects an attacking guided missile and, based on the parameters of the rocket’s movement, calculates the direction and time of shooting of pyrotechnic cartridges 13 to ensure the destruction (disruption of an attack) of the missile. From the computing devices of the on-board defense complex of the aircraft 12, signals are received about the type of pyrotechnic cartridges 13, the direction and time of their shooting to the control panel 9. Next, the control panel 9 sends to the electronic pulse generation module 5 a command to shoot the required number of pyrotechnic cartridges 13 from the guide devices 2 to ensure the destruction (disruption of an attack) of the missile. Next, the electronic pulse generation module 5 supplies the contact modules 3 with power voltage to fire pyrotechnic cartridges 13 into the calculated area of space. List of used literature:

1. Patent of the Russian Federation No. 2664254 “Device for ejecting pyrotechnic cartridges”, priority date 07/25/2017, IPC F41H 11/02, F41G 3/22, F41B 4/00;

2. Patent of the Russian Federation No. 2517549 “Passive interference emission device”, priority date 03/05/2013, IPC F41H 1/02;

3. US patent No. 4063485 “Launcher that creates a decoy target”, priority date 12/12/1966, IPC F41F 3/00, 1977;

4. US patent No. 5400690 “Multiple charge pyrotechnic cartridges and related ammunition”, priority date 06/05/1992, IPC F41F 3/042, 1994;

5. Patent of the Russian Federation No. 99610 “Ejection unit”, priority date 06.16.2010, IPC F41H 11/02, 2010.

Claims (1)

A device for ejecting pyrotechnic cartridges, containing a housing and contact modules installed on it and attachment points to the frame of the aircraft, characterized in that the housing is rigidly fixed to the aircraft and has a semicircular box-shaped shape; guide devices with locking rings are installed on its curved surface; Also on the body there are mounting points for additional ejection devices, and inside the body there is an electronic pulse generation module for triggering pyrotechnic cartridges, receiving signals from the computing devices of the on-board complex of the aircraft, with three outputs: the first output is connected to the power supply system of the aircraft, the second output is via a multiplex The data transmission channel is connected to the control panel located in the cabin of the aircraft, and the third output is connected to the blocking and check block.