RU2759356C1 - Air-to-air missile to protect hypersonic aircraft from enemy missiles - Google Patents

Abstract

FIELD: aerospace technologies.SUBSTANCE: invention relates to air-to-air missile traps and can be used to protect a hypersonic aircraft from surface-to-air missiles from air defense systems or air-to-air missiles from enemy fighters. The air-to-air missile to protect a hypersonic aircraft from enemy missiles consists of three parts connected to each other by power partitions, namely, the front aluminum casing of the body with the possibility of its destruction, the middle part of the body of the electronic control unit of the rocket, as well as a solid-fuel rocket engine (SFRE) with gas-dynamic control and side-turn engines (STE). The front aluminum part of the casing has a front-mounted video camera, and the rear part of the housing is attached to a gas generator located in an aluminum housing. In the front aluminum casing of the hull, pods are laid, made of non-combustible material and tightly attached to an air duct having holes along the entire length of the duct pipe and attached to the aluminum body of the gas generator with powder cartridges placed inside it, for each of which detonators are installed.EFFECT: possibility of effective protection of a hypersonic aircraft from surface-to-air missiles from air defense systems or air-to-air missiles from enemy fighters.4 cl, 11 dwg

Description

The invention relates to trap missiles of the air-to-air class, and can be used to protect a hypersonic aircraft from surface-to-air missiles from air defense systems or air-to-air missiles from enemy fighters.

Prior art technologies for defense against surface-to-air missiles typically use infrared sensors to detect the missiles when creating heat traps.

The problem with infrared sensors is that they are very sensitive to various natural disturbances. For example, heated air easily leads to false alarms.

Traps for missiles using ultraviolet sensors eliminate these disadvantages (see: [https://iz.ru/908099/aleksei-ramm-aleksei-kozachenko-bogdan-stepovoi/teplovoi-udar-il-76-poluchat-novye-protivoraketnye -sistemy], publ .: 11.08.2019.

The technical problem of heat traps for missiles is the effectiveness of their use mainly against enemy MANPADS, while against missiles of the enemy's air defense system, they are usually ineffective.

In addition, hypersonic aircraft usually fly at high altitudes that missiles fired from enemy MANPADS cannot reach.

Thus, the only significant threat to hypersonic aircraft are missiles of enemy air defense systems with the ability to defeat at altitudes of 10 km or air-to-air missiles of enemy fighters.

The claimed invention has no analogues.

The objective of the invention is to eliminate the specified technical problem.

The technical result of the invention is the ability to effectively protect a hypersonic aircraft from surface-to-air missiles from air defense systems or air-to-air missiles from enemy fighters.

The specified technical result is achieved due to the fact that the declared air-to-air missile to protect a hypersonic aircraft from enemy missiles, consisting of three parts connected to each other by power partitions, namely, the front aluminum shell of the hull with the possibility of its destruction, the middle part housings of an electronic missile control unit, as well as a solid-propellant rocket engine (TTRD) with gas-dynamic control and side turn engines (DBR); the front aluminum part of the body skin has a front-mounted video camera, and the rear part of the body is attached to a gas generator located in the aluminum body; In the front aluminum casing of the casing there are nacelles made of non-combustible material and tightly attached to the duct having holes along the entire length of the duct pipe and attached to the aluminum casing of the gas generator with pyrotechnical cartridges placed inside it, for each of which detonators are installed.

Preferably, the electronic missile control unit contains an ultrashort wavelength antenna, a high frequency amplifier (UHF) unit, a video signal generation unit connected to a video camera, a signal generation unit for a false control system of a hypersonic aircraft, which has a connection with a metal coating inside the nacelles formed by sputtering.

Preferably, the electronic missile control unit additionally comprises: a power unit for controlling detonators located in the gas generator of the front aluminum casing of the body, detonators that activate the operation of the TTRD, detonators that activate the gas-dynamic missile control system in the DBR.

Preferably, the TTRD contains a gas-dynamic rocket control system, namely: a DBR, consisting of a gas-dynamic turn of the rocket nozzle, as well as pipelines connecting to the nozzle check valves, which are connected by pipelines with cylinders filled with solid fuel to control the rocket, and detonators are located inside the cylinders for bringing into operation the gas-dynamic missile control system.

Brief Description of Drawings

FIG. 1 shows a general view of an air-to-air missile.

FIG. 2 shows an example of attaching air-to-air missiles to a hypersonic aircraft (bottom view).

FIG. 3 shows an example of attaching air-to-air missiles to a hypersonic aircraft (top view in hypersonic mode).

FIG. 4 shows an example of attaching air-to-air missiles to a hypersonic aircraft (side view in hypersonic mode).

FIG. 5 shows an example of an air-to-air missile release mode from a hypersonic aircraft (side view in hypersonic mode).

FIG. 6 shows an example of a hypersonic aircraft in a surface-to-air missile defense mode (side view).

FIG. 7 shows a longitudinal section of an air-to-air missile.

FIG. 8 shows a longitudinal section of an air-to-air missile gas generator.

FIG. 9 is a cross-sectional view of an air-to-air missile gas generator.

FIG. 10 shows a longitudinal section of a side turn engine of a gas dynamic control system.

FIG. 11 is a bottom view of an air-to-air missile.

In the drawings: 1 - rocket, 2 - front aluminum hull plating, 3 - electronic missile control unit, 4 - solid-propellant rocket engine (TTRD), 5 - side turn engines of the gas-dynamic control system, 6 - video camera, 7 - missile stop, 8 - the front tapered part of the skin, 9 - the slot of the front tapered part of the skin, 10 - the aircraft fuselage, 11 - the fairing, 12 - the holes in the front aluminum skin of the rocket body, 13 - the slot of the tapered part of the skin, 14 - the rear tapered part of the skin, 15 - the gas generator, 16 - nacelle, 17 - gas generator air duct, 18 - opening on the air duct pipe, 19 - gas generator pyrotechnics, 20 - steel cylinders for stacking pyro cartridges in the gas generator housing, 21 - lower aluminum part of the gas generator housing, 22 - gas generator detonators, 23 - power partitions between the front aluminum casing and electronic unit, 24 - VHF antenna of the rocket electronic unit, 25 - gas detonators dynamic rocket control system, 26 - power partitions between the electronic unit and the TTRD, 27 - TTRD air duct, 28 - TTRD nozzle, 29 - gas diffuser in the TTRD nozzle, 30 - nozzle of the gas-dynamic rocket control system, 31 - pipelines connecting the nozzle with the check valve , 32 - check valve of the side turn engine, 33 - pipeline connecting the check valve with the cylinder, 34 - cylinder of the side turn engine, 35 - aircraft radar station (radar), 36 - video camera, 37 - aircraft cockpit, 38 - enemy ground missile -air ", 39 - aircraft air duct, 40 - guide blades of the air duct, 41 - mechanism of rotation of aircraft grips, 42 - grips of the rear part of the air-to-air missile body.

Implementation of the invention

The declared rocket 1 consists of three parts, namely, the front aluminum skin of the body 2 with the possibility of its destruction, the middle part of the body of the electronic control unit 3 of the rocket control, as well as the solid-propellant rocket engine 4 (TTRD), with gas-dynamic control of the rocket, side turn engines 5 ( DBR). The front aluminum part of the hull skin 2 has a front-mounted video camera 6 on the stop 7 of the front cone-shaped part 8, which has a slot 9 for breaking the front aluminum skin of the hull 2 by means of the stop 7. The front aluminum skin of the rocket body 2 is fixed on the fuselage 10 of the hypersonic aircraft with fairing 11. Front the aluminum skin of the rocket body 2 is fixed by the front cone-shaped part 8, which has a slot 9.

On the front skin of the body 2 there are holes 12 along the entire surface of its body 2, which serve to destroy the aluminum skin.

The other part of the front aluminum skin of the body 2 is attached by a slot 13 to the rear tapered part of the body 14. The slot 13 is necessary to destroy the front aluminum skin of the rocket body 2. The rear conical part 14 of the body 2 is attached to the gas generator 15, which is located in the aluminum body of the rocket 1.

In the front aluminum skin of the rocket body 2, where the holes 12 are located, gondolas 16 made of non-combustible material are compactly laid. The nacelles 16 are tightly attached to the duct 17 having holes 18 along the entire length of the duct pipe 17 for filling the stacked nacelles 16 with gas.

The air duct 17 is attached to the aluminum body of the gas generator 15, which has inside the pyrotechnical cartridges 19, which are installed in the steel cylinders 20. In the lower aluminum part 21 there are detonators 22 for each pyrotechnic cartridge 19. To operate the gas generator 15, the aluminum body 2 of the rocket 1 is connected by power partitions 23 with the middle part of the body, where the electronic missile control unit 3 and the VHF antenna 24 are located. The power partitions 23 are made intersecting with each other, forming a lattice through the holes of which the propellant gases from the triggered squibs 19 can escape freely. This prevents the electronic boards of the electronic control unit 3 from failing in the event of detonators 22 triggering the squib 19 of the gas generator 15 , since the products of combustion of propellants in the pyrotechnic cartridges 19 create an increase in the temperature of the aluminum body of the gas generator 15, heating it strongly. This can melt the electronic boards of the electronic control unit 3. But the propellant gases escaping through the lattice of the power partitions 23 do not allow the gas generator 15 body to overheat too much.

The missile control electronic unit 3 contains: an antenna 24 of the ultrashort wave range (VHF range), a high frequency amplifier unit (UHF), a video signal generation unit connected to a video camera 6 located in front of the stop 7 of the front cone-shaped part 8, a signal generation unit for a false control system a hypersonic aircraft having a connection with a metal coating inside the nacelles 16, formed, for example, by spraying. The electronic rocket control unit 3 also contains: a power unit for controlling detonators 22 located in the gas generator 15 of the front aluminum skin of the housing 2, detonators (not shown in the drawings), which drive the main solid-propellant rocket engine (TTRD) 4, detonators 25, leading to operation of the gas-dynamic rocket control system 1 in lateral turn engines (DBR) 5.

The electronic components of the electronic control unit 3 are connected by power partitions 26 to the TTRD 4 housing. Power partitions 26 are made intersecting with each other, forming a lattice through the holes of which the combustion products of the TTRD 4 fuel can freely come out.

This makes it possible to prevent the failure of the electronic boards of the electronic control unit 3 during the operation of the TTRD 4, since the combustion products formed during its operation create a temperature rise that can melt the electronic boards of the electronic control unit 3. But, the combustion products leaving through the lattice of the power partitions 26, do not allow the electronic control unit to overheat too much 3.

TTRD 4 has an air duct 27 connected to the rocket nozzle 28, inside which is a diffuser 29 of combustion gases of the TTRD 4 fuel. Diffuser 29 evenly distributes the flow of combustion gases over the inner surface of the rocket nozzle 28, and also prolongs the operation time of the TTRD 4.

The TTRD 4 includes a gas-dynamic rocket control system 1, namely: a side-turn engine 5, consisting of a nozzle 30 for a gas-dynamic turn of a rocket, as well as pipelines 31 connecting check valves 32 with a nozzle 30. Check valves 32 are connected by pipelines 33 with cylinders 34 filled solid fuel for rocket control 1.

Detonators 25 are located inside the cylinders 34 for operating the gas-dynamic missile control system 1.

The principle of operation of an air-to-air missile to protect a hypersonic aircraft is as follows.

The hypersonic aircraft, while in flight over the enemy's zone, has the included radar 35 devices, 36 high-definition video cameras. In the pilot's cockpit 37, the enemy missile 38 detected by the radar 35 35 (for example, a surface-to-air missile fired by an air defense system or an air-to-air missile fired from an enemy fighter) is recorded on the monitor by video cameras 36.

The pilot, being in the cabin 37 of the hypersonic aircraft, dampens the speed of the turbojet engines, turns on the reverse, which lifts up the air duct 39 with guide vanes 40, which direct the exhaust gas in the opposite direction.

The hypersonic aircraft hovers in this way in the air, and the pilot sends a signal to the onboard digital computer (BTsVM) to destroy the enemy missile 38.

The on-board computer gives a signal to the power control unit for uncoupling the holding grips of the air-to-air missile 1 on the fuselage 10 of the aircraft, at the same time activates the electronic control unit 3 for the missile 1.

The front fairing 11 starts to work, moving forward horizontally of the aircraft fuselage 10, unhooking the front aluminum skin of the rocket body 2. 90 ° relative to the horizontal plane of the fuselage 10. After that, the command goes to decoupling by grippers 42 missiles 1.

The on-board computer gives a signal to the electronic control unit 3 of the missile 1, which directs the missile into the air zone of the enemy missile 38. After the video camera 6 of the missile 1 captures the image of the enemy missile 38, the signal from the video camera 6 goes to the video signal formation unit. Further, the signal from the video signal generation unit is fed to the detonator power control unit.

The main turbojet engine 4 is operating and the gas-dynamic missile control system is operating at the same time. Rocket 1 is directed into the enemy air zone. From the power unit of the rocket control voltage is supplied to the detonators 22 of the gas generator 15. The pyrotechnic cartridges 19 in the gas generator 15 are triggered, the flow of the combustion gas of the propellants in the pyrotechnic cartridges 19 creates high pressure in the duct 17 of the gas generator 15, leading to the destruction of the front aluminum skin of the rocket body 2 and the opening of the nacelles 16, in the inner bowl of which there is a metal sputtering, which has a wired connection to the block for generating a false control signal for the operation of the aircraft.

The enemy missile 38 focuses the capture of the orientation on the gondola 16 of the missile 1 and approaches it.

After confidently capturing the target with the enemy missile 38, the pilot gives the command to the on-board computer, bringing the aircraft into combat readiness, lowering the air duct 39, gaining supersonic speed, leaving the zone of air damage with the enemy missile 38, and missile 38 attacks the false target in the form of missile 1.

If the initial target lock by the fired enemy missile 38 is focused on the aircraft, then after the aircraft engine speed is canceled, and the false control signal of the aircraft operation on the missile 1 is turned on, the latter completely simulates the hypersonic aircraft and the air flows around it, transferring the target lock from the aircraft to the missile 1.

Air flows are generated from filled gas in nacelles 16.

Claims (4)

1. An "air-to-air" missile to protect a hypersonic aircraft from enemy missiles, consisting of three parts connected to each other by power partitions, namely, the front aluminum hull plating with the possibility of its destruction, the middle part of the housing of the electronic missile control unit, and solid-propellant rocket engine (TTRD) with gas-dynamic control and side turn engines (DBR); the front aluminum part of the body skin has a front-mounted video camera, and the rear part of the body is attached to a gas generator located in the aluminum body; In the front aluminum casing of the casing there are nacelles made of non-combustible material and tightly attached to the air duct having holes along the entire length of the air duct pipe and attached to the aluminum casing of the gas generator with pyro cartridge placed inside it, for each of which detonators are installed. 2. A rocket according to claim 1, characterized in that the rocket electronic control unit contains an ultrashort wavelength antenna, a high frequency amplifier unit (UHF), a video signal generation unit connected to a video camera, a signal generation unit for a false control system of a hypersonic aircraft connected to metal coating inside the nacelles, formed by spraying. 3. A rocket according to claim 1 or 2, characterized in that the electronic control unit for the rocket additionally contains: a power unit for controlling detonators located in the gas generator of the front aluminum casing of the hull, detonators that activate the operation of the TTRD, detonators that activate the gas-dynamic control system missile in the DBR. 4. The rocket according to claim 3, characterized in that the TTRD contains a gas-dynamic rocket control system, namely: DBR, consisting of a gas-dynamic turn of the rocket nozzle, as well as pipelines connecting the nozzle with check valves, which are connected by pipelines with cylinders filled with solid fuel to control the rocket, and detonators are located inside the cylinders for operating the gas-dynamic rocket control system.

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