RU2572026C2 - Aircraft missile launcher - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to airborne weapons, particularly, to the "Block"-type multibarrel missile launchers. This launcher comprises the cylindrical pipe 1, front and rear cowls 2, 3, launcher pipes 6, gas discharge pipes 7 arranged parallel with the latter, one per every launcher pipe, and disposable composite web 11. Tail section of every pipe 7 is located ahead of appropriate segment slit 15. Said slit 15 is arranged at the gate to turn the missile jet stream through 180 degrees and to feed it into gas discharge pipe 7 and, further, to appropriate section of heatproof web 11. Said design allows the pre-breakage of said web arranged ahead of the missile so that optics located at the head of missile is not damaged.

EFFECT: efficient launching of missiles with optical, electronic and laser instruments built in their heads.

2 cl, 6 dwg

Description

The invention relates to the field of aviation weapons, namely to multi-barrel launchers of the "Block" type for placement in them and launching aircraft missiles from an aircraft.

From the prior art (see, for example, “Arms and Technologies of Russia. Encyclopedia. XXI Century” / Edited by N. Spassky. - M.: Publishing House “Arms and Technologies”, Volume 10, 2008), multi-barrel launchers are known for launching aviation missiles (hereinafter - PU), including a cylindrical body with a transverse power set and external suspension components for the aircraft, a set of launch tubes for unguided aircraft missiles (hereinafter - NAR), mounted in end disks, fairings, an electrical system for supplying launch pulses to missiles, shutter for fixing missiles in PU.

Closest to the claimed invention in terms of technical nature and the technical result achieved using the invention is the launcher (B13L gun unit) for aircraft missiles described in the indicated source (see pages 266-267), including a cylindrical power case with a transverse internal set and end disks, external nodes of the suspension to the aircraft, fairings, and the front fairing is equipped with heat-shielding gaskets (disposable heat-shielding partition) installed between the front a cutter and launch tubes to protect the missiles from aerodynamic heating and destructible, upon launch, by the head of the rocket), an electrical system for supplying launch pulses, a set of launch tubes for placing the missiles and a shutter for fixing them.

The main disadvantage of the known launcher is the inability to launch rockets with built-in optical devices, photodetectors in the nose of the rocket, for example: adjustable or homing missiles due to significant shock loads acting on the nose of the rocket when it passes through a disposable heat-shielding partition at startup. The partition must be strong and withstand high-speed air pressure during the flight of the aircraft, as well as a gas stream from an adjacent launch rocket. This circumstance deprives the rocket of a guarantee of the safety of optics when it breaks through a heat-shielding partition.

The task underlying the present invention is to create a design PU, providing the ability to launch missiles having built-in optical, electronic and laser devices in the bow.

The technical result achieved by the implementation of the present invention is the possibility of launching from launchers besides NAR, also missiles for various purposes: corrected, homing, guided.

The problem with the achievement of the technical result is solved by the fact that in the launcher for aircraft missiles, which includes a power cylindrical body with a transverse inner set and end disks, external nodes of the suspension to the aircraft, fairings, and the front fairing is equipped with a heat-shielding partition, an electrical system for supplying starting pulses , a set of launch tubes for placing missiles and a shutter for fixing them, gas tubes are installed in the housing, parallel to the launch tube m and made with the possibility of supplying a jet rocket gas to the corresponding part of the heat-shielding partition.

In addition, the nose of each gas outlet pipe is fixed in the socket of the front end disk, and the outlet of the socket is connected to the internal volume of the corresponding launch pipe in the area bordering the heat shield, and the tail section is placed in front of the segment groove located on the shutter and made with the possibility of a turn 180 ° rocket jet and feeding it into a gas outlet pipe.

In addition, the axis of the outlet hole of the front end disk socket is aimed at the center of the bore of the launch tube.

Placement in the body of the exhaust pipes parallel to the launch tubes and configured to supply the gases of the rocket jet to the corresponding part of the heat shield, and the placement of the tail of the gas tubes in front of the segment grooves located on the shutter and configured to rotate the rocket jet 180 ° and supplying it to gas pipes, provides preliminary destruction of the heat-shielding partition located in front of the missiles, and guarantees the safety of op iki, located at the head of the missiles.

The presence of essential features distinctive from the prototype allows us to recognize the claimed technical solution as new.

From the prior art, no solutions have been identified that would have features that coincide with the distinguishing features of the claimed PU, so the latter meets the condition of patentability "inventive step", and the possibility of use in industry allows us to conclude that it meets the condition of "industrial applicability".

A comparative analysis of the proposed technical solution with identified analogues of the prior art, from which the invention does not explicitly follow for an aviation weapons specialist, showed that it is unknown, and taking into account the possibility of industrial manufacturing of a launcher, it can be concluded that it meets the patentability criteria.

Preferred embodiments of the proposed technical solution are described below based on the drawings, where:

- in FIG. 1 shows a general view of a launcher for aircraft missiles;

- in FIG. 2 shows the extension element A in FIG. 1, without rockets;

- in FIG. 3 - the same with rockets;

- in FIG. 4 shows the remote control B in FIG. 1, without rockets;

- in FIG. 5 - the same with rockets;

- in FIG. 6 shows a view of the shutter opening.

In graphic materials, the corresponding structural elements of the launcher for aircraft missiles are indicated by the following positions:

1. - power cylindrical body;

2. - front fairing;

3. - the rear fairing;

4. - external nodes of the suspension to the aircraft;

5. - electrical connector;

6. - launch tube;

7. - gas outlet pipe;

8. - transverse power set disk-shaped;

9. - front disc;

10. - a nest;

11. - disposable composite partition;

12. - through channel;

13. - shutter for fixing missiles;

14. - exhaust hole;

15. - segment groove;

16. - the head of the rocket;

17. - a rocket;

18. - an optical device;

19. - rolling.

The launcher for aircraft missiles consists of a housing 1, a front fairing 2, a rear fairing 3, suspension units 4 for mounting on an aircraft holder, an electrical connector 5 for connecting a control circuitry to an aircraft electrical circuitry, launch tubes 6 for placing missiles, gas vent tubes 7 ( one for each launch tube), a transverse power set 8 of a disk-like shape, for launch tubes and vent pipes. The front disk 9 has slots 10 with a through exit to the launch tube 6 at an angle. The described housing 1 from the bow is closed by a disposable composite partition 11, which is pressed against the housing by the front fairing 2, in which through channels 12 are made, coaxial with the launch tubes. The front cowl 2 has the structural possibility of a limited displacement in position B to replace the baffle before flight. In the rear part of the PU, a removable shutter 13 is installed on the housing 1, having exhaust holes 14 and segment grooves 15, and the tail parts of the vent pipes 7 are connected to the latter.

Launcher for aircraft missiles works as follows.

When an electric pulse passes to launch a rocket, a solid propellant bomb of its engine is ignited with a jet gas jet ejected through openings 14 in the shutter 13 at a speed of ≈2000 m / s, while the rocket does not move until the engine has set a given thrust (≈600 kg). Part of the jet is captured by a segmented groove of the shutter 15 and rotated through it by 180 ° due to the braking pressure, which is ≈70 atm, and is supplied through a gas outlet tube 7 to the front of the launch tube 6, into the volume limited by the baffle 11 and the head part 16 of the rocket 17 , with a sharp increase in pressure in it, which leads to the destruction of the partition 11 into parts without touching the head of the rocket and ensures the safety of the optical devices 18 installed in it. After the engine has set a predetermined thrust, the rocket crushes rolling 19 on the sleeve of the rocket 17 and starts moving along the launch tube 6; all shells of missiles remain in the pipes PU.

The design changes proposed in the invention were tested on a mock-up of launchers in polygon conditions on a fixed bench using standard S-8 missiles and high-speed filming during launches.

When frame-by-frame viewing of high-speed shooting, the stages of rocket launch are clearly visible:

- the appearance of a torch and smoke from a rocket behind the launcher, the rocket is stationary;

- the destruction of a disposable heat-shielding partition in front of the launcher and the expansion of its fragments forward in flight, the rocket is stationary;

- the appearance of the rocket from the launch tube and its forward movement along the flight in the normal mode.

The results of polygon tests of the mock PU fully confirm the reality of the claimed technical solution.

The economic effect of the invention is expressed in the difference between the cost of an armament kit for front-line aircraft according to existing standards and the cost of a unified armament kit, which will be cheaper due to the exclusion of special launchers for guided and guided missiles from it.

Claims (2)

1. Launcher for aircraft missiles, including a power cylindrical body with a transverse inner set and end disks, external suspension units to the aircraft, fairings, and the front fairing is equipped with a heat-shielding partition, an electrical system for supplying launch pulses, a set of launch tubes for placing missiles and a shutter for their fixation, characterized in that in the case there are gas exhaust pipes parallel to the launch tubes and configured to supply reactive gases rocket jets onto the corresponding part of the heat-shielding partition, while the bow of each gas outlet pipe is fixed in the socket of the front end disk, the outlet opening of the socket being connected to the internal volume of the corresponding launch pipe in the area bordering the heat-shielding partition, and the tail part is placed in front of the segment groove located on the shutter and made with the possibility of turning the rocket jet 180 ° and feeding it into the gas pipe. 2. Launcher according to claim 1, characterized in that the axis of the outlet opening of the front end disk socket is aimed at the center of the passage section of the launch tube.

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