RU131473U1 - LAUNCHER FOR AIRCRAFT ROCKETS - Google Patents

Abstract

1. Launcher for aircraft missiles, including a housing with a power set, launch tubes for missiles installed in the end disks, the suspension unit to the aircraft and the electrical system for supplying launch pulses, characterized in that it is equipped with a protective deflector made with the possibility of incomplete coverage of the protruding from the housing of the upper parts of the launch tubes. 2. Installation according to claim 1, characterized in that through perforation is made on the surfaces of the deflector and protruding from the housing of the launch tubes. Installation according to claim 1, characterized in that it is equipped with an intermediate fairing mounted on the front end disk.

Description

This utility model relates to the field of aviation weapons, namely to launchers (hereinafter referred to as launchers) of the “block” type for placing and launching aviation missiles (hereinafter referred to as missiles) of uncontrolled, adjustable and controlled from a helicopter.

From the prior art (see, for example, "Russia's Arms and Technologies. Encyclopedia. XXI Century" / Ed. N. Spassky. - M.: Arms and Technologies Publishing House, Volume 10, 2008), multi-barrel launchers are known (B8V20, B13L1, B8V7) with a flat front end, differing from each other by the number of pipes, their caliber and dimensions, and including a cylindrical body, inside of which there is a set of guiding launch tubes that serve as the missile exit from the launcher during launch and fixed in the end disks hulls, suspension units for helicopter and electric an insulating system for supplying triggering pulses.

The closest to the claimed utility model in terms of technical nature and the technical result achieved by using it is described in the indicated source (see p. 270-271 launcher (gun block B8V20-A) for aircraft missiles having a typical composition of incoming elements of known launchers, i.e., including a set of launch tubes enclosed in a housing with end disks having coaxial holes for installing the pipes, suspension units for the PU to the helicopter, and an electrical system for launching missiles.

A common drawback of the well-known gas turbines is the ability to accumulate hot gas of the flare of the rocket at launch in launch tubes and on the front end disk of the hull; moreover, after the rockets exit the launcher, the hot gas jet of the flare abruptly passes from the end disk to the cylindrical body of the installation, it is braked at the front end disk with increasing pressure, which leads to a turn of the jet in the plane of the disk across the longitudinal axis of the launcher, including in the direction of the air intakes of the helicopter. The ingress of a hot gas jet having a high speed into the air intakes sharply distorts the picture of the air flow in the turboshaft engines of the helicopter, which leads to surging with a decrease in speed or their complete stop, thereby creating an emergency situation. The operation of the helicopter engine in the surge mode leads to its destruction due to an unacceptable increase in the temperature of the gases in front of the turbine and the loss of strength of its blades, therefore, if a surge occurs, the engine must be switched to the "low gas" mode, where the surge will disappear by itself or be switched off. The increase in gas temperature can reach several hundred degrees per second and the time for the crew to make a decision is limited. The problem is aggravated by the fact that at the moment of exit from the launcher the flare of a rocket having a radius of at least 1 m, at a distance of 5 m from the nozzle, encounters axial resistance from the blunt nose of the launcher. This leads to a turn of the jet in the transverse direction and an increase in the radius of the torch up to 2-3 times (see figure 1). All measures to eliminate the afterburning torch behind the rocket nozzle only reduce the likelihood of disturbances in the normal operation of the helicopter engine, but do not lead to their complete elimination. This is explained by the fact that even in the absence of an afterburning flame, the temperatures in the jets are high enough to cause surging of the helicopter engine at rocket distances of tens of meters.

The technical task of this utility model is to eliminate the aforementioned disadvantages, namely, to reduce or eliminate the harmful effects of the flare of a rocket starting from a launcher from a helicopter, causing instability or stalling of the helicopter engines.

The technical result achieved in the implementation of this utility model is to reduce the air temperature at the inlet to the air intake when the rocket starts by 2–3 times.

The problem with the achievement of the technical result is solved by the fact that the launcher for aircraft missiles, including a housing with a power set, launch tubes for missiles installed in the end disks, the suspension unit to the aircraft and the electrical system for supplying launch pulses, is equipped with a protective deflector made with the ability to cover protruding from the body of the upper parts of the launch tubes.

In addition, through perforations are made on the surfaces of the deflector and protruding from the housing of the launch tubes.

In addition, the installation is equipped with an intermediate fairing mounted on the front end disk.

Providing a launcher for aircraft missiles with a protective deflector that is capable of incomplete coverage of the upper parts of the launch tubes, and performing through perforation on the surfaces of the deflector and protruding from the shell of the launch tubes prevents the dispersal of hot gas towards the air intake of the helicopter.

The supply of the launcher for aircraft missiles with an intermediate fairing mounted on the front end disk, contributes to the departure of the gas accumulated under the deflector back in the air stream.

A comparative analysis of the proposed technical solution with the identified analogues of the prior art, from which the utility model does not explicitly follow for the aviation weapons specialist, showed that it is not known, and taking into account the possibility of industrial manufacturing of the launcher, we can conclude that it meets the patentability criteria .

Preferred embodiments of the proposed utility model are described below based on the presented drawings, where:

- figure 1 shows a diagram of the effects of the torch on the air intakes;

- figure 2 presents a General view of the launcher for aircraft missiles;

- figure 3 shows a diagram of the passage of hot jets of gas torch after installing the deflector;

- figure 4 presents a photo of an experimental launcher for aircraft missiles;

- figure 5 shows a graph of the decrease in temperature of the air entering the air intake, depending on the embodiment of the sample.

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

1. - case;

2. - the node of the suspension to the aircraft;

3. - electrical system for supplying starting pulses;

4. - front end disk;

5. - launch tube;

6. - deflector;

7. - bracket;

8. - intermediate fairing;

9. - a rocket;

10. - vent holes;

11. - holes of the launch tube.

The launcher for aircraft missiles includes a housing 1 with a power kit, inside of which are mounted guide tubes 5 for missiles 9 fixed to the end disks of the housing 1, bolts for fixing missiles (not shown in the drawings) and an electrical system 3 for supplying launch pulses. On the body 1 is installed node 2 of the suspension to the aircraft. On the front end disk 4 of the housing 1 is fixed an intermediate fairing 8 having a conical shape, which is made with a flow angle of 15 ° to the axis of the launcher.

Above the package of protruding ends of the guiding launch tubes 5 on the brackets 7, a gas jet deflector 6 is installed, on the surface of which a through perforation is made in the form of holes 10, which is located in the upper part of the power housing 1 from the air intake side of the helicopter propulsion system and is fastened by five brackets 7.

The output ends of the guides of the launch tubes 2 are perforated, and the holes 11 are placed diametrically arranged and made with a diameter of 16 mm

The axial baffle 6 is 1/3 of the surface of a cylinder made with a radius of 20 mm greater than the radius of the power housing 1, while the holes 10 of the visor are staggered and made with a diameter of 16 mm.

Launcher for aircraft missiles works as follows.

PU is suspended on single beam holders of the helicopter and is charged with twenty missiles, which can provide for the defeat of manpower and equipment, ground or surface based. Missiles are launched both in single salvos and in series.

After the launch of the rocket, the hot gas of its torch, which is in the launch tube 5 under pressure, is vented to the atmosphere through the holes 11, while giving up a significant part of its energy. When a rocket leaves a launch tube containing perforation, the pressure accumulated in it is relieved smoothly without a shock wave, decreasing the gas temperature, as well as recoil. The gas accumulated on the front end disk, propagating across the longitudinal axis of the launcher, including towards the air intake of the helicopter, is delayed by the deflector and flows out from under it along with an oncoming flow of air through the cone-shaped slot in the direction of the tail of the launcher, bypassing the air intakes.

The design changes proposed in this technical solution were tested on a prototype obtained by finalizing a serial launcher - the NAR B8V20-AE block, 80 mm caliber, designed to launch 20 missiles from a helicopter, including from a Mi-28N helicopter with air intakes located above the launcher tubes PU, which usually repeatedly led to the pre-surge situation of the helicopter engine and its abnormal operation.

The tests were carried out in ground conditions on the prototype of the Mi-28 helicopter in the following variants:

- serial PU (B8V20-A, as the base);

- serial PU with the replacement of standard pipes on perforated;

- serial PU with an additionally installed perforated deflector of gas jets.

As a result: according to the results of testing a prototype PU containing the distinguishing features of the proposed utility model, there is a significant decrease in air temperature at the inlet to the helicopter’s air intakes during missile launches (see Fig. 5): from 127.7 ° in the first test version, up to 76 ° - in the second and up to 42 ° - in the third.

The perforated deflector of gas jets, together with the perforation of the guiding launch tubes, provides the lowest temperature effects in the air intake zone compared to other layouts, and the presence of an intermediate fairing with a 15 ° angle of flow provides a smooth flow around the PU with a satellite jet of the torch with a minimum turn in the direction of the air intake. In addition, it was found that the reflected jets of the flare of the rocket have significant dimensions, but their density is less than in other layouts. The afterburning zone is crushed by perforated jets and a gas jets deflector, moreover, the crushed jets of a stream of hot gas of low density have a small range in the direction of the air intake.

Claims (3)

1. Launcher for aircraft missiles, including a housing with a power set, launch tubes for missiles installed in the end disks, the suspension unit to the aircraft and the electrical system for supplying launch pulses, characterized in that it is equipped with a protective deflector made with the possibility of incomplete coverage of the protruding from the housing of the upper parts of the launch tubes. 2. Installation according to claim 1, characterized in that through perforation is performed on the surfaces of the deflector and protruding from the housing of the launch tubes. 3. Installation according to claim 1, characterized in that it is equipped with an intermediate fairing mounted on the front end disk.

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