RU192688U1 - Launcher - Google Patents

Abstract

The proposal belongs to the class “Weapons” and can be used for firing missiles from a carrier in a launch tube from a portable anti-aircraft missile system of the Igla, Verba type. The device contains a frame with mounting elements for launch tubes and mechanisms for translating the arms of the rocket launch control actuators incorporating a device holding the handle of the rocket launch control drive during translation, a spring-loaded cocking lever held in the cocked position by a sear connected to the trigger property. At the same time, in order to prevent unauthorized tilting of the membrane of a high-pressure gas cylinder of a ground-based power supply (NPC) docked to the missile launch tube and, consequently, the loss of the NPC and the possibility of losing time for the timely launch of an anti-aircraft missile, a device that holds the handle of the rocket launch control drive when translation, made in the form of a swinging carrier with a one-sided supporting surface pushing the handle of the rocket launch control drive during translation, and the carrier is equipped with a stop, an obstacle direct rotation of the handle of the rocket launch control drive relative to the carrier.

Description

The proposal relates to the field of rocketry and can be used to launch individual launchers from a launcher (launcher).

Known twin installation for launching individual anti-aircraft missiles (RF patent No. 2088877), containing a frame with elements for docking with missiles in launch tubes and transfer mechanisms for each missile launch control drive handles (translation mechanisms), which can be taken as an analogue due to identity applicable class of anti-aircraft missiles and the same purpose.

Each translation mechanism of the installation for launching analogue anti-aircraft missiles contains a hinged body mounted on an axis, inside which there is a torsion spring, one end of which is fixed to the end cover with cocking handle, and the other end to the end cover with a protrusion and with a groove in the protrusion serving a device holding the handle of the rocket launch control actuator during translation.

The end cover with a protrusion through the sear and the cable is connected with the trigger. The torsion spring cocked with the cocking handle is fixed with a sear, which releases it when the trigger is triggered, and it rotates the end cap with the protrusion together with the rocket launch control drive handle inserted into the groove of the protrusion to engage a ground power source (NPC) docked to the launch tube , to ensure the launch of anti-aircraft missiles.

The disadvantage of the above installation for launching anti-aircraft missiles is that for introducing the handle of the drive control the launch of the rocket into the translation mechanism, it must be undocked from the launch tube and from the pivot arm on which it is movably fixed, from the “Marching” position, turning it 90 ° to a tilted position in which it can be accidentally rotated in the direction of the “Puncture” position on the launch tube, which threatens with the loss of a NPC docked to the launch tube due to its depressurization when the gas cylinder membrane is tipped in high pressure, and in a combat situation the possibility of untimely launch of an anti-aircraft missile.

The objective of the proposal is to prevent unauthorized rotation of the handle of the rocket launch control actuator in the direction of tilting the membrane of the NPC high pressure gas cylinder and, thereby, preventing the loss of the NPC and the loss of time for the timely launch of an anti-aircraft missile.

The solution to this problem is achieved by the fact that in the launcher for launching anti-aircraft missiles of individual use from the carrier, containing a frame with rocket mounts in launch tubes and mechanisms for translating the arms of the missile launch control actuators, which include a device holding the handle of the missile launch control actuator when translation, spring-loaded cocking lever held in cocked position by a sear connected to the trigger device, a device holding the drive handle at of the rocket launch control board during translation, made in the form of a swinging carrier with a one-sided supporting surface pushing the rocket launch control drive handle during translation, and the carrier is equipped with an emphasis preventing the rotation of the rocket launch control drive handle relative to the carrier.

In FIG. 1, 2 (respectively, side view and top view) shows a variant of the twin launchers for the sequential launch of anti-aircraft missiles.

PU consists of a frame 1, on which are placed:

docking elements for two missiles in launch tubes, consisting (for each docking place) of a fork 2 with a spring-loaded axis 3 and a handle 4 fixed to the axis 3, which are elements of rocket fastening in the launch tube in its front part, lodgement 5 with a spring-loaded folding collar 6 and the lock 7 - elements for mounting the rocket in the launch tube in its rear part, and the plug connector 8, which provides docking of the rocket in the launch tube with a common electronic launch unit 9 for both missiles;

catchers 10 holding rockets in the launch tubes when loading in a position in which the docking of the PU connectors and the launch tube is excluded. Each catcher consists of a spring-loaded hinged lever 11 with a roller 12, serving as a lodgement for the rear of the launch tube when loading;

transfer mechanisms for the rocket launch control drive handle (hereinafter referred to as transfer mechanisms) for each docking place for the rocket in the launch tube. Each translation mechanism consists of a swing carrier 13 with a one-sided supporting surface pushing the handle of the rocket launch control drive during translation. An emphasis 14 is fixed to the carrier 13. The carrier 13 is connected by a rod 15 with a swinging spring-loaded cocking lever 16 with a cam 17 fixed to it and with a cocking spring engaged on the cocking lever 18.

In FIG. 1, 2, the translation mechanisms are depicted in the “Initial” position with the cocked spring cocked.

In FIG. 3 shows a cam 17 with a groove 19 connected to a sear 20 fixed to the rod 21 of the retractable core of the electromagnet 22, which acts as a trigger device. The sear 20 is supported by a self-return spring 23.

In FIG. 4 shows the elements of mounting and orientation of the rocket in the launch tube in its front part:

a fork 2 with a recess corresponding to the eyelet 24 of the launch tube inserted into it, with a tooth 25 and an opening 26 in the fork 2;

the handle of the rocket launch control actuator 27, movably mounted on the pivot arm 28 with the sleeve 29 at the base of the arm, depicted in the "marching" position;

drove 13 with an emphasis 14 and a thrust 15 in the position of the translation mechanism "Puncture".

In FIG. 5 shows a rocket in a launch tube 30 with a ground-based power source (NPC) 31 docked to the launch tube, which is mounted on the launcher with a carrier 13 and cocking lever 16 in its composition, depicted in the “Original” position.

In FIG. 6 shows the translation mechanism in the “Initial” position with the rocket 27 of the rocket launch control actuator 27 folded into the carrier 13 and movably mounted on the swing arm of the launch tube 28.

In FIG. 7 shows carrier 13 with an emphasis 14 with the rocket 27 of the rocket launch control actuator 27 pivoted into the carrier 13 with the pivoting lever 28 in the “Punched” position, as well as elements of the relative position of the pivot axes of the carrier 13 and the pivoting lever 28.

In FIG. 8 shows a launcher with a manual trigger, in which the trigger is made in the form of a handle 32 connected to a spring-loaded sear 33. The sear 33 is fixed in the groove of the cam 34, which is connected via a link 35 to the swinging spring-loaded cocking lever 36. The remaining translation elements are similar to PU (Fig. 1, 2).

The missile docking in the pipe with the launcher can be performed in any position of the translation mechanism - “Puncture” or “Initial”, while the handle of the rocket launch control drive 27 (Fig. 4) must be in the “Marching” position, i.e. folded up.

The docking of the rocket in the pipe with PU, excluding preparatory operations, consisting in removing the protective covers, plugs, etc., is done manually with the following operations (Fig. 1, 2):

open the clamp 6;

set the handle 4 to position A, as a result of which the axis 3 will sink, releasing the plug 2 for docking it with the return eye 25 (Fig. 4) of the launch pipe;

take the rocket in the pipe with both hands and lower it with the front part, the eye 24, onto the control plug 2, and the back part (Fig. 1, 2) - onto the roller 12 of the catcher 10, while the sleeve 29 (Fig. 4) located at the base the lever 28 of the launch tube, rests against the tooth 25 of the fork 2, orienting the rocket in the launch tube to dock with the launcher in such a way that the hole in the eye 24 of the launcher tube is aligned with the hole 26 and axis 3 in the launcher 2 of the launcher;

press the handle 4 (Fig. 2), located in position A, down and release it, as a result of which the spring-loaded axis 3 will enter the eye 24 (Fig. 4) and into the hole 26 of the plug 2, fixing the rocket in the launch tube in the front support PU, and the handle 4 will be in position B;

turn the lever 11 (Fig. 5) of the catcher 10 back and press the launch tube 30 from above to overcome the friction force of the contacts of the PU connectors 8 and the launch tube, after which the rocket in the launch tube, turning around axis 3, drops onto the lodgement 5 and at the same time dock electrical connector with plug 8;

lower the clamp 6 on the launch tube and snap the lock 7 - the rocket in the pipe is docked with the launcher, with the exception of the rocket launch control actuator 27 handle (Fig. 4), which is connected to the carrier 13.

Before docking the handle of the launch control actuator for rocket 27 with carrier 13, it should be in the “March” position (Fig. 4), and the translation mechanism should be in the “Initial” position (Fig. 6).

At the same time, when they try to bring the handle of the rocket launch launch control actuator 27 with the lever 28 out of the “Marching” position and turn them in the direction of the “Punched” position, the lever 28 will abut against an emphasis 14 fixed to the carrier 13, which excludes unauthorized use of a ground power source (NPC) 31 (Fig. 5), docked to the launch tube 30.

To translate the translation mechanism to the "Initial" position, cocking lever 16 (Fig. 6) is rotated manually to overcome the tensile forces of cocking spring 18.

The translation mechanism is fixed in the “Original” position when the groove 19 (Fig. 3) is combined on the cam 17 with the sear 20, which enters the groove 19 under the action of the self-return spring 23.

When docking the handle of the launch control actuator of the rocket 27 with the carrier 13 (Fig. 6), it should be pulled off on the lever 28 of the launch tube, rotated through an angle of 90 ° and brought into the carrier 13 - the docking is completed.

An authorized transfer from the “Initial” position to the “Tilt” position is possible only when the electromagnet 22 is activated (Fig. 3), in which its core connected to the rod 21 pulls the sear 20 out of the groove 19 of the cam 17 fixed to the cocking lever 16 (Fig. .6), and under the action of a cocking spring 18, through the rod 15 it turns the carrier 13 with the rocket launch control actuator 27 pressed to it, which uses a ground power supply (NPC) 31 (Fig. 5), docked to the launch tube 30 with anti-aircraft rocket inside it, for later go anti-aircraft missile launch.

At the end of the translation of the rocket launch control handle 27 (Fig. 7) to the “Tilt” position, the stop 14 disengages from the lever 28 due to the eccentric (eccentricity B) relative position of the pivot axis G of carrier 13 and the pivot axis D of lever 28, which greatly simplifies the subsequent undocking of the launch tube 30 (Fig. 5) with PU (pos. 3, 5, 6, 7, 8, 10, 11, 13, 16, 22).

In the PU variant with a manual trigger (Fig. 8), the translation mechanism is activated manually by pressing the handle 32 with the fingers of the hand laid on the bar 37, first down and then on itself.

Claims (2)

1. Launcher for launching anti-aircraft missiles of individual use from the carrier, comprising a frame with rocket fastening elements in the launch tubes and mechanisms for translating the arms of the rocket launch control actuators, comprising a device holding the rocket launch control actuator handle during translation, a spring loaded cocking lever, held in cocked position by a sear connected to the trigger device, characterized in that the device holding the handle of the rocket launch control actuator During translation, it is made in the form of a swinging carrier with a one-sided supporting surface pushing the handle of the rocket launch control actuator during translation, and the carrier is equipped with a stop preventing rotation of the rocket launch control actuator handle relative to the carrier. 2. Launcher according to claim 1, characterized in that the axis of rotation of the carrier is made by an eccentric axis of rotation of the handle of the rocket launch control actuator.

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