RU2245503C1 - Transport-launching module - Google Patents

Abstract

FIELD: rocketry, in particular, launchers of surface ships and submarines.

SUBSTANCE: the transport-launching module has a sealed casing in the form of a cup with the front and rear covers with a seal. A rocket with a nose cone is installed inside the cup. The rocket nose cone partially projects from the cup, and in the assembled state of the transport-launching module serves at the same time as the front cover of the transport-launching module cover. The transport-launching module is provided with a changeable ring component, whose one end face is conjugate to the respective end face of the cup. Longitudinally positioned threaded members (for example, bolts) are passed through the changeable ring component, with the aid of them the changeable ring component is connected to the cup. BY means of longitudinally positioned break-off components made in the form, for example, of explosive bolts, as well as of radially positioned break-off components made, for example, in the form of explosive bolts the changeable ring component is fastened to the rocket nose cone. Inside the transport-launching module provision is made for an obturator, which is positioned in the bottom (tail) section of the rocket. The cup is made with an inner smooth cylindrical surface. Detachable means for creation of a behind-rocket volume of the preset value are installed on the rear cover with the id of brackets.

EFFECT: reduced thermoerrosion effect on the casing of the transport-launching module at a launch of the rocket, which makes it re-usable.

7 cl, 6 dwg

Description

The invention relates to the field of rocketry and can be used in transport and launch modules in launchers of various bases, in particular, in launchers of surface ships and submarines.

Known ship container for storing and launching a rocket according to US patent No. 3769876, F 41 F 3/04, 1973. It contains a sealed enclosure, which has the shape of a rectangular parallelepiped, inside which the rocket is placed. Front and rear, the container body is closed by covers made of brittle material (polystyrene), which are destroyed when the rocket starts. Two half-cylinders are attached to the side walls of the container body, along which the folded aerodynamic surfaces of the rocket slide during its movement after launch. A guide is attached to the upper wall of the container body from the inside, having a groove in the cross section, which includes the rocker arms. For additional fixation of the rocket during its transportation and storage in the container, a U-shaped bracket is provided, the inner surface (pillow) of which is filled with foam. The curvature of the pillow corresponds to the curvature of the rocket body. The pillow moves with the rocket; after exiting the container, it separates. The container has a safety device and a delay device. The latter consists of a rotary bar, which at one end abuts against the front yoke of the rocket. The bar is fixed with a tear-off element (with a shear finger) and in the initial position prevents the movement of the yoke. When the traction force reaches a predetermined value, the finger is cut off, the bar under the pressure of the yoke reclines, and the rocket is released from fixation. A safety device is necessary in case of unintentional starting of the engine. In the initial position, the rear yoke is fixed by two stops connected to the power cylinder, in which the charge and igniter are located. When an electric signal is supplied through the electrical connector from the ship’s launch control system, the charge ignites, the gas pressure lifts the cylinder, and the stops rising with it release the rear yoke from fixing. According to the “start” command, the safety device is first triggered, after which the engine starts. When a delay device is triggered by the force of traction and removes the fixation of the front yoke, the rocket, moving forward, destroys the foam cover and leaves the container.

A disadvantage of the known ship container is that the container has a limited scope, because involves providing missile launch only from deck installations of surface ships. In addition, the design of such a container is difficult to manufacture and involves one-time use.

Known ship container for storing, prelaunch and missile launch, designed for use in the vertical launch launcher CCL (Concentric Canister Launcher), installed on surface ships (A. Korolev. - New ship vertical launch launch vehicle of the US Navy. - Foreign military review. 1999. No. 4, p. 47-50; V. Anisimov. -A new generation of ship launchers. Foreign military review. 1999. No. 9, p. 45-48). Known ship transport and launch container (TPK) contains a sealed enclosure with means for holding and fixing the rocket. TPK case consists of one-piece integral inner and prefabricated outer cylindrical shells, bottoms in the form of a hemispherical lower platform with a base plate and longitudinal elements (spar reinforcement) located between the outer and inner cylindrical shells. The inner cylindrical shell is used to store and launch the rocket. The annular space between the inner and outer shells of the body is used to divert the gas stream when starting the rocket engine. The gas jet of a rocket engine, passing through an adjustable hole in the base plate, changes direction by 180 ° in the hemispherical lower platform and goes out through the channels of the annular gap formed by the outer and inner cylindrical shells of the body. The decrease in the pressure and axial load parameters, which increase during the operation of the rocket engine, is carried out by regulating the size of the gas outlet in the base plate of the container.

However, the known ship TPK has a limited scope, because involves providing missile launch only from deck or below-deck installations of surface ships. In addition, TPK has a rather complicated design.

Also known is a ship container for storing and launching a rocket according to patent RU No. 2194235, F 41 F 3/04, 2002. The well-known TPK contains a sealed enclosure including an outer cylindrical shell with a destructible front cover and a removable bottom. The outer cylindrical shell is made of composite material. Inside the outer cylindrical shell, guides are made, which are a single unit with the said shell. Destructible front cover is made, for example, of spheroplastic and is able to withstand external pressure corresponding to the maximum immersion depth. Inside the outer cylindrical shell concentrically last with the ability to move along the rails installed inner cylindrical shell. The latter is made with the possibility of detachable connection with the rocket by means of removable tear-off elements in the form of pyro-bolts. Pyro bolts are arranged radially relative to the longitudinal axis of the TPK body, which is geometrically aligned with the longitudinal axis of the rocket. The inner cylindrical shell is made with the possibility of installing on it another front airtight cover that is discharged when the rocket is launched. The front sealed cover of the inner cylindrical shell is connected to the latter by means of a pyro-cord. Inside the TPK case, means are provided for holding and fixing the rocket. The latter include supporting elements fixed to the inner surface of the outer cylindrical shell. Supporting elements by means of tear-off elements made in the form of parallel-mounted explosive bolts and pyro-bolts, respectively, are connected to the tail of the rocket. An electrical connector is provided in the bottom of the TPK hull for electrical communication between the rocket and the ship’s launch control system.

When a rocket is launched from under water, simultaneously with the rocket engine starting, pyro-bolts are installed, installed in the bottom of the TPK body between the tail of the rocket and supporting elements fixed to the outer cylindrical shell. After that, from moving along the longitudinal axis of the TPK, the rocket is held by supporting elements through explosive bolts connected to the tail of the rocket. The products of fuel combustion of a rocket engine from a sub-rocket (trans-rocket) volume through the gap between the outer and inner cylindrical shells of the TPK body fall into the axillary volume between the destructible front cover of the outer cylindrical shell and the front sealed cover of the inner cylindrical shell. When the pressure inside the TPK case exceeds the external (outboard) pressure, the front cover of the outer cylindrical shell is destroyed. Under pressure and bolts, the bolts break apart. connecting the tail of the rocket with supporting elements, and the latter stop holding the rocket — The inner cylindrical shell, fastened to the rocket by means of pyro-bolts, begins to move along the guides made inside the outer cylindrical shell. After the rocket leaves the water, the signal from the onboard control system of the rocket triggers a pyro cord and pyro bolts, freeing the rocket from the inner cylindrical shell. The latter is separated from the rocket, and the rocket continues its movement without this shell. In contrast to launching from under water, in the case when the launcher is located on a surface ship, when launching a rocket after breaking bolts connecting the tail of the rocket with supporting elements, the inner cylindrical shell, being fastened by removable hooks and corresponding bolts to the outer cylindrical the shell of the TPK, remains stationary.

The rocket begins to move separately from the inner cylindrical shell inside it. After the rocket leaves the ship’s TPK, the inner cylindrical shell remains inside the TPK hull.

However, the design features of the ship’s TPK, in conjunction with the rocket launch scheme used, cause a significant thermoerosive effect on the TPK case when launching the rocket, which eliminates the possibility of reusable use of the TPK case. In addition, the known TPK has a rather complex hull structure, which increases the complexity of manufacturing ship TPK.

The closest set of essential features with the claimed device is the transport and launch module (TPM), described in the description of the invention to patent RU No. 2156941, F 41 F, 3/04, 2000, which is selected as the closest analogue of the prototype ( here and below, TPM is understood as TPK assembled with a rocket). Known TPM contains a sealed enclosure in the form of a glass with a front destructible and rear removable covers with a seal. A rocket with a head fairing is installed inside the TPM case. TPM case is made of composite material. Inside the TPM glass, guides are made that are evenly spaced around the circumference and are integral with the glass. The front collapsible cover is made, for example, of spheroplastic and is able to withstand external pressure corresponding to the maximum submersion depth of the submarine. At the same time, this lid is capable of breaking under slight excess pressure inside the container. An obturator is made in front of the TPM housing. In an embodiment of the invention, the obturator is made in the form of an intermittent annular support for the rocket and is a single unit with the housing TPM. In other embodiments, the obturator may be in the form of a perforated annular support or intermittent perforated annular support. Brackets are installed in the rear (bottom) part of the TPM case, on which a shell is detachably fixed by means of pyro-bolts. The shell is made with the possibility of coverage and fixation of the rotary nozzles of the rocket with the possibility of connection with the tail of the rocket by means of explosive bolts. Brackets through pyro-bolts, a shell and explosive bolts fix and keep the rocket from moving. The free end of the shell is made with a side cut. In the bottom part of the TPM hull, electrical connectors are installed for the electrical connection of the ship’s missile launch control system from the back of the removable cover.

During a regular launch of a rocket, a signal from the ship’s launch control system in accordance with the rocket launch sequence diagram gives a signal to turn on the rocket’s autonomous power sources and the start engine is started from the onboard control system. The products of combustion of fuel from the sub-rocket (overshot) volume through the gap between the TPM casing and the rocket enter the axillary volume. At the same time, the said guides perform the function of a device providing the necessary clearance for the passage of generated gases. If the pressure inside the TPM housing exceeds the external (outboard) pressure, the front cover is destroyed. Under the influence of pressure in the sub-rocket volume and the thrust of the starting engine, bolts are broken that fasten the tail of the rocket with a shell. Rotary nozzles of the rocket are freed from the shell. The rocket becomes controllable and begins to move along the guides of the glass. Leaving the TPM case, the rocket is always in a gas bubble, which is formed due to the products of fuel combustion passing through the obturator. If it is necessary to launch an emergency rocket, a signal is sent to trigger pyro-bolts and to start the starting engine. Pyro bolts are bursting. Under the influence of pressure in the axillary volume and thrust of the starting engine, the rocket begins to move along the guides of the glass. At the same time, the shell surrounding the nozzle of the rocket is held on the tail of the rocket by means of explosive bolts. The exit of the rocket from the container during an emergency release is carried out in the same way as during regular launch. After the rocket leaves the TPM housing, due to the deflecting component of the starting engine, due to the presence of an oblique cut of the free end of the shell, the rocket is rotated relative to its center of mass and pulled away from the carrier.

A disadvantage of the known TPM is a significant thermoerosive effect on the TPM body during missile launch, which in the case of repeated use of the TPM body involves an increase in the complexity of the work to restore the TPM body. Along with this, the well-known TPM has a rather complex housing design, which complicates the technological equipment for its manufacture.

The problem solved by the invention is the creation of a fairly simple, uncomplicated to manufacture, universal transport and launch module, providing the possibility of reusable use of its body while ensuring the launch of missiles from launchers of various bases.

This problem is solved due to the fact that the transport-launch module containing a sealed case in the form of a glass with front and rear covers with a seal, a rocket with a head fairing is installed inside the case, and the transport-launch module is made inside with a shutter, equipped with brackets located in the case , and tear-off elements for fixing and holding the rocket, according to the invention is equipped with a removable ring element, one end of which is paired with the corresponding end of the glass. Through a replaceable ring element, longitudinally threaded threaded elements are passed through which the latter is connected to the glass. At the same time, by means of longitudinally located tear-off elements, as well as the radial of the located tear-off elements, the replaceable annular element is fastened to the head fairing of the rocket. The latter is partially protruded from the glass and at the same time serves as the front cover of the transport launch module housing. The obturator is located in the bottom of the rocket. The glass is made inside with a smooth cylindrical surface. On the back cover with the help of brackets, there are detachably installed means for creating the overshot volume of a given value.

Along with this, the hull is made with thickening on the outer surface in places, the location of which corresponds to the location of the reciprocal support launcher of the ship.

In addition, at least one guide element is made at the front end of the glass, interacting with the corresponding mating element of the removable ring element, to provide a predetermined angular position of the rocket relative to the longitudinal axis of the housing of the transport-launch module.

Along with this, the longitudinally located tear-off elements are made in the form of explosive bolts.

In addition, the said radially located tear-off elements are made in the form of pyro-bolts.

The transport and launch module is equipped with a removable crosspiece with a boost cylinder filled with flame-retardant gas, while the replaceable crosspiece is detachably installed inside the transport-launch module housing between the rocket and the back cover.

Along with this, the head fairing of the rocket is made detachable in flight.

The technical result of the use of the invention lies in the fact that it allows you to create a universal transport and launch module, which, when launching a rocket installed in it, provides the opportunity to reduce the thermoerosive effect on the TPM case, which, ultimately, improves the possibility of reusable use of the TPM case. Along with this, the invention provides a simplification of the design of the housing TPM, which reduces the complexity of manufacturing TPM, in particular, by simplifying the technological equipment for its manufacture. In addition, it is possible to reduce the material consumption of the TPM by giving the head fairing of the rocket installed in the TPM an additional function, namely, the function of the front cover of the TPM housing.

Figure 1 schematically shows the transport and launch module, General view, a longitudinal section; figure 2 is the same, view along A in figure 1; figure 3 is a mounting device for a removable annular element assembly with the head fairing of the rocket to the TPM glass, a section along BB in figure 2; figure 4 - pyrobolt fastening a removable annular element with a head fairing of a rocket, a section along G-G in figure 2; figure 5 - bursting bolt fastening the removable annular element with the head fairing of the rocket, and the guide element of the glass, interacting with the mating element made on the removable ring element, a section along DD in figure 2; in Fig.6 is a removable cross with a boost cylinder and powder pressure accumulators, a cross-section along EE in Fig.1.

In an embodiment of the invention, the SST is used in a launcher, for example, a submarine (not shown in the drawing). The transport and launch module contains a sealed housing in the form of a glass 1 with a front and rear covers 2, 3 with a seal 4. In an embodiment of the invention, the glass 1 and the back cover 3 are made of composite material. A rocket 5 with a head fairing “a” is installed inside the case (glass). The rocket head fairing is partially protruded from the cup 1 and, when assembled, the TPM simultaneously acts as the front cover of the TPM body (i.e., essentially, the front cover of the cup 1 is structurally aligned with the head cowl of the rocket 5). In an embodiment of the invention, when the rocket is launched, the head fairing of the rocket, after separation from the missile assembly from the TPM body, is separated from the rocket at the initial flight site.

TPM is equipped with a removable ring element 6, one end of which is associated with the corresponding end face of the glass 1. The replaceable ring element 6 essentially serves as an adapter connecting the glass 1 with the head fairing “a” of the rocket 5. Longitudinally threaded elements are passed through the replaceable ring element 6 (for example, bolts) 7, by means of which a removable annular element is connected to the glass 1. At the same time, the removable annular element 6 is provided by longitudinally separated tear-off elements 8, as well as radially separated tear-off elements x 9 elements attached to the payload fairing "and" 5 missiles, which, when the missile is mounted inside the body (glass) 1, also serves as the front cover of the latter.

In an embodiment, the longitudinally arranged tear-off elements 8 are made in the form of explosive bolts, and the radially located tear-off elements 9 are made in the form of pyro-bolts.

At the front end of the glass 1, guide elements are made, interacting with the corresponding mating elements 10 of the removable annular element 6, to ensure a given angular position of the rocket 5 relative to the longitudinal axis 11 of the TPM body. In an embodiment of the invention, said guide elements are made, for example, in the form of blind holes “b”, and the response elements 10 are each made, for example, in the form of a cylindrical rod with a conical end.

TPM is made internally with a shutter 12, which is located in the bottom (tail) of the rocket 5. In an embodiment of the invention, the shutter 12 is made, for example, in the form of a rubber ring mounted on the rocket body. The glass 1 is made inside with a smooth cylindrical surface “c”. In an embodiment of the invention, the TPM hull is made with a thickening of “d” on the outer surface in places, the location of which corresponds to the location of the reciprocal support launcher of the ship. The same places are used as reference zones when transporting SST in a horizontal position.

On the back cover 3 TPM using brackets 13 detachably installed means 14 to create the oracle volume of a given value. In an embodiment of the invention, for example, powder pressure accumulators (PAD) are used as such means. In another embodiment (not shown), these may be, for example, spring devices.

TPM is equipped with a removable crosspiece 15 with a cylinder 16 boost, filled with non-supporting gas, for example, nitrogen. A removable crosspiece 15 is detachably installed inside the TPM case between the rocket 5 and the back cover 3.

An electrical connector is also provided in the bottom of the TPM hull for electrical communication of the ship’s missile launch control system 5 (not shown in the drawing).

Transport and launch module operates as follows.

Before loading the rocket 5 into the TPM casing on the head fairing “a” of the rocket, using detachable elements 8 and 9, fix the removable ring element (adapter) 6. After that, the rocket is loaded into the housing (glass) 1 by moving along axis 11 until the end of the replaceable ring element 6 into the corresponding end face of the cup 1. In this case, the guiding elements “b” of the cup 1, interacting with the mating elements 10 of the removable ring element 6, provide a predetermined angular position of the rocket 5 relative to the longitudinal axis 11 of the TPM body. Then, using the threaded elements 7, the replaceable annular element 6 assembled with the head fairing of the rocket (i.e., assembled with the rocket) is fixed on the cup 1. Thus, by means of the replaceable ring element 6, the threaded elements 7 and detachable connected to the head fairing of the rocket elements 8, 9 provides for fixing and holding the rocket in a predetermined position relative to the TPM body. In this form, TPM can be transported by any means of transport, as well as located in launchers of various bases (including submarines), without requiring maintenance.

When a rocket is launched by a signal, for example, from a ship control system, in accordance with the rocket launch sequence, a pyro valve (not shown) of the boost cylinder 16 is triggered. As a result of the pyro valve, the gas that does not support combustion will be pressurized in the balloon 16 enter the e-volume. Moreover, due to the presence of the obturator 12, the gas is localized inside the TPM body between the back cover 3 and the tail of the rocket 5.

After filling the e-space with the non-combustion-supporting gas, a signal is triggered to activate the pyro-bolts 9 and the powder pressure accumulators 14. Due to the obturator 12 located in the bottom (tail) part of the rocket, as a result of the pressure exerted on the rocket, the bolts 8 are burst, holding the rocket from moving relative to the TPM case. A rocket, like a piston in a cylinder, begins to move along a smooth cylindrical surface “from” cup 1. When the rocket passes a certain distance (for example, equal to half the length of its body) and a predetermined size is created, the rocket engine is turned on.

Owing to the filling of the space beyond the combustion support gas, the possibility of burning out rocket fuel inside the TPM housing is eliminated, which allows to reduce the heat flux in the bottom of the TPM housing and, accordingly, reduces the thermoerosive effect on the TPM housing. Moreover, due to the fact that before turning on the rocket engine there is an increase in the inflow volume, it is possible to shorten the period of operation of the rocket engine inside the TPM housing, which, in turn, allows to reduce the thermal erosion effect on the TPM housing.

During the launch of the rocket, an interchangeable ring element (adapter) 6 protects the corresponding end part of the cup 1 made of composite material from the direct effects of pyro-bolts 9 and from the direct gas-dynamic effects of the launch rocket.

After the rocket leaves the water, the head fairing “a” is separated (fired) at the signal from the onboard control system of the rocket, as a result of which the air intake of the rocket is released. Thus, the head fairing of the rocket 5, while performing the role of the front cover of the TPM case, provides sealing of the TPM case during storage and transportation of TPM, provides the ability to mount the rocket to the TPM body and the ability to seal the rocket’s air intake when starting from under water.

During TPM maintenance, after the rocket is launched, the threaded elements (bolts) 7 are removed and thus the removable ring element (adapter) 6 is disconnected from the cup 1. Then, with the rear cover 3 removed, the spent PADs 14 are disconnected from the brackets 14. The removable crosspiece 15 is disconnected from the TPM case with a boost cylinder 16. The TPM housing is cleaned of traces of gas-dynamic effects. Instead of the removed PAD 14 and the removable crosspiece 15 with the boost cylinder 16, respectively, new ones are installed. The back cover 3 is installed in a regular place. Thus, the TPM case is prepared for loading another rocket and for reuse.

Thus, the possibility of reusable use of the TPM hull is ensured when launching both surface ships and submarines from launchers, regardless of whether the carrier is in the surface or underwater position when launching missiles.

In other embodiments of the invention, for example, when using SST in land mobile or stationary launchers, SST works in a similar way.

Thus, due to the design features of the TPM, the invention allows the creation of a universal TPM, which, when launching a rocket installed in it, provides the opportunity to reduce the thermoerosive effect on the TPM body, which, ultimately, improves the possibility of multiple use of the TPM body. Along with this, the invention provides a simplification of the design of the housing TPM, which reduces the complexity of manufacturing TPM. In addition, the invention provides the possibility of reducing the material consumption of TPM by giving the head fairing of the rocket installed in the TPM, the function of the front cover of the TPM body.

Claims (7)

1. Transport and launch module (TPM), containing a sealed housing in the form of a glass with front and rear covers with a seal, a rocket with a head fairing is installed inside the housing, and the TPM is made inside with a shutter, equipped with brackets located in the housing, and tear-off fixation elements and holding the rocket, characterized in that it is equipped with a removable ring element, one end of which is paired with the corresponding end of the glass, longitudinally threaded threaded elements are passed through the removable ring element, whereby the latter is connected to the glass, and by means of longitudinally located tear-off elements, as well as radially located tear-off elements, the replaceable annular element is fastened to the head fairing of the rocket, while the latter is partially protruding from the glass and at the same time serves as the front cover of the TPM case, with the shutter in the bottom of the rocket, the glass is made inside with a smooth cylindrical surface, and on the back cover with brackets detachably installed means for Building zaraketnogo volume set value. 2. Transport and launch module according to claim 1, characterized in that the hull is made with a thickening on the outer surface in places, the location of which corresponds to the location of the reciprocal support launcher of the ship. 3. Transport and launch module according to claim 1 or 2, characterized in that at the front end of the glass is made at least one guide element interacting with the corresponding mating element of the removable ring element to provide a predetermined angular position of the rocket relative to the longitudinal axis of the housing TPM. 4. Transport and launch module according to any one of claims 1 to 3, characterized in that the said longitudinally located tear-off elements are made in the form of explosive bolts. 5. Transport and launch module according to any one of claims 1 to 4, characterized in that the said radially arranged tear-off elements are made in the form of pyro-bolts. 6. Transport and launch module according to any one of claims 1 to 5, characterized in that it is equipped with a removable crosspiece with a boost cylinder filled with flame retardant gas, while the replaceable crosspiece is detachably mounted inside the body between the rocket and the back cover. 7. Transport and launch module according to any one of claims 1 to 6, characterized in that the rocket head fairing is made detachable in flight.

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