RU2659450C1 - Rocket in a transport-launcher container - Google Patents

Abstract

FIELD: rocket engineering.

SUBSTANCE: invention relates to rocket engineering, namely to devices ensuring the safety of the rocket when it is placed in a transport-launcher container (TLC) on carriers, transport-charging machines, long-term storage bases. Rocket in the transport-launcher container contains an axisymmetric fuselage with support pads fixed along its outer surface, a propulsion system, folding aerodynamic surfaces, a pipe of a transport-launcher container. Fuselage of the rocket is installed in the TLC pipe with a gap, the device for sealing the internal cavities of the rocket and the TLC pipe. TLC pipe is made in the form of fastened head and tail sections. Head section is made of a material with a Young's modulus that exceeds the Young's modulus of the tail section material by at least one and a half times. Gap between the fuselage and the head section of the TLC pipe exceeds the gap between the fuselage and the tail section of the TLC pipe. Support pads are placed in the tail section of the TLC on the fuselage frames with a step not exceeding 1/7 of the length of the tail section of the TLC. Around the longitudinal axis of the fuselage of the rocket with an angular pitch not exceeding 50°, on the outer surface of the sections of the TLC pipe, support belts are made of the same material as the corresponding section. Inner surface of the tail section of the TLC pipe can be made of cylindrical shape, inner surface of the head section of the TLC pipe is cylinder-conical, expanding to the outer edge of the section. Fuselage of the rocket inside the head section is made tapering to the outer edge of the section. Part of the support pads is fixed on the line of location of the fuselage attachment assemblies of the folding aerodynamic surfaces.

EFFECT: invention makes it possible to reduce the impact loads on the rocket units in the TLC, both for the calculated and random longitudinal and transverse loads, to simplify the mounting of the TLC to the launcher.

3 cl, 3 dwg

Description

The invention relates to rocket technology, and in particular to devices that ensure the safety of the rocket when it is placed in a transport-launch container (TPK) on carriers, transport-loading machines, long-term storage bases.

The most important component of rocket safety is the protection of internal units from external mechanical influences - both longitudinal and transverse impacts.

Shocks can be divided into distributed, from external volumetric impact on the transport and launch container (for example, due to an explosion), and concentrated, for example, due to the fall of the TPK with a rocket during transportation. In the first case, the interaction of two shells, the TPK and the fuselage, has the character of the distributed internal impact of the most inertial object, the rocket, on the TPK. In the second case, a concentrated impact may occur, leading to local deformation of the TPK body and / or fuselage.

In any case, an important means of protecting the internal components of the rocket is to reduce the amplitude of the impact and dissipate the energy of the impact by the shells - the body of the launch vehicle and the fuselage of the rocket. Another tool that obviously complicates the design is the use of devices external to the TPK - shock absorbers and dampers.

A device for intercontinental ballistic missile silo-based R-36M in the transport and launch container is known - see, for example, Shevchenko S.N., Vasilenko V.V., Dolbenkov V.V. and others. "Strategic ground-based missile systems", M., Military Parade, 2007, pp. 118-125. The body of the TPK rocket (or rather, its cylindrical part, hereinafter referred to as the "pipe") is made of fiberglass. The inner surface of the TPK pipe is a guide for the rocket bearing pads made in the form of four bearing rings covering the fuselage. The design is designed so that the impact energy coming from the outside is absorbed by external damping devices and the elastic deformation of the TPK pipe material. The residual outstanding energy is transmitted through the reference sites and absorbed by the fuselage material of the ICBMs.

The disadvantages of the device are its small adaptability to absorb longitudinal impacts, the structural complexity of attaching external damping systems to a non-metallic TPK.

The closest analogue is the technical solution - RF patent No. 2215981 “Cruise missile in a transport-launch container”, authors Artamasov O.Ya., Efremov GA, Leonov AG etc. Here, a missile is installed in a transport and launch container, including a pipe, devices for sealing the inner surfaces of the rocket and TPK pipe, including, among other things, an axisymmetric fuselage, bearing pads, a propulsion system, folding aerodynamic surfaces. The fuselage is mounted relative to the inner surface of the TPK pipe with a gap. The device for protecting rocket assemblies is a transport and launch container and an axisymmetric fuselage in contact with each other by a set of separate support pads firmly fixed to the fuselage along its longitudinal axis. A large contact area allows you to more efficiently dissipate the energy of transverse impact through the system - "TPK - fuselage." Nevertheless, the disadvantage of the closest analogue is also the poor efficiency of damping the energy of longitudinal impacts or complex impacts when performing TPK from metal (the material of the container is not defined in the patent). In the case of a fiberglass TPK, the closest analogue has the disadvantages of attaching external damping devices to such TPK, which requires the implementation of transitional structural elements, as well as the limitation of the type of launchers on which the rocket can be used (as a rule, vertical launchers with TPK resting on a hard surface )

The technical result of the proposed technical solution is to improve the design of the rocket in the transport and launch container, which allows, in comparison with the closest analogue, to improve the decrease in the amplitude of the impact and dissipation of mechanical energy, both in longitudinal and transverse impacts, as well as to simplify the fastening of the TPK to devices launcher.

The specified technical result is achieved by the fact that a rocket in a transport and launch container containing an axisymmetric fuselage with support plates fixed along its outer surface, a propulsion system, folding aerodynamic surfaces, a transport and launch container tube, and the rocket fuselage is installed in the TPK pipe with a gap , devices for sealing the internal cavities of the rocket and pipe TPK, the pipe of the transport and launch container is made in the form of bonded head and tail sections, while the tin section is made of material with a Young's modulus exceeding the Young's modulus of the material of the tail section by at least one and a half times, and the gap between the fuselage and the head section of the TPK pipe exceeds the gap between the fuselage and the tail section of the TPK, supporting plates are placed in the tail section of the TPK on frames the fuselage with a step not exceeding 1/7 of the length of the tail section of the TPK, and around the longitudinal axis of the fuselage of the rocket with an angular step not exceeding 50 °, support belts made of the same material are made on the outer surface of the sections of the TPK pipe o and the corresponding section. In the particular case of execution, the inner surface of the tail section of the TPK pipe is cylindrical, the inner surface of the head section of the TPK pipe is cylindrical, expanding to the outer edge of the section, the fuselage of the rocket inside the head section is tapering to the outer edge of the section. A part of the support plates is fixed to the location line of the attachment points of the folding aerodynamic surfaces to the fuselage.

The implementation diagram of the device according to the proposed technical solution is shown in FIG. 1, 2, 3.

Designations accepted:

1 - TPK pipe, tail section;

2 - TPK pipe, head section;

3 - fuselage;

4 - fuselage frame;

5 - folding aerodynamic surfaces;

6 - supporting pad on the line of location of the attachment points to the fuselage of folding aerodynamic surfaces;

7 - a support pad outside the line of location of the attachment points to the fuselage of folding aerodynamic surfaces;

8 - a device for sealing the internal cavities of a rocket and TPK;

9 - a device for sealing the internal cavities of the TPK - the bottom of the TPK;

10 - supporting belt of the head section of the TPK;

11 - supporting belt of the tail section of the TPK;

12 - device longitudinal / transverse depreciation;

13 - device lateral depreciation;

14 - deformation of the tail section of the TPK with a transverse impact (option);

15 - direction of transmission of impact in the pipe TPK with a longitudinal impact;

16 - direction of transmission of the impact on the tail section of the pipe TPK, the fuselage and the fuselage frames with a transverse impact.

The technical solution involves the following possible schemes for securing a TPK with a rocket in a launcher, for example, vertical or inclined.

The first scheme involves fixing the TPK in the longitudinal direction with a support on the bottom (Fig. 1, pos. 9) of the TPK, and in the transverse direction with the girth for the power elements — TPK support belts (Fig. 1, pos. 10, 11) or one of them .

The second scheme involves fixing the TPK product in the longitudinal direction by "hanging" the support belt in the head of the pipe TPK, Fig. 1, pos. 10, fastening in the transverse direction by grasping the support belts (Fig. 1, pos. 10, 11) or one of them.

To implement the second scheme, the TPK pipe is rationally made of two sections. The longest, tail section (Fig. 1, pos. 1) is made of a material with the best characteristics for the dissipation of mechanical impact energy, for example, fiberglass. Another, head section (Fig. 1, pos. 2) TPK is designed to perform on it the elements of longitudinal fastening TPK, fixing the rocket in TPK, sealing devices of the internal cavities of the rocket and TPK (Fig. 1, pos. 8) and is made from a more adapted for these purposes, a material with a Young's modulus of elasticity exceeding the Young's modulus of the material of the tail section of the TPK by at least one and a half times. For example, metal (steel, titanium), the manufacture of which body parts with complex fasteners is the most technologically advanced. The sections are fastened together by a set of fixing elements, for example, metal studs. Such a connection, in addition to mechanical strength, provides at the same time a sufficient longitudinal elasticity of the connection (analogous to the use of rivets in the connection of the fuselage skin).

Other schemes for securing the rocket in the TPK in the launcher, as well as during transportation, are variations of the first two, with the redistribution of possible longitudinal and transverse loads between the support belts and the bottom of the TPK.

In all schemes, with longitudinal impacts on the TPK in the launcher, the impact energy is absorbed by external damping devices (Fig. 1, item 12). The non-absorbed energy, as well as the impact energy of the product when it is not in the launcher, is absorbed mainly by the longest section of the TPK pipe with the best dissipative properties of the material — the tail, FIG. 1, pos. 1. The section can be made of fiberglass (for reference, the Young's modulus of fiberglass is E≈21 GPa, which is 10 times lower than the Young's modulus of steel - 210 GPa, 5 times lower than the Young's modulus of titanium - 120 GPa, 3.5 times lower than the modulus Young aluminum - 70 GPa). Conventionally, the direction of impact transmission in the TPK pipe with a longitudinal impact is shown by arrows (Fig. 1, item 15).

In transverse impacts, mechanical energy not absorbed by external dampers (Fig. 1, pos. 12, 13) will be absorbed by the material of the TPK tail section, and also, through the support plates, by the fuselage material (Fig. 1, pos. 3).

The task of protecting the fuselage from concentrated impacts leading to plastic deformation requires ensuring uniform distribution of impact energy over its surface.

For this, firstly, the supporting belts of the TPK pipe (Fig. 1, pos. 10, 11) are made of the same material as the corresponding section of the TPK. For example, when performing a fiberglass section, the support belts can be made by local winding of additional layers of fabric. In the manufacture of a metal section of a TPK on a lathe or milling machine, by turning a larger diameter belt.

Secondly, the supporting pads on the fuselage should be distributed as evenly as possible along its surface - both along the length of the fuselage (along the longitudinal axis of the fuselage) and around the circumference (around the longitudinal axis of the fuselage).

The implementation of the support plates in the form of separate structural elements allows the TPK pipe to “breathe” - to deform elastically (Fig. 3, item 14) in places of their absence and independently absorb impact energy. The distribution of the support plates along the length of the fuselage allows, firstly, to distribute the shock energy not absorbed by the TPK to several power elements of the fuselage - frames (Fig. 1, item 4). Such a direction of impact transmission during transverse impact is conventionally shown by arrows in FIG. 1, pos. 16. The most rational is the uniform fastening of the support plates on the fuselage frames with a step not exceeding 1/7 of the length of the tail section of the TPK. The angular step between the support plates around the longitudinal axis of the fuselage should not exceed 50 °. For example, in the diagram of FIG. 1, 2, 3, support plates pos. 6, 7 are located symmetrically relative to the longitudinal axis of the fuselage of the rocket, in four planes, with an angular pitch equal to 45 °.

In the presence of folding aerodynamic surfaces, for example, wings and plumage (Fig. 1, 2, item 5), the rational means of reducing the overall aerodynamic drag is to place the bearing pads, FIG. 1, 2, pos. 6, on the line of arrangement of nodes (hinges) of fastening the aerodynamic surfaces to the fuselage.

The implementation of the head section of the TPK pipe from a material with a high Young's modulus of elasticity relative to the material of the tail section of the TPK pipe requires additional measures to protect the rocket assemblies in the head of the fuselage from transverse impact. Such a measure, in particular, is to increase the gap between the TPK pipe in its head section and the fuselage.

Such a locally increased gap can be achieved by making the inner surface of the tail section of the pipe TPK cylindrical, and the inner surface of the head section of the pipe with a cylindrical shape, expanding to the outer edge of the section. In this case, the fuselage of the rocket inside the head section of the TPK is tapering to the outer edge of the section, for example, conical or animated.

The implementation of the head section of the pipe TPK from a relatively easily processed material (for example, metal) technologically facilitates the task of obtaining an increased clearance. Also, such a locally increased gap can be used to place devices that provide sealing of the internal cavities of the rocket and TPK.

An additional means of protecting equipment in the head of the fuselage is the implementation of this part of the fuselage from a material with relatively high damping properties with respect to the material of the head section of the TPK, for example, carbon or fiberglass.

The proposed technical solution allows to reduce the shock loads on the rocket assemblies in the transport and launch container under both design and random longitudinal and lateral loads without complicating external shock absorbing and damping devices, as well as simplify the mounting of the TPK to the launcher.

Claims (3)

1. A missile in a transport and launch container (TPK), containing an axisymmetric fuselage with support plates fixed along its outer surface, a propulsion system, folding aerodynamic surfaces, a transport and launch container pipe, the missile fuselage being installed in the TPK pipe with a gap, a sealing device the internal cavities of the rocket and pipe TPK, characterized in that the pipe of the transport and launch container is made in the form of bonded head and tail sections, while the head section is made and of material with a Young's modulus exceeding the Young's modulus of the material of the tail section by at least one and a half times, the gap between the fuselage and the head section of the TPK pipe exceeds the gap between the fuselage and the tail section of the TPK, support plates are placed in the tail section of the TPK on the fuselage frames in increments, not exceeding 1/7 of the length of the tail section of the TPK, and around the longitudinal axis of the fuselage of the rocket with an angular pitch not exceeding 50 °, support belts are made on the outer surface of the sections of the TPK pipe from the same material as the corresponding section. 2. The rocket in the transport and launch container according to claim 1, characterized in that the inner surface of the tail section of the TPK pipe is cylindrical, the inner surface of the head section of the TPK pipe is cylindrical, expanding to the outer edge of the section, the fuselage of the rocket inside the head section is made tapering to the outer edge of the section. 3. The rocket in the transport and launch container according to claim 1, characterized in that part of the support plates is fixed to the location line of the attachment points to the fuselage of the folding aerodynamic surfaces.

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