RU2761886C1 - Shipboard unit for a simulation rocket - Google Patents

Abstract

FIELD: rocket engineering.

SUBSTANCE: invention relates to the field of rocket engineering and is used for testing and adjusting a shipboard air defense missile system in normal conditions in terms of conducting flyovers. The shipboard unit comprises a rotary apparatus and a simulation rocket placed thereon. The rotary apparatus constitutes a frame structure, installed in the back whereof is a mechanism for rotating the simulation rocket in the horizontal plane, securing the rocket in one of five positions. Also provided are means for securing the position of the simulation rocket in one of the four vertical positions. The simulation rocket consists of a homing head, a compartment with an inertial control system unit placed therein, and a back cover with electrical connectors. The simulation rocket is secured in one of the five possible horizontal positions at angles from 0° to 180° with a discreteness of 45°, wherein 0° is the position of the fore part of the simulation rocket perpendicular to the selected side of the ship. The simulation rocket is secured in one of the four possible vertical positions at angles from 0° to 45° with a discreteness of 15°.

EFFECT: proposed invention provides a possibility of orienting the simulation rocket in the horizontal and vertical planes without changing the course of the ship, and does not require the use of a sealed container for the rocket.

8 cl, 15 dwg

Description

The invention relates to the field of rocketry and is used for testing and testing under normal conditions of a shipborne anti-aircraft missile system in terms of overflights.

The purpose of the invention is to provide checks of the control loop of the missile system for ships with the capture of the signal reflected from the target by the radar homing head (RGS).

For this purpose, training missiles are used, with the use of which a number of technical problems are associated.

The use of non-pressurized training missiles necessitates their use in conjunction with a pressurized container. This leads to an increase in the mass of the entire structure and its dimensions. Due to its large dimensions, difficulties arise with the delivery of the rocket to the ship (special transport is required) and rigging.

In addition, difficulties arise with the orientation of a large-sized rocket on the ship, since after the installation of the rocket on the ship, it is no longer possible to change its orientation in relation to the ship with the available means.

At the same time, it should be borne in mind that, as a rule, overflights are carried out on both sides of the ship. In this regard, in the process of testing, it becomes necessary to perform an additional maneuver to change the side, which leads to a change in the ship's course, to an increase in the test time, and an increased fuel consumption.

From the prior art, solutions are known that are aimed at solving the above technical problems. So, for example, a shipborne launcher is known containing a platform with the ability to rotate around a vertical axis for guidance in a horizontal plane and a mechanism in the form of a pair of screw gears for guidance in a vertical plane [patent RU 2256582 C1, published 20.07.2005]. The installation known from this patent does not provide the required angle of rotation of the rocket in the vertical plane.

Also known is a ship launcher for missiles and testing, containing a support platform in the form of a frame, and adjustable in length thrust [patent RU 2232968 C1, published 20.07.2004]. The known installation does not imply a change in the orientation of the launcher relative to the horizontal plane of the ship.

The claimed invention is aimed at solving the above problems. As a result of the application of the declared ship installation, the following technical results are achieved:

- the ability to orient the imitation rocket located in the ship installation in the horizontal and vertical plane without changing the course of the ship;

- no need to use a sealed container for the rocket;

The above technical results are achieved due to the fact that:

The ship's installation for a simulated rocket contains a rotary device and a simulated rocket placed on it. The pivoting device is a frame structure, in the rear part of which there is a mechanism for rotating the imitation rocket in the horizontal plane, which secures the rocket in one of five positions, consisting of a mounting plate, a rotary plate located above it and a rotation mechanism located between them. Two vertical supports are installed on the swivel plate, on the tops of which are the attachment points for the imitation rocket installed in them at the point of the center of mass, and at the base of which two rods are hinged with longitudinal guide grooves and fasteners located in them, ensuring fixation of the position of the imitation rocket in one of four vertical positions. The imitation rocket consists of a homing head, a compartment with an inertial control system unit located in it and a rear cover with electrical connectors, and also includes means for fixing the rods in the longitudinal guide grooves.

Fixation in one of the five possible positions of the imitation rocket horizontally is performed at angles from 0 ° to 180 ° with a discreteness of 45 ° and an accuracy of +/- 30 ', where 0 ° is the position of the bow of the imitation rocket perpendicular to the selected side of the ship.

Fixation in one of the four possible positions of the imitation rocket vertically is performed at angles from 0 ° to 45 ° with a discreteness of 15 ° and an accuracy of +/- 30 '.

The frame structure has mounting assemblies for mounting on standard ship assemblies.,

In the corners of the front part of the frame structure, there are units for fixing the protective casing, which are guide corners made with the possibility of folding.

A ship installation for a simulated rocket contains a protective casing made in the form of a frame sheathed with sheet material, having rigging units in the upper part and units for fixing to the frame structure of the rotary device in the lower part.

The frame structure can be welded or bolted.

The rotary plate is made with the possibility of placing and fixing the equipment unit on it.

The design and principle of operation of the claimed shipborne installation for a simulated rocket is explained with the help of drawings:

FIG. 1 - General view of the ship installation under the protective casing;

FIG. 2 - protective casing;

FIG. 3 - rotary device with a simulated rocket;

FIG. 4 - rotary device with a simulated rocket, front view;

FIG. 5 - rotary device with a simulated rocket, top view;

FIG. 6 - niche for placing the grounding wire and fixing elements, top view;

FIG. 7 - unit for fixing the protective casing;

FIG. 8 - assembly unit for the installation of the ship installation on the standard support assemblies of the ship;

FIG. 9 - assembly unit for the installation of the ship installation on the standard support units of the ship, isometric view;

FIG. 10 - horizontal rotation mechanism;

FIG. 11 - vertical rotation mechanism;

FIG. 12 - mechanism for fixing the rotation in the horizontal plane;

FIG. 13 - mechanism for fixing the rotation in the vertical plane;

FIG. 14 is a simulated rocket, rear view;

FIG. 15 is a simulated rocket without a back cover, rear view.

Figure 1 shows a general view of a shipborne simulator rocket installation. The ship installation consists of a rotary device 1 with a protective casing 2, under which a simulation rocket 3 (Fig. 3) for the marine complex is placed on the rotary device 1. In this form, the ship installation is both in the process of storage before and after testing, and in the process of transportation to the ship and to the place of storage.

The imitation rocket according to the claimed invention is hermetically sealed. An imitation rocket is a part of a rocket containing a homing head, a compartment with an inertial control system (ISU) and a rear cover.

The protective casing 2 (Fig. 2) is designed to ensure the safety of the imitation rocket 3 (Fig. 3) during storage, transportation and rigging, and also provides rigging. The design of the protective casing is a rectangular frame, sheathed with sheet and profile material, and consists of rigging assemblies 4, guiding amplifiers 5 and locking pins 6, which serve to fix the protective casing 2 to the legs 7 (Fig. 3) of the rotary device 1.

The rotary device 1 (Fig. 3) consists of a frame structure 8 of longitudinal 9 (Fig. 6), transverse 10 (Fig. 4, 6) and support beams 11. At the ends of the longitudinal beams 9 there are legs 7 (Fig. 4), serving for placing the rotary device 1 on the means of transportation - machines for material and technical maintenance (MTO). Also, at the ends of the longitudinal beams 9 in the front of the rotary device 1, there are brackets 12 (Fig. 7) and guide corners 13 for mounting the protective casing (2). The guide corners 13 are folded relative to the brackets 12 along the axis of rotation 14 and are fixed by clamps 15 in the holes "a" at position I and in the holes "b" at position II.

The holes "a" and "b" are made in the guide corners 13, the holes "c" are in the brackets 12. To select the desired position, you need to combine the hole "a" or "b" on each guide corner 13 with the hole "c" in the corresponding bracket 12.

Along the edges of the support beams 11, the attachment points 16 of the ship device are mounted to the standard support elements 20 of the ship (Figs. 3, 4, 8), two of which have guide pins 17 located on one of the sides of the frame structure. The attachment points 16 (Fig. 2, 3) consist of a locking mechanism 18, a rotary cam 19 and are installed on the support elements 20 of the ship. Rotation of the cam 19 through an angle of 90 ° with levers 57 (Fig. 9) secures the ship mount 1 on the standard support elements 20 of the ship, followed by tightening the locking bushings 21 with levers 25. The locking mechanism 18 consists of a locking sleeve 21, with a gear wheel 22, a limiter 23, the springs 24 located in the housing of the attachment unit 18 and the lever 25. The stopping of each locking sleeve 21 from unwinding occurs through the gear wheel 22, against which the spring-loaded stop 23 rests.

In the front part of the frame structure 8, a niche 26 (Fig. 3, 6) is made to accommodate the ground wire 27 and fixation elements 28, which serve to fix the equipment unit 29. The niche 26 with the equipment is closed with a cover 30 (Fig. 5) and is fixed with locks 31 ( Fig. 5, 6).

In the rear part of the frame structure 8, a rotation mechanism 32 (Fig. 3, 10) is installed, which ensures the rotation of the simulation rocket 3 in the horizontal plane with fixation in five positions at the angles "a" (Fig. 5).

The rotation mechanism 32 (Fig. 10) is mounted on the mounting 33 and the rotary 34 plates and consists of a clamp 35 and bearings 36 (Fig. 11). A bushing 37 is located in the center of the mounting plate 33 to ensure the centering of the pivot plate 34. A bearing 38 is installed on the axis of the pivot plate 34, which is located between the bushing 37 and the flange part of the axis 39, fixed with a nut 40. On the pivot plate 34 there is a locking mechanism 41 (Fig. 10), consisting of a glass 42 (Fig. 12) with a threaded hole "g" and a retainer 43. The fixation of the rotary plate 34 at the angle "a" (Fig. 5) is performed by a retainer 43, which is screwed along the thread of the glass 42 (Fig. 12 ) and is fixed in the bushing 44 of the mounting plate 33.

Two vertical supports 45 are installed on the rotary plate 34 (Figs. 3, 4). Each support 45 is made of a triangular shape from a profile material, at the top of each vertical support there is a mounting unit for a simulated rocket in the form of a bracket 46 (Fig. 11). In the bracket body

46 there is a bearing 47, which provides rotation of the simulation rocket 3 in the vertical plane at angles "β" (Fig. 3) in four positions relative to its center of mass. Simulation rocket 3 is attached in bearings 47 through axles 48. A rod 49 is pivotally attached to the profile element of each vertical support in its lower part, for which a hole is provided for mounting it. The rods 49 provide the movement of two pins 50 (Fig. 13) of the simulation rocket 3 along the grooves "d" and fixing them in the holes "e" at the angles "β" (Fig. 3, 13). Fixation takes place by screwing the thumbs 51 into the holes "e" of the rods 49 along the threaded part of the pins 50 located on the side end surfaces of the rear cover 52 of the simulated rocket 3.

On the rear cover 52 there is a cover 53 (Fig. 14) and a plug 54, which closes the hole for testing the simulator rocket for tightness. Under cover 53 are electrical connectors 55 and a silica gel desiccant 56 (FIG. 15).

The claimed invention is industrially applicable and is carried out as follows.

The ship's installation is stored and transported to the ship by a logistics vehicle (MTO). The ship installation is fixed on a special platform of the MTO vehicle. To load the ship installation onto the ship (rigging), the standard facilities of the Navy's maintenance services are used. The work is carried out for the rigging knots 4 of the protective casing 2.

The installation of the ship installation on the ship is carried out in such a way that the longitudinal beams of the frame structure are located perpendicular to the sides of the ship. Fastening is carried out by attachment points 16 to the standard support elements 20 located on the deck of the ship (intended for the installation of technological equipment that ensures the loading of ammunition into the cellar of the ship).

After that, grounding is carried out with a ground wire stored in a niche 26. Next, the protective casing 2 is dismantled, for which, in the lower part of the protective casing, the locking pins 6 are removed from the holes on the amplifiers 5 and on the legs 7. The casing is dismantled for the rigging knots 4. After dismantling The protective casing is installed and fixed on the rotary plate 34 of the apparatus unit 29 to provide power supply and operating modes of the simulated rocket using the fastening elements 28. In addition, the guide corners 13 of the protective casing 2 are folded with their subsequent fixation in the folded position. On the rear cover 52 of the simulation rocket 3, the cover 53 is dismantled and the electrical connectors coming from the apparatus unit 29 are connected to the electrical connectors 55.

The ship mount provides simultaneous orientation of the imitation rocket in the horizontal and vertical planes (along the course and pitch) with fixation in certain positions.

The rotation of the imitation rocket 3 in the horizontal plane is carried out by manually turning the rotary plate 34. Further, fixation is performed in one of five possible positions with the retainer 43 in the sleeve 44 of the mounting plate 33 at angles from 0 ° to 180 ° with a discreteness of 45 ° and an accuracy of +/- 30 ', where 0 ° is the position of the bow of the imitation rocket 3 perpendicular to the starboard (left) side of the ship. Thus, in FIG. 5, the fixed positions of the imitation rocket I and V correspond to the directions to the starboard and left sides of the ship, and position III to the bow of the ship.

Simulation rocket 3 is located on vertical supports 45 with the help of axes of rotation 48 located in the center of mass of the simulation rocket, installed in bearings 47 of supports 45.

The rotation of the imitation rocket 3 in the vertical plane is carried out manually, simultaneously with the rotation, the pins 50, located on the side end surfaces of the rear cover 52, slide in the grooves (e) of the rods 49. Slip of each pin 50 occurs to the hole (e) corresponding to one of the four possible positions with fixing this position by screwing the winglets 51 into the holes (e) along the thread of the stud 50, at angles from 0 ° to 45 ° with a resolution of 15 ° and an accuracy of +/- 30 '.

The obtained test results are used to test the ship's anti-aircraft missile system. After the tests, the reverse sequence of actions is performed, including dismantling the ship's installation from the standard support elements 20 of the ship, loading, transporting and storing the ship's installation on the MTO machine.

Dimensions of the ship installation (L × W × H) = 2500 × 1000 × 1160 mm. Height of a product without a protective casing in a working position at an angle of 45 ° - 1900 mm, no more. Product weight does not exceed 1000 kg.

Due to the tightness of the imitation rocket, there is no need for a sealed container, which leads to a decrease in its mass and dimensions, which ultimately makes it possible to transport and store the rocket on the MTO machine of the basic maintenance facilities complex (KBSTO). The simulator is compact because it is only a part of the missile containing the seeker, the inertial control system (ISU) and the rear cover.

The proposed ship installation is compact, mobile, mounted using standard facilities of the Navy ships, and provides testing without changing the course of the ship.

Due to the constructive interconnection of the imitation rocket, the rotary device and the protective casing, the problems of storage, transportation, rigging, installation and dismantling of the ship installation are solved.

Claims (8)

1. A shipborne installation for a simulated rocket, containing a rotary device and a simulated rocket placed on it, while the rotary device is a frame structure, in the rear of which there is a mechanism for turning the simulating rocket in a horizontal plane, which provides fixation of the rocket in one of five positions, consisting of from the mounting plate, a rotary plate located above it and a rotation mechanism located between them, two vertical supports are installed on the rotary plate, on the tops of which are the attachment points for the imitation rocket, installed in them at the point of the center of mass, and at the base of which two rods are hinged with longitudinal guide grooves and fasteners located in them, ensuring the fixation of the position of the imitation rocket in one of four vertical positions, while the imitation rocket consists of a homing head, a compartment with an inertial control system unit located in it and a rear edge Lugs with electrical connectors, and also includes means for fixing in the longitudinal guide grooves of the rods. 2. A shipborne installation for a simulated rocket according to claim 1, characterized in that the fixation in one of five possible positions of the simulated rocket horizontally is performed in the range from 0 ° to 180 ° with a discreteness of 45 ° and an accuracy of +/- 30 ', where 0 ° corresponds to the position of the bow of the imitation rocket perpendicular to the selected side of the ship. 3. The shipborne simulator rocket according to claim 1, characterized in that fixation in one of the four possible vertical positions of the simulator rocket is performed in the range from 0 ° to 45 ° with 15 ° discreteness and +/- 30 'accuracy. 4. The ship installation for the imitation rocket according to claim 1, characterized in that the frame structure has mounting assemblies for mounting on the standard support assemblies of the ship. 5. The ship installation for a simulated rocket according to claim 1, characterized in that in the corners of the front part of the frame structure there are protective casing fixation units, which are guide corners made with the possibility of folding. 6. The ship installation for a simulated rocket according to claim 1, characterized in that it further comprises a protective casing made in the form of a frame sheathed with sheet material, having rigging units in the upper part and units for fixing the rotary device to the frame structure in the lower part. 7. The shipborne simulator rocket assembly according to claim 1, wherein the frame structure can be welded or by means of fasteners, such as bolted connections. 8. The ship installation for a simulated rocket according to claim 1, characterized in that the rotary plate is made with the possibility of placing and fixing a block of equipment on it to provide power supply and modes of operation of the simulated rocket.

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