RU2814878C1 - Method of solid-propellant rocket engine housing laying and fastening in transportation container - Google Patents

Abstract

FIELD: transportation; packing.

SUBSTANCE: invention relates to methods of laying and fastening solid-propellant rocket engine housings (SPRE housings) in a transportation container, the diameter of which is less than the diameter of mounting surfaces of moulded lodgements of the transportation container. Method is implemented with the help of a standard transportation container containing a base with a mounting surface and a cover fixed to the base. Upper horizontal surfaces of moulded lodgements are equipped with brackets for fastening clamps. Platform for installation of braces is fixed in the base of the container. On the concave mounting surface of the moulded lodgements, lodgements are installed in the form of bent metal plates equipped with rubber gaskets, intended for laying the SPRE housing, diameter of which is less than diameter of container mounting surfaces. Four braces in the form of turnbuckles connected to a chain are attached between the platform and lodgements. Solid-propellant rocket engine housing is laid on the surface of the lodgements. Clamps are installed in brackets, which cover engine housing from above lodgements. Uniform tension of braces and clamps is performed. Container base is closed with a cover and fixed it with locks.

EFFECT: invention provides reliable fastening, storage and transportation of SPRE housings of various diameters without their damage.

8 cl, 10 dwg

Description

Field of technology

The claimed invention relates to military equipment, namely to methods for laying, unfastening and transporting solid fuel rocket engine housings (hereinafter referred to as the solid propellant rocket engine housing) in a shipping container. The invention makes it possible to ensure the laying and unfastening of a solid propellant rocket motor body, the diameter of which is smaller than the diameter of the molded supports of the shipping container.

State of the art

Methods for stowing and transporting rocket engines are known from the prior art. Thus, from the document KR 20200048660, 05/08/2020, a supporting structure for transporting a solid fuel rocket engine is known, which can be used for engines of various sizes. The known supporting structure is not a container that ensures the tightness of the solid propellant rocket motor housing placed in it. In addition, the known load-bearing structure has an ergonomic configuration and protruding parts, which does not allow the placement of a large number of such load-bearing structures on vehicles used in the industry and designed to transport containers of certain dimensions and shapes. Also, in one of the embodiments, the known load-bearing structure requires the presence of an electrical network in the area of laying and unfastening, which complicates its use.

The technical problem to which the present invention is aimed is that the shipping container is designed for a specific size of the solid propellant rocket motor housing and has a fixed diameter of the seating surfaces corresponding to this size, which does not allow the use of the same container for stowing and transporting solid propellant rocket motor housings of smaller diameter (with equal length).

Disclosure of the invention

The technical result provided by the invention consists in expanding the functionality of a standard container, namely in the possibility of using a container designed for a certain diameter of the solid propellant rocket motor body and providing conditions for its storage and transportation, also for solid propellant motor housings of smaller diameters (including, for example, for new engine modifications).

The specified technical result is ensured by the following set of essential features of the invention.

A method for laying and securing the body of a solid fuel rocket engine in a shipping container containing a base with a landing surface in the form of molded cradle, equipped with rubber gaskets on the concave surface and brackets for fastening clamps located opposite each other on the upper horizontal surface, as well as a cover fixed to the base, consisting in that a platform is attached to the base of the container, equipped with means of connection with guy wires; on the molded cradles, cradles are installed in the form of curved metal plates equipped with rubber gaskets on the concave side and trapezoidal plates welded at an angle to the ends of the short sides, with each trapezoidal the plate is located opposite the bracket fastening bracket and is equipped on one side with a means of connection with guy wires, and on the opposite side with a means of preventing axial movement of the rocket engine body, guy wires are attached between the platform and the cradles, the body of the solid fuel rocket engine is laid on the cradles, the clamps are attached using brackets, covering the engine body above the cradle, fix the body of the solid fuel rocket engine by means of preventing axial movement, apply uniform tension on the braces, apply uniform tension on the clamps, install the lid on the base of the container and fix it.

The platform is made in the form of a steel plate, the opposite short edges of which are bent upward, and brackets welded to each of the bent parts of the plate serve as a means for connecting the platform with guy wires.

The platform is secured in the center of the container base with a bolted connection.

Cradles are installed on molded cradles using end stops welded to the ends of the longitudinal sides of a plate bent into a half ring at an angle to its plane.

The guy wires are made in the form of lanyards connected to a chain, with one fork of the lanyard used to connect to the bracket of the trapezoidal plate of the cradle, the second fork of the lanyard to connect to one loop of the guy chain, the second loop of the guy wire is connected to the bracket of the platform.

Each trapezoidal plate of the cradle contains a welded bracket as a means of connection with the brace, and as a means of preventing axial movement of the body of a solid fuel rocket engine - two U-shaped plates, which are the basis for a rotary bracket located between them, equipped with a stopper and having a screw stop.

The trapezoidal plate of the cradle has a cutout corresponding to the location of the clamp mounting bracket on the upper surface of the molded cradle.

The clamps are made in the form of a bent steel sheet tape with rubber pressed onto its flat surfaces.

The claimed invention is illustrated with the help of drawings.

Brief description of the drawings.

Fig. 1 - Lodgment;

Fig. 2 - Clamp;

Fig. 3 - Platform;

Fig. 4 - Stretching;

Fig. 5 - General view of the container base with the installed platform, supports, clamps, and braces. View from above;

Fig. 6 - Section A-A, Fig.5;

Fig. 7 - View B, Fig.5;

Fig. 8 - Scheme of laying and securing the solid propellant rocket motor body;

Fig. 9 - Section A-A, Fig.8;

Fig. 10 - Layout of solid propellant rocket motor housings of various diameters in a shipping container.

In the drawings the following positions are indicated by numbers:

1 - metal plate in the form of a half ring;

2 - trapezoidal plate;

3 - rubber gasket;

4 - screw;

5 - end stop;

6 - rectangular cutout;

7 - bracket;

8 - U-shaped plate;

9 - swivel bracket;

10 - screw stop;

11 - stopper;

12 - nut;

13 - tape;

14 - rubber;

15 - cylinder;

16 - cross bar;

17 - hole;

18 - side bar;

19 - axis;

20 - steel plate;

21 - hole;

22 - emphasis;

23 - bracket;

24 - lanyard;

25 - coupling;

26 - screw rod;

27 - fork;

28 - nut;

29 - chain;

30 - loop;

31 - hairpin;

32 - molded cradle;

33 - bolt;

34 - rubber gasket of the molded cradle;

35 - clamp mounting bracket;

36 - hairpin;

37 - stopper;

38 - nut;

39 - solid propellant rocket motor housing;

40 - housing support zones.

Carrying out the invention

The method is implemented using a standard shipping container designed for a specific diameter of the solid propellant rocket motor body. A typical shipping container is made of fiberglass and consists of a molded base and lid. At the base, closer to the ends of the container, there are seating surfaces (cradles molded during the manufacture of the container with a rubber gasket installed on them) for laying on them a solid propellant rocket motor body having a diameter corresponding to the diameter of the seating surfaces. On the upper horizontal surface of each molded cradle there is a pair of brackets located opposite each other and intended for fastening clamps covering the solid propellant motor body from above.

To enable placement and fastening of a solid propellant motor body of a smaller diameter in a container, 2 pieces of cradle (Fig. 1), 2 pieces of clamps (Fig. 2), 1 piece of platform (Fig. 3) are installed in the container. stretch marks (Fig. 4) in the amount of 4 pcs. After laying and unfastening the solid propellant motor body, the container is closed from above with a lid, which ensures the tightness of the container and is secured with locks. The container is then used to store or transport the solid propellant motor housing on typical vehicles used in the industry.

The cradle (Fig. 1) is a rectangular metal plate (1) bent in the form of a ring segment (for example, a half ring), to the ends of the short sides of which trapezoidal plates (2) are welded at an angle to its plane. The required angle is calculated in such a way that when implementing the method, the trapezoidal plates are located horizontally on the upper horizontal surfaces of the molded cradle. A rubber gasket (3) is attached to the concave inner surface of the plate (1) with screws (4). In its finished form, the shape of the inner surface of the cradle (a curved metal plate with a rubber gasket installed on it) must correspond to the shape of the cross-section of the solid propellant motor body in the area of its support (40) on the cradle. End stops (5) are welded to the ends of the longitudinal sides of the curved plate (1) at an angle to its plane, intended for positioning the cradle (Fig. 1) on the molded cradle (32) of the container. Each trapezoidal plate (2) has a rectangular cutout (6) of such a size that it can accommodate the clamp mounting bracket (35). On one edge of each trapezoidal plate (2) there is a bracket (7) for connection with one fork (27) of the stretch lanyard (Fig. 4), on the opposite - two U-shaped plates (8), which are the basis for the rotary bracket located between them (9) with screw stop (10). To fix the rotating bracket (9), stoppers (11) are used. Nuts (12) are used to lock the screw stops.

The clamp (Fig. 2) is designed to cover the upper part of the solid propellant motor housing and ensure fixation of its position above the support area (40) (the area of contact of the engine housing with the cradle). The clamp is a curved steel strip (13), onto the flat surfaces of which rubber (14) is pressed. Cylinders (15) are welded to the ends of the tape (13), to which the attachment points of the clamp to the brackets (35) on the molded container supports are attached. Each fastening unit consists of a transverse strip (16) with a hole (17) and two side strips (18). The parts of the fastening unit are connected to each other by axes (19).

The platform (Fig. 3) is a rectangular steel plate (20), the opposite short sides of which are shaped like trapezoids and bent upward. A pair of brackets (23) located opposite each other are welded to each bent part of the plate. The width of the central flat part of the slab allows the housing of a stacked solid propellant rocket motor of a given diameter to be placed. In the central flat part of the plate (20) there are six holes (21) for bolts for attaching the platform to the base of the container, and two pairs of stops (22) are welded. The stops (22) are designed to provide the possibility of unfastening solid propellant rocket motor bodies that have protruding parts on the body, such as rigging units or yokes.

The stretcher (Fig. 4) is designed to provide axial fixation of the solid propellant rocket engine body placed on supports, and is a lanyard connected to a chain. The lanyard (24) consists of a coupling (25) and two screw rods (26), the ends of which end in forks (27). One fork (27) of the lanyard is used to connect to the bracket (7) of the trapezoidal plate (2), the second fork (27) of the lanyard is used to connect to the loop (30) of the tension chain (29). To lock the rods (26) relative to the coupling (25), nuts (28) are used. Loops (30) are installed at the ends of the chain (29) using pins (31). One loop serves as a connecting link between the chain (29) and the fork (27) of the lanyard (24), the other - between the chain (29) and the bracket (23) of the platform plate (20).

To implement the method of laying and unfastening the solid propellant rocket motor body, the platform, supports, braces and clamps are installed in the shipping container as shown in Fig. 5.

Between the molded housings (32) of the body, which are located at its end edges, a platform (Fig. 3) is installed at the base of the container using six bolts (33) screwed through the holes (21) of the plate (20).

On the upper (horizontal) surface of each molded cradle (32) there are two brackets (35) for attaching clamps, located opposite each other. The clamp fastening bracket (35) is a base in the form of a rectangular metal plate, to which two vertical plates with coaxial holes are welded for installing a pin (36) for fixing the clamp. At the base of the bracket there are mounting holes intended for installing screws for fastening the bracket to the horizontal surface of the molded container cradle.

The concave surface of each molded cradle (32) is equipped with a rubber gasket (34).

Cradles are installed on the molded cradle (32), positioning them in such a way that the metal plate (1), bent in the form of a ring segment, rests with its convex side on the rubber gasket (34) of the molded cradle (32), the end stops (5) are located in their intended positions. places on the molded cradle (32), ensuring positioning of the cradle in its lower convex part, trapezoidal plates (2) were located on the upper horizontal surface of the molded cradle, and rectangular cutouts (6) in the trapezoidal plates (2) corresponded to the locations of the brackets (35) on the upper (horizontal) surface of each molded cradle, as a result of which the brackets (35) will be located inside the cutouts (6).

Next, four stretchers (Fig. 4) are attached between the platform (Fig. 3) and the cradle (Fig. 1) (pre-installation, without tension) so that the fork (27) of the lanyard is docked to the bracket (7) of the cradle, and to the bracket ( 23) the platform was docked with a loop (30).

Then the solid propellant rocket motor body is placed on the supports, while contact of the body with the supports occurs in the support areas (40) of the housing, which are located at its end edges. The layout of the solid propellant rocket motor body is shown in Fig. 8-10.

Next, clamps are installed (pre-installation, without tension), covering the engine housing from above the cradle. The installation diagram is shown in Fig. 6-7. To install the clamps, studs (36) are used, which are installed in the brackets (35) and secured with stoppers (37). The crossbar (16) is installed through the hole (17) onto the stud (36), then the nut (38) is screwed on.

To prevent axial movement of the solid propellant motor body relative to the cradle, the solid propellant motor body is pressed with four screw stops (10): the rotary brackets (9) are fixed in the U-shaped plates (8) using stoppers (11), the screw stops (10) are screwed into the rotary brackets (9 ) all the way to the end surface of the housing, followed by locking with nuts (12).

Next, uniform tension is applied to the four stretch marks (Fig. 4) by twisting the couplings (25) of the turnbuckles (24). The locking of the forks (27) of the turnbuckles (24) is carried out with nuts (28). The trapezoidal shape of the plates (2) of the cradle is due to the direction of the braces at an angle relative to the platform, which ensures uniform distribution of force on the brackets (7) when tensioning the braces.

Then the solid propellant rocket motor body is secured to the supports by tensioning the clamps. The tension of the clamp is ensured by uniform tightening of the nuts (38).

Then install the lid on the base of the container and secure it in the closed position with locks.

The described method allows the use of standard containers, originally designed for certain sizes of solid propellant rocket motor housings, also for solid propellant motor housings of smaller diameters, without loss of quality in the standards of their storage and transportation (with respect to the tightness, shape, dimensions and weight of the container, etc.).

Examples of method implementation

There is a container with a landing surface (molded lodgements with a rubber gasket installed on them) with a diameter of 390 mm to accommodate the solid propellant rocket motor housing, the diameter of which, accordingly, is 390 mm. The inventive method makes it possible to use the same container for laying and unfastening solid propellant rocket bodies of smaller diameters, for example, 350 mm and 300 mm. A diagram of examples of laying housings of different diameters is presented in Fig. 10.

Example 1. Method of laying and unfastening a solid propellant rocket motor body with a diameter of 350 mm into a container having a diameter of the seating surface of the molded cradle of 390 mm.

To implement the method, a platform (Fig. 3) in the form of a steel plate (20) is attached to the base of the container between the molded cradle (32) using a bolted connection. On the upper surface of each molded cradle (32) there are two brackets (35) located opposite each other. Cradles (Fig. 1) are installed on the molded cradles (32) of the container with a rubber gasket (34) installed on them, the fixation of which is ensured by stops (5) and the location of the brackets (35) for fastening the clamps in the areas of rectangular cutouts (6). The thickness of the metal plate (1) curved in the form of a half ring is 5 mm, the thickness of the rubber gasket (3) is 15 mm. Then the guy wires are installed (Fig. 4). Next, lay the solid propellant rocket motor body (manually or mechanically) and tighten it with screw stops (10). Then clamps are installed (Fig. 2), the solid propellant rocket motor body is fixed to prevent its axial movement inside the container, pressing it with screw stops (10). Tension is applied to the braces and clamps, finally fixing the solid propellant rocket motor body of a given diameter. Next, close the shipping container with a lid and secure it with locks. The laying and unfastening of a solid propellant rocket body with a diameter of 350 mm produced by the proposed method provides conditions for its storage and transportation in a container having a diameter of molded supports of 390 mm.

Example 2. Method of laying and unfastening a solid propellant rocket motor body with a diameter of 300 mm into a container having a seating surface diameter of 390 mm.

The steps for implementing the method are similar to those described in Example 1. The thickness of the metal plate (1) bent in the form of a half ring is 10 mm, the thickness of the rubber gasket (3) is 35 mm. The laying and unfastening of a solid propellant rocket body with a diameter of 300 mm produced by the proposed method provides conditions for its storage and transportation in a container having a diameter of molded supports of 390 mm.

The industrial applicability of the proposed method is confirmed by the serial use of containers for laying and unfastening solid propellant rocket bodies of various diameters. Based on the results of transport tests of containers with solid propellant motor housings placed in them, it was established that this method is applicable for transporting and storing solid propellant motor housings of various diameters without their displacement inside the transport container and damage.

Claims (8)

1. A method for laying and securing the body of a solid fuel rocket engine in a shipping container containing a base with a landing surface in the form of molded cradle, equipped with rubber gaskets on the concave surface and brackets for fastening clamps located opposite each other on the upper horizontal surface, as well as a cover fixed to the base , which consists in attaching a platform equipped with means of connection with guy wires to the base of the container; on the molded cradles, cradles are installed in the form of curved metal plates equipped with rubber gaskets on the concave side and trapezoidal plates welded at an angle to the ends of the short sides, while each trapezoidal plate is located opposite the bracket fastening bracket and is equipped on one side with a means of connection with guy wires, and on the opposite side with a means of preventing axial movement of the rocket engine body, the guy wires are attached between the platform and the cradles, the body of the solid fuel rocket engine is laid on the cradles, and secured using the brackets clamps covering the engine body above the cradle fix the solid fuel rocket engine body by means of preventing axial movement, produce uniform tension on the braces, produce uniform tension on the clamps, install the lid on the base of the container and fix it. 2. The method according to claim 1, characterized in that the platform is made in the form of a steel plate, the opposite short edges of which are bent upward, and brackets welded to each of the bent parts of the plate serve as a means for connecting the platform with guy wires. 3. The method according to claim 1, characterized in that the platform is secured in the center of the container base with a bolted connection. 4. The method according to claim 1, characterized in that the cradles are installed on molded cradles using end stops welded to the ends of the longitudinal sides of the plate bent into a half ring at an angle to its plane. 5. The method according to claim 1, characterized in that the guy wires are made in the form of lanyards connected to a chain, with one fork of the lanyard serving to connect to the bracket of the trapezoidal plate of the lodgement, the second fork of the lanyard to connect to one loop of the guy chain, the second loop guy wire is connected to the platform bracket. 6. The method according to claim 1, characterized in that each trapezoidal plate of the cradle contains a welded bracket as a means of connection with the brace, and as a means of preventing axial movement of the solid fuel rocket engine housing - two U-shaped plates, which are the basis for the one located between them a rotating bracket equipped with a stopper and having a screw stop. 7. The method according to claim 1, characterized in that the trapezoidal plate of the cradle has a cutout corresponding to the location of the clamp mounting bracket on the upper surface of the molded cradle. 8. The method according to claim 1, characterized in that the clamps are made in the form of a bent steel sheet tape with rubber pressed onto its flat surfaces.

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