RU2374480C2 - Mixed rocket propellant charge and method of its production - Google Patents

Abstract

FIELD: rocketry.

SUBSTANCE: rocket propellant charge comprises casing with nozzle face, mixed rocket propellant charge (MRPC) furnished with at least one element reducing the charge combustion time and insert arranged in the casing, on the side of nozzle face, to form preset-size through gaps and furnished with through perforation. Every element reducing the charge combustion time is oriented in MRPC volume with the help of thread-like element with its one end fixed in aforesaid insert and the other one attached to the casing front face. Insert and every element reducing the charge combustion time are made from propellant or polymer material with higher combustion rate compared to that of MRPC. Invention covers also the method of producing above described charge.

EFFECT: higher efficiency, ease of manufacture and safety.

5 cl, 2 dwg, 2 ex

Description

The group of inventions relates to rocket technology and can be used to create operational-tactical missiles, air-to-air missiles, multiple launch rocket systems, missiles such as PTU PC, grenade launchers, etc.

The prior art known charge mixed propellant (CPT) according to US patent No. 3300549 (publ. 01.24.1967), adopted for the prototype, comprising a housing, a fuel charge, equipped with at least one non-removable forming element.

A known charge, with the advantage of changing the nature of combustion from the end to the channel, has significant disadvantages:

- reduced charge efficiency due to the use of solid fuel checkers with reduced energy characteristics;

- the inability to use as the main high-energy low-modulus fuel (there are no structural elements that hold the fuel in the body);

- the complexity and increased danger of manufacturing a charge due to the use of explosives in the design.

In the same patent all describes a method of manufacturing a charge that is closest to the proposed one, which involves placing at least one forming element in the charge, filling the housing with fuel.

In the known method, before filling the body with main fuel, several technological processes are carried out: small solid fuel checkers are made, axial holes are made in them, they are equipped with explosive rods, small pieces are glued into one large one, which is centered in the body volume, which determines the complexity and duration of the process . The prototype method has an increased risk due to the use of three fuels in the manufacturing process of a charge: solid fuel for drafts, explosive rods and main charge fuel. In addition, the known method does not allow you to use as the main low-modulus fuel, because It does not include actions to ensure retention of this type of fuel in the volume of the body. The implementation of the prototype method does not allow to produce a highly efficient charge.

As a group of inventions, a CPT charge and a method of its manufacture are proposed that solve the same problem - increasing the charge efficiency when using it, increasing manufacturability and manufacturing safety by implementing conditions to ensure the possibility of using low-modulus fuel with a wide range of elastic modulus up to plastic while providing a dual-mode process of charge operation (starting and marching modes) in a monoblock fuel.

The problem is solved by the proposed CPT charge, comprising a housing, a fuel charge equipped with at least one forming element, which reduces the operating time. The peculiarity lies in the fact that the forming element is made of a polymeric material with a higher burning rate than that of CPT, is rigidly fixed in the body volume in an oriented position by means of a threadlike element, while the charge is equipped with an end insert with through perforation fastened along part of its side surface with the formation of through gaps of a given size.

The quantity, configuration and placement in the fuel volume of the forming elements is selected from the condition of ensuring the march mode of charge operation.

In particular, the filamentary element is made of metal or fibrous material.

In particular, the surface of the end liner facing the fuel is provided with protrusions and / or grooves, and / or other geometric shapes, the number, configuration, and placement of which are selected from the condition of ensuring the starting charge operation mode.

A comparative analysis shows that the claimed charge of the CPT differs from the closest analogue by fixing each forming element in the body volume by means of a filiform element (in the prototype, each forming element is fixed in a checker), the material used to make the forming element can be varied by the presence of an end insert with a developed surface.

The CPT charge of rocket fuel is produced by a method involving the placement in the charge of at least one forming element, filling the body with fuel. The peculiarity lies in the fact that each forming element is rigidly fixed in the body volume in an oriented position by means of a threadlike element, while before filling the body with fuel, a perforated end insert is installed in it and fastened along part of the side surface with the body with the formation of through gaps of a given size.

A comparative analysis shows that the inventive method of manufacturing a CPT charge differs from the closest analogue by the different organization of fixing in the body volume of each forming element — by means of a filamentary element (in the prototype — in the volume of a solid fuel checker) and the presence of an operation to install an end insert.

The proposed mixed propellant charge is illustrated by graphic images:

Figure 1 is a longitudinal section of the charge.

Figure 2 is a view of the charge from the side of the end liner.

The charge includes a housing 1, CPT 2, forming elements 3, fixed in the volume of the housing 1 by means of threadlike elements 4. The charge is equipped with an end insert 5 with holes 6, protrusions 7 and gaps 8. The insert 5 is fastened to the housing 1 along part of its side surface 9.

During storage and operation, fuel 2 is affected by gravity and various overloads. Fastened to the housing 1, the end sleeve 5 with holes 6 and gaps 8, the dimensions of which prevent the outflow of CPT 2, encapsulates it in the volume of the housing 1 and prevents the possibility of its displacement towards the nozzle (not shown conditionally).

The charge of the proposed design works as follows. After the igniter has been triggered (not shown conditionally), the fuel 2 is first ignited in the holes 6 and the gaps 8 of the liner 5. Then the flame breaks along the inner surface of the liner 5. A large surface of the CPT 2 formed by the projections 7 is involved in the combustion process. work charge. Then there is a slip of the flame along the forming elements 3, the axial channel is lengthened, and the high initial surface formed by the protrusions 7 is leveled. Further charge burnup occurs in marching mode at a lower combustion surface than the initial one. In this case, the nature of the charge burning will be channel, the combustion surface will be higher than that of the end charge, and the burning time is much shorter. As experiments have shown, the threadlike element 4 of a fibrous material (for example, of cotton fiber) does not affect the nature of combustion, and made of metal (for example, copper or aluminum) can significantly increase the burning rate of CPT 2.

The proposed design is tested on the charge of the experimental low-modulus fuel using the end liner and the forming element. The charge had dimensions: length 150 mm, diameter 60 mm.

Example 1. The end liner and the forming element was made of expanded polystyrene. A 4 mm thick insert had an annular protrusion 20 mm high and perforation holes with a diameter of 4 mm. A molding element with a diameter of 15 mm and a length of 30 mm was fixed along the axis of the body on a cotton thread with a diameter of 0.8 mm at a distance of 100 mm from the liner. The burning time of such a charge was reduced in comparison with the control (without the forming element) from 6 to 3.2 s.

When a filamentous element made of copper was used in a similar charge, the burning time of the charge decreased in comparison with the control from 6 to 2.5 s.

The pressure-time curve in all cases had a bimodal character.

Example 2. The liner and the forming element, structurally made, as in example 1, was made of fast-burning (50 mm / s at P = 9.8 MPa) fuel "Frame". The forming element was fixed by means of a cotton thread. The burning time of such a charge decreased from 6 to 2.8 in comparison with the control charge (without the forming element). When a forming element was connected to combustion, a characteristic peak was present on the pressure curve.

The proposed method, tested in the manufacture of the inventive charge of CPT, is as follows.

The forming element (or elements, depending on the present need) is fastened with a threadlike element. In this case, the forming elements can be strung and fixed on a thread-like element, and can be connected by a thread-like element between themselves. One end of each threadlike element is fixed in the end liner. The entire assembly is inserted into the housing, and the insert is fastened to the housing from the nozzle end side. A technological cover is installed on the front end of the housing. Through it, the free end of each threadlike element is brought out, which is rigidly fixed to ensure that each forming element is held in an oriented position. From the side of the end liner, a technological cover is fitted tightly adjacent to the liner. Then the housing is filled with fuel, which, if necessary, is cured. After that, the charge is ready for flaw detection and assembly into the engine.

Thus, the claimed charge of CPT and the method of its manufacture are practically feasible, can satisfy a long-standing need for solving the problem.

Claims (5)

1. The charge of rocket fuel containing a housing with a nozzle end face, the charge of mixed rocket fuel (CPT), equipped with at least one element to reduce the burning time of the charge of rocket fuel, characterized in that it contains a liner placed in the housing from the nozzle end side, fastened to the housing along part of its side surface with the formation of through gaps of a given size and made with through perforation, each element to reduce the burning time of the charge of rocket fuel is oriented in the volume for CPT venom by threadlike element, one end of which is fixed in the insert, and the other end is secured by the front end of the housing, the insert and each element to minimize the time of burning propellant charge or fuel made of polymeric material burning faster than the charge CPT. 2. The charge according to claim 1, characterized in that the elements to reduce the burning time of the charge of rocket fuel are oriented in the volume of the charge of the CPT with the marching mode of operation of the charge of rocket fuel. 3. The charge according to claim 1, characterized in that the filamentary element is made of metal or fibrous material. 4. The charge according to claim 1, characterized in that the surface of the liner on the side facing the charge of mixed propellant is made with protrusions and / or grooves. 5. A method of manufacturing a rocket fuel charge, comprising placing at least one element in the housing with the nozzle end to reduce the burning time of the rocket fuel charge, filling the CPT housing with the formation of a CPT charge, characterized in that placing at least one element in the housing to reduce the burning time of the charge of rocket fuel is carried out with orientation by means of a filamentary element, while in the case from the nozzle end side, an insert made with through perforation is placed th, and fasten it to the housing along part of the side surface with the formation of through gaps of a given size, and the liner and each element to reduce the burning time of the rocket fuel charge is made of fuel or polymer material burning faster than the charge of the CPT, at the front end of the housing set technological the cover, one end of the threadlike element is fixed in the liner, and the other end is fixed in the technological cover, then the technological adjacent to the liner is installed on the housing from the insert Ryshkov.

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