RU101501U1 - MISSION MODEL ENGINE FOR SUBMARINE RUNNING - Google Patents

Abstract

 1. An underwater launch model rocket engine containing a combustion chamber with a nozzle block mounted on the rear bottom, a solid fuel charge from tubular cylindrical blocks and a charge ignition system with a pyro cartridge, characterized in that the combustion chamber is made in the form of two or three pipes, hermetically and rigidly, for example, by welding mounted on the rear bottom parallel to each other along the longitudinal axis of the engine, forming with its internal cavities together with the pre-nozzle volume a common intracameral volume the engine’s combustion chambers, and the tubular cylindrical charge checkers placed in pairs one above the other with a given clearance are made armored: some according to the outer diameter of the checkers, and others along the internal channel of the checkers, while the charge ignition system contains three ignitors installed: the first one between the squib and the checker armored by the inner channel and mounted above the checker armored by the outer diameter, the second - under the checker armored by the inner channel and located at the bottom of goy pipe of the combustion chamber, and the third - the top of this same tube on the saber armored OD and mounted above the saber armored the internal channel. ! 2. The engine according to claim 1, characterized in that the rear bottom of the engine is equipped with a shank serving as the bottom of the rocket model.

Description

The utility model relates to the field of experimental bench testing of the hydrodynamics of an underwater launch of missiles, and more particularly to the design of engines of rocket models for working off an underwater launch.

The proposed utility model is intended for use in developing an underwater launch of missiles by catapulting rocket models from a model launcher under the influence of engine thrust.

There are known designs of model rocket engines [1-7], which, due to their specificity, cannot be used to test parameters of missiles with underwater launch, because they solve other problems.

The known design of a model engine [8] (p. 120, Fig. 60), containing a thick-walled pipe, safety valve, bottom, copper gasket, nozzle block.

Also known is the design of a model engine [8] (p. 128, Fig. 63), which includes a housing, a head, a shank, a diaphragm, an insert nozzle, a compression sleeve, a fitting, an arm. The disadvantages of the above devices is that the housing of the combustion chamber is made of a thick-walled pipe, and this leads to an increase in the weight and moment of inertia of the engine and, accordingly, the model of the rocket in which it is mounted. Despite these shortcomings, the design of the model engine [8] (p. 128, Fig. 63) can be taken as a prototype.

The technical result aimed at eliminating these shortcomings is the creation of a rocket model engine for working off an underwater launch, which allows:

- reduce the weight and moment of inertia of the engine and, accordingly, the model of the rocket in which it is installed;

- improve the centering characteristics of the rocket model and reduce its moment of inertia;

- use in the experiment powder bombs mass-produced by industry, and not create special ones;

- increase engine operating time by lengthening the combustion chamber when placing the required amount of solid fuel in it.

The specified technical result is achieved by the fact that the patented rocket model engine for developing an underwater launch comprises a combustion chamber with a nozzle block mounted on the rear bottom, a solid fuel charge from tubular cylindrical blocks and a charge ignition system with a pyro cartridge. The combustion chamber is made in the form of two or three pipes, hermetically and rigidly (for example, by welding) mounted on the rear bottom parallel to each other along the longitudinal axis of the engine, forming with its internal cavities together with the pre-nozzle volume the total intracameral volume of the engine combustion chamber, and placed in pipes in pairs one above the other with a given gap, the tubular cylindrical charge checkers are made armored: some on the outer diameter of the checkers, and others on the internal channel of the checkers. In this case, the charge ignition system contains three igniters installed: the first - between the squib and the checker, armored in the inner channel and installed above the checker, armored in the outer diameter, the second - under the checker, armored in the inner channel and located in the lower part of the other combustion chamber pipe and the third - in the upper part of the same pipe above the checker, armored by the outer diameter and installed above the checker, armored by the internal channel.

The rear bottom of the engine for ease of layout in the rocket model is equipped with a shank serving as the bottom of the rocket model.

The essence of the utility model is illustrated by graphic materials, where:

- figure 1 shows a General view of the engine installed in the rocket model, the combustion chamber of which is formed using two pipes.

- figure 2 shows a section aa in figure 1;

- figure 3 shows a section bB in figure 1;

- figure 4 shows a section bb in figure 1.

The engine of the rocket model for practicing underwater launch, (Figure 1) consists of a combustion chamber formed by the internal cavities of two pipes 1, rigidly and tightly (for example, by welding) installed on the rear bottom 2 of the engine, on which the nozzle block 3 with a replaceable nozzle insert 4 and nozzle plug (membrane) 5. Pipes 1 are placed parallel to each other along the longitudinal axis of the engine and form their internal cavities together with the cavity “C” of the pre-nozzle volume, the total volume of the combustion chamber of the engine.

Depending on the tasks to be solved in the experiment, two or three pipes 1 can be installed in the engine.

The combustion chamber, made using pipes 1, provides the requirements of the modeling procedure for mass inertia characteristics and centering of the rocket model, traction consumption characteristics and engine operating time.

The engine is equipped with a solid fuel charge made in the form of tubular cylindrical powder checkers 6, 7, 8, 9 installed in the pipes 1 of the combustion chamber in pairs one above the other with a given clearance, which is provided by gratings (diaphragms) 10, and a pair of checkers is installed in each pipe , one of which is equipped with an armor (armor plating) 11 applied to the surface of the internal channel, on the other checker armor (armor plating) 12 is applied to the outer (external) surface of the checker. In the above embodiment of the engine with two pipes 1, the checkers 6 and 8 are armored along the internal channel, and the checkers 7 and 9 are armored on the external (external) surface.

To increase the reliability of ignition of the charge from one igniter 13 (installed in the upper part of one of the pipes 1), the ignition system contains three igniters 14, 15, 16. Igniter 14 is installed between the igniter 13 and the checker 6 installed above the checker 7. The second igniter 15 is installed under the checker 8, located in the lower part of the other pipe 1 of the combustion chamber, and the third igniter 16 is above the checker 9. In the upper part of the other pipe 1, a pressure sensor 17 is installed to monitor the pressure in the combustion chamber when the engine is running.

The engine in assembled form is placed inside the rocket model 18. For the convenience of installing the engine in the rocket model, the rear bottom 2 of the engine is equipped with a shank 19, which serves as the bottom of the rocket model.

The rocket model engine operates as follows.

After the electric command is supplied to the igniter 13, it triggers and sequentially activates the igniters 14, 15 and 16. The gases generated from the igniters create the pressure and temperature in the combustion chamber of the engine necessary to ignite the cylindrical powder checkers 6, 7, 8, 9. Checkers 6 and 8 begin to burn from the outer surface, and checkers 7 and 9 from the inner surface of the channel. The combustion products of the checkers create operating pressure in the combustion chamber. After the engine enters the mode and the nozzle plug 5 breaks through, the combustion products expiring through the nozzle block 3 create the reactive force (thrust) necessary for the rocket model to move. During engine operation, a sensor 17 controls the pressure in the combustion chamber.

By varying the number of pipes (two or three) of the combustion chamber, their diameter and length, the size of the blocks, the ratio of the areas of the armored surfaces, the diameter of the critical section of the replaceable nozzle insert, provide the required engine operating modes, and, accordingly, the model motion parameters on the underwater section of the trajectory.

A useful model of a patented engine of a rocket model for working off an underwater launch allows you to: improve the centering characteristics of the rocket model and reduce the moment of inertia, reduce the weight of the engine and, accordingly, the model of the rocket, use in the experiment powder bombs commercially available from the industry, increase the engine operating time by lengthening the combustion chamber placing in it the number of solid fuel drafts required for the experiment.

Information sources:

1. Patent SU 81772. Model rocket engine, cl. IPC F02K 9/08 (2006.01), F42B 15/10 (2006.01). Priority 03/27/2008

2. Patent RU 76815. Model rocket engine, cl. IPC A63H 27/26 (2006.01), F42B 15/10 (2006.01). Priority 03/27/2008

3. Patent RU 2215170. Model engine for determining the burning rate of solid rocket fuel, cl. IPC F02K 9/96 (2006.01). Priority 04/05/2002

4. Patent RU 2201520. Model engine for determining the rate of combustion of TRT in a stress-strain state, Priority dated January 29, 2002.

5. Patent SU 2362605. Model rocket engine, cl. IPC F02K 9/70 (2006.01), A63H 27/00 (2006.01). Priority May 23, 2007

6. Patent SU 2362604. Model rocket engine, cl. IPC F02K 9/12 (2006.01), А63Н 27/00 (2006.01). Priority June 25, 2007

7. Patent SU 2341314. Model rocket engine, cl. IPC A63H 27/00 (2006.01), F02K 9/70 (2006.01). Priority May 23, 2007

8. V.A. Emelyanov, G.P. Ivanov, Yu.V. Mikhailovsky, A.I. Salomykov Guide to laboratory work on the theory of jet engines. Edition of the Ministry of Defense of the USSR, 1968

Claims (2)

1. An underwater launch model rocket engine containing a combustion chamber with a nozzle block mounted on the rear bottom, a solid fuel charge from tubular cylindrical blocks and a charge ignition system with a pyro cartridge, characterized in that the combustion chamber is made in the form of two or three pipes, hermetically and rigidly, for example, by welding mounted on the rear bottom parallel to each other along the longitudinal axis of the engine, forming with its internal cavities together with the pre-nozzle volume a common intracameral volume the engine’s combustion chambers, and the tubular cylindrical charge checkers placed in pairs one above the other with a given clearance are made armored: some according to the outer diameter of the checkers, and others along the internal channel of the checkers, while the charge ignition system contains three ignitors installed: the first one between the squib and the checker armored by the inner channel and mounted above the checker armored by the outer diameter, the second - under the checker armored by the inner channel and located at the bottom of goy pipe of the combustion chamber, and the third - the top of this same tube on the saber armored OD and mounted above the saber armored the internal channel. 2. The engine according to claim 1, characterized in that the rear bottom of the engine is equipped with a shank serving as the bottom of the rocket model.