KR101063793B1 - Promotion Organization - Google Patents

Abstract

The present invention is a combustion tube having a propellant therein; An igniter disposed in the combustion tube and igniting the propellant; An output nozzle mounted at one end of the combustion tube and configured to discharge propellant gas; And a sealing member disposed inside the output nozzle and configured to discharge the combustion gas generated in the igniter after a predetermined time stays in the combustion tube, and the sealing member is elastically deformed by the combustion gas by a predetermined amount. The present invention relates to a propulsion engine configured to rupture, and to improve the ignition performance and increase the reliability of the propulsion engine by increasing the combustion gas residence time inside the combustion tube.

Description

Propulsion Institution {PROPULSIVE EQUIPMENT}

The present invention relates to a propulsion engine having improved ignition performance by increasing the residence time of combustion gases generated in the igniter.

The propulsion engine is a device that provides power to move the payload to the target position. Recently, a lot of research is being conducted on the propulsion engine that can move payload more accurately in the aerospace industry and guided weapon field.

Generally, a propellant is filled with a propellant located therein, and a propellant is ignited by an igniter to generate combustion gas. The propulsion engine is operated by the thrust generated as the combustion gas is discharged to the outside.

When the igniter of the propulsion engine is located near the output nozzle for discharging the combustion gas, the time for which the combustion gas generated in the igniter stays in the combustion chamber is shortened, thereby reducing the efficiency of the ignition energy delivered to the propellant. .

In addition, not only the efficiency of the ignition energy is lowered, but the proper pressure necessary for the combustion of the ignition agent and the propellant is not formed in the combustion chamber, and thus, the development speed of the flame is lowered, thereby causing a problem that the thrust generation time is delayed or the ignition is not performed.

At present, various attempts have been made to solve the above problems in the field of propulsion engines.

The present invention is to solve the above problems, to improve the ignition performance and to improve the reliability of the propulsion engine by increasing the combustion gas residence time inside the combustion tube of the propulsion engine.

The present invention for achieving the above object is a combustion tube having a propellant therein; An igniter disposed in the combustion tube and igniting the propellant; An output nozzle mounted at one end of the combustion tube and configured to discharge propellant gas; And a sealing member disposed inside the output nozzle and configured to discharge the combustion gas generated in the igniter after a predetermined time stays in the combustion tube, and the sealing member is elastically deformed by the combustion gas by a predetermined amount. Disclosed is a propulsion engine configured to rupture.

The output nozzle is fixed to one end of the combustion tube; A nozzle reduction unit extending from the fixing unit and formed to have a narrower cross-sectional area than the fixing unit; And a nozzle neck extending to open at an end portion of the nozzle reduction part by a predetermined size.

The sealing member may be configured to elastically deform to the position of the nozzle reducing portion by the combustion gas, and then rupture an area corresponding to the position of the nozzle neck.

A reinforcing member may be further provided between the igniter and the sealing member to support the pressure transmitted to the sealing member for a predetermined time after the operation of the igniter.

The reinforcing member may be a combustible paper having a thickness capable of supporting the pressure of the combustion gas and configured to extinguish after being combusted for a predetermined time.

An auxiliary ignition agent for ignition of the propellant may be additionally provided in the reinforcing member.

According to the present invention, a ruptured sealing member that expands to a predetermined pressure and then ruptures is mounted on a combustion tube to increase combustion gas residence time inside the combustion tube, thereby improving ignition performance and improving reliability of the propulsion engine.

In addition, the present invention can increase the burst pressure by configuring the burst in the nozzle neck portion of the sealing member.

In addition, the present invention can provide a reinforcing member between the igniter and the sealing member to suppress the expansion of the sealing member at the beginning of the ignition, thereby stably spreading the flame at the initial ignition.

In addition, by providing an auxiliary ignition agent in the reinforcing member, it is possible to improve the ignition performance of the propulsion engine.

EMBODIMENT OF THE INVENTION Hereinafter, the propulsion engine which concerns on this invention is demonstrated in detail with reference to drawings.

1 is a perspective view of a propulsion engine according to an embodiment of the present invention, and FIGS. 2A and 2B are cross-sectional views of the propulsion engine shown in FIG. 1.

The propulsion engine 100 according to the present embodiment includes a combustion tube 110, an igniter 120, and a sealing member 130.

Combustion tube 110 is formed in the form of a cylinder having an inner space. The inside of the combustion pipe 110 is provided with a propellant 111 for generating a thrust of the propulsion engine. The propellant 111 may be filled in the combustion tube 110 in a solid form. An opening may be formed at one end of the combustion tube 110, and an output nozzle 140 may be mounted at the opening to discharge combustion gas generated by the combustion of the propellant 111.

The output nozzle 140 may include a fixing part 141 fixed to the opening, a nozzle reducing part 142 extending from the fixing part, and a nozzle neck 143 extending from the nozzle reducing part 142.

The fixing part 141 is fixed to the main surface of the opening to surround the outer circumferential surface of the combustion tube 110. In addition, the nozzle reducing part 142 is formed to have a narrower cross-sectional area than the fixing part 141, and the nozzle neck 143 extends to be opened by a predetermined size at the end of the nozzle reducing part 142.

The igniter 120 is for igniting the propellant 111 and is disposed inside the combustion tube 110. The igniter 120 may be disposed at the rear end of the combustion tube 110 and may be mounted on a mounting groove formed in the propellant 111.

The igniter 120 may include an igniter body 121, a igniter 122, and an ignition agent 123.

The igniter body 121 constitutes an appearance of the igniter 120 and has a space therein. The igniter 122 and the ignition agent 123 are disposed in the igniter main body 121.

The igniter 122 is configured to ignite the ignition agent 123 by an electrical signal, and the flame generated from the ignition agent 123 ignites the propellant 111.

The sealing member 130 is disposed to seal the opening and discharges the combustion gas generated as the ignition agent 123 of the igniter 120 is burned for a predetermined time.

The sealing member 130 is formed to be elastically deformable and is configured to rupture after being elastically deformed by a predetermined amount by the combustion gas of the ignition agent 123. Combustion gas of the ignition agent 123 is discharged to the outside of the combustion tube 110 through the ruptured portion of the sealing member 130. As the material of the sealing member 130, a heat resistant rubber capable of withstanding the heat of the combustion gas may be used.

The sealing member 130 includes a support part 131 supported by the inner circumferential surface of the combustion tube 110 and a cover part 132 covering the branch opening. Here, the cover part 132 is bent and extended at the end of the support part 131.

The sealing member 130 is configured to elastically deform as shown in FIG. 2B by the combustion gas of the ignition agent 123 in the state of FIG. 2A. Here, the cover part 132 is elastically deformed to the position of the nozzle reducing part 142 and is supported by the nozzle reducing part 142.

When the internal pressure of the combustion tube 110 becomes a predetermined value or more, the cover part 132 is configured to rupture only an area corresponding to the position of the nozzle neck 143.

3 is a photograph showing the sealing member 130 ruptured only the area corresponding to the position of the nozzle neck 143. The sealing member 130 may have a high elastic material that can be elastically deformed up to the position of the nozzle reducing part 142. For this purpose, the sealing member 130 preferably has a strain of 400% or more.

A reinforcement member 150 may be additionally provided between the igniter 120 and the sealing member 130 to support the pressure transmitted to the sealing member 130 for a predetermined time after the igniter 120 is operated.

4A is a plan view of the reinforcing member shown in FIGS. 2A and 2B, and FIG. 4B is a cross-sectional view of the reinforcing member of FIG. 4A.

The reinforcing member 150 may be implemented in the form of combustible paper having a thickness capable of supporting the pressure of the combustion gas of the igniter 120. The reinforcing member 150 may be a paper containing 80% or more of gunpowder (for example, Nitorcellulose).

The reinforcing member 150 is configured to burn as the igniter 120 generates a flame, and is extinguished after being burned while supporting the pressure of the combustion gas for a predetermined time.

An auxiliary ignition agent 151 for ignition of the propellant 111 may be disposed in the reinforcing member 150. A plurality of through holes may be formed in the reinforcing member 150, and the auxiliary ignition agent 151 may be filled in the through holes. The through-holes are arranged in a plurality of places of the reinforcing member 150 to be evenly distributed on the combustion surface of the propellant 111. Covers 152a and 152b may be attached to both sides of the reinforcing member 150 to prevent the auxiliary ignition agent 151 from leaking out.

The propulsion engine according to the present embodiment may be manufactured by a method of fixing the sealing member 130 after covering the opening with the reinforcing member 150 in a state where the igniter 120 is fixed to the mounting groove. Here, the sealing member 130 may be fixed by the elastically deformable adhesive 112.

Hereinafter, the operation state of the propulsion engine related to the present invention will be described based on the description of the configuration of the propulsion engine.

In the state of FIG. 2A, the igniter 122 ignites the ignition agent 123 by an electrical signal, and thus combustion gas is generated in the ignition agent 123.

The combustion gas generated from the ignition agent 123 provides ignition energy to the propellant 111 such that the propellant 111 is ignited. Here, the combustion gas increases the pressure inside the combustion tube 110, and provides a pressure for expanding the sealing member 130.

In this process, the reinforcing member 150 supports the pressure delivered by the combustion gas to the sealing member 130 at the initial stage of ignition. That is, the reinforcing member 150 suppresses the expansion of the sealing member 130 for a predetermined time for the stable diffusion of the flame at the initial ignition. As a result, a pressure drop around the igniter can be prevented from affecting the flame spread.

In addition, the auxiliary ignition agent 151 disposed inside the reinforcing member 150 additionally provides ignition energy to the propellant 111 so that the propellant can be stably ignited. That is, the auxiliary ignition agent 151 functions to supplement the ignition performance of the igniter 120.

5A and 5B are photographs comparing the degree of expansion of the sealing member in a state where the reinforcing member 150 is mounted and not.

When the reinforcing member 150 is mounted as shown in FIG. 5A, the expansion of the sealing member 130 is suppressed at the initial stage of ignition. However, when the reinforcing member 150 is not mounted as shown in FIG. 5B, the sealing member 130 is initially opened. Swelled. As such, the reinforcing member 150 prevents a pressure drop phenomenon due to the expansion of the sealing member 130 at the initial stage of ignition.

When the reinforcing member 150 is completely burned, the sealing member 130 is expanded by the pressure of the combustion gas. The sealing member 130 is elastically deformed to the position of the nozzle reducing part 142 to be in close contact with the nozzle reducing part 142. When the pressure inside the combustion tube 110 reaches a predetermined value or more, the sealing member 130 is ruptured so that the combustion gas is discharged to the outside of the combustion tube 110. Here, the sealing member 130 is ruptured the area corresponding to the position of the nozzle neck 143 as described above.

As described above, the discharge of the combustion gas may be suppressed until the burst pressure of the sealing member 130 is reached, thereby increasing the time for which the combustion gas stays inside the combustion tube 110. Accordingly, the efficiency of the ignition energy delivered to the propellant by the combustion gas can be improved.

Here, the sealing member 130 may be configured to expand to the nozzle reducing portion as much as possible, thereby maximizing the bursting pressure reaching time of the sealing member 130. As the sealing member 130 is in close contact with the nozzle reducing part 142, the bursting effective surface of the sealing member 130 may be reduced within the diameter of the nozzle neck 143 to increase the burst pressure of the sealing member 130.

In addition, as the burst of the sealing member 130 is concentrated on the nozzle neck 143 portion, the burst may be made within a relatively constant pressure range, thereby increasing the ignition reliability of the propulsion engine.

6 shows the pressure inside the combustion tube 110 in the state where the sealing member 130 and the reinforcing member 150 are mounted, and the inside of the combustion tube 110 in the state where the sealing member 130 and the reinforcing member 150 are not mounted. It is a graph comparing pressure. 6, the thick line represents the case where the sealing member 130 and the reinforcing member 150 are mounted, and the thin line represents the case where the sealing member 130 and the reinforcing member 150 are not mounted.

Referring to FIG. 6, the time required for the pressure inside the combustion tube 110 to reach the reference value or more at the time of supplying the ignition power is 200ms when the time is 'not installed', whereas when it is 'mounted', the improvement is 20ms. It can be seen that.

Combustion gas generated from the propellant 111 is discharged to the outside of the combustion tube 110 through the ruptured portion of the sealing member 130, so that the propulsion engine obtains a propulsion force.

In the above description, the propulsion engine according to the present invention has been described with reference to the accompanying drawings, but the present invention is not limited to the embodiments and drawings disclosed in the present specification, and various modifications are made by those skilled in the art within the scope of the technical idea of the present invention. Modifications can be made.

1 is a perspective view of a propulsion engine associated with one embodiment of the present invention;

2a and 2b are sectional views of the propulsion engine shown in FIG.

3 is a photograph showing a sealing member in which only an area corresponding to the position of the nozzle neck is ruptured.

4A is a plan view of the reinforcing member shown in FIGS. 2A and 2B.

4B is a cross-sectional view of the reinforcing member shown in FIG. 4A.

5a and 5b are photographs comparing the degree of expansion of the sealing member in the state with and without the reinforcing member mounted.

Figure 6 is a graph comparing the pressure inside the combustion tube in the state with and without the sealing member and the reinforcing member is mounted.

Claims (12)

Combustion tube having a propellant therein; An igniter disposed in the combustion tube and configured to ignite the propellant; An output nozzle mounted at one end of the combustion tube and configured to discharge propellant gas; A sealing member disposed inside the output nozzle and configured to discharge the combustion gas generated in the igniter after a predetermined time stays in the combustion tube, and configured to rupture after being elastically deformed by the combustion gas by a predetermined amount; A reinforcing member disposed between the igniter and the sealing member, the reinforcing member being formed to support the pressure transmitted to the sealing member after the igniter is ignited; And The propulsion engine is disposed inside the reinforcing member, characterized in that it comprises an auxiliary igniter to provide additional ignition energy to the propellant. The method of claim 1, wherein the igniter, An igniter body mounted to a mounting groove formed on the propellant and having an ignition agent therein; And A propulsion engine disposed within the igniter body and including a igniter to ignite the ignition agent. The method of claim 1, And the igniter is located at a rear end of the combustion tube. The method of claim 3, wherein the output nozzle, A fixed part fixed to one end of the combustion tube; A nozzle reduction unit extending from the fixing unit and formed to have a narrower cross-sectional area than the fixing unit; And And a nozzle neck extending to open at an end portion of the nozzle reduction portion by a predetermined size. 5. The method of claim 4, And the sealing member is elastically deformed to the position of the nozzle reducing portion by the combustion gas, and then the propulsion engine is configured to rupture only an area corresponding to the position of the nozzle neck. 5. The method of claim 4, The sealing member is characterized in that the propulsion engine having a strain of 400% or more. The method of claim 1, wherein the sealing member, A support part supported by the inner circumferential surface of the combustion tube; And And a cover part extending from the support part and covering the opening of the combustion tube. The method of claim 7, wherein The support and the cover part is a propulsion engine, characterized in that fixed to the combustion tube by an elastic adhesive. delete The method of claim 1, The reinforcing member is a propulsion engine, characterized in that it is made to be able to support the pressure of the combustion gas in the initial stage of the ignition, and is combustible member is formed to be extinguished after the combustion while supporting the pressure. delete The method of claim 1, The reinforcing member is formed with a plurality of through holes made to penetrate from one surface toward the other surface, And the auxiliary ignition agent is filled in the plurality of through holes, respectively.

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