A high efficiency force dissipator

Abstract

The present invention discloses a high-efficiency force isolator, including a shell, a gas chamber channel in the center of the shell for the piston cylinder to pass through, the bottom of the gas chamber channel is connected to a thrust termination device, and the first and second level flow diversion channels and the first and second level flow guide plates are symmetrically arranged on both sides of the gas chamber channel along the movement direction of the piston cylinder, and the top of the gas chamber channel is a contracted piston cylinder outlet. The force isolator of the present application is provided with a two-stage flow diversion channel to divide the fuel gas into five parts, thereby reducing the fuel gas flow at the piston cylinder outlet, and at the same time, the two-stage flow guide plates are used to form a reaction force, thereby reducing the residual thrust and reducing the impact disturbance to the rocket engine at the moment of thrust termination. The measured force elimination efficiency can reach 50%; and the structure is simple, light, and easy to disassemble, and the structure size can be adjusted to adapt to thrust termination devices of different sizes. It provides a new solution for reducing the impact and residual thrust when the thrust of a small solid rocket engine is terminated.

Description

Technical Field

[0001] The invention relates to the field of solid rocket engines, and in particular to a high-efficiency dampener installed at the outlet of a thrust termination device of a small solid rocket engine. Background Art

[0002] Thrust termination is a mature and effective technology for achieving interstage separation of solid rocket engines, adjusting missile range and controlling flight accuracy, and multiple starts or terminations of flight. It is widely used in various large and medium-sized solid rocket engines at home and abroad. The existing small solid rocket engines are subject to space limitations and technical requirements such as decompression rate and thrust output. The thrust termination scheme mainly adopts the decompression flameout method, but this scheme has the following problems:

[0003] a) After the thrust termination device is activated, there is a situation where the charge cannot be extinguished, that is, there is still residual thrust output after the thrust is terminated;

[0004] b) When the thrust termination device is activated, the piston cylinder flies out instantly and the pressure in the combustion chamber drops suddenly, which causes a huge impact disturbance to the small thrust engine. Summary of the invention

[0005] The present invention provides a high-efficiency damper, which adopts a tapered outlet design and divides the residual fuel gas into five by arranging primary and secondary diversion channels, thereby effectively reducing the output of residual thrust and reducing the impact disturbance caused by thrust termination. The damper has the characteristics of simple structure, light weight, easy disassembly and high efficiency.

[0006] To achieve the above object, the present invention adopts the following technical solutions:

[0007] A high-efficiency dampener acts on a rocket engine thrust termination device, comprising a shell, a gas chamber channel in the center of the shell for the piston cylinder to pass through, the bottom end of the gas chamber channel is connected to the thrust termination device, primary and secondary flow diversion channels and primary and secondary guide plates are symmetrically arranged on both sides of the gas chamber channel along the movement direction of the piston cylinder, and the top of the gas chamber channel is a contracted piston cylinder outlet.

[0008] As a preferred embodiment of the above scheme, the shell is a cylindrical structure with openings at both ends, and the bottom end is connected to the thrust termination device through a threaded connection port.

[0009] As a preferred embodiment of the above scheme, the ratio of the sum of the areas of the primary and secondary flow diversion channels to the outlet area of ​​the piston cylinder is 1:1.

[0010] As a preferred embodiment of the above scheme, a conical inclined surface is provided at the lower portion of the piston cylinder outlet.

[0011] As a preferred embodiment of the above solution, the angle between the inclined surface and the center line of the shell is set to 30°.

[0012] As a preferred embodiment of the above scheme, the secondary guide plate is arranged at the top of the secondary diversion channel, and the angle between the secondary guide plate and the center line of the shell is set to 75°.

[0013] As a preferred embodiment of the above scheme, the primary guide plate is arranged at the top of the primary diversion channel, and the angle between the primary guide plate and the center line of the shell is set to 90°.

[0014] Due to the above structure, the beneficial effects of the present invention are:

[0015] (1) A two-stage diversion channel is set up to divide the fuel gas into five parts, reducing the fuel gas flow rate at the piston cylinder outlet. At the same time, a two-stage guide plate is used to form a reaction force, thereby reducing the residual thrust and the impact disturbance to the rocket engine at the moment of thrust termination. The measured force elimination efficiency can reach 50%.

[0016] (2) The setting angle of the secondary guide plate is 75°, which can more effectively utilize the residual gas to form a reaction force, thereby offsetting part of the thrust; the setting angle of the primary guide plate is 90°, which can block the gas returning from the secondary guide plate to a certain extent, avoid damaging other components, and improve the reliability and safety of the diversion process.

[0017] (3) The structure is simple, light, and easy to disassemble. The size of the structure can be adjusted to accommodate thrust termination devices of different sizes. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for describing the embodiments are briefly introduced below.

[0019] Figure 1 The working principle diagram of the high-efficiency force dissipator of the present invention;

[0020] Figure 2 This is the installation diagram of the high-efficiency force dissipator structure of the present invention. DETAILED DESCRIPTION

[0021] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present invention.

[0022] like Figure 1 , Figure 2As shown, this embodiment provides a high-efficiency dampener, which acts on the thrust termination device of a rocket engine, including a shell, a gas chamber channel 6 in the center of the shell, for the piston cylinder 10 to pass through, the bottom end of the gas chamber channel 6 is connected to the thrust termination device 20, and the two sides of the gas chamber channel 6 are symmetrically arranged along the movement direction of the piston cylinder 10 with a primary diversion channel 5, a secondary diversion channel 4 and a primary guide plate 3, and a secondary guide plate 2, and the top of the gas chamber channel 6 is a contracted piston cylinder outlet 1.

[0023] In this embodiment, the shell is a cylindrical structure with openings at both ends, and the bottom end is connected to the thrust termination device 20 through a threaded connection port 7, so that the outlet of the thrust termination device 20 is connected to the air chamber channel 6.

[0024] In this embodiment, the ratio of the sum of the areas of the primary and secondary flow-dividing channels 5 and 4 to the area of ​​the piston cylinder outlet 1 is 1:1.

[0025] In this embodiment, a conical inclined surface is provided at the lower part of the piston cylinder outlet 1, and preferably, the angle between the inclined surface and the center line of the shell is set to 30 degrees, so that the piston cylinder outlet 1 is designed as a whole with a conical mouth, which is conducive to blocking the gas and allowing the gas to flow to the primary and secondary diversion channels 5 and 4 on both sides.

[0026] In this embodiment, the primary guide plate 3 is arranged at the top of the primary diversion channel 5, and the angle between the primary guide plate 3 and the center line of the shell is set to 90°, which can block the gas refluxed by the secondary guide plate 2 to a certain extent, avoid damaging other components, and improve the reliability and safety of the diversion process.

[0027] In this embodiment, the secondary guide plate 2 is arranged at the top of the secondary diversion channel 4, and the angle between the secondary guide plate 2 and the center line of the shell is set to 75°, which can more effectively utilize the residual gas to form a reaction force to offset part of the thrust.

[0028] The working principle of the above structure is:

[0029] At the moment the thrust termination device is activated, the residual compressed gas is released from the outlet of the thrust termination device, instantly generating a huge impact disturbance. The design of the first and second level diverter channels and the first and second level guide plates on both sides can effectively reduce the gas flow at the outlet of the piston cylinder and generate a reaction force, thereby reducing the impact. Similarly, after the thrust is terminated, the first and second level diverter channels and the first and second level guide plates also reduce the residual thrust by reducing the outlet flow and generating a reaction force.

[0030] The force dissipation device of this embodiment divides the combustion gas into five parts by setting up a two-stage diversion channel, thereby reducing the combustion gas flow rate at the piston cylinder outlet, and at the same time utilizes the two-stage guide plate to form a reaction force, thereby reducing the residual thrust and reducing the impact disturbance to the rocket engine at the moment of thrust termination. The actual measured force dissipation efficiency can reach 50%.

[0031] The setting angle of the secondary guide plate is 75°, which can more effectively utilize the residual gas to form a reaction force, thereby offsetting part of the thrust; the setting angle of the primary guide plate is 90°, which can block the gas returning from the secondary guide plate to a certain extent, avoid damage to other components, and improve the reliability and safety of the diversion process.

[0032] The damper of this embodiment has a simple structure, is light in weight, and is easy to disassemble. The size of the structure can be adjusted to accommodate thrust termination devices of different sizes.

[0033] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A high-efficiency damper, acting on a rocket engine thrust termination device, characterized in that: The housing comprises a cylindrical structure with openings at both ends, an air chamber channel in the center of the housing for the piston cylinder to pass through, the bottom end of the air chamber channel is connected to a thrust termination device, a primary flow distribution channel, a primary flow guide plate, a secondary flow distribution channel and a secondary flow guide plate are symmetrically arranged in sequence on both sides of the air chamber channel along the movement direction of the piston cylinder, and the top of the air chamber channel is a contracted piston cylinder outlet; The secondary guide plate is arranged at the top of the secondary flow diversion channel, and the angle between the secondary guide plate and the center line of the shell is set to 75°; The primary guide plate is arranged at the top of the primary diversion channel, and the angle between the primary guide plate and the center line of the shell is set to 90°.

2. The high-efficiency force dissipator according to claim 1 is characterized in that: The bottom end of the shell is connected to the thrust termination device through a threaded connection port.

3. The high-efficiency force dissipator according to claim 1 is characterized in that: The ratio of the sum of the areas of the primary and secondary flow diversion channels to the outlet area of ​​the piston cylinder is 1:

1.

4. The high-efficiency force dissipator according to claim 1 is characterized in that: A conical inclined surface is provided at the lower part of the piston cylinder outlet.

5. The high-efficiency force dissipator according to claim 4 is characterized in that: The angle between the inclined surface and the center line of the shell is set to 30°.

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