阅读说明：本技术 一种高效消力器 (High-efficient chest-developer ) 是由 张迎港 曾雪宁 于 2020-12-22 设计创作，主要内容包括：本发明公开了一种高效消力器,包括壳体,壳体中央为气室通道,供活塞筒通行,气室通道底端与推力终止装置相连,气室通道两侧沿活塞筒运动方向依次对称设置有一、二级分流通道及一、二级导流板,气室通道顶部为缩口式活塞筒出口。本申请的消力器,设置两级分流通道,使燃气一分为五,减小活塞筒出口燃气流量,同时利用两级导流板形成反作用力,以此减小残余推力,降低推力终止瞬间火箭发动机受到的冲击扰动,实测消力效率可达50％；而且结构简单、质量轻便、拆卸方便,可调整结构大小以适应不同尺寸的推力终止装置。为小型固体火箭发动机推力终止时,降低冲击,减小残余推力提供了一种新的方案。(The invention discloses a high-efficiency force-eliminating device, which comprises a shell, wherein the center of the shell is provided with an air chamber channel for a piston cylinder to pass through, the bottom end of the air chamber channel is connected with a thrust termination device, two sides of the air chamber channel are sequentially and symmetrically provided with a first-stage flow dividing channel, a second-stage flow dividing channel, a first-stage flow guide plate and a second-stage flow guide plate along the motion direction of the piston cylinder, and the top of the air chamber channel is. The force absorber is provided with the two-stage flow dividing channel, so that the first gas is divided into five, the gas flow at the outlet of the piston cylinder is reduced, and meanwhile, the two-stage flow guide plates form a reaction force, so that the residual thrust is reduced, the impact disturbance on the rocket engine at the moment of thrust termination is reduced, and the actually measured force absorbing efficiency can reach 50%; and simple structure, light weight, convenient dismantlement, adjustable structure size is in order to adapt to the thrust termination device of different sizes. A new scheme is provided for reducing impact and reducing residual thrust when the thrust of the small solid rocket engine is terminated.)

1. The utility model provides a high-efficient chest expander acts on rocket engine thrust termination, its characterized in that: the thrust stopping device comprises a shell, wherein an air chamber channel is arranged in the center of the shell and is used for a piston cylinder to pass through, the bottom end of the air chamber channel is connected with the thrust stopping device, a first-stage flow dividing channel, a second-stage flow dividing channel, a first-stage flow guide plate and a second-stage flow guide plate are sequentially and symmetrically arranged on two sides of the air chamber channel along the motion direction of the piston cylinder, and a necking piston cylinder.

2. The efficient force dissipater of claim 1, wherein: the shell is of a cylindrical structure with openings at two ends, and the bottom end of the shell is connected with the thrust termination device through a threaded connector.

3. The efficient force dissipater of claim 1, wherein: the ratio of the sum of the areas of the first-stage flow dividing channel and the second-stage flow dividing channel to the area of the outlet of the piston cylinder is 1: 1.

4. The efficient force dissipater of claim 1, wherein: the lower part of the outlet of the piston cylinder is provided with a conical inclined surface.

5. The efficient force dissipater of claim 4, wherein: the angle between the inclined surface and the center line of the housing is set to 30 °.

6. The efficient force dissipater of claim 1, wherein: the second grade guide plate is located second grade reposition of redundant personnel passageway top, and the angle between second grade guide plate and the casing central line is set for 75.

7. The efficient force dissipater of claim 1, wherein: the one-level guide plate is arranged at the top end of the one-level flow distribution channel, and the angle between the one-level guide plate and the central line of the shell is set to be 90 degrees.

Technical Field

The invention relates to the field of solid rocket engines, in particular to a high-efficiency power absorber which is arranged at an outlet of a thrust termination device of a small-sized solid rocket engine.

Background

Thrust termination is a mature and effective technology for realizing the interstage separation of the solid rocket engine, adjusting the missile range, controlling the flight precision and starting or terminating the flight for multiple times, and is widely applied to various large and medium-sized solid rocket engines at home and abroad. The existing small solid rocket engine is limited by space limitation, decompression rate, thrust output and other technical requirements, and the thrust termination scheme mainly adopts a decompression quenching method, but the scheme has the following problems:

a) the situation that the explosive column cannot be flamed out exists after the thrust stopping device acts, namely residual thrust is still output after the thrust is stopped;

b) the thrust stopping device acts instantaneously, and due to instantaneous flying-out of the piston cylinder and sudden pressure drop of the combustion chamber, great impact disturbance is generated on the small-thrust engine.

Disclosure of Invention

The invention provides a high-efficiency power absorber which adopts a necking outlet design, divides residual fuel gas into five by arranging a first-stage flow dividing channel and a second-stage flow dividing channel, effectively reduces the output of residual thrust, simultaneously reduces impact disturbance caused when the thrust is terminated, and has the characteristics of simple structure, light weight, convenient disassembly and high efficiency.

In order to achieve the purpose, the invention adopts the following technical scheme:

the utility model provides a high-efficient chest expander acts on rocket engine thrust termination, includes the casing, and casing central authorities are the air chamber passageway, supply the piston barrel to pass, and air chamber passageway bottom links to each other with thrust termination, and air chamber passageway both sides are followed piston barrel direction of motion and are set up one, second grade reposition of redundant personnel passageway and one, second grade guide plate in proper order symmetrically, and air chamber passageway top is the export of throat formula piston barrel.

Preferably, the housing has a cylindrical structure with two open ends, and the bottom end of the housing is connected to the thrust stop device through a threaded connection port.

Preferably, the ratio of the sum of the areas of the first-stage flow dividing channel and the second-stage flow dividing channel to the area of the outlet of the piston cylinder is 1: 1.

Preferably, the lower part of the outlet of the piston cylinder is provided with a conical inclined surface.

Preferably, an angle between the inclined surface and a center line of the housing is set to 30 °.

Preferably, the secondary guide plate is arranged at the top end of the secondary flow dividing channel, and the angle between the secondary guide plate and the central line of the shell is set to be 75 degrees.

Preferably, the first-stage guide plate is arranged at the top end of the first-stage diversion channel, and the angle between the first-stage guide plate and the center line of the shell is set to be 90 degrees.

Due to the structure, the invention has the advantages that:

(1) the two-stage flow dividing channel is arranged, so that the gas is divided into five, the gas flow at the outlet of the piston cylinder is reduced, and meanwhile, the reaction force is formed by the two stages of flow guide plates, so that the residual thrust is reduced, the impact disturbance on the rocket engine at the moment of thrust termination is reduced, and the actually measured force eliminating efficiency can reach 50%.

(2) The set angle of the secondary guide plate is 75 degrees, so that the residual gas can be more effectively utilized to form a reaction force, and partial thrust is offset; the angle of setting for the one-level guide plate is 90, can the separation to a certain extent follow the gas of second grade guide plate backward flow, avoids hindering other parts, has improved the reliability and the security of reposition of redundant personnel process.

(3) Simple structure, light weight, convenient disassembly and adjustable structure size to adapt to thrust terminating devices of different sizes.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below.

FIG. 1 is a schematic diagram of the operation of the high efficiency force dissipater of the present invention;

fig. 2 is a mounting diagram of the structure of the high-efficiency force absorber.

Detailed Description

The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

As shown in fig. 1 and fig. 2, the embodiment provides a high-efficiency force absorber acting on a thrust termination device of a rocket engine, which includes a housing, wherein an air chamber channel 6 is arranged in the center of the housing for a piston cylinder 10 to pass through, the bottom end of the air chamber channel 6 is connected with the thrust termination device 20, a first-stage flow dividing channel 5, a second-stage flow dividing channel 4, a first-stage flow guide plate 3 and a second-stage flow guide plate 2 are symmetrically arranged on two sides of the air chamber channel 6 in sequence along the motion direction of the piston cylinder 10, and a necking piston cylinder outlet 1 is.

In this embodiment, the housing is a cylindrical structure with two open ends, the bottom end of the housing is connected with the thrust terminating device 20 through the threaded connection port 7, and the outlet of the thrust terminating device 20 is communicated with the air chamber channel 6.

In the embodiment, the ratio of the sum of the areas of the primary flow dividing channel 5 and the secondary flow dividing channel 4 to the area of the piston cylinder outlet 1 is 1: 1.

In this embodiment, the lower portion of the piston cylinder outlet 1 is provided with a tapered inclined surface, and preferably, the angle between the inclined surface and the center line of the housing is set to 30 °. The outlet 1 of the piston cylinder is integrally designed in a necking mode, so that the gas can be blocked, and the gas can flow to the first-stage and second-stage flow dividing channels 5 and 4 on two sides.

In this embodiment, 5 tops of one-level reposition of redundant personnel passageway are located to one-level guide plate 3, and the angle between one-level guide plate 3 and the casing central line sets for 90, can the separation to a certain extent by the gas of 2 refluxes of second grade guide plate, avoids hindering other parts, has improved the reliability and the security of reposition of redundant personnel process.

In this embodiment, the second-stage baffle 2 is disposed at the top end of the second-stage flow dividing channel 4, and the angle between the second-stage baffle 2 and the center line of the casing is set to 75 °, so that the residual gas can be more effectively utilized to form a reaction force, thereby offsetting partial thrust.

The working principle of the structure is as follows:

the thrust termination device acts instantaneously, residual compressed gas is released from the outlet of the thrust termination device, and extremely large impact disturbance is generated instantaneously, and the design of the first-stage flow dividing channel and the second-stage flow dividing channel on the two sides can effectively reduce the gas flow at the outlet of the piston cylinder structurally and generate reaction force, so that the impact is reduced; similarly, after the thrust is terminated, the primary and secondary diversion channels and the primary and secondary guide plates reduce the residual thrust in a mode of reducing outlet flow and generating reaction force.

The force dissipater of this embodiment through setting up two-stage reposition of redundant personnel passageway, makes the gas divide into five, reduces piston cylinder export gas flow, utilizes the two-stage guide plate to form reaction force simultaneously to this reduces residual thrust, reduces the thrust termination impact disturbance that rocket engine received in the twinkling of an eye, and actual measurement efficiency of absorbing force can reach 50%.

The set angle of the secondary guide plate is 75 degrees, so that the residual gas can be more effectively utilized to form a reaction force, and partial thrust is offset; the angle of setting for the one-level guide plate is 90, can the separation to a certain extent follow the gas of second grade guide plate backward flow, avoids hindering other parts, has improved the reliability and the security of reposition of redundant personnel process.

The force absorber of this embodiment, simple structure, the quality is light, it is convenient to dismantle, adjustable structure size is in order to adapt to the thrust termination device of unidimensional not.

The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.