阅读说明：本技术 一种多脉冲固体火箭发动机 (Multi-pulse solid rocket engine ) 是由 马立坤 冯运超 夏智勋 段炼 李洋 何志成 于 2020-05-18 设计创作，主要内容包括：本发明公开了一种多脉冲固体火箭发动机,包括发动机壳体、前封头、喷管,还包括：外电极,具有多个致密排列的蜂窝状通孔,每个蜂窝状通孔的内腔作为一个燃烧室且截面呈正多边形；内电极,具有中心距离边缘不等距离的截面,一端连接内电极固定座；电控固体推进剂,装填于外电极与内电极之间；电源,一极连接外电极、另一极连接内电极。本发明通过将外电极设计成具有多个致密排列的蜂窝状通孔结构,且每个蜂窝状通孔的内腔作为一个燃烧室,并将蜂窝状燃烧室作为外电极整体连接到电源的一极,在不显著降低发动机质量比的同时,既可以获得较大推力,又可以满足电控固体推进剂的工作特性,实现多脉冲固体火箭发动机的重复启动和推力可调。(The invention discloses a multi-pulse solid rocket engine, which comprises an engine shell, a front seal head and a spray pipe, and also comprises: the outer electrode is provided with a plurality of densely arranged honeycomb-shaped through holes, the inner cavity of each honeycomb-shaped through hole is used as a combustion chamber, and the cross section of each honeycomb-shaped through hole is in a regular polygon shape; the inner electrode is provided with a cross section with the center at unequal distances from the edge, and one end of the inner electrode is connected with the inner electrode fixing seat; the electric control solid propellant is filled between the outer electrode and the inner electrode; one pole of the power supply is connected with the outer electrode, and the other pole is connected with the inner electrode. According to the invention, the outer electrode is designed to be provided with a plurality of densely arranged honeycomb-shaped through hole structures, the inner cavity of each honeycomb-shaped through hole is used as a combustion chamber, and the honeycomb-shaped combustion chamber is used as the outer electrode and is integrally connected to one pole of a power supply, so that the mass ratio of the engine is not remarkably reduced, a larger thrust can be obtained, the working characteristics of the electric control solid propellant can be met, and the repeated starting and the thrust adjustment of the multi-pulse solid rocket engine are realized.)

1. A multi-pulse solid rocket engine comprises an engine shell (5) with a hollow structure inside, a front seal head (6) sleeved at one end of the engine shell (5), and a spray pipe (7) sleeved at the other end of the engine shell (5), and is characterized by further comprising:

the outer electrode (1) is provided with a plurality of densely arranged honeycomb-shaped through holes (13), the inner cavity of each honeycomb-shaped through hole (13) is used as a combustion chamber, and the cross section of each honeycomb-shaped through hole is in a regular polygon shape;

the inner electrodes (2) are provided with cross sections with centers at different distances from edges, the number of the cross sections is the same as that of the honeycomb-shaped through holes (13), the cross sections are embedded into the centers of the honeycomb-shaped through holes (13), and one end, close to the front end socket (6), of the inner electrodes is fixedly connected with an inner electrode fixing seat (9);

the electric control solid propellant (3) is filled between the outer electrode (1) and the inner electrode (2);

a power supply (8), one pole of which is electrically connected to the outer electrode (1) through a lead (10), the other pole of which is electrically connected to a plurality of inner electrodes (2) which are mutually connected in parallel through leads (10), and an intermediate coupling connection control system so as to adjust the output power of the power supply (8) in real time;

when the circuit between the power supply (8) and the electric control solid propellant (3) is conducted, the power supply (8), the outer electrode (1), the electric control solid propellant (3) and the inner electrode (2) form a closed loop, and the electric control solid propellant (3) in each honeycomb-shaped through hole (13) is electrified and ignited to burn at the same time, so that the engine generates thrust; when a circuit between a power supply (8) and the electric control solid propellant (3) is disconnected, the electric control solid propellant (3) in each honeycomb-shaped through hole (13) is simultaneously powered off and extinguished, so that the engine stops generating thrust; when the power loaded between the inner electrode (2) and the outer electrode (1) is adjusted through the control system, the burning speed of the electric control solid propellant (3) in each honeycomb through hole (13) is changed, and the thrust of the engine is adjusted.

2. A multi-pulse solid rocket engine according to claim 1 further comprising an insulating layer (4), said insulating layer (4) covering the inner wall surfaces of the engine casing (5), the front head (6) and the nozzle (7).

3. A multi-pulse solid rocket engine according to claim 2 wherein: the electric control solid propellant filling device is characterized by further comprising a medicine blocking plate (12) which is abutted against two ends of the outer electrode (1) and used for fixing the electric control solid propellant (3), a filling cavity (11) is formed between the electrode fixing seat (9) and the front end enclosure (6), and a sealing soft glue is filled in the filling cavity (11).

4. A multi-pulse solid rocket engine according to claim 3 wherein: the electric control solid propellant (3) comprises an oxidant, a metal fuel, an adhesive and an additive, wherein the ratio of the oxidant, the metal fuel, the adhesive and the additive is 5-6: 1-2: 0.5-1.5: 1.5-2.5 by weight percentage.

5. The multi-pulse solid rocket engine of claim 4 wherein the oxidizer is any one or a mixture of hydroxylamine nitrate, ammonium nitrate and perchlorate; the metal fuel is any one or mixture of magnesium powder, aluminum powder and boron powder; the adhesive is polyvinyl alcohol and/or methyl cellulose; the additive is a burning rate catalyst and/or a curing agent.

6. A multi-pulse solid rocket engine according to claim 1 wherein: the section of the inner electrode (2) along the length direction is any one of a star shape, a windmill shape, a gear shape, a trefoil shape and a multi-thorn shape.

7. A multi-pulse solid rocket engine according to claim 1 wherein: the power supply (8) provides electric energy in the form of any one of alternating current, direct current or capacitor discharge.

8. A multi-pulse solid rocket engine according to claim 7, wherein said engine housing (5) is detachably connected to said nozzle (7) and front head (6) by means of threads or flanges, respectively.

9. A multi-pulse solid rocket engine according to claim 7 wherein: the engine shell (5) is detachably connected with the spray pipe (7) and the front seal head (6) through flanges respectively.

10. A multi-pulse solid rocket engine according to any one of claims 2 to 5 wherein: the insulating and heat-insulating layer (4) is made of any one or a mixture of bakelite, phenol or tetrafluoroethylene.

Technical Field

The invention relates to the technical field of solid rocket engines, in particular to a multi-pulse solid rocket engine.

Background

The solid rocket engine has the characteristics of simple structure, good economy, high reliability and the like, is widely applied to the fields of aerospace and national defense, and can provide power for devices such as missiles, space vehicles and the like. The solid rocket engine is a rocket engine using a solid propellant as a fuel, the solid propellant is easy to store, high in mass ratio, convenient to use and easy to transport, but compared with a liquid rocket engine or a solid-liquid hybrid rocket engine, the solid rocket engine has the biggest defects that: on one hand, the solid propellant is difficult to ignite again after flameout, and repeated starting cannot be realized; on the other hand, the solid propellant is not controlled in the combustion process, and parameters such as the flow of the liquid propellant and the like cannot be controlled by using devices such as a valve and the like a liquid propellant engine so as to control the combustion of the propellant, so that the application range of the solid rocket engine is greatly limited due to the two reasons.

Although some schemes can be adopted to control the thrust of the solid rocket engine, such as changing the shape and structure of propellant grains, sectionally charging and changing the burning speed of the propellant at different positions, all the schemes work according to a preset thrust curve and cannot randomly control the thrust in real time. Some schemes such as adjusting the throat area of a spray pipe, controlling the mass burning rate of a propellant, using a colloidal propellant capable of providing fuel in a pulse mode and the like can control the thrust in real time, or firstly make the engine stall through modes of reducing pressure, spraying a fire extinguishing agent and the like, and then realize the restart of the engine through an ignition system capable of starting for many times, but the technologies of the schemes are complex and the achievable effect is limited.

The electric control solid propellant has special electric control performance, is a insensitive propellant with electric control effect, is burnt when being electrified and extinguished when being powered off, and breaks through the inherent obstacle that the traditional solid propellant cannot be randomly flamed out and restarted. The propellant can be ignited and burnt by inputting a certain current, the flame is immediately extinguished after the power is cut off, and the burning speed of the propellant can be adjusted by changing the magnitude of the input current or voltage in the burning process, so that the thrust of the solid rocket engine can be controlled in real time and can be repeatedly started, and the thrust can be randomly and accurately controlled in a simple manner; however, under the influence of the characteristics of the electrically controlled solid propellant, the combustion surface is small, the combustion injection efficiency is low, and the thrust of the electrically controlled solid propellant rocket engine is limited.

Disclosure of Invention

The invention provides a multi-pulse solid rocket engine aiming at the technical problem to be solved, and aims to solve the problem that the traditional electric control solid propellant rocket engine has smaller thrust.

In order to solve the technical problems, the invention is realized by the following technical scheme: a multi-pulse solid rocket engine comprises an engine shell with a hollow structure inside, a front seal head sleeved at one end of the engine shell, and a spray pipe sleeved at the other end of the engine shell, and further comprises:

the outer electrode is provided with a plurality of densely arranged honeycomb-shaped through holes, the inner cavity of each honeycomb-shaped through hole is used as a combustion chamber, and the cross section of each honeycomb-shaped through hole is in a regular polygon shape;

the inner electrodes are provided with cross sections with centers at different distances from the edges, the number of the inner electrodes is the same as that of the honeycomb-shaped through holes, the inner electrodes are embedded into the centers of the honeycomb-shaped through holes, and one end of each inner electrode, which is close to the front end socket, is fixedly connected with an inner electrode fixing seat;

the electric control solid propellant is filled between the outer electrode and the inner electrode;

a power supply, one pole of which is electrically connected to the outer electrode through a lead, the other pole of which is electrically connected to a plurality of inner electrodes which are mutually connected in parallel through leads, and an intermediate coupling connection control system to adjust the output power of the power supply in real time;

when a circuit between a power supply and the electric control solid propellant is conducted, the power supply, the outer electrode, the electric control solid propellant and the inner electrode form a closed loop, and the electric control solid propellant in each honeycomb-shaped through hole is electrified and ignited to burn at the same time, so that the engine generates thrust;

when a circuit between a power supply and the electric control solid propellant is disconnected, the electric control solid propellant in each honeycomb-shaped through hole is simultaneously powered off and extinguished, so that the engine stops generating thrust;

when the control system is used for adjusting the power loaded between the inner electrode and the outer electrode, the burning speed of the electric control solid propellant in each honeycomb-shaped through hole is changed, and the thrust of the engine is adjusted.

Furthermore, the solid rocket engine also comprises an insulating layer, and the insulating layer covers the inner wall surfaces of the engine shell, the front seal head and the spray pipe.

Furthermore, the solid rocket engine also comprises a medicine baffle plate which is abutted against two ends of the outer electrode and used for fixing the electric control solid propellant, a filling cavity is formed between the electrode fixing seat and the front seal head, and sealing soft glue is filled in the filling cavity.

Further, the electronic control solid propellant at least comprises an oxidant, a metal fuel, an adhesive and an additive, wherein the ratio of the oxidant, the metal fuel, the adhesive and the additive is 5-6: 1-2: 0.5-1.5: 1.5-2.5 by weight percentage.

Further, the oxidant is any one or mixture of more of hydroxylamine nitrate, ammonium nitrate and perchlorate; the metal fuel is any one or mixture of magnesium powder, aluminum powder and boron powder; the adhesive is polyvinyl alcohol and/or methyl cellulose; the additive is a burning rate catalyst and/or a curing agent.

Furthermore, the cross section of the inner electrode along the length direction of the inner electrode is any one of a star shape, a windmill shape, a gear shape, a trefoil shape and a multi-thorn shape.

Further, the power supply provides electrical energy in the form of any one of alternating current, direct current, or capacitive discharge.

Furthermore, the engine shell is detachably connected with the spray pipe and the front seal head through threads respectively.

Furthermore, the engine shell is detachably connected with the spray pipe and the front seal head through flanges respectively.

Furthermore, the insulating and heat-insulating layer is made of any one or a mixture of more of bakelite, phenol or tetrafluoroethylene.

Compared with the prior art, the invention has the advantages that:

according to the multi-pulse solid rocket engine provided by the invention, the outer electrode is designed to be provided with a plurality of densely arranged honeycomb-shaped through hole structures, the inner cavity of each honeycomb-shaped through hole is used as a combustion chamber, and the honeycomb-shaped combustion chamber is used as the outer electrode and is integrally connected to one pole of a power supply, so that the mass ratio of the engine is not remarkably reduced, the larger thrust can be obtained, the working characteristics of an electric control solid propellant can be met, and the repeated starting and the adjustable thrust of the multi-pulse solid rocket engine are realized.

In the invention, the inner electrode is designed into the section with the center at unequal distances from the edge, such as a star shape, a windmill shape, a gear shape, a trilobal shape, a multi-thorn shape and the like, so that the inner electrode is in contact with the electrically-controlled solid propellant in a larger area, and the initial combustion area of the electrically-controlled solid propellant is increased.

The invention saves the ignition device of the traditional rocket engine, can realize larger thrust while controlling the thrust of the engine in real time, and has wide application prospect in the field of multi-pulse rocket engines needing to generate large thrust.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.

The invention is further described below with reference to the accompanying drawings:

FIG. 1 is a partial perspective view of a solid rocket engine according to the present invention;

FIG. 2 is a full sectional view of the solid rocket engine of the present invention;

FIG. 3 is a cross-sectional view of FIG. 2;

FIG. 4 is a cross-sectional view of an outer electrode according to one embodiment;

FIG. 5 is a perspective view of an inner electrode according to one embodiment;

1. an outer electrode; 2. an inner electrode; 3. a solid propellant; 4. an insulating and heat insulating layer; 5. an engine housing; 6. a front end enclosure; 7. a nozzle; 8. a power source; 9. an inner electrode holder; 10. a wire; 11. filling the cavity; 12. a medicine baffle plate; 13. and honeycomb-shaped through holes.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. 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.

It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.

In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.