阅读说明：本技术 一种固体脉冲动力装置 (Solid pulse power device ) 是由 高辉 季朦 李晨轩 许诺 于 2021-06-24 设计创作，主要内容包括：本申请揭示了一种固体脉冲动力装置,属于固体推进技术领域。该固体脉冲动力装置,包括结构主体、喷口、PCB电路板、固体发动机,所述喷口与所述固体发动机一一对应设置,各个喷口周向间隔地排布于所述结构主体上,所述PCB电路板与所述固体发动机的点火器的表面贴合且电性连接；每个固体发动机均包括点火器、燃烧室、药柱,所述药柱容置于所述燃烧室内,所述点火器位于所述燃烧室端部中心位置且与所述药柱压紧配合,与所述固体发动机对应的喷口安装于所述固体发动机远离所述点火器的一端。本申请通过在结构主体上设置的绕轴线阵列排布的喷口以及对应的燃烧室,提供了导弹所需的与飞行方向垂直的燃气动力,实现导弹弹道的机动或姿态的俯仰与滚动的调整。(The application discloses solid pulse power device belongs to solid propulsion technical field. The solid pulse power device comprises a structure main body, nozzles, a PCB (printed circuit board) and a solid engine, wherein the nozzles and the solid engine are arranged in a one-to-one correspondence manner, the nozzles are circumferentially arranged on the structure main body at intervals, and the PCB is attached to and electrically connected with the surface of an igniter of the solid engine; each solid engine comprises an igniter, a combustion chamber and a grain, the grain is contained in the combustion chamber, the igniter is located in the center of the end of the combustion chamber and is in compression fit with the grain, and a nozzle corresponding to the solid engine is installed at one end, far away from the igniter, of the solid engine. The nozzles arranged in an array around the axis and the corresponding combustion chambers are arranged on the structural body, so that the gas power which is required by the missile and is vertical to the flight direction is provided, and the maneuvering of the missile trajectory or the pitching and rolling adjustment of the attitude are realized.)

1. The solid pulse power device is characterized by comprising a structure main body, nozzles, a PCB circuit board and a solid engine, wherein the nozzles and the solid engine are arranged in a one-to-one correspondence manner, the nozzles are circumferentially arranged on the structure main body at intervals, and the PCB circuit board is attached to and electrically connected with the surface of an igniter of the solid engine;

each solid engine comprises an igniter, a combustion chamber and a grain, the grain is contained in the combustion chamber, the igniter is located in the center of the end of the combustion chamber and is in compression fit with the grain, and a nozzle corresponding to the solid engine is installed at one end, far away from the igniter, of the solid engine.

2. The solid pulse power plant of claim 1, wherein each solid engine further comprises a jet orifice blocking piece and a flow director, the jet orifice blocking piece is installed at a connecting channel of the combustion chamber and the jet orifice, the jet orifice blocking piece and the combustion chamber are sealed by gluing, and the flow director is installed in the combustion chamber on the jet orifice blocking piece.

3. The solid pulse power plant of claim 2, wherein petal-shaped flow guide holes are arranged in the flow guide, and the nozzle block is made of an organic film or a metal film.

4. The solid pulse power device of claim 1, wherein the combustion chambers of two adjacent solid engines are respectively located at two sides of the circumferential direction of the nozzle and distributed in a staggered manner; alternatively, the combustion chambers of each solid engine are located on the same side in the circumferential direction of the nozzle.

5. The solid state pulse power unit of claim 4, wherein there are two PCB boards, and two PCB boards are attached to the igniter in each combustion chamber on the same side.

6. The solid state pulse power unit of claim 1, wherein the PCB is a flexible circuit board comprising a PCB body structure and an annular circuit board at an inner ring of the end of the body structure, the PCB body structure having a cover plate attached thereto.

7. The solid state impulse power device of claim 1, further comprising a fastener securing said PCB circuit board to said structural body and a sealing layer between said combustion chamber end face and said PCB circuit board.

8. The solid state pulse power unit of claim 1 wherein the axis of each jet is perpendicular to the axis of the structural body.

9. The solid state pulse power plant of claim 1, wherein each jet orifice is arranged at an inclination such that there is a moment arm between each jet orifice and the axis of the structural body.

10. The solid state pulse power plant of claim 1, wherein each jet opening is provided on the structural body, the structural body and each combustion chamber being integrally formed by 3D metal printing or machining; alternatively, each combustion chamber may be detachably attached to the structural body.

Technical Field

The application belongs to the technical field of solid propulsion, and relates to a solid pulse power device.

Background

The solid pulse engine is an actuating device for rapidly adjusting the initial attitude of aircrafts such as missiles and the like. Generally, after the missile is launched, a lateral force is provided by using an attitude control engine to realize large-angle maneuvering turning or attitude deviation correction. To accommodate any orientation adjustment, multiple pulse motors are typically required to work individually or in combination as needed. With the development of the missile to miniaturization, the pulse engine of the missile also needs to be miniaturized.

Aiming at the micro engine, the array of the solid pulse engine is realized by 3D printing of some two-dimensional arrays, and the functions of explosive column, sealing, heat insulation, ignition control and the like are realized by printing similar to a sandwich structure. The shell and the bottom plate are made of silicon materials, and the shell further comprises a heat insulating material and the like. The printing structure can solve the magnitude of 1mm of the diameter of the combustion chamber, and has the problem of insufficient printing structure strength in the aspect of the engine with the diameter of the 10mm combustion chamber, and meanwhile, the problem of the combined use of the missile on the pulse engine cannot be solved.

Disclosure of Invention

In order to solve the problems of the related art, the application provides a solid pulse power device, which comprises the following technical scheme:

a solid pulse power device comprises a structure main body, nozzles, a PCB (printed circuit board) and a solid engine, wherein the nozzles and the solid engine are arranged in a one-to-one correspondence manner, the nozzles are circumferentially arranged on the structure main body at intervals, and the PCB is attached to and electrically connected with the surface of an igniter of the solid engine;

each solid engine comprises an igniter, a combustion chamber and a grain, the grain is contained in the combustion chamber, the igniter is located in the center of the end of the combustion chamber and is in compression fit with the grain, and a nozzle corresponding to the solid engine is installed at one end, far away from the igniter, of the solid engine.

Optionally, the plurality of jets and plurality of solid engines are arranged in an annular array about the axis of the structural body.

Optionally, every solid engine still includes spout closure piece and divertor, the spout closure piece is installed the combustion chamber with the joint channel department of spout, the spout closure piece with the combustion chamber realizes sealedly through gluing, the divertor install in the combustion chamber on the spout closure piece.

Optionally, petal-shaped flow guide holes are formed in the flow guider, and the nozzle blocking piece is made of an organic film or a metal film.

Optionally, the combustion chambers of two adjacent solid engines are respectively located at two sides of the circumferential direction of the nozzle and are distributed in a staggered manner; alternatively, the combustion chambers of each solid engine are located on the same side in the circumferential direction of the nozzle.

Optionally, the number of the PCB circuit boards is two, and the two PCB circuit boards are respectively attached to the igniters in the combustion chambers on the same side.

Optionally, the PCB is a flexible circuit board, the flexible circuit board includes a PCB main structure and an annular circuit board located at an inner ring of an end of the main structure, and the PCB main structure is additionally provided with a layer of cover plate.

Optionally, the solid pulse power device further comprises a fastener and a sealing layer, the fastener fastens the PCB circuit board to the structural body, and the sealing layer is located between the combustion chamber end face and the PCB circuit board.

Optionally, the axis of each spout is perpendicular to the axis of the structural body.

Optionally, each spout is arranged at an angle such that there is a moment arm between each spout and the axis of the structural body.

Optionally, each nozzle is arranged on the structure main body, and the structure main body and each combustion chamber are integrally formed through 3D metal printing or machining; alternatively, each combustion chamber may be detachably attached to the structural body.

Based on the technical characteristics, the application can at least realize the following beneficial effects:

the nozzles arranged in an axis array mode and the corresponding solid engines are arranged on the structure body, so that gas power perpendicular to the flight direction and required by the missile is provided, and the maneuvering of the missile trajectory or the pitching and rolling adjustment of the attitude are realized.

Aiming at kilogram-level satellites and missiles with diameters below 100mm, the problem of structural design and array configuration of the pulse engine is solved according to the requirement that the diameter of a combustion chamber of the pulse engine is within the range of 2 mm-20 mm.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and together with the description, serve to explain the principles of the invention.

FIG. 1 is a schematic structural diagram of a solid state impulse power plant as provided in one embodiment of the present application;

FIG. 2 is a schematic representation of a toroidal cross-section of a solid state impulse power plant as provided in one embodiment of the present application;

FIG. 3 is a schematic illustration of an application of a solid state impulse power plant as provided in one embodiment of the present application;

FIG. 4 is a schematic structural diagram of a solid state impulse power plant as provided in another embodiment of the present application;

FIG. 5 is a schematic view of a PCB mounted on a solid state impulse power device as provided in another embodiment of the present application;

fig. 6 is a schematic view of a jet arrangement provided in another embodiment of the present application.

Wherein the reference numbers are as follows:

1. a structural body; 2. a spout; 3. a PCB circuit board; 31. a flexible circuit board; 41. an igniter; 42. a combustion chamber; 43. carrying out grain treatment; 44. a spout blocking piece; 45. a fluid director; 5. a fastener; 6. a sealing layer; 7. a micro missile.

Detailed Description

Reference will now be made in detail to the exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, like numbers in different drawings represent the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Rather, they are merely examples of apparatus and methods consistent with certain aspects of the invention, as detailed in the appended claims.

Fig. 1 is a schematic structural diagram of a solid pulse power device provided in an embodiment of the present application, and fig. 2 is a schematic sectional view of a torus of the solid pulse power device provided in an embodiment of the present application, and in conjunction with fig. 1 and fig. 2, the solid pulse power device provided in the present application may include a structural body 1, nozzles 2, a PCB circuit board 3, and a solid engine, where the nozzles 2 are disposed in one-to-one correspondence with the solid engine, the nozzles 2 are circumferentially spaced apart from each other and arranged on the structural body 1, and the solid engine includes a plurality of combustion chambers circumferentially arrayed around an axis of the structural body 1. The PCB 3 is attached to and electrically connected with the surface of an igniter of the solid engine. The igniter is directly attached to the PCB, so that connecting leads between the driving control panel and the igniter are saved, the assembly is simpler and more convenient, and the space is saved. The upper end face of the PCB 3 is mounted with other circuit elements except the igniter. The nozzles and the corresponding solid engines are arranged on the same plane in an annular array manner, and the nozzles and the solid engines are arranged in an array manner along the circumferential direction, so that the structure is compact, the gas power which is required by the missile and is vertical to the flight direction is provided, and the maneuvering of the missile trajectory or the pitching and rolling adjustment of the attitude are realized. Referring to fig. 2, each solid engine may include an igniter 41, a combustion chamber 42, and a charge 43, the charge 43 is accommodated in the combustion chamber 42, the igniter 41 is located at a central position of an end portion of the combustion chamber 42 and is in press fit with the charge 43, and a nozzle 2 corresponding to the solid engine is mounted at an end of the solid engine away from the igniter 41. The solid engine realizes ignition of the propellant through the igniter, the propellant establishes stable combustion under the sealing of the combustion chamber plug, after a certain pressure, the fuel gas orderly passes through and breaks the plug under the action of the fluid director, the plug is broken, and the fuel gas is sprayed out of the nozzle to generate thrust.

In a possible implementation manner, each solid engine may further include a nozzle blocking piece 44 and a flow guide 45, the nozzle blocking piece 44 is installed at a connection channel between the combustion chamber 42 and the nozzle 2, the nozzle blocking piece 44 and the combustion chamber 42 are sealed by gluing, and the flow guide 45 is installed in the combustion chamber 42 on the nozzle blocking piece 44. The nozzle blocking piece is arranged between the combustion chamber and the nozzle, so that the combustion chamber can be sealed and protected when the engine does not work. When the engine works, the initial pressure is established, and the fuel gas is broken when a certain pressure is reached, so that the fuel gas is sprayed out.

Petal-shaped flow guide holes are formed in the flow guider 45, so that pressure control of fuel gas is realized, and incomplete combustion and ejection of the explosive columns 43 are prevented. The spout closure 44 is made of an organic film or a metal film. The petal-shaped guide holes can guide the passing gas, so that the gas is more uniform when passing, and the pressure control of the gas is facilitated.

Optionally, each nozzle 2 is opened on the structural body 1, and the structural body 1 and each combustion chamber 42 are integrally formed by 3D metal printing or machining; alternatively, each combustion chamber 42 may be detachably attached to the structural body 1.

The solid state impulse power device may further comprise a fastening member 5 and a sealing layer 6, wherein the fastening member 5 fastens the PCB circuit board 3 to the structural body 1, and the sealing layer 6 is located between the end face of the combustion chamber 42 and the PCB circuit board 3.

The solid pulse power device provided by the application provides the gas power which is required by the missile and is vertical to the flight direction through the nozzles 2 arranged on the structure body 1 in an axial line manner and the corresponding combustion chambers 42, and realizes the maneuvering of the missile trajectory or the pitching and rolling adjustment of the attitude.

For example, as shown in fig. 3, which is an application schematic diagram of the solid pulse power device provided in an embodiment of the present application, the micro missile 7 sends an instruction to the solid pulse power device through a missile-borne computer, the solid pulse power device is switched through a circuit logic, and a command channel is connected to realize combustion of a grain where a target nozzle 2 corresponding to the instruction is located, generate high-pressure gas to be ejected, provide gas power perpendicular to a flight direction required by the micro missile 7, and realize maneuvering or attitude pitching and rolling adjustment of a trajectory of the micro missile 7.

When the combustion chamber 42 is relatively large, the combustion chambers 42 of two adjacent solid engines can be respectively positioned at two sides of the circumferential direction of the nozzle 2 and distributed in a staggered manner, as shown in fig. 4; alternatively, when the combustion chamber 42 is relatively small, the combustion chamber 42 of each solid engine is located on the same side in the circumferential direction as the nozzle 2. In a typical arrangement, the combustion chamber 42 may be cylindrical or oblong, etc.

Optionally, there are two PCB circuit boards 3, and the two PCB circuit boards 3 are respectively attached to the igniters 41 in the combustion chambers 42 on the same side.

Optionally, the PCB 3 is a flexible circuit board 31, the flexible circuit board 31 includes a PCB main structure and an annular circuit board located at an inner ring of an end of the main structure 1, as shown in fig. 5, a layer of cover plate is attached to the PCB main structure.

In an implementation mode, the axis of each nozzle 2 is perpendicular to the axis of the structural body 1, when the maneuvering or pitching and rolling of the attitude of the guided missile needs to be adjusted, the guided missile issues a corresponding command to the solid pulse power device, and when the solid pulse power device controls the combustion chamber 42 corresponding to the command to be ignited by using the PCB 3, the solid pulse power device is ejected through the nozzle 2 of the combustion chamber 42 to generate the gas power perpendicular to the flight direction, which is needed by the guided missile, so that the maneuvering or pitching of the attitude of the guided missile is adjusted.

In another implementation, each spout 2 is arranged obliquely so that there is a moment arm between each spout 2 and the axis of the structural body 1, as shown in fig. 6. When the maneuvering or the rolling of the attitude of the guided missile needs to be adjusted, the guided missile issues a corresponding instruction to the solid pulse power device, and the solid pulse power device controls the combustion chamber 42 corresponding to the instruction to be ignited by utilizing the PCB 3, and the instruction is ejected out through the nozzle 2 of the combustion chamber 42 to generate gas power which is required by the guided missile and generates a certain angle with the flight direction, so that the maneuvering or the rolling of the attitude of the guided missile is adjusted.

To sum up, the solid pulse power device that this application provided, through the spout and the combustion chamber that correspond that the axis array that sets up on the main structure body arranged, provided the required and flight direction vertically gas power of guided missile, the regulation of the pitching and the rolling of the maneuver or the gesture of realization guided missile trajectory.

Aiming at kilogram-level satellites and missiles with diameters below 100mm, the problem of structural design and array configuration of the pulse engine is solved according to the requirement that the diameter of a combustion chamber of the pulse engine is within the range of 2 mm-20 mm.

Other embodiments of the invention will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the invention being indicated by the following claims.

It will be understood that the invention is not limited to the precise arrangements described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the invention is limited only by the appended claims.