阅读说明：本技术 一种瞬态爆轰脉冲发动机及径向多脉冲推力矢量装置 (Transient detonation pulse engine and radial multi-pulse thrust vector device ) 是由 管雪元 于 2020-07-08 设计创作，主要内容包括：本发明公开了一种瞬态爆轰脉冲发动机及径向多脉冲推力矢量装置,发动机包括发动机本体,发动机本体两端分别设置有喷口密封体、封头体,发动机本体内安装有加强套,封头体内侧设置有绝缘体；所述加强套内装填有猛炸药；所述绝缘体内安装有等离子点火具、混合点火药,等离子点火具上连接有电极、电极；所述等离子点火具和混合点火药结合构成微米级线宽桥箔含能等离子点火具器件；所述径向多脉冲推力矢量装置包括金属本体和沿金属本体径向均匀分布多个瞬态爆轰脉冲发动机。本发明的瞬态爆轰脉冲发动机的工作时间小于30ms,可在高过载和飞行体旋转速度可达300转/秒环境下工作。(The invention discloses a transient detonation pulse engine and a radial multi-pulse thrust vector device, wherein the engine comprises an engine body, two ends of the engine body are respectively provided with a nozzle sealing body and a sealing head body, a reinforcing sleeve is arranged in the engine body, and the inner side of the sealing head body is provided with an insulator; the reinforcing sleeve is filled with high explosive; a plasma igniter and mixed ignition powder are arranged in the insulator, and the plasma igniter is connected with an electrode and an electrode; the plasma igniter and the mixed ignition powder are combined to form a micron-scale line width bridge foil energetic plasma igniter device; the radial multi-pulse thrust vector device comprises a metal body and a plurality of transient detonation pulse engines which are uniformly distributed along the radial direction of the metal body. The working time of the transient detonation pulse engine is less than 30ms, and the transient detonation pulse engine can work under the environment of high overload and 300 revolutions per second of the rotating speed of a flying body.)

1. The utility model provides a transient state detonation pulse engine, includes engine body (20), and engine body (20) both ends are provided with spout seal body (20-6), seal body (20-7) respectively, its characterized in that: a reinforcing sleeve (20-1) is arranged in the engine body (20), and an insulator (20-3) is arranged on the inner side of the seal head body (20-7); the reinforcing sleeve (20-1) is filled with high explosive (20-5); a plasma igniter (20-2) and a mixed ignition powder (20-4) are arranged in the insulator (20-3), and the plasma igniter (20-2) is connected with an electrode A and an electrode B; the plasma igniter (20-2) and the mixed igniter (20-4) are combined to form a micron-scale linear width bridge foil energy-containing plasma igniter device.

2. The transient detonation pulse engine of claim 1, characterized in that: the mixed ignition powder (20-4) adopts KK ignition powder + PETN, KK ignition powder + RDX or potassium picrate ignition powder + PETN mixed powder.

3. The transient detonation pulse engine of claim 1, characterized in that: the high explosive (20-5) is PETN or RDX high explosive.

4. The transient detonation pulse engine of claim 1, characterized in that: the plasma igniter (20-2) is an ion igniter device manufactured on an insulating plate by adopting a vacuum sputtering metal coating process or a printed circuit board process.

5. The transient detonation pulse engine of claim 4, characterized in that: the ion igniter device comprises an electrode pad a and an electrode pad B, a micron-sized line width metal bridge foil line is arranged between the bulges on the two electrode pads, the micron-sized line width metal bridge foil line is used for short-circuiting the electrode a and the electrode B, and the electrode pad a and the electrode pad B correspond to a welding electrode A and an electrode B outgoing line.

6. The transient detonation pulse engine of claim 5, characterized in that: and the resistance value of the micron-sized line width metal bridge foil line is less than or equal to 1m omega.

7. A radial multi-pulse thrust vectoring device, characterized by: a transient detonation pulse engine comprising a metal body (100) and a transient detonation pulse engine according to any of claims 1-5.

8. The radial multi-pulse thrust vector apparatus of claim 7, wherein: the metal body (100) is radially and uniformly distributed with a plurality of transient detonation pulse engines.

9. The radial multi-pulse thrust vector apparatus of claim 7, wherein: the center hole of the metal body (100) is provided with a multi-pulse thrust vector control intelligent circuit system board (30).

Technical Field

The invention relates to a high-speed rotating aircraft applied to barrel launching, in particular to a transient detonation pulse engine and a radial multi-pulse thrust vector device.

Background

The basic principle of the direct force control of the radial pulse jet flow is that a plurality of pulse engines are arranged near the center of mass of the projectile, and the flight path of the projectile is quickly corrected by means of radial reaction control force directly generated by high-speed gas flow sprayed by the pulse engines. The correction method has the advantages of simple system, low cost and the like, and is a common system for intelligently transforming the conventional barrel launching aircraft.

The basic structure of the existing charge pulse engine is shown in figure 1 and comprises an engine body 10, a rocket explosive column 10-1, an explosive column baffle 10-2, a seal head 10-3, an electric ignition explosive package 10-4, a porous explosive column partition plate 10-5, an electrode a and an electrode b. The working principle is as follows: when the electrode a and the electrode b are connected to start a power supply, the electric ignition explosive charge 10-4 is ignited, the ignited explosive gas flow enters the inner diameter of the explosive column 10-1 through the inner hole in the explosive column baffle 10-2, the explosive surface of the cylindrical area of the inner diameter of the ignited explosive column generates high-pressure and high-temperature gas flow, and the high-pressure and high-temperature gas flow is ejected from the spray pipe at high speed through the porous explosive column baffle 10-5 to form thrust. The working time of the engine is the time from the beginning of the combustion of the explosive surface with the area of the inner diameter cylinder of the explosive column, the gas is continuously sprayed out from the spray pipe at a high speed, the inner diameter combustion cylinder is continuously expanded (from the inner diameter to the outer diameter) until the explosive column is completely combusted.

The existing pulse engine belongs to a pulse engine with solid charge, the working time from the start ignition to the end of work is longer, and the working time is generally more than 30ms, so that the control precision of the radial attitude of the flying rotator is low, and the precision of the landing point of the flying rotator is influenced.

Disclosure of Invention

The invention aims to provide a transient detonation pulse engine and a radial multi-pulse thrust vector device, wherein the working time of the transient detonation pulse engine is less than 30ms, and the transient detonation pulse engine can work under the environment with high overload and the rotating speed of a flying body up to 300 revolutions per second.

The technical solution for realizing the purpose of the invention is as follows: a transient detonation pulse engine comprises an engine body, wherein a nozzle sealing body and a sealing head body are respectively arranged at two ends of the engine body, a reinforcing sleeve is installed in the engine body, and an insulator is arranged on the inner side of the sealing head body; the reinforcing sleeve is filled with high explosive; a plasma igniter and mixed ignition powder are arranged in the insulator, and the plasma igniter is connected with an electrode A and an electrode B; the plasma igniter and the mixed ignition powder are combined to form a micron-scale line width bridge foil energy-containing plasma igniter device.

Furthermore, the mixed ignition powder adopts KK ignition powder + PETN, KK ignition powder + RDX or potassium picrate ignition powder + PETN.

Further, the high explosive is PETN or RDX high explosive.

Furthermore, the plasma igniter is an ion igniter device manufactured on an insulating plate by adopting a vacuum sputtering metal coating process or a printed circuit board process.

Furthermore, the ion igniter device comprises an electrode pad a and an electrode pad B, a micron-sized line width metal bridge foil line is arranged between the bulges on the two electrode pads, the micron-sized line width metal bridge foil line is used for short-circuiting the electrode a and the electrode B, and the electrode pad a and the electrode pad B correspond to the welding electrode A and the electrode B leading-out wire.

Further, the resistance value of the micron-sized line width metal bridge foil line is less than or equal to 1m omega.

The invention also provides a radial multi-pulse thrust vector device which comprises a metal body and the transient detonation pulse engine.

Further, a plurality of transient detonation pulse engines are radially and uniformly distributed on the metal body.

Furthermore, a plurality of intelligent control circuit systems of the transient detonation pulse engine are installed in the center hole of the metal body.

Compared with the prior art, the invention has the following remarkable advantages: the transient detonation pulse engine can accurately control the working time to be less than or equal to 30ms, and can work in the environment with high overload and the rotating speed of a flying body to be 300 r/s; the invention also provides a radial multi-pulse thrust vector device consisting of the transient detonation pulse engine.

Drawings

Figure 1 is a basic block diagram of a prior art pulse motor with a charge.

FIG. 2 is a block diagram of a transient detonation pulse engine of the present invention.

FIG. 3 is an enlarged view of a plasma igniter used in the present invention.

Fig. 4 is a structural view of a radial multi-pulse thrust vectoring device of the present invention.

Detailed Description

As shown in FIG. 2, the transient detonation pulse engine of the present invention is composed of an engine body 20, a reinforcing sleeve 20-1, a plasma igniter 20-2, an insulator 20-3, a mixed ignition charge 20-4, a high explosive 20-5, a nozzle sealing body 20-6, a sealing body 20-7, an electrode A and an electrode B.

A reinforcing sleeve 20-1 is arranged in the engine body 20, and high explosive 20-5 is filled in the reinforcing sleeve 20-1; the insulator 20-3 is provided with a plasma igniter 20-2 and a mixed ignition powder 20-4, and the plasma igniter 20-2 is connected with an electrode A and an electrode B.

The plasma igniter 20-2 and the mixed igniter 20-4 form a micron-sized bridge foil energy-containing plasma igniter device; the plasma igniter 20-2 is an ion igniter device manufactured on an insulating plate by a vacuum sputtering metal coating process or a printed circuit board process, and is shown in fig. 3, wherein the ion igniter device has two circuit patterns, which are shown in fig. 3 (C) and (D); in the drawings (C) and (D), the black surface is a metal thin film circuit pattern, a and b are electrode pads, and a metal thin filmA micron-sized wire width metal bridge foil line is arranged between the bulges, the micron-sized wire width metal bridge foil line is used for short-circuiting the electrodes a and B, the resistance value of the micron-sized wire width metal bridge foil line between the electrodes a and B is less than or equal to 1m omega, and electrode pads a and B on the plasma igniter 20-2 are correspondingly used for welding electrode A and electrode B outgoing lines; when the two ends of the electrode A and the electrode B are connected with a power supply of more than or equal to 20V, the micron-sized line width metal bridge foil wire is instantly connected with heavy current for discharging, the micron-sized line width metal bridge foil wire is vaporized into high-pressure and high-temperature metal plasma gaseous shock waves at the same time, and the plasma gaseous shock waves excite the mixed ignition powder 20-4 to form detonation waves which are propagated in the high explosive 20-5 to form strong detonation waves; the bottom of the strong detonation wave pressure shear reinforcing sleeve 20-1 formed by the high explosive 20-5 and the spout sealing body 20-6 are ejected to form pulse detonation wave thrust.

Referring to fig. 4, there is shown a structure diagram of the radial multi-pulse thrust vectoring device of the present invention, which is composed of a metal body 100 and a plurality of independent transient detonation pulse engines 20. The metal body 100 is radially and uniformly distributed with a plurality of transient detonation pulse engines 20; in the embodiment, 8 transient detonation pulse engines 20 are adopted to form a radial multi-pulse thrust vector device; the large hole in the center of the metal body 100 can be provided with a multi-pulse thrust vector control intelligent circuit system board 30.

The above description is only one practical embodiment of the present invention, and some modifications and variations made on the basis of the above description should also be considered to be within the scope of the present invention.