阅读说明：本技术 一种小型化多功能的火箭发动机 (Miniaturized multifunctional rocket engine ) 是由 孙理论 张成成 胡鹏程 李燊 李群 多学武 于 2021-07-26 设计创作，主要内容包括：本发明公开了一种小型化多功能的火箭发动机,该小型化多功能的火箭发动机,包括外壳,所述外壳采用燃烧室和长尾管一体化设计结构,所述外壳一端连接有发射发电装置,能够为发动机提供电能并为弹体提供出膛动力,所述长尾管外圆面安装有折叠式尾翼,所述折叠式尾翼通过内部设置的尾翼锁紧装置锁定于外壳外部,所述外壳尾部连接有喷管,所述喷管内部设置有延期点火模块,所述燃烧室内腔一侧设置有顶盖,所述顶盖与燃烧室之间填充有固体推进剂,所述顶盖与固体推进剂前端面之间设置有点火具；本发明采用电源、发射、飞行稳定、延期点火、勤务安全等功能一体化设计,提高了产品安全性,使用方便,利于推广。(The invention discloses a miniaturized multifunctional rocket engine, which comprises a shell, wherein the shell adopts an integrated design structure of a combustion chamber and a long tail pipe, one end of the shell is connected with a launching power generation device which can provide electric energy for the engine and provide chamber power for a projectile body, the circular surface of the long tail pipe is provided with a folding tail wing, the folding tail wing is locked outside the shell through an internally arranged tail wing locking device, the tail part of the shell is connected with a spray pipe, a delay ignition module is arranged inside the spray pipe, one side of the inner cavity of the combustion chamber is provided with a top cover, a solid propellant is filled between the top cover and the combustion chamber, and an ignition tool is arranged between the top cover and the front end surface of the solid propellant; the invention adopts the function integrated design of power supply, launching, stable flight, delayed ignition, service safety and the like, improves the product safety, is convenient to use and is beneficial to popularization.)

1. The utility model provides a miniaturized multi-functional rocket engine, includes the shell, its characterized in that, the shell adopts combustion chamber and long tailpipe integrated design structure, shell one end is connected with transmission power generation facility, transmission power generation facility can provide the electric energy and provide out of the bore power for the projectile body for the engine, foldable fin is installed to long tailpipe excircle face, foldable fin locks in the shell outside through the fin locking device of inside setting, the shell connection of after section has the spray tube, the inside ignition module that postpones that is provided with of spray tube.

2. The miniaturized multi-functional rocket engine of claim 1, wherein a top cover is disposed at one side of the inner cavity of the combustion chamber, a solid propellant is filled between the top cover and the combustion chamber, an igniter is disposed between the top cover and the front end face of the solid propellant, and the igniter is mounted at the front position of the central through hole of the solid propellant.

3. The miniaturized multi-functional rocket engine of claim 2, wherein the long tail tube is embedded with a thermal protection layer, and a pressure maintaining device is arranged at a bell mouth position at the front end of the thermal protection layer.

4. The miniaturized multi-functional rocket engine of claim 2 wherein the solid propellant is a butylated hydroxyl composite propellant with a mold casting and center through hole structure, and a heat insulating layer is arranged between the solid propellant and the outer casing.

5. A small multi-function rocket engine according to claim 1 wherein said delay fire module is mounted in a pre-defined slot within the nozzle and potted.

6. The miniaturized multi-functional rocket engine of claim 1 wherein the launch power unit is externally provided with a primer, the launch power unit being capable of being excited by the primer.

7. A miniaturized multifunctional rocket engine as defined in claim 1, wherein said transmission power generating device is externally provided with a protective cover.

Technical Field

The invention relates to the technical field of rocket engines, in particular to a miniaturized multifunctional rocket engine.

Background

The miniaturized multifunctional design of weapons and ammunitions is one of the development directions of military equipment, an important ring in the weapons and ammunitions is a solid rocket engine, and the solid rocket engine has the advantages of simple structure, reliable work, convenient use and the like, so the miniaturized multifunctional design has a great application prospect on the weapons and the application of the solid rocket engine on various weapons is limited due to the influence of factors such as space, a propellant, a power supply, launching, a stable system, an ignition mode, safety and the like in the miniaturized design process of the solid rocket engine.

Therefore, the solid rocket engine which integrates multiple functions of power supply, launching, flight stability, delayed ignition, service safety and the like and can launch by using weaponry such as ground unmanned vehicles, individual hand-held grenade guns, unmanned planes and the like is very necessary.

Disclosure of Invention

The invention aims to provide a miniaturized multifunctional rocket engine to solve the problem that the existing solid rocket engine has single function in the process of miniaturization design.

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

the utility model provides a miniaturized multi-functional rocket engine, includes the shell, the shell adopts combustion chamber and long tail pipe integrated design structure, shell one end is connected with the transmission power generation facility, the transmission power generation facility can provide the electric energy and provide out of the thorax power for the projectile body for the engine, foldable fin is installed to long tail pipe excircle face, foldable fin locks in the shell outside through the fin locking device of inside setting, the shell connection of after section has the spray tube, the inside ignition module that delays that is provided with of spray tube.

On the basis of the technical scheme, the invention also provides the following optional technical scheme:

in one alternative: the solid propellant gas burner is characterized in that a top cover is arranged on one side of the inner cavity of the combustion chamber, a solid propellant is filled between the top cover and the combustion chamber, an igniter is arranged between the top cover and the front end face of the solid propellant, and the igniter is arranged at the front position of a central through hole of the solid propellant.

In one alternative: the long tail pipe is internally embedded with a thermal protection layer, and a pressure maintaining device is arranged at the position of a horn mouth at the front end of the thermal protection layer.

In one alternative: the solid propellant is a hydroxyl-terminated composite propellant with a mold casting molding and center through hole type structure, and the outer cylindrical surface, the front end surface and the rear end surface of the solid propellant are coated by a heat insulating layer with a certain thickness and then are bonded with the shell into a whole.

In one alternative: the delay ignition module is arranged in a preset groove in the spray pipe and is subjected to encapsulation treatment.

In one alternative: the external portion of the emission power generation device is provided with a primer, and the emission power generation device can be excited through the primer.

In one alternative: and a protective cover is arranged outside the transmitting and generating device.

Compared with the prior art, the invention has the following beneficial effects:

1. the miniaturized multifunctional rocket engine adopts the function integrated design of power supply, launching, flight stability, delayed ignition, service safety and the like, is completely isolated from a fuse, a warhead, a control cabin and the like of a rocket projectile or a missile, and improves the product safety.

2. The invention can provide primary eviscerating power for the projectile body, can also provide secondary endurance power for the projectile body by the self-generating ignition engine, and is provided with a folding tail wing which is locked in service and opened in flight for stabilizing the flight attitude of the projectile body.

3. The invention has wide application range, simple structure, convenient use and easy popularization.

Drawings

FIG. 1 is a schematic view of a miniaturized multi-function rocket engine when not in use.

Fig. 2 is a schematic structural diagram of a miniaturized multifunctional rocket engine after being launched.

Notations for reference numerals: 1-top cover, 2-igniter, 3-solid propellant, 301-heat insulating layer, 4-shell, 401-combustion chamber, 402-long tail pipe, 5-pressure maintaining device, 6-heat protective layer, 7-folding tail wing, 8-nozzle, 9-tail wing locking device, 10-protective cover, 11-emission power generation device, 12-primer and 13-delay ignition module.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Specific implementations of the present invention are described in detail below with reference to specific embodiments.

As shown in fig. 1-2, a miniaturized multifunctional rocket engine provided for an embodiment of the present invention comprises a housing 4, wherein the housing 4 adopts an integrated design structure of a combustion chamber 401 and a long tail pipe 402, one end of the housing 4 is connected with a launch power generation device 11, the launch power generation device 11 can provide electric energy for the engine and provide power for firing a projectile body, a folding tail wing 7 is installed on the outer circular surface of the long tail pipe 402, the folding tail wing 7 is locked outside the housing 4 through a tail wing locking device 9 arranged inside, and the folding tail wing 7 is locked in an enveloping circle smaller than the outer diameter of the engine through the tail wing locking device 9 in a service state; after the fire, the protective cover 10 is separated from the engine, the restraint on the tail wing locking device 9 is removed, then the tail wing locking device 9 removes the locking on the folding tail wing 7, the tail part of the shell 4 is connected with the spray pipe 8 through threads, and the delay ignition module 13 is arranged in the spray pipe 8.

The multifunctional small rocket engine is internally provided with a launching and power generating device 11 which can provide electric energy for the engine and can also provide power for the projectile body to be taken out of the chamber, the folding tail wing 7 is unfolded after the projectile body is taken out of the chamber, the flying stability of the projectile is improved, as an embodiment, the left, right, upper and lower positions of all components shown in the attached drawings are only an arrangement mode, and the specific positions are set according to specific requirements.

As shown in fig. 1, as a preferred embodiment of the present invention, a top cover 1 is disposed on one side of an inner cavity of a combustion chamber 401, a solid propellant 3 is filled between the top cover 1 and the combustion chamber 401, an igniter 2 is disposed between the top cover 1 and a front end face of the solid propellant 3, the igniter 2 is mounted at a front position of a central through hole of the solid propellant 3, the top cover 1 and the front end face of the solid propellant 3 are matched to compress the igniter 2, the igniter 2 adopts a rear ignition mode, the top cover 1 has no through hole, threading and routing are not required, a housing of the igniter 2 adopts a combustible housing, and blockage of a nozzle 8 caused by ignition is avoided.

As shown in fig. 1, as a preferred embodiment of the present invention, a thermal protection layer 6 is embedded in the long tail pipe 402, a pressurizer 5 is disposed at a bell-mouth position at the front end of the thermal protection layer 6, and the pressurizer 5 has a function of maintaining ignition pressure.

As shown in fig. 1, as a preferred embodiment of the present invention, the solid propellant 3 is a butylated hydroxytoluene composite propellant with a mold casting and central through hole structure, and the outer cylindrical surface and the front and rear end surfaces of the solid propellant 3 are coated with a heat insulating layer 301 with a certain thickness and then bonded with the casing 4 into a whole.

As shown in fig. 1, as a preferred embodiment of the present invention, the delay ignition module 13 is installed in a preset groove inside the nozzle 8 and is encapsulated, the delay ignition module 13 stores the electric energy provided by the transmitting and generating device 11 in the energy storage capacitor, and the ignition device is ignited by delaying a preset time with the completion of charging as a starting point, so as to ignite the engine.

As shown in fig. 1, as a preferred embodiment of the present invention, a primer 12 is disposed outside the launching power generation device 11, the launching power generation device 11 can be excited by the primer 12, the launching power generation device 11 is connected with the casing 4 in a ring riveting manner, and the primer 12 is used for excitation, so as to provide both electric energy for the engine and power for discharging the projectile body.

As shown in fig. 1-2, as a preferred embodiment of the present invention, a protective cover 10 is provided outside the launching power generation device 11, and the protective cover 10 can ensure that the nozzle 8, the delay ignition module 13, the solid propellant 3 and other components are in a space isolation state from the launching power generation device 11 during launching, and the service state has the function of restraining the tail locking device 9 and the short circuit igniter 2.

The working principle is as follows: after the primer 12 acts, high-temperature and high-pressure gas is generated inside the emission power generation device 11. The high-pressure gas acts in the launching power generation device 12 to provide the chamber-exiting power for the projectile motion and ignition energy of the delay ignition module 13. The projectile body (without the launching power generation device 11) is pushed out of the bore by the power of the firing, the protective cover 10 falls off, the tail wing locking device 9 is released from being restrained, then the tail wing locking device 9 releases the locking of the folding tail wing 7, the folding tail wing 7 is unfolded, the flight attitude is stabilized, meanwhile, the short circuit of the igniter 2 is released, and the igniter 2 is in a state of being cocked. And when the projectile body is discharged for a certain time, the delay ignition module 13 sends an ignition instruction to ignite the igniter 2, so that the engine is ignited to provide endurance power for the projectile body to fly.

The above description is only for the specific embodiments of the present disclosure, but the scope of the present disclosure is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present disclosure, and all the changes or substitutions should be covered within the scope of the present disclosure. Therefore, the protection scope of the present disclosure shall be subject to the protection scope of the claims.