阅读说明：本技术 一种弹射发动机 (Ejection engine ) 是由 龚建良 张�杰 于 2020-08-07 设计创作，主要内容包括：本发明涉及一种弹射发动机,包括壳体、装药组件、后顶盖、喷管、点火装置、螺环、前螺栓、后螺栓、前顶盖密封圈、后顶盖密封圈、喷管密封圈。弹射发动机具有大增面比、结构简单、工艺成熟、工作温度范围广、弹道性能好等优点。在燃烧室壳体内均布两排装药组件,发动机点火后随时间逐渐增加弹射发动机的燃气量。在头部安装双路电发火管,进行冗余设计,提供可靠的点火能量,点燃球形药。在尾部采用螺环固定喷管,工艺成熟、简单方便。本发明能够应用于导弹或者运载火箭在大范围温度内发射,初始过载小,提高导弹或运载火箭发射的平稳性、可靠性。(The invention relates to an ejection engine which comprises a shell, a charging assembly, a rear top cover, a spray pipe, an ignition device, a spiral ring, a front bolt, a rear bolt, a front top cover sealing ring, a rear top cover sealing ring and a spray pipe sealing ring. The ejection engine has the advantages of large area increasing ratio, simple structure, mature process, wide working temperature range, good ballistic performance and the like. Two rows of charge assemblies are uniformly distributed in the combustion chamber shell, and the fuel gas quantity of the ejection engine is gradually increased along with the time after the engine is ignited. A double-circuit electric ignition tube is arranged at the head part, redundant design is carried out, reliable ignition energy is provided, and the spherical explosive is ignited. The spiral fixed spray pipe is adopted at the tail part, and the process is mature, simple and convenient. The invention can be applied to the launching of the missile or the carrier rocket in a large range of temperature, has small initial overload and improves the launching stability and reliability of the missile or the carrier rocket.)

1. An ejection engine is characterized by comprising a shell (1), a charging component (2), a rear top cover (3), a spray pipe (4) and an ignition device (5); two rows of powder charging assemblies (2) are uniformly distributed in the shell (1); each row of charge components (2) are arranged in a ring shape; the charging component (2) is a spherical charging component.

2. The ejection engine of claim 1, wherein: the head of the shell is provided with an ignition device.

3. The ejection engine of claim 1, wherein: the tail part of the shell is connected with a rear top cover.

4. The ejection engine of claim 3, wherein: and a spray pipe is arranged in the rear top cover.

5. The ejection engine of claim 4, wherein: the spray pipe is fixed by adopting a spiral ring and is radially sealed by adopting an O-shaped sealing ring.

6. The ejection engine of claim 2, wherein: the head of the shell and the ignition device are sealed by an O-shaped sealing ring end face.

7. The ejection engine of claim 3, wherein: the tail part of the shell and the rear top cover are radially sealed by an O-shaped sealing ring.

8. The ejection engine of claim 1, wherein: each medicine charging component (2) comprises a medicine shell (2-1), a medicine coating (2-2), spherical medicines (2-3) and a support cover plate (2-5); after the medicine is pasted in the medicine shell for coating, spherical medicine is cast in the medicine shell to form a hemispherical structure, and after solidification is finished, a plurality of hemispherical structures are longitudinally fixed on the support cover plate (2-5); the position of the bracket cover plate corresponding to the spherical medicine is provided with a through hole.

9. The ejection engine of claim 8, wherein: the inner surface and the outer surface of the spherical medicine (2-3) are spherical surfaces.

10. The ejection engine of claim 1, wherein: the ignition device adopts an electric ignition tube as an excitation source to ignite the ignition medicine box and finally ignite the spherical medicine.

Technical Field

The invention belongs to the field of missile launching, and particularly relates to an ejection engine.

Background

The ejection engine can be used for launching a missile or a carrier rocket, and the launching maneuverability of the missile or the carrier rocket can be improved; on the other hand, the missile or the carrier rocket is ignited at high altitude after being ejected, so that the negative influence of the tail flame on ground equipment and personnel can be reduced. The existing ejection engine adopts columnar charge, has small area increasing ratio and large overload, produces adverse effect on a platform device, even destroys platform equipment, and causes failure in launching.

Disclosure of Invention

The invention aims to provide an ejection engine, which overcomes the defects of the prior art, can realize large area increasing ratio, good ignition synchronism of a combustion surface and impulse provision within a certain range in specified time, and ensures reliable ejection work of a missile or a carrier rocket.

The technical scheme of the invention is as follows: an ejection engine is characterized by comprising a shell 1, a charging component 2, a rear top cover 3, a spray pipe 4 and an ignition device 5; two rows of charging assemblies 2 are uniformly distributed in the shell 1; each row of charge assemblies 2 is arranged in a ring shape; the charge assembly 2 is a spherical charge assembly.

Has the advantages that: the invention can greatly increase the area ratio, has high ignition synchronism of the combustion surface, simple structure, good sealing performance, mature process, high reliability and wide working temperature range.

1. The requirement of a large flow ratio of the launching platform is met, the launching overload is small, and the cylinder discharging is stable.

2. The operating temperature range of the ejection engine is wide.

3. The assembly process of the ejection engine is mature, simple and reliable.

Drawings

Fig. 1 is a three-dimensional structural view of an ejection engine of the present invention.

In the figure, 1-shell, 2-explosive component, 3-rear top cover, 4-nozzle, 5-ignition device, 6-spiral ring, 7-front bolt, 8-rear bolt, 9-front top cover sealing ring, 10-rear top cover sealing ring and 11-nozzle sealing ring.

Fig. 2 is a two-dimensional cross-sectional view of the ejector engine of the present invention.

Figure 3 is a diagram of a charge assembly of the present invention.

2-1-medicine shell, 2-2 medicine coating, 2-3 spherical medicine, 2-4 bracket bottom plate, 2-5 bracket cover plate and 2-6 slotted screw;

fig. 4 is a view a-a of fig. 2.

Detailed Description

The present invention will be described in further detail with reference to specific embodiments thereof for the purpose of making apparent the objects, contents and advantages thereof.

The invention provides an ejection engine which comprises a shell, a charging component, a rear top cover, a spray pipe, an ignition device, a spiral ring, a front bolt, a rear bolt, a front top cover sealing ring, a rear top cover sealing ring and a spray pipe sealing ring. The ejection engine adopts two rows of spherical charge components which are arranged concentrically and fixed in an engine shell, and each row of charge components 2 are arranged in a ring shape; an ignition device is arranged at the head of the shell, and the end face of the ignition device is sealed by an O-shaped sealing ring. The tail part of the engine shell is connected with a rear top cover, and an O-shaped sealing ring is adopted for radial sealing. And the spray pipe is arranged in the rear top cover, is fixed by adopting a spiral ring and is radially sealed by adopting an O-shaped sealing ring. The ignition device adopts a double-circuit electric ignition tube as an excitation source, carries out redundancy design, provides reliable ignition energy, ignites an ignition medicine box, and finally ignites spherical medicines.

From the gas flow formula 1 and the zero-dimensional internal trajectory formula 2, the gas flow of the engine can be knownWith combustion surface A_tPush button

The power is proportional, where n is less than 1. Therefore, the launching platform has the characteristics of small initial gas flow and large later gas flow, and meets the requirement of large gas flow ratio. At present, the gas flow ratio of a columnar charge ejection engine is small, and the area of a columnar charge combustion surface is in a linear relation with the radius. However, the spherical charge ejection engine has a quadratic relation between the charge combustion surface area and the radius, and can improve the performance index of the gas flow ratio. Therefore, the ejection engine with spherical powder charge is designed, and can be used for ejecting dynamic powder charge from the platform, reducing the overload of the platform and improving the launching stability.

Wherein:is the ejection engine gas flow;

P_cis the combustion chamber pressure;

A_tis the throat area;

A_bis the area of the combustion surface;

C_Fis the thrust coefficient;

rho is the density of the propellant;

c^*is a characteristic coefficient;

a is a burning rate coefficient;

n is a pressure index.

Figure 1 depicts a three-dimensional modeling diagram of a catapult engine. Fig. 2 depicts a two-dimensional cross-sectional view of an ejection engine. The device mainly comprises a shell 1, a charging component 2, a rear top cover 3, a spray pipe 4, an ignition device 5, a spiral ring 6, a front bolt 7, a rear bolt 8, a front top cover sealing ring 9, a rear top cover sealing ring 10 and a spray pipe sealing ring 11;

wherein the medicine charging component 2 comprises a medicine shell 2-1, a medicine coating 2-2, spherical medicines 2-3, a bracket bottom plate 2-4, a bracket cover plate 2-5 and slotted screws 2-6;

firstly, sticking medicine coating 2-2 in a medicine shell 2-1, casting spherical medicine 2-3 in the medicine shell to form a hemispherical structure, after solidification, longitudinally placing a plurality of hemispherical structures into a support bottom plate 2-4, packaging the hemispherical structures by a support cover plate 2-5, and connecting the support bottom plate 2-4 and the support cover plate 2-5 by slotted screws 2-6 to form a medicine charging assembly 2. Through holes are arranged on the positions, corresponding to the spherical medicines 2-3, of the support cover plates 2-5; the inner surface and the outer surface of the spherical medicine 2-3 are spherical surfaces.

Secondly, sequentially loading the powder charging components 2 into the shell 1; the spray pipe sealing ring 11 is arranged in the spray pipe 4, and is arranged in the rear cover plate 3 together, and is fixed by the spiral ring 6; the back cover plate packing 10 is fitted into the back cover plate 3. Meanwhile, the housing 1 is butted with the rear cover plate 3 and fixed by the rear bolt 8. Finally, after the front head gasket 9 is fitted into the ignition device 5, the ignition device 5 is fixed to the front head 3 with the front bolts 7. And finishing the assembly of the ejection engine.

The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.