阅读说明：本技术 一种双脉冲固体发动机 (Double-pulse solid engine ) 是由 张翔宇 郭运强 李青频 黄薇薇 童天赐 汪海滨 甘晓松 张仲 于 2019-08-20 设计创作，主要内容包括：本发明公开了一种双脉冲固体发动机,包括点火器、顶盖、隔层、连接件、药柱、绝热壳体和喷管；药柱设置在绝热壳体内,所述隔层将药柱沿轴向分隔成两段；绝热壳体一端由顶盖密封,另一端与喷管固定连接,同时所述顶盖通过连接件与隔层固定连接并实现自密封,点火器固定在顶盖上。本发明径向隔层与顶盖连接易于实现、可靠性高。(The invention discloses a double-pulse solid engine which comprises an igniter, a top cover, an interlayer, a connecting piece, a explosive column, a heat insulation shell and a spray pipe, wherein the igniter is arranged on the top cover; the explosive column is arranged in the heat insulation shell, and the interlayer divides the explosive column into two sections along the axial direction; one end of the heat insulation shell is sealed by a top cover, the other end of the heat insulation shell is fixedly connected with the spray pipe, meanwhile, the top cover is fixedly connected with the interlayer through a connecting piece and realizes self sealing, and the igniter is fixed on the top cover. The connection between the radial interlayer and the top cover is easy to realize and the reliability is high.)

1. A double-pulse solid engine is characterized by comprising an igniter, a top cover, an interlayer, a connecting piece, a explosive column, a heat insulation shell and a spray pipe;

the explosive column is arranged in the heat insulation shell, and the interlayer divides the explosive column into two sections along the axial direction; one end of the heat insulation shell is sealed by a top cover, the other end of the heat insulation shell is fixedly connected with the spray pipe, meanwhile, the top cover is fixedly connected with the interlayer through a connecting piece and realizes self sealing, and the igniter is fixed on the top cover.

2. The dipulse solid engine as set forth in claim 1, wherein said connecting member is annular, and annular protrusions are provided at positions corresponding to the inner and outer circumferential surfaces, said annular protrusions being axially and uniformly distributed, and mounting holes for fixedly connecting with the partition are provided between the annular protrusions.

3. The dual pulse solid engine of claim 2, wherein the barrier is bolted to the connector, the bolt is secured within the mounting hole, and insulation is provided at both ends of the bolt.

4. The dual pulse solid engine of claim 2, wherein the connector is connected to the top cover by threads or radial screws.

Technical Field

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

Background

In order to meet the power requirements of a new-generation tactical missile, a double-pulse solid engine with the energy management advantage is developed by the operation, the energy of the whole working process of the engine can be effectively distributed by designing I/II pulse working time and pulse interval time, the average speed of the missile is effectively improved under the condition of not improving the maximum speed of the missile, the requirement of controllable energy of a missile power device is better met, and the operational efficiency of the missile is improved.

The interlayer isolation mode is one of advanced schemes for realizing the double-pulse technology of the solid engine, has the advantages of light passive mass and high performance, but the structure of the double-pulse engine is more complex, so the design and the final assembly of the interlayer, the propellant charge of the engine and the like become the main technical difficulties of the interlayer type double-pulse engine.

The structure and the assembly method of the interlayer determine the process method adopted by the interlayer manufacture and the general assembly process of the engine, and at present, the conventional structure of the interlayer type double-pulse solid engine is shown in a figure 1 and comprises an I pulse igniter 1, a top cover 2, an II pulse igniter 3, an I pulse grain 7, a radial interlayer 5, an axial interlayer 6, an II pulse grain 4, a heat insulation shell 8 and a spray pipe 9. The radial interlayer 5 and the top cover 2 are manufactured by adopting an integral forming process, and in order to ensure the bonding and sealing performance between the radial interlayer and the top cover, an adhesive molding and integral forming process is mostly adopted, and the structure is shown in figure 2. The manufacturing process limits the forming technology of the radial interlayer 5, and the radial interlayer and the top cover 2 are integrally molded, so that the production efficiency and the product reasonable rate of the integral forming are low, and particularly, the manufacturing of the radial interlayer 5 of a large-size double-pulse engine is very difficult, and the existing process level even cannot be manufactured and formed.

Disclosure of Invention

In view of this, the invention provides a double-pulse solid engine, and the connection between the radial interlayer and the top cover is easy to realize and has high reliability.

The specific embodiment of the invention is as follows:

a double-pulse solid engine comprises an igniter, a top cover, an interlayer, a connecting piece, a explosive column, a heat insulation shell and a spray pipe;

the explosive column is arranged in the heat insulation shell, and the interlayer divides the explosive column into two sections along the axial direction; one end of the heat insulation shell is sealed by a top cover, the other end of the heat insulation shell is fixedly connected with the spray pipe, meanwhile, the top cover is fixedly connected with the interlayer through a connecting piece and realizes self sealing, and the igniter is fixed on the top cover.

Furthermore, the connecting piece is annular, and the corresponding position of interior, outer periphery is equipped with annular protrusion, annular protrusion is along axial equipartition, is equipped with the mounting hole that is used for linking firmly with the interlayer between the annular protrusion.

Further, the interlayer is connected with the connecting piece through bolts, the bolts are fixed in the mounting holes, and heat insulation materials are arranged at two ends of each bolt.

Further, the connecting piece is connected with the top cover through threads or radial screws.

Has the advantages that:

the radial interlayer and the top cover are connected in a self-sealing mode through the connecting piece, the manufacturing technical bottleneck that the radial interlayer and the top cover are integrally formed at present is broken through, the radial interlayer manufacturing method is easy to realize and high in reliability, the radial interlayer can be manufactured by adopting various die pressing processes or segmented manufacturing bonding processes, the radial interlayer manufacturing method is more suitable for manufacturing large-size radial interlayers, the production efficiency and the product percent of pass of the radial interlayer can be effectively improved, and the overall assembly process of the interlayer type double-pulse engine is optimized.

Drawings

FIG. 1 is a schematic diagram of a conventional stratified twin-pulse engine;

FIG. 2 is a schematic view of a conventional radial spacer and top cap integrated structure;

FIG. 3 is a schematic view of the sealing structure for connecting the radial partition and the top cover according to the present invention;

FIG. 4 is a partial enlarged view of the connection portion;

FIG. 5 is a schematic structural view of a connector;

FIG. 6 is a cross-sectional view of the connector;

the device comprises a 1-I pulse igniter, a 2-top cover, a 3-II pulse igniter, a 4-II pulse explosive column, a 5-radial interlayer, a 6-axial interlayer, a 7-I pulse explosive column, an 8-heat insulation shell, a 9-spray pipe and a 10-connecting piece.

Detailed Description

The invention is described in detail below by way of example with reference to the accompanying drawings.

The double-pulse solid engine provided by the embodiment comprises a pulse igniter 1I, a top cover 2, a pulse igniter 3 II, a radial interlayer 5, an axial interlayer 6, a connecting piece 10, a pulse explosive column I7, a pulse explosive column II 4, a heat insulation shell 8 and a spray pipe 9, as shown in fig. 3.

As shown in fig. 5 and 6, the connecting member 10 is annular, and the inner and outer circumferential surfaces have annular protrusions, i.e., self-sealing rings, which are uniformly distributed along the axial direction, and mounting holes for fixedly connecting with the radial spacers 5 are formed between the annular protrusions.

The explosive column is arranged in the heat insulation shell 8, and the radial interlayer 5 and the axial interlayer 6 divide the explosive column into two sections along the axial direction, namely a pulse explosive column I7 and a pulse explosive column II 4. One end of the heat insulation shell 8 is sealed by the top cover 2, the other end is fixedly connected with the spray pipe 9, and meanwhile, the top cover 2 is fixedly connected with the radial interlayer 5 through the connecting piece 10. As shown in fig. 4, one end of the connecting member 10 is connected to the top cover 2 by a screw thread or a radial screw, and the other end of the connecting member 10 is embedded inside the radial spacer 5 and connected to the radial spacer 5 by a bolt. Because the self-sealing rings are arranged at a plurality of positions, in the process of bolt compression, the radial interlayer 5 which belongs to rubber materials can deform and enter the gap between the self-sealing rings in the axial direction, a compression self-sealing structure is formed, and the connection and sealing functions are synchronously realized. After the bolt is installed, high-temperature-resistant putty is coated at two ends of the bolt for heat insulation protection, so that the bolt is prevented from losing strength at high temperature.

II pulse powder columns 7 are located the front end, keep away from spray tube 11, and I pulse powder column 9 is located the rear end, and I pulse igniter 1, II pulse igniter 3 all fix on top cap 2, are used for igniting I pulse powder column 7, II pulse powder column 4 respectively. Radial interlayer 5 wraps up in II pulse explosive column 4 inner circumferential face, and axial interlayer 8 wraps up in II pulse explosive column 4 and I pulse explosive column 7 relative terminal surface, and radial interlayer 5 overlap joint is inboard at axial interlayer 6 simultaneously to the solid engine axis place is interior.

In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.