阅读说明：本技术 一种整体隔层式双脉冲发动机 (A kind of entirety interlayer type dipulse engine ) 是由 张翔宇 郭运强 甘晓松 利凤祥 郜伟伟 黄薇薇 李青频 张兵 赵康 薛太旭 于 2019-08-20 设计创作，主要内容包括：本发明公开了一种整体隔层式双脉冲发动机,包括点火器、顶盖、隔层、药柱、绝热壳体和喷管；药柱设置在绝热壳体内,所述隔层整体成型,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,同时所述顶盖与隔层固定连接,点火器固定在顶盖上。本发明装配工艺简单、连接可靠、易于实现。(The invention discloses a kind of whole interlayer type dipulse engines, including igniter, top cover, interlayer, powder column, insulated case and jet pipe；Powder column is arranged in insulated case, and the interlayer is integrally formed, and interlayer is by powder column along axially spaced at two sections；Insulated case one end is fixedly connected by top seal, the other end with jet pipe, while the top cover is fixedly connected with interlayer, and igniter is fixed on top cover.Assembly technology of the present invention is simple, connection is reliable, easy to realize.)

1. a kind of entirety interlayer type dipulse engine, which is characterized in that including igniter, top cover, interlayer, powder column, insulated shell Body and jet pipe；

Powder column is arranged in insulated case, and the interlayer is integrally formed, and interlayer is by powder column along axially spaced at two sections；Insulated case One end is fixedly connected by top seal, the other end with jet pipe, while the top cover is fixedly connected with interlayer, and igniter is fixed on top It covers.

2. entirety interlayer type dipulse engine as described in claim 1, which is characterized in that interlayer radial component end It is provided inwardly with flange；The top cover is split type structure, the flange for inside and outside clamping interlayer.

Technical field

The present invention relates to dipulse solid engines technical fields, and in particular to it is a kind of entirety interlayer type dipulse start Machine.

Background technique

To adapt to tactical missile power demand of new generation, the dipulse solid engines with energy management advantage meet the tendency of and It is raw, by I/II pulse working time of design and interpulse period, the energy of engine operation whole process can effectively be divided Match, guided missile average speed is effectively improved in the case where not improving guided missile maximum speed, better meets missile propulsion system energy Controllable demand is measured, the fighting efficiency of guided missile is improved.

Interlayer isolation method is one of the advanced approach for realizing solid engines double-pulsed technology, have passive light weight, The high advantage of performance, but dipulse engine structure is increasingly complex, therefore design, general assembly and the engine propellant loading of interlayer Deng the technical difficult points for becoming interlayer type dipulse engine.

The structure of conventional interlayer type dipulse solid engines is as shown in Figure 1, by I pulse igniter 1, top cover 2, II pulse Igniter 3, I pulse powder column 7, radial interlayer 5, axial interlayer 6, II pulse powder column 4, insulated case 8 and jet pipe 9 form.Interlayer Structure and assembly method determine that interlayer manufactures the general assembly process of adoptable process and engine, it is conventional it is radial every Layer 5 is manufactured with top cover 2 using integral forming process, in order to guarantee the bonding and sealing performance between the two, bonding is mostly used to be molded Integral forming process, structure are as shown in Figure 2.The manufacturing process limits the forming technique of radial interlayer 5 itself, it is necessary to top cover 2 integral die shapings, integrally formed production efficiency and the reasonable rate of product are lower.

The assembling process of conventional interlayer type dipulse engine is as shown in Figure 3.1. completing combustion chamber manufacture, including insulated shell Body 8, I/II pulse powder column and axial interlayer 6；2. top cover 2 after molding and radial interlayer 5 are packed into combustion chamber, and complete diameter To the bonding of interlayer 5 and axial interlayer 6；3. installing jet pipe 9；4. installing I/II pulse igniter, the double arteries and veins of conventional interlayer type are completed Rush the assembly of engine.But for large scale, big L/D ratio dipulse engine, I pulse powder column, 7 length is longer, therefore radial The adhesive asserably process of interlayer 5 and axial interlayer 6 is very difficult, and current technology is difficult to ensure bonding quality, directly limits The development and production of large scale interlayer type dipulse engine.

Summary of the invention

In view of this, the present invention provides a kind of whole interlayer type dipulse engine, assembly technology is simple, connection can It leans on, be easily achieved.

Specific embodiments of the present invention are as follows:

A kind of entirety interlayer type dipulse engine, including igniter, top cover, interlayer, powder column, insulated case and jet pipe；

Powder column is arranged in insulated case, and the interlayer is integrally formed, and interlayer is by powder column along axially spaced at two sections；Insulation Shell one end is fixedly connected by top seal, the other end with jet pipe, while the top cover is fixedly connected with interlayer, and igniter is fixed On top cover.

Further, interlayer radial component end is provided inwardly with flange；The top cover is split type structure, is used for The flange of inside and outside clamping interlayer.

The utility model has the advantages that

The present invention solves the technical problem of radial interlayer and axial interlayer adhesive asserably using integrally formed interlayer, makes Interlayer manufacturing process liberated, be achieved in the monoblock type technique fabrication scheme of interlayer, can using various ways at Type improves production efficiency；Moreover, by the way of assembling integrally formed interlayer and top cover after, get rid of it is radial at present every Layer is limited with the integrally formed manufacturing process of top cover, connection be reliable, easy to realize be particularly suitable for large scale, big L/D ratio every Laminar dipulse solid engines.

Detailed description of the invention

Fig. 1 is conventional interlayer type dipulse engine schematic diagram；

Fig. 2 is conventional radial interlayer and top cover integral structure schematic diagram；

Fig. 3 is the assembling process schematic diagram of conventional interlayer type dipulse engine；

Fig. 4 connect sealed structural schematic diagram with top cover for integrally formed interlayer；

Fig. 5 is that integrally formed interlayer connect sealing structure partial enlargement diagram with top cover；

Fig. 6 is integrally formed interlayer and top cover assembling process schematic diagram；

Wherein, I pulse igniter of 1-, 2- top cover, II pulse igniter of 3-, II pulse powder column of 4-, 5- radial direction interlayer, 6- axis To interlayer, I pulse powder column of 7-, 8- insulated case, 9- jet pipe, 10- internal head cover, the outer top cover of 11-, 12- bolt.

Specific embodiment

The present invention will now be described in detail with reference to the accompanying drawings and examples.

A kind of whole interlayer type dipulse engine provided in this embodiment, including I pulse igniter 1, top cover 2, II arteries and veins Rush igniter 3, I pulse powder column 7, interlayer, II pulse powder column 4, insulated case 8 and jet pipe 9.

As shown in Figure 4, Figure 5, interlayer is integrally formed, and radial component end is provided inwardly with flange, and interlayer is soft rubber class Material has and compresses self-sealing characteristics.

Top cover 2 is split type structure, including internal head cover 10, outer top cover 11, and 10 outer circumference surface of internal head cover is equipped with and interlayer The end face engaged on the inside of flange.

Powder column be arranged in insulated case 8, interlayer by powder column along axially spaced at two sections, respectively I pulse powder column 7, II Pulse powder column 4；8 one end of insulated case is sealed by top cover 2, and the other end is fixedly connected with jet pipe 9, at the same the end face of internal head cover 10 with The engaging of interlayer flange, outer top cover 11 are fixed on the outside of interlayer flange, and inside and outside clamping interlayer turns over respectively for internal head cover 10, outer top cover 11 Side, and be fixed together by bolt 12.I pulse igniter 1, II pulse igniter 3 are each attached on top cover 2.

Specific design implementation process is as follows:

(1) it is required to design integrally formed spacer structure and 2 structure of top cover according to dipulse solid engines performance indicator, it is bright Connection closure size between true the two.

(2) integrally formed interlayer is manufactured using suitable technique, completes combustion chamber manufacture, combustion chamber include insulated case 8, I/II pulse powder column and integrally formed interlayer, wherein integrally formed interlayer front end protrudes head of combustion chamber.

(3) as shown in fig. 6, internal head cover 10 is packed into inside interlayer front end, outer top cover 11 is connected with engine insulated case 8 It connects, while ensuring to fill internal head cover 10 and being aligned with outer 11 threaded hole of top cover；Internal head cover 10 and outer top cover 11, the two is bolted Interlayer flange is compressed, sealing function is played.

(4) to be assembled to carry out airtight detection after the completion, examine connection structure sealing effect.

In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention. All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention Within protection scope.