阅读说明：本技术 一种降低双脉冲固体发动机隔层应变的隔层结构 (Interlayer structure for reducing interlayer strain of double-pulse solid engine ) 是由 张翔宇 利凤祥 甘晓松 郭运强 郜伟伟 李青频 黄薇薇 张兵 李泽卫 于 2019-08-20 设计创作，主要内容包括：本发明公开了一种降低双脉冲固体发动机隔层应变的隔层结构,隔层结构将药柱分隔Ⅰ脉冲药柱和Ⅱ脉冲药柱,所述隔层结构包括轴向隔层和径向隔层；径向隔层包裹在Ⅱ脉冲药柱内圆周面,径向隔层尾部搭接在轴向隔层首部内侧；所述轴向隔层由首部圆弧过渡到尾部,轴向隔层包裹在Ⅱ脉冲药柱与Ⅰ脉冲药柱相对的端面。本发明能够减小径向隔层的环向应变,从而降低双脉冲固体发动机隔层应变。(The invention discloses an interlayer structure for reducing interlayer strain of a double-pulse solid engine, which separates a powder column into a pulse powder column I and a pulse powder column II, and comprises an axial interlayer and a radial interlayer; the radial interlayer is wrapped on the inner circumferential surface of the II pulse grain column, and the tail part of the radial interlayer is lapped on the inner side of the head part of the axial interlayer; the axial interlayer is transited from a head arc to a tail, and the axial interlayer wraps the end face, opposite to the pulse explosive column I, of the pulse explosive column II. The invention can reduce the circumferential strain of the radial interlayer, thereby reducing the interlayer strain of the double-pulse solid engine.)

1. An interlayer structure for reducing interlayer strain of a double-pulse solid engine separates a powder column into a pulse powder column I and a pulse powder column II, and is characterized in that the interlayer structure comprises an axial interlayer and a radial interlayer; the radial interlayer is wrapped on the inner circumferential surface of the II pulse grain column, and the tail part of the radial interlayer is lapped on the inner side of the head part of the axial interlayer; the axial interlayer is transited from a head arc to a tail, and the axial interlayer wraps the end face, opposite to the pulse explosive column I, of the pulse explosive column II.

2. A barrier construction for reducing barrier strain in a dipulse solid engine as claimed in claim 1, wherein said axial barrier comprises three arcs, each arc having an angle of no less than 90 °, a first arc opening facing outwardly, a second arc opening facing inwardly and a trailing arc opening facing outwardly.

Technical Field

The invention relates to the technical field of solid engines, in particular to an interlayer structure for reducing interlayer strain of 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 the advanced schemes for realizing the double-pulse technology of the solid engine, and has the advantages of light passive mass and high performance. The difficulty is that the interlayer can be strained and easily damaged when bearing the I pulse working pressure of the engine, so that the interlayer fails and even the engine explodes. The interlayer is composed of an axial interlayer and a radial interlayer, wherein the radial interlayer is changed greatly under pressure and is easier to damage. The bearing capacity of the radial partition is closely related to the structure of the radial partition, and is limited by the structural size requirement of the engine and the requirement of ballistic characteristics in I/II pulse, and the design and the manufacture of the partition are one of the core technologies of the double-pulse solid engine.

At present, an effective method for reducing radial interlayer strain and easily realizing I/II pulse internal trajectory control is lacked in interlayer design, the method is often limited by an interlayer manufacturing process, and an experimental and trial mode is mostly adopted, so that the development cost and the development period are greatly increased.

The interlayer needs to bear high temperature and high pressure environment in the combustion process of I pulse grain of the engine, and ensures the sealing and heat insulation performance, wherein the radial interlayer can generate larger annular strain under the pressure bearing, and the failure is very easy to damage. The radial interlayer of the conventional interlayer type double-pulse solid engine is shown in figure 1, a radial interlayer A and an axial interlayer B are designed in a vertical structure, an I/II pulse charge column has a simple structure, and the adjusting capacity of an inner trajectory is weak; under the same quality requirement of the I/II pulse grain, the length of the radial interlayer is longer, so the annular stress under pressure is changed greatly, and the damage is easier.

Disclosure of Invention

In view of this, the invention provides an interlayer structure for reducing interlayer strain of a double-pulse solid engine, which can reduce circumferential strain of a radial interlayer, thereby reducing interlayer strain of the double-pulse solid engine.

The specific embodiment of the invention is as follows:

an interlayer structure for reducing interlayer strain of a double-pulse solid engine separates a first pulse explosive column from a second pulse explosive column by the interlayer structure, and the interlayer structure comprises an axial interlayer and a radial interlayer; the radial interlayer is wrapped on the inner circumferential surface of the II pulse grain column, and the tail part of the radial interlayer is lapped on the inner side of the head part of the axial interlayer; the axial interlayer is transited from a head arc to a tail, and the axial interlayer wraps the end face, opposite to the pulse explosive column I, of the pulse explosive column II.

Furthermore, the axial interlayer comprises three sections of circular arcs, the angle of each section of circular arc is not smaller than 90 degrees, the opening of the first section of circular arc faces outwards, the opening of the second section of circular arc faces inwards, and the opening of the tail end circular arc faces outwards.

Has the advantages that:

1. the arc-transition axial interlayer structure shortens the length of the radial interlayer under the condition that the I/II pulse grain charging ratio is certain, thereby reducing the circumferential strain of the radial interlayer and reducing the possibility of pressure-bearing damage; and secondly, as the vertical structure of the axial interlayer is changed, the parameter of the arc angle of the axial interlayer is increased, which is equivalent to the adjustment parameter of the combustion surface of the I/II pulse grain, so that the inner trajectory adjustment performance is improved.

2. The axial interlayer of the invention is composed of three sections of arcs, the structure is simple, the realization is easy, the arc angle of each section of arc is adjusted according to the inner ballistic requirement of each type of double-pulse engine and the calculation result of the circumferential strain of the radial interlayer, and the optimal combination can be obtained.

Drawings

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

FIG. 2 is a schematic diagram of a stratified double pulse engine according to the present invention;

FIG. 3 is a schematic view of a spacer structure according to the present invention;

wherein, 1-I pulse igniter, 2-II pulse igniter, 3-II pulse grain, 4-radial interlayer, 5-axial interlayer, 6-I pulse grain, 7-spray pipe and 8-heat insulation shell.

Detailed Description

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

As shown in figure 2, the interlayer type double-pulse solid engine structure comprises an I pulse igniter 1, an II pulse igniter 2, an I pulse grain 6, an interlayer structure, an II pulse grain 3, a spray pipe 7 and a heat insulation shell 8, wherein the interlayer structure separates the grain into the I pulse grain 6 and the II pulse grain 3.

The interlayer structure for reducing interlayer strain of the double-pulse solid engine provided by the embodiment comprises a radial interlayer 4 and an axial interlayer 5, wherein the radial interlayer 4 wraps the inner circumferential surface of the II pulse explosive column 3, the axis of the solid engine is arranged in the interlayer, the tail part of the radial interlayer 4 is bonded on the inner side of the head part of the axial interlayer 5 to form an integral sealing structure of the interlayer, and the radius length of a bonding part C is consistent with the radius length of the radial interlayer 4. Axial interlayer 5 wraps up at II pulse powder columns 3 and the relative terminal surface of I pulse powder column 6, and axial interlayer 5 passes through the afterbody by the head circular arc, and axial interlayer 5 includes the three-section circular arc, and the angle of every section circular arc is all not less than 90, and the first section circular arc opening is outwards, and the second section circular arc opening is inwards, and the tail end circular arc opening is outwards.