A pyrotechnic diaphragm for a multiple-start liquid rocket engine

Abstract

The present invention belongs to the technical field of liquid rocket engines, and discloses an initiator diaphragm for a multiple-start liquid rocket engine, comprising: a diaphragm body; an outer ring score line, an inner ring score line and a star-shaped score line are provided on the first disk surface of the diaphragm body; the star-shaped score line is arranged between the outer ring score line and the inner ring score line, and the two ends of the star-shaped score line are respectively connected to the outer ring score line and the inner ring score line; the inner ring score line is an open arc score line, and the outer ring score line is a closed circular ring score line. The initiator diaphragm for a multiple-start liquid rocket engine provided by the present invention can greatly increase the difference in pressure on the front and back sides of the initiator diaphragm, and improve working reliability and safety factor.

Description

Technical Field

[0001] The invention relates to the technical field, and in particular to an initiator diaphragm for a multiple-start liquid rocket engine. Background Art

[0002] Liquid rocket engines widely use pyrotechnics for ignition, which requires that the pyrotechnics cannot be ignited by the combustion gas in the engine. Usually, a pyrotechnic diaphragm is used to isolate and seal the pyrotechnic gunpowder from the engine. The pyrotechnic diaphragm needs to have the following characteristics: 1) When the pyrotechnic is ignited, the first side of the pyrotechnic diaphragm can be broken at a relatively low pressure to avoid an explosion caused by excessive pressure in the pyrotechnic shell; 2) The second side of the pyrotechnic diaphragm can withstand the high pressure and high temperature environment generated by the combustion gas in the engine cavity; that is, the pyrotechnic diaphragm needs to be able to withstand the reverse high temperature environment, and at the same time, the positive and negative pressure bearing capacity must have a sufficiently large difference, so as to ensure that it has a sufficiently high reliability and safety factor. The existing pyrotechnic diaphragm is a diaphragm structure with star-shaped engraved lines. The positive and negative pressure bearing capacity of this structure is not much different, and the reliability and safety factor are relatively low. Summary of the invention

[0003] The invention provides an initiator diaphragm for a multiple-start liquid rocket engine, which solves the technical problems in the prior art that the initiator diaphragm has little difference in forward and reverse pressure bearing capacity and a low safety factor.

[0004] In order to solve the above technical problems, the present invention provides an initiator diaphragm for a multiple-start liquid rocket engine, comprising: a diaphragm body;

[0005] The first disk surface of the diaphragm body is provided with outer ring engraved lines, inner ring engraved lines and star-shaped engraved lines;

[0006] The star-shaped engraved line is arranged between the outer ring engraved line and the inner ring engraved line, and two ends of the star-shaped engraved line are respectively connected to the outer ring engraved line and the inner ring engraved line;

[0007] The inner ring engraved lines are open arc engraved lines, and the outer ring engraved lines are closed circular ring-shaped engraved lines.

[0008] Further, the outer ring score line includes: a circular ring-shaped groove;

[0009] The width of the annular groove is 0.5 mm.

[0010] Further, an open arc-shaped groove;

[0011] The width of the open arc-shaped groove is 0.5 mm.

[0012] Furthermore, the arc angle of the open arc-shaped groove ranges from 4 / 3π to 3 / 2π.

[0013] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages:

[0014] The pyrotechnic diaphragm for multiple-start liquid rocket engines provided in the embodiment of the present application makes the diaphragm easier to deform by providing outer ring score lines and star-shaped score lines on the diaphragm body, and arranges inner ring score lines inside the star-shaped score lines so that the stress generated by the deformation is concentrated here, so that it is easier to rupture when subjected to positive pressure; it is also worth noting that the setting of the three-layer score lines can increase the stress peak value of the diaphragm when subjected to positive pressure, so that the diaphragm can be ruptured under a relatively low positive pressure. On the other hand, by utilizing the condition that the area of ​​the diaphragm subjected to reverse pressure is smaller than the area subjected to forward pressure in the assembled state, the outer ring score lines and the star-shaped score lines are pressed against the wall of the nozzle, and only the area within the inner ring score lines is subjected to reverse pressure, and there are no score lines, so it has a strong ability to withstand reverse pressure; thereby achieving the effect of reducing the tolerable forward pressure and increasing the tolerable reverse pressure, thereby greatly improving the difference in the forward and reverse pressure bearing capacity of the pyrotechnic diaphragm, and ensuring working reliability and safety factor. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present invention. Moreover, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0016] Figure 1 A schematic structural diagram of an initiator diaphragm for a multiple-start liquid rocket engine provided by an embodiment of the present invention;

[0017] Figure 2 A cross-sectional view of an initiator diaphragm for a multiple-start liquid rocket engine provided by an embodiment of the present invention;

[0018] Figure 3 A schematic structural diagram of a pressure testing device for a diaphragm of an initiator for a multiple-start liquid rocket engine provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0019] The embodiment of the present application provides an pyrotechnic diaphragm for a multiple-start liquid rocket engine, thereby solving the technical problem in the prior art that the pyrotechnic diaphragm has little difference in its positive and negative pressure bearing capacity and a low safety factor.

[0020] In order to better understand the above-mentioned technical scheme, the above-mentioned technical scheme will be described in detail below in conjunction with the accompanying drawings and specific implementation methods. It should be understood that the embodiments of the present invention and the specific features in the embodiments are detailed descriptions of the technical scheme of the present application, rather than limitations on the technical scheme of the present application. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other.

[0021] See also Figure 1 and Figure 2 A pyrotechnic diaphragm for a multiple-start liquid rocket engine comprises: a diaphragm body 1; an outer ring score line 11, an inner ring score line 12 and a star-shaped score line 13 are provided on the first disk surface of the diaphragm body 1; a three-layer score line structure is formed, and in the assembled state, the large disk surface is under pressure, thereby increasing the stress peak value when the diaphragm is subjected to positive pressure, so that the diaphragm can be ruptured under a lower positive pressure, thereby reducing the positive pressure bearing capacity.

[0022] The star-shaped engraved line 13 is arranged between the outer ring engraved line 11 and the inner ring engraved line 12, and the two ends of the star-shaped engraved line 13 are respectively connected to the outer ring engraved line 11 and the inner ring engraved line 12; by providing the outer ring engraved line 11 and the star-shaped engraved line 13 on the diaphragm body 1, the diaphragm is more easily deformed, and the inner ring engraved line 12 is arranged inside the star-shaped engraved line 13 so that the stress generated by the deformation is concentrated here, so that it is easier to rupture when subjected to positive pressure; thereby further reducing the ability to resist positive pressure.

[0023] In this embodiment, in order to ensure the deformation ability, the outer ring score line 11 is a circular groove with a width of 0.5 mm.

[0024] In order to ensure combustion safety and prevent the ruptured diaphragm body from entering the interior of the equipment, the inner ring score line 12 is an open arc score line, that is, the inner ring score line 12 is a non-closed circular groove, and a part will remain integral with the diaphragm body 1, so that after breaking along the inner ring score line 12, it will still be connected to the diaphragm body 1.

[0025] Similarly, the open-type arc-shaped engraved line is an arc-shaped groove with a width of 0.55 mm, thereby ensuring a larger rupture path and facilitating positive pressure rupture.

[0026] Furthermore, in this embodiment, the curvature range of the open arc-shaped groove is 4 / 3π to 3 / 2π.

[0027] The groove shape of the annular groove and the arc-shaped groove is rectangular or V-shaped.

[0028] See also Figure 3 This embodiment also provides a tool that is convenient for pressure testing the diaphragm of the pyrotechnic device.

[0029] The tooling includes: a connecting body 2; a first connecting pipe port 21 and a second connecting pipe port 25 are provided on the connecting body 2; and there is an obvious inner diameter difference between the two connecting parts, that is, the first connecting pipe port 21 is a small inner diameter pipe port, and a pressure platform is arranged at its bottom end. During operation, the diaphragm body 1 is pressed against the pressure platform by a gasket 22 and a clamping block 23 arranged in the second connecting pipe port 25, so that the first connecting pipe port 21 faces the area within the inner ring scale line 12, and the second connecting pipe port 25 corresponds to the outer ring scale line 11 and all areas inside it. The gasket 22 and the clamping block 23 are both provided with through holes 24 in the center, so that external fluid pressure equipment can be connected during pressure testing.

[0030] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages:

[0031] The pyrotechnic diaphragm for multiple-start liquid rocket engines provided in the embodiment of the present application makes the diaphragm easier to deform by providing outer ring score lines and star-shaped score lines on the diaphragm body, and arranges inner ring score lines inside the star-shaped score lines so that the stress generated by the deformation is concentrated here, so that it is easier to rupture when subjected to positive pressure; it is also worth noting that the setting of the three-layer score lines can increase the stress peak value of the diaphragm when subjected to positive pressure, so that the diaphragm can be ruptured under a relatively low positive pressure. On the other hand, by utilizing the condition that the area of ​​the diaphragm subjected to reverse pressure is smaller than the area subjected to forward pressure in the assembled state, the outer ring score lines and the star-shaped score lines are pressed against the wall of the nozzle, and only the area within the inner ring score lines is subjected to reverse pressure, and there are no score lines, so it has a strong ability to withstand reverse pressure; thereby achieving the effect of reducing the tolerable forward pressure and increasing the tolerable reverse pressure, thereby greatly improving the difference in the forward and reverse pressure bearing capacity of the pyrotechnic diaphragm, and ensuring working reliability and safety factor.

[0032] Finally, it should be noted that the above specific implementation methods are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to examples, those skilled in the art should understand that the technical solution of the present invention can be modified or replaced by equivalents without departing from the spirit and scope of the technical solution of the present invention, which should be included in the scope of the claims of the present invention.

Claims

1. A pyrotechnic diaphragm for a multiple-start liquid rocket engine, characterized in that: include: Diaphragm body; The first disk surface of the diaphragm body is provided with outer ring engraved lines, inner ring engraved lines and star-shaped engraved lines; The star-shaped engraved line is arranged between the outer ring engraved line and the inner ring engraved line, and two ends of the star-shaped engraved line are respectively connected to the outer ring engraved line and the inner ring engraved line; The inner ring engraved lines are open arc engraved lines, and the outer ring engraved lines are closed circular ring-shaped engraved lines.

2. The pyrotechnic diaphragm for a multiple-start liquid rocket engine according to claim 1, characterized in that: The outer ring score line includes: a circular ring groove; The width of the annular groove is 0.5 mm.

3. The pyrotechnic diaphragm for a multiple-start liquid rocket engine according to claim 2, characterized in that: The open-type circular arc engraved lines include: an open-type circular arc groove; The width of the open arc-shaped groove is 0.5 mm.

4. The pyrotechnic diaphragm for a multiple-start liquid rocket engine according to claim 3, characterized in that: The arc angle of the open circular arc groove ranges from 4 / 3π to 3 / 2π.

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