Solid rocket engine middle ignition support installed on convergent section of spray pipe

Abstract

The invention discloses a solid rocket engine middle ignition support installed on a nozzle contraction section. The solid rocket engine middle ignition support comprises an igniter support base, an igniter support rod, an igniter cross-shaped support, a sponge gasket, an ignition device and a screw. The outer end face of the igniter support base is of a cambered surface structure and used for being bonded with a nozzle contraction section, and the center of the igniter support base is of a threaded hole structure and used for being in threaded connection with one end of an igniter support rod. The other end of the igniter support rod is of a small disc structure and used for installing an igniter cross-shaped support. The ignition device receives an external ignition signal through a wire extending to the middle of the combustion chamber to achieve ignition. Compared with the prior art, the solid rocket engine middle ignition support structure installed on the convergence section of the spray pipe has the advantages that installation and maintenance are convenient, and meanwhile the energy utilization rate and ignition reliability of ignition powder are improved; head and tail cavities of an engine combustion chamber are not occupied, and the explosive loading amount is increased.

Description

Technical Field

[0001] The invention relates to the field of solid rocket engines, in particular to a solid rocket engine middle ignition bracket installed on a nozzle convergence section. Background Art

[0002] The installation position of the solid rocket engine ignition device is an important factor affecting the ignition performance. It can generally be divided into a head ignition scheme installed on the engine head and a tail ignition scheme installed on the nozzle plug cover.

[0003] The tail ignition scheme generally installs the igniter on the nozzle convergence ring or plugging cover of the solid rocket engine, which has the advantages of easy installation and maintenance. However, due to the short ignition channel, once the engine nozzle plugging cover is opened, the igniter combustion products will be quickly discharged from the nozzle, causing part of the combustion of the ignition powder to be directly ejected from the nozzle. The combustion gas will increase the ignition pressure build-up time and the ignition delay time, and the energy utilization rate is low. In extreme cases, ignition failure may occur. The head ignition scheme refers to installing the igniter at the head of the engine. When the head ignition scheme is adopted, the ignition channel is longer, and all gases generated by the combustion of the ignition powder participate in the combustion, and the energy utilization rate is high. However, the installation and maintenance of the head ignition scheme are more complicated, and it will occupy the charge space at the head of the combustion chamber.

[0004] The existing solid rocket engine ignition structure generally simply adopts the tail ignition scheme or the head ignition scheme, which fails to achieve a balance between installation, maintenance convenience, charge amount, energy utilization and ignition reliability. Summary of the invention

[0005] The object of the present invention is to provide a solid rocket engine middle ignition bracket installed in the nozzle convergence section, which is convenient to install and maintain and increases the charge amount while improving the energy utilization rate and ignition reliability of the ignition powder.

[0006] The technical solution of the present invention is: to provide a solid rocket engine middle ignition bracket installed in the nozzle convergence section, including an igniter bracket base, an igniter bracket rod, an igniter cross bracket and a sponge gasket;

[0007] The outer end surface of the igniter bracket base is a curved surface structure, which is used to bond with the nozzle convergence section. The center of the igniter bracket base is a threaded hole structure, which is used to be threadedly connected with one end of the igniter bracket rod; the other end of the igniter bracket rod is a small disc structure, which is used to install the igniter cross bracket. The middle part of the two ends of the igniter bracket rod is a long straight hollow core tube, which is used to extend the installation position of the ignition device to the middle of the combustion chamber;

[0008] The igniter cross bracket is a cross-shaped bracket structure, in which one side of the far end of the cross is connected to the ignition device by screws, and the other side of the center of the cross is connected to the igniter bracket rod by screws; the sponge gasket is a circular flat gasket, which is used to provide radial support for the ignition device; the ignition device receives high-voltage pulse current from the external circuit box through a wire extending to the middle of the combustion chamber to achieve ignition.

[0009] Furthermore, the igniter bracket base, the igniter bracket rod, and the igniter cross bracket are all made of 2A12T4 aluminum alloy; and the sponge gasket is made of sponge rubber sheet.

[0010] Furthermore, the arc surface profile of the outer end surface of the igniter bracket base matches the profile of the bonding surface of the nozzle convergent section to ensure reliable bonding between the two; the middle parts of the two ends of the igniter bracket base are hollow I-beam structures.

[0011] Furthermore, one end of the igniter bracket rod is an external thread structure for threaded connection with the igniter bracket base; the other end of the igniter bracket rod is a small disc structure with six threaded through holes evenly distributed around the circumference of its upper edge for mounting the igniter cross bracket.

[0012] Furthermore, four threaded through holes are evenly distributed on the circumference of the cross distal end of the igniter cross bracket for connection with the ignition device by screws; and six through holes are evenly distributed on the circumference of the center of the cross.

[0013] Furthermore, the inner wall surface of the sponge gasket cooperates with the outer cylindrical surface of the ignition device, and the outer wall surface cooperates with the inner surface of the combustion chamber charge column, so as to provide radial support for the ignition device.

[0014] The solid rocket engine middle ignition bracket provided by the present invention and installed at the nozzle convergence section has the following beneficial effects:

[0015] (1) By bonding the ignition structure to the nozzle convergence section, the inconvenience of installation and maintenance when installed on the engine head is avoided, the length of the ignition channel is shortened, the engine's propellant space is increased, and the propellant amount is increased;

[0016] (2) By extending the ignition device to the middle of the engine, it is avoided that when it is installed at the rear of the engine, part of the ignition powder is burned and the generated gas is directly ejected from the nozzle, resulting in increased ignition pressure build-up time and ignition delay time, low energy utilization, and ignition failure in extreme cases;

[0017] (3) A balance is achieved between installation, maintenance convenience, charge quantity and ignition charge energy utilization.

[0018] (4) The lightweight, high-strength and low-melting-point 2A12 T4 aluminum alloy material can provide high-strength load support and can melt quickly after the engine is running without producing excess ejecta. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The invention will be further described below in conjunction with the accompanying drawings:

[0020] Figure 1 The present invention is a schematic diagram of the structure of a middle ignition bracket of a solid rocket engine installed in the nozzle convergence section.

[0021] In the figure: 1. igniter bracket base, 2. igniter bracket rod, 3. igniter cross bracket, 4. sponge gasket, 5. ignition device, 6. connecting screw M2.5×6, 7. connecting screw M2×4, 8. nozzle, 9. combustion chamber charge. DETAILED DESCRIPTION

[0022] The following is a further detailed description of the solid rocket engine middle ignition bracket installed in the nozzle convergence section proposed by the present invention in conjunction with the accompanying drawings and specific embodiments. The advantages and features of the present invention will become clearer according to the following description and claims. It should be noted that the accompanying drawings are all in a very simplified form and use non-precise ratios, which are only used to conveniently and clearly assist in explaining the purpose of the embodiments of the present invention.

[0023] The present invention provides a solid rocket engine middle ignition bracket structure installed in the nozzle convergence section, such as Figure 1 As shown, it includes an igniter bracket base, an igniter bracket rod, an igniter cross bracket, a sponge gasket, an ignition device, and screws.

[0024] The outer end face of the igniter bracket base is an R30 arc surface structure, which is used for bonding with the nozzle convergent section. Its arc surface contour matches the contour of the bonding surface of the nozzle convergent section to ensure reliable bonding between the two. The center of the igniter bracket base is an M10×1 internal threaded hole structure, which is used for threaded connection with one end of the igniter bracket rod. The middle part of both ends is a hollow wheel-type I-beam structure, and the three beams are evenly distributed in a 120° circle.

[0025] One end of the igniter bracket rod is an M10×1 external thread structure with a thread section length of 6mm, which is used for threaded connection with the M10×1 internal threaded hole of the igniter bracket base; the other end is a small disc structure with an outer diameter of 20mm, and six M2 threaded through holes are evenly distributed on the circumference of the upper edge, which is used to install the igniter cross bracket; the middle part of both ends is a hollow tube with a length of 120mm, which is used to extend the installation position of the ignition device to the middle of the combustion chamber, and there are 22 through holes with a diameter of 8mm hollowed out on the hollow tube.

[0026] The igniter cross bracket is a cross-shaped bracket structure, with four M2.5 threaded through holes evenly distributed around the circumference at the far end of the cross at a diameter of 70mm, which are used to connect to the ignition device through four M2.5×6 screws; six through holes with a diameter of 2.5mm are evenly distributed around the center circumference of the cross to leave installation space for the six M2×4 screws on the igniter bracket rod.

[0027] The sponge gasket is a circular flat gasket with an outer diameter of 85mm, an inner diameter of 62mm and a thickness of 6mm. Its inner wall surface matches the outer cylindrical surface of the ignition device, and its outer wall surface matches the inner surface of the combustion chamber charge column, which is used to provide radial support for the ignition device.

[0028] The central ignition bracket structure of the present invention has been put into engineering application, and the product processability, manufacturability and assembly processability have been verified. It has passed ground and flight test assessments, has a reliable structure, stable functions, and meets the use requirements.

[0029] The contents not described in detail in this specification belong to the prior art known to those skilled in the art. It is obvious to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention.

Claims

1. A solid rocket engine middle ignition bracket installed at the nozzle convergence section, characterized in that: It includes an igniter bracket base, an igniter bracket rod, an igniter cross bracket and a sponge gasket; The outer end surface of the igniter bracket base is a curved surface structure, which is used to bond with the nozzle convergence section. The center of the igniter bracket base is a threaded hole structure, which is used to be threadedly connected with one end of the igniter bracket rod; the other end of the igniter bracket rod is a small disc structure, which is used to install the igniter cross bracket. The middle part of the two ends of the igniter bracket rod is a long straight hollow core tube, which is used to extend the installation position of the ignition device to the middle of the combustion chamber; The igniter cross bracket is a cross-shaped bracket structure, in which one side of the far end of the cross is connected to the ignition device by screws, and the other side of the center of the cross is connected to the igniter bracket rod by screws; the sponge gasket is a circular flat gasket, which is used to provide radial support for the ignition device; the ignition device receives high-voltage pulse current from the external circuit box through a wire extending to the middle of the combustion chamber to achieve ignition.

2. The solid rocket engine middle ignition bracket installed at the nozzle convergence section according to claim 1, characterized in that: The materials of the igniter bracket base, the igniter bracket rod and the igniter cross bracket are all 2A12 T4 aluminum alloy; the material of the sponge gasket is a sponge rubber plate.

3. The solid rocket engine middle ignition bracket installed in the nozzle convergence section according to claim 1 or 2, characterized in that: The arc surface profile of the outer end surface of the igniter bracket base matches the profile of the bonding surface of the nozzle convergence section to ensure reliable bonding between the two; the middle parts of the two ends of the igniter bracket base are hollow I-beam structures.

4. The solid rocket engine middle ignition bracket installed at the nozzle convergence section according to claim 1, characterized in that: One end of the igniter bracket rod is an external thread structure for threaded connection with the igniter bracket base; the other end of the igniter bracket rod is a small disc structure with six threaded through holes evenly distributed around the upper edge for mounting the igniter cross bracket.

5. The solid rocket engine middle ignition bracket installed at the nozzle convergence section according to claim 4, characterized in that: The cross distal end of the igniter cross bracket has four threaded through holes evenly distributed on its circumference, which are used to be connected to the ignition device by screws; and six through holes are evenly distributed on the central circumference of the cross.

6. The solid rocket engine middle ignition bracket installed at the nozzle convergence section according to claim 4, characterized in that: The inner wall surface of the sponge gasket matches with the outer cylindrical surface of the ignition device, and the outer wall surface matches with the inner profile surface of the combustion chamber charge column, so as to provide radial support for the ignition device.

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