Ignition support for solid rocket engine in middle of convergent section of nozzle

Abstract

The application discloses a middle ignition support of a solid rocket engine installed on a convergent section of a nozzle, which comprises an igniter support base, an igniter support rod, an igniter cross support, a sponge gasket, an ignition device and a screw. The outer end surface of the igniter support base is an arc surface structure used for bonding with the convergent section of the nozzle, and the center is a threaded hole structure used for threaded connection with one end of the igniter support rod; the other end of the igniter support rod is a small disc structure used for mounting the igniter cross support; the ignition device receives an external ignition signal through a lead wire extended into the middle part of the combustion chamber to realize ignition. Compared with the prior art, the middle ignition support of the solid rocket engine installed on the convergent section of the nozzle has the advantages and beneficial effects that: the energy utilization rate of the ignition powder and the ignition reliability are improved while the installation and maintenance are convenient; the middle ignition support does not occupy the head and tail cavity of the engine combustion chamber, and the charge capacity is improved.

Description

Technical Field

[0001] This invention relates to the field of solid rocket engines, and in particular to an ignition bracket installed in the converging section of a solid rocket engine. Background Technology

[0002] The installation location of the ignition device of a solid rocket engine is an important factor affecting ignition performance. It can generally be divided into head ignition schemes, which are installed at the engine head, and tail ignition schemes, which are installed on the nozzle plug.

[0003] Tail-end ignition schemes typically mount the igniter on the nozzle convergence ring or cap of the solid rocket motor, offering advantages in installation and maintenance. However, due to the short ignition path, if the nozzle cap is opened, combustion products from the igniter will rapidly escape from the nozzle, causing some of the propellant combustion gases to be directly ejected. This leads to increased ignition pressure build-up time and ignition delay time, low energy utilization, and in extreme cases, ignition failure. Head-end ignition schemes, on the other hand, mount the igniter at the head of the engine. With head-end ignition, the ignition path is longer, and all gases generated by the propellant combustion participate in combustion, resulting in high energy utilization. However, head-end ignition schemes are more complex to install and maintain, and they occupy the propellant loading space at the head of the combustion chamber.

[0004] Existing solid rocket motor ignition structures generally use simple tail ignition or head ignition schemes, which cannot achieve a balance between ease of installation and maintenance, propellant load, energy utilization rate and ignition reliability. Summary of the Invention

[0005] The purpose of this invention is to provide an ignition bracket for the middle section of a solid rocket motor installed in the converging section of the nozzle, which improves the energy utilization rate and ignition reliability of the propellant while being convenient to install and maintain and increasing the amount of propellant.

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

[0007] The outer end face of the igniter bracket base is an arc-shaped structure for bonding with the converging section of the nozzle. The center of the igniter bracket base is a threaded hole structure for threaded connection with one end of the igniter bracket rod. The other end of the igniter bracket rod is a small disc structure for mounting the igniter cross bracket. The middle part of both ends of the igniter bracket rod is a long, straight, hollow core tube for extending the ignition device installation position to the middle of the combustion chamber.

[0008] The igniter cross bracket is a cross-shaped bracket structure, wherein 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 pad is a circular flat pad 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, igniter bracket rod, and igniter cross bracket are all made of 2A12T4 aluminum alloy; the sponge pad is made of sponge rubber sheet.

[0010] Furthermore, the arc contour of the outer end face of the igniter bracket base matches the contour of the bonding surface of the nozzle convergent section to ensure reliable bonding between the two; the middle part of both ends of the igniter bracket base is a hollow I-beam structure.

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

[0012] Furthermore, the igniter cross bracket has four threaded through holes evenly distributed around the distal circumference of the cross for connection with the ignition device via screws; and six through holes evenly distributed around the central circumference of the cross.

[0013] Furthermore, the inner wall surface of the sponge pad mates with the outer cylindrical surface of the ignition device, and the outer wall surface mates with the inner profile of the combustion chamber propellant grain, thereby providing radial support for the ignition device.

[0014] The beneficial effects of the solid rocket motor ignition bracket installed in the converging section of the nozzle provided by this invention are:

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

[0016] (2) By extending the ignition device to the middle of the engine, the combustion gas generated by the combustion of some ignition propellant when it is installed at the rear of the engine is avoided from being directly ejected from the nozzle, which would increase the ignition pressure build-up time and ignition delay time, resulting in low energy utilization and, in extreme cases, ignition failure.

[0017] (3) It achieves a balance between ease of installation and maintenance, charge quantity and ignition energy utilization rate.

[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 working, without producing excess ejected material. Attached Figure Description

[0019] The invention will be further described below with reference to the accompanying drawings:

[0020] Figure 1 This is a schematic diagram of the ignition support structure in the middle of a solid rocket motor installed in the converging section of the nozzle, according to the present invention.

[0021] In the diagram: 1. Igniter bracket base, 2. Igniter bracket rod, 3. Igniter cross bracket, 4. Sponge pad, 5. Ignition device, 6. Connecting screw M2.5×6, 7. Connecting screw M2×4, 8. Nozzle, 9. Combustion chamber propellant. Detailed Implementation

[0022] The following detailed description, in conjunction with the accompanying drawings and specific embodiments, provides a more comprehensive account of the solid rocket motor ignition bracket mounted in the nozzle convergence section proposed in this invention. The advantages and features of this invention will become clearer from the following description and claims. It should be noted that the drawings are all in a very simplified form and use non-precise ratios, and are only used to facilitate and clarify the illustration of the embodiments of this invention.

[0023] This invention provides a solid rocket motor mid-section ignition support 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 pad, an ignition device, and screws.

[0024] The outer end face of the igniter bracket base is an R30 arc surface structure, which is used to bond 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. The center of the igniter bracket base is an M10×1 internal thread hole structure, which is used to connect with one end of the igniter bracket rod. The middle of both ends is a hollow disc-shaped I-beam structure, with the three beams evenly distributed in a 120° circle.

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

[0026] The igniter cross bracket has a cross-shaped bracket structure. At the far end of the cross, 70mm in diameter, there are four M2.5 threaded through holes evenly distributed around the circumference for connection with the ignition device via four M2.5×6 screws. At the center of the cross, there are six 2.5mm diameter through holes evenly distributed around the circumference to provide installation space for the six M2×4 screws on the igniter bracket rod.

[0027] The sponge pad is a circular flat pad with an outer diameter of 85mm, an inner diameter of 62mm, and a thickness of 6mm. Its inner wall surface mates with the outer cylindrical surface of the ignition device, and its outer wall surface mates with the inner profile of the combustion chamber propellant grain, thus providing radial support for the ignition device.

[0028] The central ignition bracket structure described in this invention has been applied in engineering. The product's manufacturability, production feasibility, and assembly processability have all been verified. It has also passed ground and flight tests, demonstrating structural reliability, stable function, and meeting usage requirements.

[0029] The contents not described in detail in this specification are prior art known to those skilled in the art. It will be apparent 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 invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within the present invention.

Claims

1. An ignition bracket installed in the middle of the nozzle convergence section of a solid rocket motor, characterized in that, Includes igniter bracket base, igniter bracket rod, igniter cross bracket and sponge pad; The outer end face of the igniter bracket base is an arc-shaped structure for bonding with the converging section of the nozzle. The center of the igniter bracket base is a threaded hole structure for threaded connection with one end of the igniter bracket rod. The other end of the igniter bracket rod is a small disc structure for mounting the igniter cross bracket. The middle part of both ends of the igniter bracket rod is a long, straight, hollow core tube for extending the ignition device installation position to the middle of the combustion chamber. The igniter cross bracket is a cross-shaped bracket structure, wherein 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 pad is a circular flat pad 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 motor ignition bracket installed in the converging section of the nozzle as described in claim 1, characterized in that, The igniter bracket base, igniter bracket rod, and igniter cross bracket are all made of 2A12 T4 aluminum alloy; the sponge pad is made of sponge rubber sheet.

3. The solid rocket motor ignition bracket installed in the converging section of the nozzle as described in claim 1 or 2, characterized in that, The arc contour of the outer end face of the igniter bracket base matches the contour of the bonding surface of the nozzle convergence section to ensure reliable bonding between the two; the middle part of both ends of the igniter bracket base is a hollow I-beam structure.

4. The solid rocket motor ignition bracket installed in the converging section of the nozzle as described in claim 1, characterized in that, One end of the igniter bracket rod has an external thread structure for threaded connection with the igniter bracket base; the other end of the igniter bracket rod has a small disc structure with six threaded through holes evenly distributed around its upper edge for mounting the igniter cross bracket.

5. The solid rocket motor ignition bracket installed in the converging section of the nozzle as described in claim 4, characterized in that, The igniter cross bracket has four threaded through holes evenly distributed around the distal circumference of the cross for connection with the ignition device via screws; and six through holes evenly distributed around the central circumference of the cross.

6. The solid rocket motor ignition bracket installed in the converging section of the nozzle as described in claim 4, characterized in that, The inner wall surface of the sponge pad mates with the outer cylindrical surface of the ignition device, and the outer wall surface mates with the inner profile of the combustion chamber propellant grain, thereby providing radial support for the ignition device.

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