A solid rocket motor with a completely ablation-embedded impeller ignition tube

Abstract

This invention discloses a completely ablation-embedded impact ignition tube for solid rocket motors, belonging to the field of solid rocket motor design. The ignition tube includes a shell, a sintered glass base, an integrated explosive foil chip, a primary HNS-IV propellant grain, a primary propellant grain positioning ring, a sealing aluminum foil sheet, a secondary BPN propellant grain, and an insulating gasket. After receiving pulsed high-voltage energy from the pin on the sintered glass base, the integrated explosive foil chip operates and outputs a high-speed flying blade, which impacts and detonates the HNS-IV propellant grain. After the detonation wave attenuates, it impacts and ignites the BPN propellant grain, ultimately igniting the main propellant charge of the engine. This invention designs an "impact-detonation-ignition" ignition sequence, fully utilizing the short-pulse impact energy of the small-sized thin flying blade, improving the safety and reliability of the product. Simultaneously, the raw materials can be completely ablated, avoiding blockage or damage to the engine nozzle; therefore, it does not affect the internal ballistic performance of the engine after application.

Description

Technical Field

[0001] This invention relates to a solid rocket motor with a completely ablation-embedded impact plate ignition tube, belonging to the field of solid rocket motors. Background Technology

[0002] In the field of solid rocket motors, inline ignition devices are used to ignite the engine's ignition system. These next-generation safe ignition devices feature both electronic safety mechanisms and intrinsically safe pyrotechnic components. For single-chamber dual-thrust or multi-pulse engines, mid-stage ignition or firing is typically required. Therefore, the impact-plate ignition tube in the inline ignition device needs to be embedded within the engine's combustion chamber. This embedded ignition scheme requires a small impact-plate ignition tube structure that can be completely ablated at the high temperatures (not less than 2500K) of the engine combustion chamber, ensuring that no solid debris will cause blockage or damage to the nozzle, thus preserving the engine's internal ballistic performance. Summary of the Invention

[0003] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a solid rocket motor with a completely ablation-embedded impact plate ignition tube. Through structural design and raw material design, the problems of large volume and incomplete ablation of the impact plate ignition tube are solved, thereby improving safety and reliability.

[0004] The technical solution of this invention is:

[0005] A solid rocket motor with a completely ablation-embedded impeller ignition tube includes a shell, a glass sintered seat, an integrated explosive foil chip, a primary HNS-IV propellant grain, a primary propellant grain positioning ring, a sealing aluminum foil sheet, a secondary BPN propellant grain, and an insulating gasket.

[0006] The outer shell is made of aluminum alloy, and the inner cavity contains a glass sintering seat, an integrated explosive foil chip, a primary HNS-IV propellant, a primary propellant positioning ring, a sealing aluminum foil sheet, a secondary BPN propellant and an insulating pad.

[0007] The glass sintering base includes a glass body and two conductive pins, which are prepared by a sintering process;

[0008] The integrated explosive foil chip is fixed between two conductive pins and connected to the two conductive pins through the chip pads to achieve electrical conduction;

[0009] The primary HNS-IV propellant grain is placed in the primary propellant grain positioning ring, which is located on the upper surface of the integrated explosive foil chip.

[0010] The secondary BPN propellant grain is located above the primary propellant grain positioning ring;

[0011] The sealing aluminum foil is used to seal the outlet of the ignition tube;

[0012] The insulating pad circumferentially wraps around the pins, providing electrical insulation between the pins and between the pins and the housing.

[0013] Furthermore, a semi-circular step is cut at the head of each of the two conductive pins, and the integrated explosion foil chip is fixed on the two semi-circular steps.

[0014] Furthermore, the primary propellant positioning ring is provided with an HNS-IV propellant detonation attenuation channel, located directly above the primary HNS-IV propellant, with a detonation wave attenuation distance of 0.5mm to 5mm, realizing the impact-to-combustion process of the HNS-IV propellant on the BPN propellant.

[0015] Furthermore, the secondary BPN propellant, serving as the output propellant, is a hollow cylindrical shape, eliminating the impact of the impact pressure caused by the detonation of the primary HNS-IV propellant on the structural integrity.

[0016] Furthermore, the inner wall of the outer shell adopts a tapered and stop-limiting design to prevent the glass sintering seat from falling off in the reverse direction due to impact.

[0017] Furthermore, the outer wall of the casing is threaded to secure the ignition tube in the ignition device.

[0018] Furthermore, the chip pads and two conductive pins are electrically connected through gold wire bonding or soldering processes.

[0019] Furthermore, the outer casing is made of aluminum alloy rods.

[0020] Furthermore, a potting compound with excellent electrical and structural properties is injected into the tail end of the ignition tube and cured at room temperature.

[0021] Furthermore, the working process of the impact ignition tube is as follows: two conductive pins receive pulsed high-voltage energy, the integrated explosive foil chip outputs a high-speed flying plate, which impacts and detonates the primary HNS-IV propellant, and after the detonation wave decays, it impacts and ignites the secondary BPN propellant, which finally ignites the main propellant of the engine.

[0022] The advantages of this invention compared to the prior art are:

[0023] (1) The present invention designs an embedded impact plate ignition tube that can be completely ablated. Compared with existing products, the raw materials used in the impact plate ignition tube of the present invention can be completely ablated, avoiding blockage or damage to the engine nozzle.

[0024] (2) The present invention designs an “impact-detonation-deflagration” ignition sequence to replace the existing “impact-combustion” sequence, which makes full use of the short pulse impact energy of the small-sized thin flying blade, and fundamentally improves the safety and reliability of the product from the perspective of pyrotechnics.

[0025] (3) The shell of the present invention adopts a tapered and stop limit design to avoid the sintering seat from falling off during the impact process, fully utilize the detonation energy of the primary HNS-IV propellant, and ensure that the combustion flame of the secondary BPN propellant is output from the head rather than the tail.

[0026] (4) The outer shell of the present invention is designed with mounting threads, which is beneficial for fixing the impact plate ignition tube in the ignition device. Attached Figure Description

[0027] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0028] Figure 1 This is a schematic diagram of the embedded impact plate ignition tube structure according to an embodiment of the present invention;

[0029] Figure 2 This is a schematic diagram of the glass sintering base and integrated exploding foil chip mounting structure according to an embodiment of the present invention;

[0030] Figure 3 This is a schematic diagram of the outer shell structure according to an embodiment of the present invention. Detailed Implementation

[0031] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

[0032] This invention proposes a completely ablation-embedded impact ignition tube for solid rocket motors, such as... Figure 1 As shown, the components include a housing 1, a glass sintered seat 2, an integrated explosive foil chip 3, a primary HNS-IV (Type IV hexanitrostilbene) propellant 4, a primary propellant locating ring 5, a sealing aluminum foil sheet 6, a secondary BPN (B / KNO3) propellant 7, an insulating gasket 8, and a potting compound 9. The raw materials used in the above components can be completely burned under the high-temperature combustion gas inside the engine, without producing any flying debris, and will not cause nozzle blockage or damage, thus not affecting the internal ballistic performance of the engine.

[0033] The glass sintering base 2 is made of glass, which can be completely ablated by the high temperature of the combustion chamber. It is fabricated by sintering the glass body and two conductive Kovar alloy or copper pins, enabling the structural installation and electrical connection of the integrated explosive foil chip. Specifically, the integrated explosive foil chip is installed between the two pins of the sintering base, and the electrical connection between the pins and the chip is achieved through gold wire bonding or soldering. Figure 2 As shown, the pin diameter is 1mm, and in order to reduce the product diameter, a semi-circular step with a diameter of 0.5mm and a depth of 1mm is cut at the pin head, and the integrated explosion foil chip 3 is fixed on the semi-circular step.

[0034] The integrated explosive foil chip 3 is mass-produced using microelectromechanical systems (MEMS) technology, as detailed in "Research on the Ignition Performance of MEMS Integrated Explosive Foil Chips". The integrated explosive foil chip 3 is placed above two pin steps. Using gold wire bonding or soldering, eight 25μm diameter gold wires are bonded between the chip pads and pins on both sides, achieving internal electrical conduction and ultimately converting pulse capacitor energy into flyer kinetic energy.

[0035] The outer casing 1 provides component mounting, structural support, and mounting threads. The outer wall of the casing is designed with M10×1-6g threads to provide structural mounting for the ignition tube. The outer casing 1 uses 2A12 grade bars as specified in GB / T3191-2019 "Aluminum and Aluminum Alloy Extruded Bars," and the aluminum alloy material can be completely ablated under the high-temperature environment of the engine combustion chamber. The internal casing employs a tapered and stop-limit design, such as... Figure 3 As shown, the taper is 1:5 and the stop step width is 0.4mm to prevent the sintering seat from falling off in the reverse direction due to impact.

[0036] The primary HNS-IV charge 4 is the permissible charge for the in-line safety ignition device, making full use of the short-pulse impact energy of the small-sized, thin explosive foil chip. The secondary BPN charge 7, as the output charge, is a hollow cylindrical shape, eliminating the impact of the high impact pressure caused by the detonation of the primary HNS-IV charge 4 on structural integrity, and has sufficient output energy to ensure a reliable ignition device.

[0037] The secondary BPN propellant column 7 serves as the output propellant column, and its formulation meets the requirements specified in GJB6217-2008 "Specification for Boron / Potassium Nitrate Ignition Explosives". It has sufficient output energy to ensure a reliable ignition device.

[0038] HNS-IV and BPN drug columns 4 and 7, with specific mass and density, were compressed into a drug ring using a mature drug compression process. HNS-IV drug column 4 had a mass of 10 mg and a density of 1.6 g / cm³. 3 The BPN drug column 7 has a mass of 370 mg and a density of 1.75 g / cm³. 3 .

[0039] The primary propellant positioning ring 5 provides a detonation attenuation channel, located directly above the primary HNS-IV propellant 4. The height of the attenuation channel is set to 1 mm and the diameter to 1.8 mm, reliably realizing the impact-to-combustion process of the HNS-IV propellant to the BPN propellant.

[0040] The sealing aluminum foil sheet 6 is used for the assembly of the impact plate ignition tube. After the edge is rolled, the product is sealed to protect the output end from contamination and moisture.

[0041] The insulating gasket 8 is made of polyimide material and wraps around the pins to ensure electrical insulation between the pins and between the pins and the housing 1.

[0042] As the final step in assembly, potting involves injecting a potting compound with excellent electrical and structural properties into the end of the product and allowing it to cure at room temperature.

[0043] The working process of the impact ignition tube is as follows: the sintering seat 2 pin receives pulse high-voltage energy, the integrated explosive foil chip 3 outputs a high-speed flying plate, impacts and detonates the HNS-IV propellant 4, and after the detonation wave decays, it impacts and ignites the BPN propellant 7, which finally ignites the main charge of the engine.

[0044] The embodiments described above are merely preferred embodiments of the present invention. Ordinary variations and substitutions made by those skilled in the art within the scope of the technical solution of the present invention should be included within the protection scope of the present invention.

Claims

1. A solid rocket motor with a completely ablation-capable embedded impact ignition tube, characterized in that, Includes a housing, a glass sintering base, an integrated explosive foil chip, a primary HNS-IV propellant grain, a primary propellant grain positioning ring, a sealing aluminum foil sheet, a secondary BPN propellant grain, and an insulating gasket; The outer shell is made of aluminum alloy, and the inner cavity contains a glass sintering seat, an integrated explosive foil chip, a primary HNS-IV propellant, a primary propellant positioning ring, a sealing aluminum foil sheet, a secondary BPN propellant and an insulating pad. The glass sintering base includes a glass body and two conductive pins, which are prepared by a sintering process; The integrated explosive foil chip is fixed between two conductive pins and connected to the two conductive pins through the chip pads to achieve electrical conduction; The primary HNS-IV propellant grain is placed in the primary propellant grain positioning ring, which is located on the upper surface of the integrated explosive foil chip. The secondary BPN propellant grain is located above the primary propellant grain positioning ring; The sealing aluminum foil is used to seal the outlet of the ignition tube; The insulating pad circumferentially wraps around the pins, providing electrical insulation between the pins and between the pins and the outer casing; A semi-circular step is cut at the head of each of the two conductive pins, and the integrated explosion foil chip is fixed on the two semi-circular steps. The primary propellant positioning ring is equipped with an HNS-IV propellant detonation attenuation channel, located directly above the primary HNS-IV propellant, to realize the impact-to-combustion process of the primary HNS-IV propellant on the secondary BPN propellant. The secondary BPN propellant, serving as the output propellant, is a hollow cylindrical shape, eliminating the impact of the impact pressure caused by the detonation of the primary HNS-IV propellant on the structural integrity.

2. The solid rocket motor ignition tube with completely ablation-capable embedded impact plate according to claim 1, characterized in that, The detonation wave attenuation distance of the HNS-IV charge detonation attenuation channel is 0.5mm to 5mm.

3. The solid rocket motor ignition tube with a completely ablation-capable embedded impact plate according to claim 1, characterized in that, The inner wall of the outer shell adopts a tapered and stop-limiting design to prevent the glass sintering seat from falling off in the reverse direction due to impact.

4. The solid rocket motor with a completely ablation-resistant embedded impact ignition tube according to claim 1 or 3, characterized in that, The outer wall of the casing is threaded to secure the ignition tube in the ignition device.

5. The solid rocket motor ignition tube with completely ablation-capable embedded impact plate according to claim 1, characterized in that, The electrical connection between the chip pads and the two conductive pins is achieved through gold wire bonding or soldering processes.

6. The solid rocket motor ignition tube with completely ablation-capable embedded impact plate according to claim 1, characterized in that, The outer shell is made of aluminum alloy rods.

7. The solid rocket motor ignition tube with a completely ablation-capable embedded impact plate according to claim 1, characterized in that, A potting compound with excellent electrical and structural properties is injected into the tail end of the ignition tube and cured at room temperature.

8. The solid rocket motor ignition tube with completely ablation-capable embedded impact plate according to claim 1, characterized in that, The working process of the impact ignition tube is as follows: two conductive pins receive pulsed high-voltage energy, the integrated explosive foil chip outputs a high-speed flying plate, which impacts and detonates the primary HNS-IV propellant. After the detonation wave decays, it impacts and ignites the secondary BPN propellant, which finally ignites the main propellant of the engine.

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