Completely-ablative embedded slapper ignition tube for solid engine

Abstract

The invention discloses a completely-ablative embedded slapper ignition tube for a solid engine, and belongs to the field of solid rocket engine design. The ignition tube comprises a shell, a glass sintering base, an integrated exploding foil chip, a primary HNS-IV grain, a primary grain positioning ring, a sealing aluminum foil piece, a secondary BPN grain and an insulating spacer, after a contact pin on the glass sintering base receives pulse high-voltage energy, the integrated exploding foil chip works and outputs a high-speed flying piece to impact and detonate the HNS-IV grain, detonation waves impact and ignite the BPN grain after being attenuated, and the high-speed flying piece is output; and finally, main charge of the engine is ignited. The impact-detonation-detonation fire transfer sequence is designed, the short pulse impact energy of the small-size thin flyer is fully utilized, the safety and reliability of a product are improved, meanwhile, raw materials can be completely ablated, blockage or damage to an engine jet pipe is avoided, and therefore the ballistic performance in an engine cannot be affected after the impact-detonation-detonation fire transfer sequence acts on the jet pipe.

Description

Technical Field

[0001] The invention relates to a completely ablative embedded impact piece firing tube for a solid engine, belonging to the field of solid rocket engines. Background Art

[0002] In the field of solid rocket engines, the in-line ignition device is used to ignite the engine ignition device. It is a new generation of safe ignition device with dual safety mechanisms of electronic safety insurance and pyrotechnic intrinsic safety. For single-chamber dual-thrust or multi-pulse engines, it is usually necessary to carry out central ignition or ignition, so the impact piece ignition tube in the in-line ignition device needs to be buried in the engine combustion chamber. The internal ignition solution requires that the impact piece ignition tube structure has a small size and can be completely ablated in the high temperature environment of the engine combustion chamber (not less than 2500K), ensuring that no solid flying objects will cause blockage or damage to the nozzle, thereby not affecting the internal ballistic performance of the engine. Summary of the invention

[0003] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, and to propose a completely ablative embedded impact piece ignition tube for a solid engine. Through structural design and raw material design, the problems of large volume and incomplete ablation of the impact piece ignition tube are solved, thereby improving safety and reliability.

[0004] The technical solution of the present invention is:

[0005] A completely ablative embedded impact piece firing tube for a solid motor, comprising a shell, a glass sintering seat, an integrated exploding foil chip, a primary HNS-IV charge, a primary charge positioning ring, a sealing aluminum foil, a secondary BPN charge and an insulating gasket;

[0006] The shell is made of aluminum alloy, and the inner cavity is equipped with a glass sintering seat, an integrated explosive foil chip, a primary HNS-IV charge, a primary charge positioning ring, a sealing aluminum foil, a secondary BPN charge and an insulating gasket;

[0007] The glass sintering seat includes a glass body and two conductive pins, and is prepared by a sintering process;

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

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

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

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

[0012] The insulating gasket wraps the pins in an annular direction to electrically insulate the pins from each other and from the housing.

[0013] Furthermore, a semicircular step is cut on each of the two conductive pin heads, and the integrated exploding foil chip is fixed on the two semicircular steps.

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

[0015] Furthermore, the secondary BPN charge, as the output charge, is in the shape of a hollow cylinder, eliminating the influence of the shock pressure caused by the detonation of the primary HNS-IV charge on the structural integrity.

[0016] Furthermore, the inner wall of the shell adopts a taper and stop limit design to prevent the reverse tail of the glass sintering seat from falling off due to impact.

[0017] Furthermore, the outer wall of the shell is provided with threads so that the ignition tube is fixed in the ignition device.

[0018] Furthermore, the chip pad and the two conductive pins are electrically connected through gold wire bonding or welding process.

[0019] Furthermore, the shell is made of aluminum alloy bar.

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

[0021] Furthermore, the working process of the impact piece firing tube is as follows: two conductive pins receive pulsed high-voltage energy, the integrated exploding foil chip outputs high-speed flying pieces, which impact and detonate the primary HNS-IV charge, and after the detonation wave decays, the secondary BPN charge is impact-ignited, and finally the main charge of the engine is ignited.

[0022] The advantages of the present invention compared with the prior art are:

[0023] (1) The present invention designs a completely ablative embedded impact plate ignition tube. Compared with existing products, the raw materials used in the impact plate ignition tube of the present invention can be completely ablated to avoid clogging or damaging the engine nozzle.

[0024] (2) The present invention designs an "impact-detonation-deflagration" fire transmission sequence to replace the existing "impact-combustion" sequence, making full use of the short-pulse impact energy of small-sized thin flying pieces, and essentially improving the safety and reliability of the product from the perspective of pyrotechnics.

[0025] (3) The interior of the shell of the present invention adopts a taper and stop limit design to prevent the sintering seat from falling off during the impact process, fully utilize the detonation energy of the primary HNS-IV charge, and ensure that the combustion flame of the secondary BPN charge 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 conducive to fixing the impact piece ignition tube in the ignition device. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] 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:

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

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

[0030] Figure 3 Schematic diagram of the shell structure of an embodiment of the present invention. DETAILED DESCRIPTION

[0031] The exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art.

[0032] The present invention proposes a completely ablative embedded impact piece firing tube for a solid rocket engine, such as Figure 1 As shown, it includes an outer shell 1, a glass sintering seat 2, an integrated explosive foil chip 3, a primary HNS-IV (IV type hexanitrostilbene) charge 4, a primary charge positioning ring 5, a sealing aluminum foil 6, a secondary BPN (B / KNO3) charge 7, an insulating gasket 8 and a potting glue 9. The raw materials used in the above components can be completely burned under the high-temperature combustion gas inside the engine, without producing flying objects, causing nozzle blockage or damage, and also without affecting the internal ballistic performance of the engine.

[0033] The main body of the glass sintering seat 2 is made of glass material, which can be completely ablated by the high temperature of the combustion chamber. It is prepared by sintering the glass main body and two conductive Kovar alloy pins or copper pins, which can realize the structural installation and electrical connection of the integrated explosive foil chip, that is, the integrated explosive foil chip is installed between the two pins of the sintering seat, and the electrical connection between the pins and the chip is realized by gold wire bonding or welding process. Figure 2 As shown, the diameter of the pin is 1 mm, and in order to reduce the diameter of the product, a semicircular step with a diameter of 0.5 mm and a depth of 1 mm is cut on the pin head, and the integrated exploding foil chip 3 is fixed on the semicircular step.

[0034] The integrated exploding foil chip 3 is mass-produced by micro-electromechanical system technology, for details, see "Research on the Ignition Performance of MEMS Integrated Exploding Foil Chips". The integrated exploding foil chip 3 is placed above the two pin steps, and eight gold wires with a diameter of 25 μm are bonded between the chip pads and the pins on the left and right sides by gold wire bonding or welding technology to achieve internal electrical conduction of the integrated exploding foil chip 3, and finally realize the conversion of pulse capacitor energy storage into flying chip kinetic energy.

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

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

[0037] The secondary BPN charge 7 is used as the output charge, and its formula meets the requirements of GJB6217-2008 "Specifications for Boron / Potassium Nitrate Ignition Powder", and has sufficient output energy to ensure reliable ignition of the ignition device.

[0038] The mature drug pressing process is used to press HNS-IV drug column 4 and BPN drug column 7 of specific mass and density in the drug ring, where the mass of HNS-IV drug column 4 is 10 mg and the density is 1.6 g / cm 3 The mass of BPN column 7 is 370 mg and the density is 1.75 g / cm 3 .

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

[0040] The sealing aluminum foil sheet 6 is used to seal the product after the impact piece ignition tube is assembled and the end is closed and curled, so as to protect the output end from pollution and moisture.

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

[0042] As the final step of assembly, potting is performed by injecting a potting compound 9 with excellent electrical and structural properties into the tail of the product and curing it at room temperature.

[0043] The working process of the impact piece firing tube is as follows: the pin of the sintering seat 2 receives the pulse high-voltage energy, the integrated exploding foil chip 3 outputs high-speed flying pieces, the HNS-IV charge 4 is impact-detonated, and the BPN charge 7 is impact-ignited after the detonation wave decays, and finally the main charge of the engine is ignited.

[0044] The above-described embodiments are only preferred specific implementations of the present invention. Common changes and substitutions made by those skilled in the art within the scope of the technical solution of the present invention should be included in the protection scope of the present invention.

Claims

1. A completely ablative embedded impact piece firing tube for a solid rocket engine, characterized in that: It includes a shell, a glass sintering seat, an integrated explosive foil chip, a primary HNS-IV charge, a primary charge positioning ring, a sealing aluminum foil, a secondary BPN charge and an insulating gasket; The shell is made of aluminum alloy, and the inner cavity is equipped with a glass sintering seat, an integrated explosive foil chip, a primary HNS-IV charge, a primary charge positioning ring, a sealing aluminum foil, a secondary BPN charge and an insulating gasket; The glass sintering seat includes a glass body and two conductive pins, and is prepared by a sintering process; The integrated exploding foil chip is fixed between two conductive pins and connected through the chip pad and the two conductive pins to achieve electrical conduction; The primary HNS-IV charge is placed in a primary charge positioning ring, which is located on the upper surface of the integrated explosive foil chip; The secondary BPN charge is located above the primary charge positioning ring; The sealing aluminum foil is used to seal the output port of the ignition tube; The insulating gasket wraps the pins in an annular direction to electrically insulate the pins from each other and from the housing.

2. The completely ablative embedded impact piece firing tube for a solid rocket engine according to claim 1, characterized in that: A semicircular step is cut on each of the two conductive pin heads, and the integrated exploding foil chip is fixed on the two semicircular steps.

3. The completely ablative embedded impact piece firing tube for a solid rocket engine according to claim 1, characterized in that: The primary charge positioning ring is provided with an HNS-IV charge detonation attenuation channel, which is located directly above the primary HNS-IV charge. The detonation wave attenuation distance is 0.5 mm to 5 mm, realizing the impact-to-combustion process of the HNS-IV charge on the BPN charge.

4. The completely ablative embedded impact piece firing tube for a solid rocket engine according to claim 1 or 3, characterized in that: The secondary BPN charge is used as an output charge and is in a hollow cylindrical shape, eliminating the influence of the shock pressure caused by the detonation of the primary HNS-IV charge on the structural integrity.

5. The completely ablative embedded impact piece firing tube for a solid rocket engine according to claim 1, characterized in that: The inner wall of the shell adopts a taper and stop limit design to prevent the reverse tail of the glass sintering seat from falling off due to impact.

6. The completely ablative embedded impact piece firing tube for a solid rocket engine according to claim 1 or 5, characterized in that: The outer wall of the shell is provided with threads to fix the ignition tube in the ignition device.

7. The completely ablative embedded impact piece firing tube for a solid rocket engine according to claim 1, characterized in that: The electrical connection between the chip pad and the two conductive pins is achieved through gold wire bonding or welding process.

8. The completely ablative embedded impact piece firing tube for a solid rocket engine according to claim 1, characterized in that: The housing is made of aluminum alloy bar.

9. The completely ablative embedded impact piece firing tube for a solid rocket engine according to claim 1, characterized in that: A potting glue with excellent electrical and structural properties is injected into the tail of the ignition tube and cured at room temperature.

10. The completely ablative embedded impact piece firing tube for a solid rocket engine according to claim 1, characterized in that: The working process of the impact piece firing tube is as follows: two conductive pins receive pulsed high-voltage energy, the integrated exploding foil chip outputs high-speed flying pieces, which impact and detonate the primary HNS-IV charge, and after the detonation wave decays, the secondary BPN charge is impact-ignited, and finally the main charge of the engine is ignited.

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