Solid rocket engine ignition powder and ignition device

Abstract

The present invention discloses an ignition powder and ignition device for a solid rocket engine. The ignition powder comprises an oxidizer (50-70%), a binder (10-30%), a coupling agent (3-10%), and a fuel (10-35%). The ignition powder has a combustion heat of over 6,000 kJ / kg. Furthermore, the ignition powder has lower mechanical sensitivity than commonly used black powder, improving safety during the ignition operation of the solid rocket engine. The ignition device fully covers the combustion end surface of the solid propellant in the solid rocket engine, achieving full-burning surface ignition of the solid propellant and significantly shortening the engine ignition delay time. The thin-layer metal ignition electrode and polymer insulating film used are completely burned out after the ignition powder burns, without negatively impacting the burning surface of the solid propellant.

Description

Technical Field

[0001] The present invention relates to the technical field of solid rocket engines, in particular to an ignition powder and an ignition device for a solid rocket engine. Background Art

[0002] Solid rocket motors, with their high specific impulse, simple structure, and easy maintenance, are the primary propulsion system for rocket and missile weapons. The ignition and combustion process of solid rocket motors plays a crucial role in engine performance. Currently, ignition propellants commonly used in solid rocket motors, such as black powder, have high sensitivity to impact, friction, and static electricity, increasing the risk of engine ignition preparation. Furthermore, the storage of ignition propellants places stringent environmental requirements on their storage.

[0003] Furthermore, existing solid rocket engine ignition methods primarily involve placing ignition powder in a cartridge or ignition box, with an ignition wire positioned inside. The ignition wire is then energized and heated to ignite the ignition powder, thereby achieving ignition and combustion of the solid propellant. However, because the area of ​​the ignition powder package or ignition box is smaller than the surface area of ​​the solid propellant, ignition of the ignition powder package or ignition box only initiates combustion of the propellant's burning surface, which in turn drives combustion of other parts. Therefore, existing ignition technology is unable to achieve full-burning surface ignition and combustion of the solid rocket engine propellant. This non-full-burning surface ignition method is prone to causing ignition delays in solid rocket engines, a phenomenon that is particularly prominent for large-diameter solid rocket engines and those with complex burning surfaces, such as those with circular or star-shaped shapes. Summary of the Invention

[0004] The present invention provides a solid rocket engine ignition powder and an ignition device, which are used to overcome the defects of the prior art such as high mechanical sensitivity of the ignition powder and inability of solid propellant to achieve full combustion surface ignition.

[0005] To achieve the above-mentioned object, the present invention provides a solid rocket engine ignition powder, comprising:

[0006] Oxidant: 50~70%;

[0007] Adhesive: 10~30%;

[0008] Coupling agent: 3~10%;

[0009] Fuel: 10~35%;

[0010] The oxidant is at least one of potassium perchlorate, ammonium perchlorate, ammonium nitrate and potassium nitrate;

[0011] The adhesive is at least one of fluororubber, parafluoroether rubber and fluorosilicone rubber;

[0012] The coupling agent is at least one of monoaminosilane oligomer, bisaminosilane oligomer, epoxysilane oligomer, octyltrimethoxysilane oligomer and octyltriethoxysilane oligomer;

[0013] The fuel is at least one of magnesium powder, aluminum powder, boron powder, chromium boride, aluminum boride, calcium boride, manganese boride, ferric oxide, chromium oxide, tellurium dioxide and bismuth oxide.

[0014] To achieve the above object, the present invention further provides a solid rocket engine ignition device, comprising:

[0015] Ignition assembly, attached to the solid propellant combustion end face;

[0016] The ignition assembly includes a metal ignition electrode and a polymer insulating film, wherein the metal ignition electrode is adhered to the polymer insulating film; the metal ignition electrode is arranged in a resistor form or in a staggered positive and negative electrode form;

[0017] The ignition powder is coated on the ignition component;

[0018] A power supply system is electrically connected to the metal ignition electrode.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] 1. The solid rocket engine ignition powder provided by the present invention comprises an oxidizer (50-70%), a binder (10-30%), a coupling agent (3-10%), and a fuel (10-35%). This ignition powder has a heat of combustion exceeding 6000 kJ / kg. Furthermore, this ignition powder has lower mechanical sensitivity than conventional black powder, improving safety during solid rocket engine ignition operations.

[0021] 2. The solid rocket engine ignition device provided by the present invention fully covers the combustion end surface of the solid propellant in the solid rocket engine, achieving full-surface ignition of the solid propellant and significantly shortening the engine ignition delay time. The thin-layer metal ignition electrode and polymer insulating film used are completely consumed after the ignition powder burns, without negatively impacting the solid propellant's combustion surface. Furthermore, the ignition device of the present invention exhibits excellent deformability and is adaptable to ignite solid propellants with combustion surfaces of varying shapes, providing a new ignition method for full-surface ignition of solid rocket engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0023] Figure 1 This is a structural diagram of the thin-layer metal ignition electrode used in Example 1 arranged on a polymer film;

[0024] Figure 2 This is a diagram of the engine structure in which the ignition device is applied to a solid rocket engine in Example 1;

[0025] Figure 3 This is a structural diagram of the polymer insulating film used in Example 2 to adhere to the thin metal ignition electrode;

[0026] Figure 4 This is a structural diagram of the polymer insulating film used in Example 3 to adhere to the thin metal ignition electrode;

[0027] Figure 5 This is a structural diagram of the polymer insulating film used in Example 4 to adhere to the thin metal ignition electrode;

[0028] Figure 6 This is a structural diagram of the polymer insulating film for the adhered thin-layer metal ignition electrode used in Example 5.

[0029] Explanation of the accompanying figures: 1—solid rocket engine, 2—ignition powder, 3—polymer insulating film, 4—combustion chamber, 5—nozzle, 6—grain, 7—positive and negative electrode wires.

[0030] The purpose, features and advantages of the present invention will be further described with reference to the accompanying drawings and in conjunction with the embodiments. DETAILED DESCRIPTION

[0031] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0032] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in this field can implement it. When the combination of technical solutions is mutually contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0033] Unless otherwise specified, all drugs / reagents used were commercially available.

[0034] The present invention provides a solid rocket engine ignition powder, comprising:

[0035] Oxidant: 50~70%;

[0036] Adhesive: 10~30%;

[0037] Coupling agent: 3~10%;

[0038] Fuel: 10~35%;

[0039] The oxidant is at least one of potassium perchlorate, ammonium perchlorate, ammonium nitrate and potassium nitrate;

[0040] The adhesive is at least one of fluororubber, parafluoroether rubber and fluorosilicone rubber;

[0041] The coupling agent is at least one of monoaminosilane oligomer, bisaminosilane oligomer, epoxysilane oligomer, octyltrimethoxysilane oligomer and octyltriethoxysilane oligomer;

[0042] The fuel is at least one of magnesium powder, aluminum powder, boron powder, chromium boride, aluminum boride, calcium boride, manganese boride, ferric oxide, chromium oxide, tellurium dioxide and bismuth oxide.

[0043] Preferably, the particle size of the magnesium powder, aluminum powder and boron powder is 0.1-30 μm;

[0044] The particle size of the chromium boride, aluminum boride, calcium boride, manganese boride, ferric oxide, chromium oxide, tellurium dioxide and bismuth oxide ranges from 10 to 50 μm.

[0045] Preferably, the particle size of the oxidant is in the range of 10-40 μm.

[0046] Control the particle size to increase the uniformity of the ignition powder mixture and increase the burning rate of the ignition powder.

[0047] Preferably, the method for preparing the ignition powder comprises the following steps:

[0048] S1: Weigh the oxidant, binder, coupling agent, and fuel in a mass ratio of 50-70: 10-30: 3-10: 10-35, and dissolve the binder in an organic solvent to prepare a 5-20% solution;

[0049] S2: adding an oxidizing agent and a coupling agent to the solution obtained in step S1 in sequence and stirring evenly;

[0050] S3: adding fuel to the mixture obtained in step S2 and stirring the mixture evenly to obtain ignition powder slurry.

[0051] Preferably, the organic solvent is at least one of methanol, ethanol, ethyl acetate, ether, petroleum ether and acetone;

[0052] In step S2 and step S3, the stirring rate is 100-300 r / min.

[0053] The present invention also provides a solid rocket engine ignition device, comprising:

[0054] Ignition assembly, attached to the solid propellant combustion end face;

[0055] The ignition assembly includes a metal ignition electrode and a polymer insulating film, wherein the metal ignition electrode is adhered to the polymer insulating film; the metal ignition electrode is arranged in a resistor form or in a staggered positive and negative electrode form;

[0056] The ignition powder is coated on the ignition component;

[0057] A power supply system is electrically connected to the metal ignition electrode.

[0058] Preferably, the specific method of attaching the ignition assembly to the combustion end face of the solid propellant is:

[0059] Select the binder in the ignition powder component and prepare an organic solvent solution with a binder concentration of 5-20%;

[0060] The organic solvent solution is used to wet the solid propellant combustion end surface, and then the ignition component is directly pasted on the solid propellant combustion end surface to achieve pasting.

[0061] Preferably, the thickness of the metal ignition electrode is 0.1-0.5 mm, the electrode width is 1-5 mm, the electrode spacing is 1-5 mm, and the resistance between the positive and negative electrodes is 4-10 Ω.

[0062] Preferably, the material of the metal ignition electrode is one of gold, silver, aluminum, nickel and nickel-chromium alloy.

[0063] Preferably, the polymer insulating film is one of a polyethylene film, a polypropylene film, a polyimide film, a polystyrene film, a polycarbonate film and a polytetrafluoroethylene film.

[0064] Preferably, the thickness of the polymer insulating film is 0.1-1 mm.

[0065] Preferably, the ignition powder is coated on the ignition component, specifically:

[0066] The ignition powder slurry is applied to each surface of the ignition component and dried;

[0067] The coating thickness of the ignition powder slurry is 0.2~0.8mm; the thickness is controlled in order to reduce the thickness of the ignition device as much as possible and increase its deformability so that it is suitable for powder columns with different burning surface shapes.

[0068] The drying temperature is 20~50℃ and the drying time is 8~72 h.

[0069] Example 1

[0070] This embodiment provides a solid rocket engine ignition device, such as Figure 2 As shown, the thin-layer metal ignition electrode used is a thin-layer aluminum ignition electrode, and its structure is as follows Figure 1 As shown. The electrode thickness is 0.5 mm, the electrode width is 3 mm, the distance between the positive and negative electrodes is 2 mm, and the positive and negative electrode resistance is 8 Ω. The polymer insulating film 3 is a polyethylene film with a thickness of 0.6 mm. The metal ignition electrode and the polymer insulating film 3 constitute the ignition assembly, and the metal ignition electrode is attached to the polymer insulating film 3. The ignition powder 2 is coated on the ignition assembly. The power supply system is electrically connected to the metal ignition electrode.

[0071] like Figure 2 As shown, it includes a solid rocket engine 1, ignition powder 2, a polymer insulating film 3, a combustion chamber 4, a nozzle 5, a powder column 6, and positive and negative electrode wires 7.

[0072] The ignition powder used in this example includes the raw materials and their mass fractions shown in Table 1:

[0073] Table 1 Ignition powder composition of Example 1

[0074]

[0075] The assembly process of the solid rocket motor ignition device is as follows:

[0076] S1: Dissolve fluororubber in ethyl acetate to prepare a 10% solution;

[0077] S2: adding potassium perchlorate, ammonium perchlorate and bisaminosilane oligomer to the solution obtained in step S1 in sequence, and stirring at a speed of 100 r / min;

[0078] S3: adding magnesium powder and tellurium dioxide to the mixture obtained in step S2, and stirring at a speed of 100 r / min until uniform;

[0079] S4: evenly apply the ignition powder slurry obtained in step S3 on all surfaces of the ignition component to a coating thickness of 0.8 mm; and dry in a hot air circulation drying oven at 50° C. for 8 h.

[0080] S5: Wet the solid propellant combustion end face in the solid rocket engine with 10% fluororubber solution, and then directly stick the ignition assembly to the solid propellant combustion end face to achieve sticking.

[0081] In this embodiment, one end of the positive and negative wires 7 is connected to a thin metal ignition electrode, and the other end is connected to the solid rocket engine control system. These wires are used to transmit ignition signals from the solid rocket engine control system to the thin metal ignition electrode. When the positive and negative wires 7 are energized and ignited, the ignition charge 2 on the surface of the ignition assembly rapidly and comprehensively ignites and burns, generating a high-temperature flame and energy sufficient to ignite the solid rocket engine. This ensures rapid, comprehensive ignition and combustion of the solid propellant grains within the solid rocket engine. After the solid propellant ignites and burns, the thin metal ignition electrode and polymer insulating film are rapidly consumed in the high-temperature combustion environment.

[0082] In this embodiment, the combustion heat of the ignition charge is 8726 kJ / kg, and the impact sensitivity is H 50 ≥25cm, friction sensitivity P ≤0%, the ignition delay time from ignition charge to full combustion surface of the engine is 663 ms.

[0083] Example 2

[0084] This embodiment provides a solid rocket engine ignition device, the thin metal electrode used is a thin nickel-chromium alloy ignition electrode, the structure is as follows Figure 3 As shown in the figure, the electrode thickness is 0.2 mm, the electrode width is 5 mm, the distance between the positive and negative electrodes is 3 mm, the positive and negative electrode resistance is 6 Ω, and the polymer insulating film is a polyimide film with a thickness of 0.4 mm.

[0085] The ignition assembly consists of a metal ignition electrode and a polymer insulating film, to which the metal ignition electrode is attached. Ignition powder is applied to the ignition assembly. A power supply system is electrically connected to the metal ignition electrode.

[0086] The ignition powder used in this example includes the raw materials and their mass fractions shown in Table 2:

[0087] Table 2 Ignition powder composition of Example 2

[0088]

[0089] The assembly process of the solid rocket motor ignition device is as follows:

[0090] S1: Dissolve fluororubber in ethyl acetate to prepare a 20% solution;

[0091] S2: adding potassium nitrate, ammonium nitrate and epoxysilane oligomer to the solution obtained in step S1 in sequence, and stirring the mixture at a speed of 150 r / min;

[0092] S3: aluminum powder, bismuth oxide, and boron powder are sequentially added to the mixture obtained in step S2, and stirred at a speed of 150 r / min;

[0093] S4: evenly apply the ignition powder slurry obtained in step S3 on all surfaces of the ignition component with a coating thickness of 0.5 mm; and place in a hot air circulation drying oven at 35° C. to dry for 36 hours.

[0094] S5: Wet the solid propellant combustion end face in the solid rocket engine with 20% fluororubber solution, and then directly stick the ignition assembly to the solid propellant combustion end face to achieve sticking.

[0095] In this embodiment, one end of the positive and negative wires is connected to a thin metal ignition electrode, and the other end is connected to the solid rocket motor control system. This wire is used to transmit the ignition signal from the solid rocket motor control system to the thin metal ignition electrode. Ignition is initiated by energizing the positive and negative wires, causing the ignition charge on the surface of the ignition assembly to rapidly and comprehensively ignite and burn, generating a high-temperature flame and energy required to ignite the solid rocket motor, ensuring rapid and comprehensive ignition and combustion of the solid propellant grain within the solid rocket motor. After the solid propellant ignites and burns, the thin metal ignition electrode and polymer insulating film are rapidly consumed in the high-temperature combustion environment.

[0096] In this embodiment, the combustion heat of the ignition charge is 10998 kJ / kg, and the impact sensitivity is H 50 ≥25cm, friction sensitivity P ≤0%, the ignition delay time from ignition charge to full combustion surface of the engine is 536 ms.

[0097] Example 3

[0098] This embodiment provides a solid rocket engine ignition device, the thin metal electrode used is a thin nickel-chromium alloy ignition electrode, the structure is as follows Figure 4 As shown in the figure, the electrode thickness is 0.3 mm, the electrode width is 2 mm, the distance between the positive and negative electrodes is 2 mm, the positive and negative electrode resistance is 5 Ω, and the polymer insulating film is a polycarbonate film with a thickness of 0.8 mm.

[0099] The ignition assembly consists of a metal ignition electrode and a polymer insulating film, to which the metal ignition electrode is attached. Ignition powder is applied to the ignition assembly. A power supply system is electrically connected to the metal ignition electrode.

[0100] The ignition powder used in this example includes the raw materials and their mass fractions shown in Table 3:

[0101] Table 3 Ignition powder composition of Example 3

[0102]

[0103] In this embodiment, the combustion heat of the ignition powder is 12053 kJ / kg, and the impact sensitivity is H 50 ≥25cm, friction sensitivity P ≤0%, the ignition delay time from ignition charge to full combustion surface of the engine is 467 ms.

[0104] Example 4

[0105] This embodiment provides a solid rocket engine ignition device, the thin metal electrode used is a thin nickel-chromium alloy ignition electrode, the structure is as follows Figure 5 As shown in the figure, the electrode thickness is 0.2 mm, the electrode width is 2 mm, the distance between the positive and negative electrodes is 1 mm, the positive and negative electrode resistance is 4 Ω, and the polymer insulating film is a polystyrene film with a thickness of 0.3 mm.

[0106] The ignition assembly consists of a metal ignition electrode and a polymer insulating film, to which the metal ignition electrode is attached. Ignition powder is applied to the ignition assembly. A power supply system is electrically connected to the metal ignition electrode.

[0107] The ignition powder used in this example includes the raw materials and their mass fractions shown in Table 4:

[0108] Table 4 Ignition powder composition of Example 4

[0109]

[0110] In this embodiment, the combustion heat of the ignition charge is 10057 kJ / kg, and the impact sensitivity is H 50 ≥25cm, friction sensitivity P ≤0%, the ignition delay time from ignition charge to full combustion surface of the engine is 583 ms.

[0111] Example 5

[0112] This embodiment provides a solid rocket engine ignition device, the thin metal electrode used is a thin nickel-chromium alloy ignition electrode, the structure is as follows Figure 6 As shown in the figure, the electrode thickness is 0.4 mm, the electrode width is 4 mm, the distance between the positive and negative electrodes is 5 mm, the positive and negative electrode resistance is 10 Ω, and the polymer insulating film is a polypropylene film with a thickness of 0.8 mm.

[0113] The ignition assembly consists of a metal ignition electrode and a polymer insulating film, to which the metal ignition electrode is attached. Ignition powder is applied to the ignition assembly. A power supply system is electrically connected to the metal ignition electrode.

[0114] The ignition powder used in this example includes the raw materials and their mass fractions shown in Table 5:

[0115] Table 5 Ignition powder composition of Example 5

[0116]

[0117] In this embodiment, the combustion heat of the ignition powder is 12468 kJ / kg, and the impact sensitivity is H 50 ≥25cm, friction sensitivity P ≤0%, the ignition delay time from ignition charge to full combustion of the engine is 415 ms.

[0118] The above description is only a preferred embodiment of the present invention and does not limit the patent scope of the present invention. All equivalent structural transformations made by using the contents of the present invention description and drawings under the inventive concept of the present invention, or direct / indirect application in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. A solid rocket engine ignition powder, characterized in that: include: Oxidant: 50~70%; Adhesive: 10~30%; Coupling agent: 3~10%; Fuel: 10~35%; The oxidant is at least one of potassium perchlorate, ammonium perchlorate, ammonium nitrate and potassium nitrate; the particle size of the oxidant is in the range of 10 to 40 μm; The adhesive is at least one of fluororubber, parafluoroether rubber and fluorosilicone rubber; The coupling agent is at least one of monoaminosilane oligomer, bisaminosilane oligomer, epoxysilane oligomer, octyltrimethoxysilane oligomer and octyltriethoxysilane oligomer; The fuel is at least one of magnesium powder, aluminum powder, boron powder, chromium boride, aluminum boride, calcium boride, manganese boride, ferric oxide, chromium oxide, tellurium dioxide, and bismuth oxide; the particle size of the magnesium powder, aluminum powder, and boron powder is 0.1 to 30 μm; the particle size of the chromium boride, aluminum boride, calcium boride, manganese boride, ferric oxide, chromium oxide, tellurium dioxide, and bismuth oxide is 10 to 50 μm; The ignition powder has a combustion heat of more than 6000 kJ / kg. The preparation method of the ignition powder comprises the following steps: S1: Weigh an oxidant, a binder, a coupling agent, and a fuel in a mass ratio of 50-70: 10-30: 3-10: 10-35, and dissolve the binder in an organic solvent to prepare a 5-20% solution; the organic solvent is at least one of methanol, ethanol, ethyl acetate, ether, petroleum ether, and acetone; S2: adding an oxidizing agent and a coupling agent to the solution obtained in step S1 in sequence and stirring evenly; S3: adding fuel to the mixture obtained in step S2 and stirring evenly to obtain ignition powder slurry; In step S2 and step S3, the stirring rate is 100-300 r / min.

2. A solid rocket engine ignition device, characterized in that: include: The ignition assembly is attached to the combustion end face of the solid propellant to achieve full combustion surface ignition of the solid propellant; The ignition assembly includes a metal ignition electrode and a polymer insulating film, wherein the metal ignition electrode is adhered to the polymer insulating film; the metal ignition electrode is arranged in a resistor form or in a staggered positive and negative electrode form; the thickness of the metal ignition electrode is 0.1-0.5 mm, the electrode width is 1-5 mm, the electrode spacing is 1-5 mm, and the resistance between the positive and negative electrodes is 4-10 Ω; the polymer insulating film is one of a polyethylene film, a polypropylene film, a polyimide film, a polystyrene film, a polycarbonate film, and a polytetrafluoroethylene film; the thickness of the polymer insulating film is 0.1-1 mm; The ignition powder according to claim 1, coated on the ignition component, is specifically: The ignition powder slurry is applied to each surface of the ignition component and dried; The coating thickness of the ignition powder slurry is 0.2~0.8mm; The drying temperature is 20~50℃ and the drying time is 8~72 hours; A power supply system is electrically connected to the metal ignition electrode.

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