Hydrogen peroxide solid-liquid rocket engine igniter and ignition structure

Abstract

The invention belongs to the technical field of aerospace, and particularly relates to a hydrogen peroxide solid-liquid rocket engine igniter and an ignition structure. The igniter comprises an igniter shell and an ignition powder column. An igniter cavity extending in the axial direction of the igniter shell is formed in the igniter shell, the igniter cavity comprises an ignition chamber and an ignition chamber which are arranged at intervals in the axial direction and communicate with each other, the igniter shell is provided with a plurality of ignition holes, and the ignition holes are located in the peripheral wall of the igniter shell and communicate with the ignition chamber. The ignition powder column is arranged in the ignition chamber and can generate a violent chemical reaction after making contact with hydrogen peroxide at the normal temperature to form fuel gas, and the fuel gas is sprayed out of the ignition chamber through the ignition holes. The igniter provided by the invention is a miniaturized igniter capable of reacting with hydrogen peroxide and provided with a high-energy solid grain capable of spontaneous combustion, and has the advantages of fast ignition response, high ignition energy, low price, light weight and the like.

Description

Technical Field

[0001] This application belongs to the field of aerospace technology, and particularly relates to an igniter and ignition structure for a hydrogen peroxide solid-liquid rocket engine. Background Art

[0002] The hydrogen peroxide solid-liquid rocket engine has advantages such as good safety, easy thrust adjustment, shutdown and multiple start-up capabilities, non-toxic and pollution-free, good propellant column stability, low temperature sensitivity, and good economy. It fully meets the requirements of the power system of near-space vehicles for rapidity, economy, reliability, safety, greenness, large airspace, large thrust adjustment, and thrust intelligent control.

[0003] The hydrogen peroxide solid-liquid rocket engine generally uses catalytic decomposition or a pyrotechnic igniter to achieve ignition and start-up. Catalytic bed ignition utilizes the characteristics of hydrogen peroxide decomposition. Hydrogen peroxide will rapidly decompose into a high-temperature mixed gas of oxygen and water vapor under the action of a catalyst, and its thermal decomposition temperature can reach about 940 °C (generally 1000 - 1200 K), with an ignition delay of approximately 100 - 500 ms. The hydrogen peroxide catalytic gas injection structure can be used for multiple ignition and start-up of solid-liquid rocket engines. A pyrotechnic igniter consists of an initiator (such as an electric ignition tube) that starts working upon receiving a start signal, and a certain amount of ignition powder. The ignition powder burns to generate initial high-temperature and high-pressure gas, which impacts the combustion surface of the main charge to ignite the main charge.

[0004] Currently, the hydrogen peroxide catalytic bed has defects such as slow catalytic response, low ignition energy, high price, and heavy weight. The pyrotechnic igniter has problems such as a complex firing system and the danger of explosion and combustion of pyrotechnic devices. Summary of the Invention

[0005] This application provides an igniter and ignition structure for a hydrogen peroxide solid-liquid rocket engine to solve the technical problems of slow response, low ignition energy, high price, and heavy weight in existing ignition methods.

[0006] According to one aspect of this application, an igniter is provided, including an igniter housing and an ignition charge column. An igniter chamber extending along the axial direction of the igniter housing is formed inside the igniter housing. The igniter chamber includes an ignition chamber and a firing chamber that are axially spaced and connected. The igniter housing is provided with a plurality of firing holes, and the plurality of firing holes are located on the outer peripheral wall of the igniter housing and communicate with the firing chamber. The ignition charge column is arranged in the ignition chamber. Hydrogen peroxide injected into the ignition chamber through a spray panel contacts the inner hole surface of the ignition charge column at room temperature and undergoes a violent oxidation-reduction reaction with the reducing substances in the ignition charge column, thereby causing a self-ignition phenomenon. Then, the organic polymer in the fuel is ignited, further increasing the gas temperature, and is ejected from the firing chamber through the plurality of firing holes.

[0007] In an alternative embodiment of the present application, it further includes an igniter joint and an igniter outlet plug, which are respectively disposed at two axial ends of the igniter housing. The igniter joint communicates with the ignition chamber and is capable of guiding the injection of hydrogen peroxide into the ignition chamber. The igniter outlet plug seals the firing chamber to ensure that the combustion gas sprays out from the firing holes only.

[0008] In an alternative embodiment of the present application, the ignition grain is provided with a central hole extending axially therethrough, and the igniter joint is capable of guiding hydrogen peroxide into the central hole of the ignition grain.

[0009] In an alternative embodiment of the present application, the igniter housing is provided with a baffle plate, which is located in the igniter chamber and divides the igniter chamber into an ignition chamber and a firing chamber. The baffle plate is provided with gas through-holes to communicate the ignition chamber and the firing chamber. The gas through-holes communicate with the central hole of the ignition grain. The baffle plate can be connected to one axial end of the ignition grain to define the installation depth of the ignition grain and prevent the ignition grain from moving.

[0010] In an alternative embodiment of the present application, the raw materials of the ignition grain include a polymer and a strongly reducing substance. The polymer includes at least one of polyethylene, hydroxyl-terminated polybutadiene, carboxyl-terminated polybutadiene, polymethyl methacrylate, paraffin wax, polysulfide rubber, pulverized coal, dicyclopentadiene. The strongly reducing substance includes at least one of borohydrides of alkali metals, aluminum hydrides of alkali metals, and boron nitride compounds.

[0011] In an alternative embodiment of the present application, the mass percentage of the polymer in the raw materials of the ignition grain is 30% to 90%; and / or the mass percentage of the strongly reducing substance in the raw materials of the ignition grain is 10% to 70%.

[0012] According to another aspect of the present application, a rocket engine ignition structure is provided, which includes an igniter, a pre-combustion chamber housing, a liquid inlet chamber housing assembly, a combustion chamber housing, and a fuel grain. A pre-combustion chamber is formed in the pre-combustion chamber housing, and the pre-combustion chamber axially penetrates the pre-combustion chamber housing. The liquid inlet chamber housing assembly is disposed at one axial end of the pre-combustion chamber housing and covers the axial end opening of the pre-combustion chamber. A liquid inlet chamber communicating with the pre-combustion chamber is formed in the liquid inlet chamber housing assembly. The combustion chamber housing is disposed at the other axial end of the pre-combustion chamber housing and covers the axial end opening of the pre-combustion chamber. A combustion chamber communicating with the pre-combustion chamber is formed in the combustion chamber housing. The fuel grain is disposed in the combustion chamber and is provided with internal combustion holes in the grain. One axial end of the igniter close to the ignition chamber is connected to the liquid inlet chamber housing assembly, so that the hydrogen peroxide injected into the liquid inlet chamber can enter the igniter, and at least a part of the igniter provided with firing holes extends into the internal combustion holes in the fuel grain.

[0013] In an alternative embodiment of the present application, the liquid inlet chamber housing assembly includes a liquid inlet chamber housing and a jet plate. A liquid inlet chamber is formed within the liquid inlet chamber housing. The jet plate is disposed within the liquid inlet chamber and at the axially one - end opening side of the pre - combustion chamber. The jet plate is provided with a plurality of jet holes for communicating the liquid inlet chamber with the pre - combustion chamber, and the central jet hole among the plurality of jet holes communicates with the ignition chamber.

[0014] In an alternative embodiment of the present application, the ignition structure of the rocket engine further includes a pre - combustion chamber heat insulation layer, which is disposed within the pre - combustion chamber and arranged in contact with the inner peripheral wall of the pre - combustion chamber housing.

[0015] In an alternative embodiment of the present application, the ignition structure of the rocket engine further includes a first sealing ring and a second sealing ring. The first sealing ring is clamped between the pre - combustion chamber housing and the liquid inlet chamber housing assembly, and the second sealing ring is clamped between the pre - combustion chamber housing and the combustion chamber housing.

[0016] In summary, the hydrogen peroxide solid - liquid rocket engine igniter and ignition structure provided by the present application have at least the following

[0017] Beneficial effects:

[0018] The igniter adopted in the present invention uses an ignition grain (a high - energy self - igniting solid grain) that can directly chemically react with hydrogen peroxide, and forms high - temperature and high - pressure gas ejected outward within the igniter housing for igniting the fuel grain in the ignition structure of the hydrogen peroxide solid - liquid rocket engine.

[0019] Compared with the existing catalytic bed ignition scheme, the ignition grain undergoes a violent oxidation - reduction reaction and combustion reaction with hydrogen peroxide, having advantages such as high ignition energy and fast ignition response. Compared with the existing gunpowder igniter scheme, it has advantages such as simplified ignition method, miniaturization, simple structure, light weight, and low price.

[0020] Furthermore, the composition of the ignition grain is a strongly reducing substance and an organic polymer. The role of the strongly reducing substance is to undergo a violent oxidation - reduction reaction with hydrogen peroxide, having a low ignition delay, which can reach within 10 ms. The role of the organic polymer is to bond the strongly reducing substance into a solid and can also undergo a combustion reaction with hydrogen peroxide to increase the ignition temperature and gas generation amount. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present application. For those skilled in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0022] Figure 1 A cross-sectional view of an ignition structure of a hydrogen peroxide solid-liquid rocket engine provided according to one embodiment of the present application;

[0023] Figure 2 Disclosed is Figure 1 a cross-sectional view of the igniter in

[0024] Figure 3 is Figure 2 a cross-sectional view of the igniter housing in

[0025] Figure 4 is Figure 1 a schematic diagram of the injection plate in

[0026] The reference numerals are as follows:

[0027] 100, igniter; 10, igniter housing; R1, igniter chamber; R11, ignition chamber; R12, firing chamber; H1, firing hole; 11, medicine blocking plate; H2, gas passing hole;

[0028] 20, ignition grain; H3, grain center hole;

[0029] 30, igniter joint;

[0030] 40, igniter outlet plug;

[0031] 200, pre-combustion chamber housing; R2, pre-combustion chamber;

[0032] 300, liquid inlet chamber housing assembly; 310, liquid inlet chamber housing; 320, injection plate; R3, liquid inlet chamber; H5, injection hole;

[0033] 400, combustion chamber housing; 410, flange; R4, combustion chamber;

[0034] 500, fuel grain; H4, internal combustion hole of grain;

[0035] 600, pre-combustion chamber heat insulation layer; 710, first sealing ring; 720, second sealing ring. Detailed implementation manners

[0036] In the description of the present application, features defined with "first" and "second" are only for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Features defined with "first" and "second" may explicitly or implicitly include at least one of the defined features. When the description "a plurality of" appears, it generally means at least two, such as two, three, etc., unless otherwise specifically defined.

[0037] In this application, unless otherwise clearly specified and defined, terms such as "installed", "connected", "linked", "fixed", etc. shall be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection, it can be directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two components or the interaction relationship between two components. For those skilled in the art, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0038] In the description of this specification, terms such as "one embodiment", "some embodiments", "example", "specific example", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of this application. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0039] Figure 1 It is a cross-sectional view of an ignition structure of a hydrogen peroxide solid-liquid rocket engine provided according to one embodiment of this application. The ignition structure of the hydrogen peroxide solid-liquid rocket engine includes an igniter 100, a pre-combustion chamber housing 200, a liquid inlet chamber housing assembly 300, a combustion chamber housing 400, and a fuel grain 500. A pre-combustion chamber R2 is formed inside the pre-combustion chamber housing 200, and the pre-combustion chamber R2 penetrates the pre-combustion chamber housing 200 along the axial direction of the pre-combustion chamber housing 200.

[0040] The liquid inlet chamber housing assembly 300 is arranged at one axial end of the pre-combustion chamber housing 200 and covers the axial end opening of the pre-combustion chamber R2. A liquid inlet chamber R3 communicating with the pre-combustion chamber R2 is formed inside the liquid inlet chamber housing assembly 300.

[0041] The combustion chamber housing 400 is arranged at the other axial end of the pre-combustion chamber housing 200 and covers the axial end opening of the pre-combustion chamber R2. A combustion chamber R4 communicating with the pre-combustion chamber R2 is formed inside the combustion chamber housing 400. The fuel grain 500 is arranged inside the combustion chamber R4 and is provided with an internal combustion hole H4 of the grain.

[0042] In the ignition structure of the hydrogen peroxide solid-liquid rocket engine of this embodiment, the liquid inlet chamber housing assembly 300, the pre-combustion chamber housing 200, and the combustion chamber housing 400 are spliced in sequence axially, and moreover, the liquid inlet chamber R3 inside the liquid inlet chamber housing assembly 300, the pre-combustion chamber R2 inside the pre-combustion chamber housing 200, and the combustion chamber R4 inside the combustion chamber housing 400 are communicated in sequence axially.

[0043] Specifically, the liquid inlet chamber housing assembly 300 and the combustion chamber housing 400 are respectively located at the axial two ends of the pre-combustion chamber housing 200. The liquid inlet chamber housing assembly 300 can be communicated with the hydrogen peroxide supply pipeline to introduce hydrogen peroxide into the liquid inlet chamber R3, and then enter the combustion chamber R4 through the pre-combustion chamber R2, and contact the fuel grain 500 in the combustion chamber R4 to assist in igniting the fuel grain 500 and its combustion.

[0044] It should be noted that the ignition of the fuel grain 500 also depends on the function of the igniter 100. Moreover, the shape of the fuel grain 500 is not limited to the single-round-hole type. Exemplarily, it can also be a multi-round-hole type, a star type, a wheel type, etc. Figure 2 Disclosed Figure 1 The cross-sectional view of the igniter 100 in Figure 3 is Figure 2 The cross-sectional view of the igniter housing 10 in Figure 2 and Figure 3 . The igniter 100 includes an igniter housing 10 and an ignition charge 20.

[0045] An igniter chamber R1 extending along the axis of the igniter housing 10 is formed in the igniter housing 10. The igniter chamber R1 includes an ignition chamber R11 and a firing chamber R12 which are axially spaced and communicated. The igniter housing 10 is provided with a plurality of firing holes H1, and the plurality of firing holes H1 are located on the outer peripheral wall of the igniter housing 10 and communicate with the firing chamber R12.

[0046] The ignition charge 20 is arranged in the ignition chamber R11 and can undergo a violent chemical reaction after contacting hydrogen peroxide at room temperature to form gas, and the gas is formed in the firing chamber R12 and ejected through the plurality of firing holes H1.

[0047] In this embodiment, the igniter housing 10 is a hollow structure, and the internal hollow space corresponds to the igniter chamber R1, and the igniter chamber R1 is divided into an ignition chamber R11 and a firing chamber R12, and the two are communicated.

[0048] The ignition charge 20 is installed in the ignition chamber R11, and it can undergo a chemical reaction under the action of hydrogen peroxide and form high-temperature and high-pressure gas, and these gases are ejected through the firing holes H1. It should be noted that the room temperature here refers to about 25°C. Specifically, the room temperature can be 10°C to 40°C.

[0049] Please refer to Figure 1 , one axial end of the igniter 100 close to the ignition chamber R11 is connected to the liquid inlet chamber housing assembly 300, so that the hydrogen peroxide entering from the liquid inlet chamber R3 can enter the igniter 100, and at least part of the igniter 100 provided with the firing holes H1 extends into the internal combustion hole H4 of the fuel grain 500 for combustion.

[0050] In one embodiment, a plurality of ignition holes H1 form an ignition hole ring arranged at intervals along the axial direction. Each ignition hole ring includes ignition holes H1 arranged at intervals along the circumferential direction of the ignition chamber R12. Preferably, the plurality of ignition holes H1 are arranged as densely as possible over the entire housing portion corresponding to the ignition chamber R12. Further, the entire portion of the igniter 100 provided with the ignition holes H1 is located within the internal combustion holes H4 of the fuel grain 500. That is, the entire housing portion corresponding to the ignition chamber R12 extends into the internal combustion holes H4 of the fuel grain 500.

[0051] The ignition process in the solution of this application is as follows. First, hydrogen peroxide can enter the liquid inlet chamber R3 through a pipeline. A part of the hydrogen peroxide can enter the ignition chamber R11 in the igniter 100 to undergo a violent redox reaction and combustion reaction with the ignition charge 20 in the ignition chamber R11, generating high-temperature and high-pressure gas. The high-temperature and high-pressure gas enters the ignition chamber R12 and is ejected through the ignition holes H1. Obviously, the high-temperature and high-pressure gas ejected from the ignition holes H1 is sprayed onto the inner surface of the fuel grain 500.

[0052] At the same time, another part of the hydrogen peroxide in the liquid inlet chamber R3 enters the combustion chamber R4 through the pre-combustion chamber R2. The high-temperature and high-pressure gas in the combustion chamber R4 can heat the liquid hydrogen peroxide and decompose the liquid hydrogen peroxide by heating to form high-temperature water vapor and oxygen, providing the oxygen required for the combustion of the fuel grain 500 and generating a large amount of heat, so as to cooperate with the igniter 100 to complete ignition.

[0053] It should be noted that both the ignition charge 20 and the fuel grain 500 here are solid charges, and the materials used for the two are not exactly the same. Among them, the ignition charge 20 is a high-energy solid charge compared with the fuel grain 500, and the ignition charge 20 can directly undergo a redox reaction and a combustion reaction with hydrogen peroxide.

[0054] In this solution, the igniter 100 uses an ignition charge 20 (a high-energy self-igniting solid charge) that can directly chemically react with hydrogen peroxide, and forms high-temperature and high-pressure gas ejected outward within the igniter housing 10 for igniting the fuel grain 500.

[0055] Compared with the existing catalytic bed ignition solution, the ignition charge 20 undergoes a violent redox reaction and combustion reaction with hydrogen peroxide, having advantages such as high ignition energy and fast ignition response. Compared with the existing solution using a gunpowder igniter, it has advantages such as simple ignition method, miniaturization, simple structure, light weight, and low price.

[0056] In some alternative embodiments, the raw materials of the ignition grain 20 include a polymer and a strong reducing agent. It should be noted that hydrogen peroxide undergoes a violent redox reaction with the strong reducing agent in the ignition grain 20, generating a large amount of heat and igniting simultaneously. Moreover, the organic polymer in the ignition grain 20 undergoes a combustion reaction with the high-temperature oxygen decomposed from hydrogen peroxide, further increasing the combustion temperature and gas production. In this embodiment, the gas temperature formed by the ignition grain 20 can reach 2500 - 3000 K (Kelvin), and the ignition delay can be less than 10 ms.

[0057] In specific applications, the polymer in the raw materials of the ignition grain 20 includes at least one of polyethylene, hydroxyl-terminated polybutadiene, carboxyl-terminated polybutadiene, polymethyl methacrylate, paraffin wax, polysulfide rubber, pulverized coal, and dicyclopentadiene. That is, the polymer can be any one or a combination of polyethylene, hydroxyl-terminated polybutadiene, carboxyl-terminated polybutadiene, polymethyl methacrylate, paraffin wax, polysulfide rubber, pulverized coal, and dicyclopentadiene.

[0058] The strong reducing agent in the raw materials of the ignition grain 20 includes at least one of alkali metal borohydrides, alkali metal aluminum hydrides, and boron-nitrogen compounds. That is, the strong reducing agent can be any one or a combination of alkali metal borohydrides, alkali metal aluminum hydrides, and boron-nitrogen compounds. Exemplarily, such as sodium borohydride, potassium borohydride, sodium aluminum hydride, potassium aluminum hydride, etc.

[0059] In a preferred embodiment, the mass percentage of the polymer in the raw materials of the ignition grain 20 is 30% to 90%. The mass percentage of the strong reducing agent in the raw materials of the ignition grain 20 is 10% to 70%. Exemplarily, the mass percentage of the polymer can be 30%, 40%, 50%, 60%, 70%, 80%, 90%. Correspondingly, the mass percentage of the strong reducing agent can be 70%, 60%, 50%, 40%, 30%, 20%, 10%, as long as the sum of the two is 100%.

[0060] Figure 4 is Figure 1 a schematic view of the middle injection plate 320 from a perspective. Please refer to Figure 4 , in some alternative embodiments, the liquid inlet chamber housing assembly 300 includes a liquid inlet chamber housing 310 and an injection plate 320. A liquid inlet chamber R3 is formed inside the liquid inlet chamber housing 310.

[0061] The injection plate 320 is disposed inside the liquid inlet chamber R3 and at the axially one-end opening side of the pre-combustion chamber R2. The injection plate 320 is provided with a plurality of injection holes H5 to communicate the liquid inlet chamber R3 with the pre-combustion chamber R2, and the central injection hole among the plurality of injection holes H5 communicates with the ignition chamber R11.

[0062] In this embodiment, the injection plate 320 is fixedly installed in the liquid inlet chamber R3 within the liquid inlet chamber housing 310 and is located at the axially one - end opening side of the pre - combustion chamber R2. Thus, the hydrogen peroxide in the liquid inlet chamber R3 needs to pass through the injection plate 320 before entering the pre - combustion chamber R2.

[0063] The injection plate 320 is provided with a plurality of injection holes H5, and these injection holes H5 allow hydrogen peroxide to pass through. Thus, the hydrogen peroxide can enter the pre - combustion chamber R2 through these injection holes H5 and reach the fuel grain 500.

[0064] In the illustrated embodiment, a passage is also formed within the liquid inlet chamber housing 310 to allow hydrogen peroxide to enter the liquid inlet chamber R3. Moreover, the cross - section of the liquid inlet chamber R3 is gradually expanded in the axial direction and towards the pre - combustion chamber R2. Also, the injection plate 320 almost covers the entire axially one - end opening of the pre - combustion chamber R2.

[0065] Thus, in specific applications, the liquid inlet chamber R3 can ensure that the hydrogen peroxide maintains a relatively stable pressure and can only enter the pre - combustion chamber R2 through the injection holes H5 on the injection plate 320. Further, the injection plate 320 is a circular plate and the plurality of injection holes H5 on the injection plate 320 are arranged in a circumferential array. Furthermore, these injection holes H5 on the injection plate 320 can spray the liquid hydrogen peroxide onto the fuel grain 500 uniformly, continuously, at a certain speed and pressure. Additionally, in Figure 4 the illustrated embodiment, the central injection hole refers to the injection hole H5 located at the center of the circle of the injection plate 320.

[0066] It can be understood that by reasonably designing the aperture diameters of these injection holes H5, the liquid hydrogen peroxide can be atomized, increasing the contact area between the hydrogen peroxide and the fuel grain 500, which is conducive to the redox reaction occurring in the fuel grain 500.

[0067] In addition, the injection plate 320 can be made of austenitic stainless steel 316 which has good compatibility with hydrogen peroxide. And the injection plate 320 and the inner peripheral wall of the liquid inlet chamber housing 310 are integrally connected by a welding process. Of course, it is not limited thereto. For example, a screwing connection or other methods can also be used. Moreover, the injection holes H5 on the injection plate 320 are straight - through injection holes, that is, these injection holes H5 penetrate through the injection plate 320 in the thickness direction (also the axial direction) of the injection plate 320.

[0068] It should be understood that the pre - combustion chamber R2 is located between the injection plate 320 and the fuel grain 500. Due to the atomization effect of the injection plate 320 and the high - temperature and high - pressure gas formed by the igniter 100, the pre - combustion chamber R2 can serve as a reflux region for the mixed gas, increasing the degree of mixing of the mixed gas and improving the combustion efficiency of the fuel grain 500.

[0069] In a further optional embodiment, the igniter 100 further includes an igniter structure 30 and an igniter plug 40. The igniter joint 30 and the igniter outlet plug 40 are respectively disposed at two axial ends of the igniter housing 10.

[0070] The igniter joint 30 communicates with the ignition chamber R11 and is capable of guiding the injection of hydrogen peroxide into the ignition chamber R11. The igniter outlet plug 40 seals the firing chamber R12.

[0071] In this embodiment, the igniter joint 30 and the igniter outlet plug 40 are respectively fixedly installed at two axial ends of the igniter housing 10. A through hole is provided in the igniter joint 30 to communicate with the ignition chamber R11. The through hole in the igniter joint 30 allows hydrogen peroxide to pass through and be injected into the ignition chamber R11, enabling the hydrogen peroxide to react with the ignition charge 20 in the ignition chamber R11 to form high-temperature and high-pressure gas.

[0072] In addition, since the igniter outlet plug 40 blocks the outlet of the firing chamber R12, the high-temperature and high-pressure gas can only be ejected through the firing hole H1.

[0073] In a specific application, the igniter joint 30 and the igniter outlet plug 40 are respectively threadedly connected to two axial ends of the igniter housing 10. And, one axial end of the igniter 100 is fixedly installed on the injection plate 320.

[0074] In one embodiment, the injection hole H5 at the center of the injection plate 320 is a threaded hole for threadedly connecting with the igniter joint 30 at one axial end of the igniter 100, thereby realizing the communication between the injection hole H5 and the ignition chamber R11, so that hydrogen peroxide can enter the ignition chamber R11 to chemically react with the ignition charge 20 in the ignition chamber R11.

[0075] It should be noted that the hole position on the injection plate 320 communicating with the igniter joint 30 is generally the injection hole H5 at the center of the injection plate 320, and it is not limited to the case where the injection plate 320 is circular..

[0076] In a further optional embodiment, a central hole H3 extending axially is provided in the ignition charge 20, and the igniter joint 30 can guide hydrogen peroxide into the central hole H3 of the charge.

[0077] In this embodiment, the igniter joint 30 directly guides hydrogen peroxide into the central hole H3 of the charge, so that hydrogen peroxide and the ignition charge 20 are in full contact and undergo a chemical reaction to form high-temperature and high-pressure gas.

[0078] Through the design of the central hole H3 of the charge, the liquid hydrogen peroxide can flow axially through the entire ignition charge 20, ensuring full contact between the hydrogen peroxide and the ignition charge 20 and preventing the occurrence of hydrogen peroxide blockage.

[0079] It should be noted that the shape of the ignition charge 20 is not limited to the single-round-hole type. Exemplarily, it can also be a multi-round-hole type, a star type, a wheel type, etc.

[0080] In a further optional embodiment, the igniter housing 10 is provided with a baffle plate 11. The baffle plate 11 is located in the igniter chamber R1 and divides the igniter chamber R1 into an ignition chamber R11 and a firing chamber R12.

[0081] The baffle plate 11 is provided with a gas through-hole H2 to communicate the ignition chamber R11 and the firing chamber R12. The gas through-hole H2 communicates with the center hole H3 of the charge. The baffle plate 11 can be in contact with one axial end of the ignition charge 20 to define the insertion depth of the ignition charge 20 and prevent the ignition charge 20 from moving.

[0082] In this embodiment, a baffle plate 11 is provided in the igniter housing 10. The baffle plate 11 is located in the igniter chamber R1 and further divides the igniter chamber R1 into an ignition chamber R11 and a firing chamber R12 in the axial direction. Further, the baffle plate 11 is provided with a gas through-hole H2 to communicate the ignition chamber R11 and the firing chamber R12, and the gas through-hole H2 also communicates with the center hole H3 of the charge.

[0083] In the illustrated embodiment, the structure of the igniter housing 10 is a cylindrical structure with threads at both ends and a baffle plate 11 in the middle. The baffle plate 11 is an annular ear plate radially extending inward from the inner wall of the igniter housing 10, and a gas through-hole H2 is formed in the middle thereof. Further, the through-hole in the igniter adapter 30 allowing hydrogen peroxide to pass through, the center hole H3 of the charge, and the gas through-hole H2 are coaxially arranged.

[0084] In addition, during the installation of the ignition charge 20, one axial end of the ignition charge 20 can abut against the baffle plate 11 to define the insertion depth of the ignition charge 20 and also prevent the ignition charge 20 from moving.

[0085] Please continue to refer to Figure 1 , in some optional embodiments, the ignition structure of the hydrogen peroxide solid-liquid rocket engine further includes a pre-combustion chamber heat insulation layer 600. The pre-combustion chamber heat insulation layer 600 is disposed in the pre-combustion chamber R2 and is arranged in contact with the inner peripheral wall of the pre-combustion chamber housing 200.

[0086] In this embodiment, a pre-combustion chamber heat insulation layer 600 is further provided in the pre-combustion chamber housing 200. The pre-combustion chamber heat insulation layer 600 is located in the pre-combustion chamber R2 and is in contact with the inner peripheral wall, reducing the heat radiation damage to the surrounding components caused by the charge.

[0087] In specific applications, the pre-combustion chamber heat insulation layer 600 is made of heat insulation materials, including, for example, ceramics, graphite, alloys with heat insulation functions, etc., but is not limited thereto.

[0088] In a further optional embodiment, the ignition structure of the hydrogen peroxide solid-liquid rocket engine further includes a first sealing ring 710 and a second sealing ring 720. The first sealing ring 710 is clamped between the front combustion chamber housing 200 and the liquid inlet chamber housing assembly 300, and the second sealing ring 720 is clamped between the front combustion chamber housing 200 and the combustion chamber housing 400.

[0089] In this embodiment, the first sealing ring 710 is located at the splicing joint of the front combustion chamber housing 200 and the liquid inlet chamber housing assembly 300, and the second sealing ring 720 is located at the splicing joint of the front combustion chamber housing 200 and the combustion chamber housing 400. The first sealing ring 710 and the second sealing ring 720 prevent leakage at the splicing joint, that is, ensure the airtightness of the ignition structure of the hydrogen peroxide solid-liquid rocket engine.

[0090] In an optional embodiment, a flange 410 is provided at one axial end of the combustion chamber housing 400 to be connected to the front combustion chamber housing 200. In a specific application, a plurality of assembly hole positions that can be aligned are provided on the flange 410, the front combustion chamber housing 200, and the liquid inlet chamber housing 310, and then locking and fixing are achieved through screw connectors (such as bolts and nuts).

[0091] In addition, the ignition structure of the hydrogen peroxide solid-liquid rocket engine has all the advantages brought by the above-mentioned igniter 100, which will not be repeated here.

[0092] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present application. Those skilled in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present application.

Claims

1. An igniter, characterized in that: include: An igniter housing (10) is formed with an igniter chamber (R1) extending in the axial direction of the igniter housing (10), the igniter chamber (R1) comprising an ignition chamber (R11) and an ignition chamber (R12) arranged in an axial direction and connected to each other, the igniter housing (10) is provided with a plurality of ignition holes (H1), the plurality of ignition holes (H1) are located on the outer peripheral wall of the igniter housing (10) and connected to the ignition chamber (R12); as well as The ignition charge column (20) is arranged in the ignition chamber (R11) and can undergo a violent chemical reaction with hydrogen peroxide at room temperature to form combustion gas, which is ejected from the ignition chamber (R12) through the plurality of ignition holes (H1).

2. The igniter according to claim 1, characterized in that: It also includes an igniter connector (30) and an igniter outlet plugging cover (40), wherein the igniter connector (30) and the igniter outlet plugging cover (40) are respectively arranged at two axial ends of the igniter housing (10); The igniter connector (30) is connected to the ignition chamber (R11) to inject hydrogen peroxide into the ignition chamber (R11), and the igniter outlet plugging cover (40) blocks the ignition chamber (R12).

3. The igniter according to claim 2, characterized in that: The ignition charge (20) is provided with a charge center hole (H3) penetrating along the axial direction, and the igniter joint (30) is capable of injecting hydrogen peroxide into the charge center hole (H3).

4. The igniter according to claim 3, characterized in that: The igniter housing (10) is provided with a medicine baffle (11), and the medicine baffle (11) is located in the igniter chamber (R1) and divides the igniter chamber (R1) into the ignition chamber (R11) and the ignition chamber (R12); The medicine baffle (11) is provided with a gas through hole (H2) to connect the ignition chamber (R11) and the ignition chamber (R12); the gas through hole (H2) is connected to the center hole (H3) of the medicine column; the medicine baffle (11) can be connected to one axial end of the ignition medicine column (20) to limit the installation depth of the ignition medicine column (20) and prevent the ignition medicine column (20) from moving.

5. The igniter according to any one of claims 1 to 4, characterized in that: The raw materials of the ignition charge column (20) include polymer and strong reducing substance; The polymer includes at least one of polyethylene, hydroxyl-terminated polybutadiene, carboxyl-terminated polybutadiene, polymethyl methacrylate, paraffin, polysulfide rubber, coal powder, and dicyclopentadiene; The strong reducing substance includes at least one of alkali metal borohydrides, alkali metal aluminum hydrides, and boron nitrogen compounds.

6. The igniter according to claim 5, characterized in that The mass percentage of the polymer in the ignition charge (20) is 30% to 90%; The mass percentage of the strong reducing substance in the ignition charge (20) is 10% to 70%.

7. A hydrogen peroxide solid-liquid rocket engine ignition structure, characterized in that: include A front combustion chamber shell (200) is formed with a front combustion chamber (R2) therein, wherein the front combustion chamber (R2) penetrates the front combustion chamber shell (200) along the axial direction of the front combustion chamber shell (200); A liquid inlet chamber housing assembly (300) is arranged at one axial end of the front combustion chamber housing (200) and covers an opening at one axial end of the front combustion chamber (R2); a liquid inlet chamber (R3) communicating with the front combustion chamber (R2) is formed in the liquid inlet chamber housing assembly (300); A combustion chamber housing (400) is arranged at the other axial end of the front combustion chamber housing (200) and covers the other axial end opening of the front combustion chamber (R2); a combustion chamber (R4) communicating with the front combustion chamber (R2) is formed in the combustion chamber housing (400); A fuel charge (500) is disposed in the combustion chamber (R4) and is provided with a charge inner combustion hole (H4); and According to the igniter (100) according to any one of claims 1 to 6, the igniter (100) is connected to the liquid inlet chamber housing assembly (300) at one axial end close to the ignition chamber (R11), so that the hydrogen peroxide injected from the liquid inlet chamber (R3) can enter the igniter (100), and the igniter (100) is arranged with at least a portion of the ignition hole (H1) extending into the fuel column combustion hole (H4) in the fuel column (500).

8. The hydrogen peroxide solid-liquid rocket engine ignition structure according to claim 7, characterized in that: The liquid inlet chamber housing assembly (300) comprises a liquid inlet chamber housing (310) and an injection plate (320), and the liquid inlet chamber (R3) is formed in the liquid inlet chamber housing (310); The injection plate (320) is arranged in the liquid inlet chamber (R3) and is located at the axial opening side of one end of the pre-combustion chamber (R2). The injection plate (320) is provided with a plurality of injection holes (H5) to connect the liquid inlet chamber (R3) and the pre-combustion chamber (R2), and the central injection hole among the plurality of injection holes (H5) is connected to the ignition chamber (R11).

9. The ignition structure of a hydrogen peroxide solid-liquid rocket engine according to claim 7, characterized in that: It also includes a front combustion chamber heat insulation layer (600), which is arranged in the front combustion chamber (R2) and is arranged in contact with the inner peripheral wall of the front combustion chamber shell (200).

10. The ignition structure of a hydrogen peroxide solid-liquid rocket engine according to any one of claims 7 to 9, characterized in that: Also includes a first sealing ring (710) and a second sealing ring (720); The first sealing ring (710) is sandwiched between the front combustion chamber housing (200) and the liquid inlet chamber housing assembly (300), and the second sealing ring (720) is sandwiched between the front combustion chamber housing (200) and the combustion chamber housing (400).

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