Spontaneous combustion solid-liquid rocket engine grain and preparation method and application thereof

Abstract

The invention provides a spontaneous combustion solid-liquid rocket engine grain and a preparation method and application thereof. The spontaneous combustion solid-liquid rocket engine grain is prepared from the following raw materials in parts by weight: 50-90 parts of solid-liquid rocket engine fuel and 5-50 parts of a strong reducing substance. The ignition delay of the spontaneous combustion solid-liquid rocket engine grain is extremely low and can range from several milliseconds to dozens of milliseconds, the performance is good, the specific impulse and the adiabatic flame temperature of the solid-liquid rocket engine cannot be affected, and the spontaneous combustion solid-liquid rocket engine grain has the repeated ignition capacity.

Description

Technical Field

[0001] The invention relates to the technical field of solid-liquid rocket engines, and in particular to a self-igniting solid-liquid rocket engine powder column and a preparation method and application thereof. Background Art

[0002] Solid-liquid hybrid rocket engines have the advantages of low cost, safety and non-toxicity, high performance, good environmental protection, good grain stability, low temperature sensitivity, adjustable thrust and multiple starts. In recent years, they have been widely used in launch vehicles, sounding rockets, suborbital vehicles, boosters, upper stage engines, attitude and orbit control engines, targets, tactical missiles and commercial aerospace. For typical solid-liquid rocket engines, a combination of liquid (or gas) oxidizer + solid fuel grain is usually used. Different combinations of oxidizers and fuels make solid-liquid engines have different working characteristics and applicable fields. Commonly used oxidizers are liquid oxygen, N 2 O, H 2 O 2 Etc., oxidizers are usually supplied in extrusion format; commonly used solid fuel propellants include polyurethane (PU), polyethylene (PE), hydroxy-terminated polybutadiene (HTPB), carboxyl-terminated polybutadiene (CTPB), paraffin, etc.

[0003] High concentration H 2 O 2 It is a green, non-toxic, high-performance liquid oxidizer that can be stored at room temperature. Hydrogen peroxide solid-liquid rocket engines have the advantages of good safety, easy thrust adjustment, ability to shut down and start multiple times, non-toxic and pollution-free, good grain stability, low temperature sensitivity and good economy. It fully meets the requirements of near-space vehicle power systems for fast, economical, reliable, safe, green, large airspace, large thrust adjustment and thrust intelligent control.

[0004] The ignition technologies of hydrogen peroxide solid-liquid rocket engines usually include gunpowder igniter ignition, catalytic bed ignition, torch ignition, radiation ignition, laser ignition and so on.

[0005] Among them, the disadvantages of the gunpowder igniter are: an additional and complex ignition system is required, the gunpowder igniter requires additional installation space, the ignition powder is a flammable and explosive pyrotechnic product, and there is a risk of explosion during engine storage. In addition, when the engine is working, the unused ignition powder also has the risk of failure and explosion due to vibration friction or severe overload. If multiple ignitions are required, multiple ignition devices need to be installed. When ignition is used for ignition, the number of starts is limited by the number of ignition devices. When the ignition powder is consumed, the engine will no longer have the ability to start. If multiple sets of ignition powder are carried, the negative mass of the engine will also increase, which is not conducive to improving the overall performance of the engine.

[0006] Among them, the disadvantages of hydrogen peroxide catalytic ignition are: when using a catalytic bed for ignition, the oxidant used by the engine must have the characteristics of self-decomposition and heat release. Some commonly used oxidants, such as oxygen, cannot be ignited in this way. This method limits the types of oxidants that can be used in the engine. In addition, the catalytic bed also has certain restrictions on the flow rate of the oxidant, that is, the bed load is limited. The catalytic bed has a large structural size, a large weight, a large flow resistance, a small flow rate, a large pressure drop, a short life, poor starting performance, easy loss of the catalyst, and an expensive catalyst.

[0007] Among them, the disadvantages of the torch ignition solution are: this method requires an additional ignition gas circuit and a spark plug. The ignition system occupies additional space and weight, and has a complex structure, and has strict requirements on the timing and flow control of the ignition gas circuit.

[0008] Therefore, it is urgent to develop a fuel charge that does not require an additional ignition device and can generate a combustion reaction when the oxidant hydrogen peroxide contacts the solid fuel.

[0009] In view of this, the present invention is proposed. Summary of the invention

[0010] The present invention aims to provide a self-igniting solid-liquid rocket engine grain, wherein the raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight, 50 to 90 parts of solid-liquid rocket engine fuel and 5 to 50 parts of strong reducing substances. The grain is a solid-liquid rocket engine grain that can self-ignite with hydrogen peroxide, does not require an additional ignition device, and a combustion reaction can occur when the oxidant hydrogen peroxide contacts the solid fuel, and the ignition delay is in the order of milliseconds.

[0011] The second object of the present invention is to provide a method for preparing the self-igniting solid-liquid rocket engine grain, which specifically includes the following steps: mixing the various preparation raw materials of the self-igniting solid-liquid rocket engine grain, and then casting through a mold, cooling and solidifying, to prepare the self-igniting solid-liquid rocket engine grain.

[0012] The third object of the present invention is to provide an application of the self-igniting solid-liquid rocket engine powder in the preparation of a self-igniting hydrogen peroxide-catalyzed solid-liquid rocket engine.

[0013] The fourth object of the present invention is to provide a hydrogen peroxide solid-liquid rocket engine, which includes a hydrogen peroxide delivery system and an engine main body system, and the hydrogen peroxide solid-liquid rocket engine has no ignition device; the engine main body system includes a combustion chamber, and the combustion chamber includes the above-mentioned self-igniting solid-liquid rocket engine powder.

[0014] In order to achieve the above-mentioned purpose of the present invention, the following technical solutions are particularly adopted:

[0015] In a first aspect, the present invention provides a self-igniting solid-liquid rocket engine grain, wherein the raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight: 50 to 90 parts of solid-liquid rocket engine fuel and 5 to 50 parts of a strong reducing substance;

[0016] The strong reducing substance is selected from any one of alkali metal borohydrides, alkali metal aluminum hydrides or boron nitrogen compounds, or a combination of at least two thereof.

[0017] The self-igniting solid-liquid rocket engine grain of the present invention realizes an ignition mechanism without the need for an external ignition device. The grain can instantly trigger a self-ignition reaction when it comes into contact with an oxidant. The core principle involves an efficient redox reaction between the oxidant and a specific strong reducing substance in the grain. An increase in the proportion of strong reducing substances helps promote the redox reaction, thereby further reducing the ignition delay time. This redox reaction releases a large amount of heat energy, rapidly raising the fuel temperature to the ignition point. At the same time, the temperature increase causes hydrogen peroxide to decompose to produce oxygen and release heat.

[0018] Furthermore, the solid-liquid rocket engine fuel forms liquid hydrocarbon droplets while burning on the surface, and the vapor formed by these droplets after evaporation can also continue to burn, ensuring the continuous propulsion of the rocket engine. Therefore, the self-igniting solid-liquid rocket engine grain has an extremely low ignition delay time, which only takes a few milliseconds to tens of milliseconds. The specific value can be adjusted to a certain extent according to the type and proportion of the formula.

[0019] The self-igniting solid-liquid rocket engine grain of the present invention has good performance and hardly affects the specific impulse and adiabatic flame temperature of the solid-liquid rocket engine, thereby ensuring the good performance of the rocket engine. In addition, the self-igniting grain can be started multiple times. After the oxidant stops supplying, the rocket engine will shut down. When hydrogen peroxide is supplied again, the engine will ignite again, and the re-ignition delay only takes a few milliseconds to tens of milliseconds.

[0020] In the present invention, the content of solid-liquid rocket engine fuel is 50-90 parts, for example, it can be 50 parts, 52 parts, 54 parts, 56 parts, 58 parts, 60 parts, 62 parts, 64 parts, 66 parts, 68 parts, 70 parts, 72 parts, 74 parts, 76 parts, 78 parts, 80 parts, 82 parts, 84 parts, 86 parts, 88 parts, 90 parts, etc.

[0021] The above-mentioned solid-liquid rocket engine fuel mainly contains elements such as C and H, which are the main energy and working fluid source of the propellant and occupy most of the grain. It needs to have good bonding and mechanical properties, mainly to make the grain have sufficient strength, elastic modulus and elongation; its proportion can be adjusted according to the types of oxidizer and main fuel.

[0022] In the present invention, the content of the strong reducing substance is 5 to 50 parts, for example, it can be 5 parts, 6 parts, 8 parts, 10 parts, 12 parts, 14 parts, 16 parts, 18 parts, 20 parts, 22 parts, 24 parts, 26 parts, 28 parts, 30 parts, 32 parts, 34 parts, 36 parts, 38 parts, 40 parts, 42 parts, 44 parts, 46 parts, 48 ​​parts, 50 parts, etc.

[0023] The above-mentioned strong reducing substance is selected from any one or a combination of at least two of alkali metal borohydrides, alkali metal aluminum hydrides or boron nitrogen compounds, mainly to achieve the self-ignition function. The strong reducing substance can spontaneously undergo a strong redox reaction when in contact with the oxidant, releasing a large amount of hot ignition charge, while also providing H element as fuel and providing metal elements to generate condensed phase particles.

[0024] Preferably, the solid-liquid rocket engine fuel is selected from any one or a combination of at least two of polyethylene, hydroxy-terminated polybutadiene, carboxyl-terminated polybutadiene, polymethyl methacrylate, paraffin, polysulfide rubber, coal powder or dicyclopentadiene.

[0025] Furthermore, the solid-liquid rocket engine fuel is selected from any one of paraffin, polyethylene, dicyclopentadiene or terminal hydroxyl polybutadiene, or a combination of at least two thereof.

[0026] The above-mentioned solid-liquid rocket engine fuel has better processability and is easy to pour; in addition, as a fuel, it is required to have high combustion heat release, high calorific value, large gas generation, high inherent enthalpy, high density, good physical and chemical stability, low cost, etc.

[0027] Preferably, the alkali metal borohydride is selected from any one of lithium borohydride, sodium borohydride or potassium borohydride, or a combination of at least two thereof.

[0028] Preferably, the alkali metal aluminum hydride is lithium aluminum hydride.

[0029] Preferably, the boron-nitrogen compound is selected from ammonia borane and / or ethylenediaminebisborane.

[0030] Preferably, the raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of metal fuel, for example, it can be 0.05 parts, 0.08 parts, 0.1 parts, 0.2 parts, 0.4 parts, 0.6 parts, 0.8 parts, 1 parts, 1.2 parts, 1.4 parts, 1.6 parts, 1.8 parts, 2 parts, 2.2 parts, 2.4 parts, 2.6 parts, 2.8 parts, 3 parts, 3.2 parts, 3.4 parts, 3.6 parts, 3.8 parts, 4 parts, 4.2 parts, 4.4 parts, 4.6 parts, 4.8 parts, 5 parts, etc.

[0031] Preferably, the metal fuel is selected from any one of magnesium, aluminum, beryllium, lithium or zirconium, or a combination of at least two thereof.

[0032] The above-mentioned metal fuel has a high density, which increases the overall density of the propellant column, and has a high combustion calorific value. The condensed phase particles in the combustion products can also suppress high-frequency unstable combustion: In addition, the above-mentioned metal fuel also has the advantages of high combustion calorific value, high density, good compatibility with other components, low oxygen consumption, and low price.

[0033] Preferably, the raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 10 parts of additives, for example, it can be 0.05 parts, 0.08 parts, 0.1 parts, 0.2 parts, 0.4 parts, 0.6 parts, 0.8 parts, 1 parts, 1.2 parts, 1.4 parts, 1.6 parts, 1.8 parts, 2 parts, 2.2 parts, 2.4 parts, 2.6 parts, 2.8 parts, 3 parts, 3.2 parts, 3.4 parts, 3.6 parts, 3.8 parts, 4 parts, 4.2 parts, 4.4 parts, 4.6 parts, 4.8 parts, 5 parts, 5.5 parts, 6 parts, 6.5 parts, 7 parts, 7.5 parts, 8 parts, 8.5 parts, 9 parts, 9.5 parts, 10 parts, etc.

[0034] Preferably, the additive is selected from any one of a curing agent, a cross-linking agent, a plasticizer, a combustion rate catalyst, a catalytic combustion aid, an anti-aging agent or a non-metallic powder, or a combination of at least two thereof.

[0035] It should be noted that the present invention can determine whether to add additives, the proportion of addition and the type of additives to be selected according to other components of the drug column.

[0036] Preferably, the particle size of the additive is 10 to 240 μm, for example, 10 μm, 20 μm, 40 μm, 60 μm, 80 μm, 100 μm, 120 μm, 140 μm, 160 μm, 180 μm, 200 μm, 220 μm, 240 μm, etc.

[0037] In the present invention, the ignition delay time can be shortened and the combustion of the hydrocarbon matrix can be improved by improving the particle size parameters of the additive.

[0038] Preferably, the raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of a curing agent, for example, 0.05 parts, 0.08 parts, 0.1 parts, 0.2 parts, 0.4 parts, 0.6 parts, 0.8 parts, 1 parts, 1.2 parts, 1.4 parts, 1.6 parts, 1.8 parts, 2 parts, 2.2 parts, 2.4 parts, 2.6 parts, 2.8 parts, 3 parts, 3.2 parts, 3.4 parts, 3.6 parts, 3.8 parts, 4 parts, 4.2 parts, 4.4 parts, 4.6 parts, 4.8 parts, 5 parts, etc.

[0039] Preferably, the curing agent is diisocyanate.

[0040] The function of the curing agent is to convert the linear low molecular weight prepolymer of the binder component into a moderately cross-linked network structure polymer to form a matrix, achieve curing, and give the propellant the necessary mechanical strength. For example, the curing agent used for the hydroxy prepolymer is diisocyanate.

[0041] Preferably, the diisocyanate is selected from any one or a combination of at least two of isophorone diisocyanate, toluene diisocyanate, 1,6-hexamethylene diisocyanate, dimer fatty acid diisocyanate or multifunctional isocyanate.

[0042] Preferably, the raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of a cross-linking agent.

[0043] Preferably, the cross-linking agent is selected from triethanolamine.

[0044] The cross-linking agent used at the same time as the above-mentioned curing agent is mainly used to form three-dimensional spatial cross-linking, so that the adhesive becomes a three-dimensional network structure to prevent the propellant from plastic flow.

[0045] Preferably, the raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of plasticizer, for example, it can be 0.05 parts, 0.08 parts, 0.1 parts, 0.2 parts, 0.4 parts, 0.6 parts, 0.8 parts, 1 parts, 1.2 parts, 1.4 parts, 1.6 parts, 1.8 parts, 2 parts, 2.2 parts, 2.4 parts, 2.6 parts, 2.8 parts, 3 parts, 3.2 parts, 3.4 parts, 3.6 parts, 3.8 parts, 4 parts, 4.2 parts, 4.4 parts, 4.6 parts, 4.8 parts, 5 parts, etc.

[0046] Preferably, the plasticizer is selected from dibutyl phthalate.

[0047] The above-mentioned plasticizer has two functions: one is to reduce the viscosity of the uncured propellant slurry and increase its fluidity to facilitate casting; the other is to reduce the glass transition temperature of the propellant and improve its low-temperature mechanical properties.

[0048] Preferably, the raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of a burning rate catalyst, for example, 0.05 parts, 0.08 parts, 0.1 parts, 0.2 parts, 0.4 parts, 0.6 parts, 0.8 parts, 1 parts, 1.2 parts, 1.4 parts, 1.6 parts, 1.8 parts, 2 parts, 2.2 parts, 2.4 parts, 2.6 parts, 2.8 parts, 3 parts, 3.2 parts, 3.4 parts, 3.6 parts, 3.8 parts, 4 parts, 4.2 parts, 4.4 parts, 4.6 parts, 4.8 parts, 5 parts, etc.

[0049] Preferably, the burning rate catalyst is selected from any one of ferric oxide, chromite or carbon black, or a combination of at least two thereof.

[0050] Preferably, the raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of a catalytic combustion aid, for example, it can be 0.05 parts, 0.08 parts, 0.1 parts, 0.2 parts, 0.4 parts, 0.6 parts, 0.8 parts, 1 parts, 1.2 parts, 1.4 parts, 1.6 parts, 1.8 parts, 2 parts, 2.2 parts, 2.4 parts, 2.6 parts, 2.8 parts, 3 parts, 3.2 parts, 3.4 parts, 3.6 parts, 3.8 parts, 4 parts, 4.2 parts, 4.4 parts, 4.6 parts, 4.8 parts, 5 parts, etc.

[0051] Preferably, the catalytic combustion improver is selected from palladium-carbon powder.

[0052] Preferably, the raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of an anti-aging agent, for example, it can be 0.05 parts, 0.08 parts, 0.1 parts, 0.2 parts, 0.4 parts, 0.6 parts, 0.8 parts, 1 parts, 1.2 parts, 1.4 parts, 1.6 parts, 1.8 parts, 2 parts, 2.2 parts, 2.4 parts, 2.6 parts, 2.8 parts, 3 parts, 3.2 parts, 3.4 parts, 3.6 parts, 3.8 parts, 4 parts, 4.2 parts, 4.4 parts, 4.6 parts, 4.8 parts, 5 parts, etc.

[0053] Preferably, the anti-aging agent is selected from any one of diphenylamine, phenylnaphthylamine or magnesium oxide, or a combination of at least two thereof.

[0054] The above-mentioned anti-aging agent can preferably prevent the solid-liquid rocket engine grain from being oxidized by air.

[0055] Preferably, the raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of non-metallic powder, for example, it can be 0.05 parts, 0.08 parts, 0.1 parts, 0.2 parts, 0.4 parts, 0.6 parts, 0.8 parts, 1 parts, 1.2 parts, 1.4 parts, 1.6 parts, 1.8 parts, 2 parts, 2.2 parts, 2.4 parts, 2.6 parts, 2.8 parts, 3 parts, 3.2 parts, 3.4 parts, 3.6 parts, 3.8 parts, 4 parts, 4.2 parts, 4.4 parts, 4.6 parts, 4.8 parts, 5 parts, etc.

[0056] Preferably, the non-metallic powder is selected from boron powder and / or carbon powder.

[0057] Among them, the combustion heat of boron powder is very high, and carbon powder can be used as a fuel while providing lubrication to improve processing performance.

[0058] In a second aspect, the present invention provides a method for preparing a self-igniting solid-liquid rocket engine grain as described in the first aspect, wherein the preparation method specifically comprises the following steps:

[0059] The raw materials for preparing the self-igniting solid-liquid rocket engine grain are mixed, and then poured through a mold, cooled and solidified to prepare the self-igniting solid-liquid rocket engine grain.

[0060] Preferably, the mixing temperature is 60-180°C, for example, it can be 60°C, 70°C, 80°C, 90°C, 100°C, 110°C, 120°C, 130°C, 140°C, 150°C, 160°C, 170°C, 180°C, etc., and the mixing speed is 500-2000rpm, for example, it can be 500rpm, 600rpm, 800rpm, 1000rpm, 1200rpm, 1400rpm, 1600rpm, 1800rpm, 2000rpm, etc.

[0061] Preferably, the pouring temperature is 60-160°C, for example, it can be 60°C, 70°C, 80°C, 90°C, 100°C, 110°C, 120°C, 130°C, 140°C, 150°C, 160°C, etc.

[0062] Preferably, the cooling and curing temperature is 0 to 50°C, for example, it may be 0°C, 5°C, 10°C, 15°C, 20°C, 25°C, 30°C, 35°C, 40°C, 45°C, 50°C, etc.

[0063] In a third aspect, the present invention provides a use of the self-igniting solid-liquid rocket engine charge described in the first aspect in the preparation of a self-igniting hydrogen peroxide-catalyzed solid-liquid rocket engine.

[0064] Preferably, the concentration of hydrogen peroxide is above 90%, for example, it may be 90%, 91%, 92%, 93%, 94%, 95%, 96%, 97%, 98%, 99%, etc.

[0065] The above-mentioned solid-liquid rocket engine formula capable of achieving spontaneous combustion of the present invention can be fine-tuned within a small range, and the ignition delay time varies from a few milliseconds to tens of milliseconds according to different formulas.

[0066] In a fourth aspect, the present invention provides a hydrogen peroxide solid-liquid rocket engine, which includes a hydrogen peroxide delivery system and an engine main body system, and the hydrogen peroxide solid-liquid rocket engine has no ignition device.

[0067] Wherein, the engine main body system includes a combustion chamber, and the combustion chamber includes the self-igniting solid-liquid rocket engine charge as described in the first aspect.

[0068] Compared with the prior art, the present invention has the following beneficial effects:

[0069] (1) The self-igniting solid-liquid rocket engine grain of the present invention can instantly trigger a self-ignition reaction through a highly efficient redox reaction between the oxidant and the strong reducing substance when in contact with the oxidant, thereby realizing an ignition mechanism without the need for an external ignition device.

[0070] (2) The solid-liquid rocket engine propellant of the present invention forms liquid hydrocarbon droplets while burning on the surface. The vapor formed by these droplets after evaporation can also continue to burn, ensuring the continuous propulsion of the rocket engine. The propellant has an extremely low ignition delay time of only a few milliseconds to tens of milliseconds.

[0071] (3) The propellant of the present invention meets the requirements of rapid ignition, multiple starts, thrust adjustability, long-term fuel storage, and large thrust, and can be applied to attitude and orbit control engines. It has the advantages of simple structure, high safety, good performance, small size, long storage period, and easy maintenance and use. DETAILED DESCRIPTION

[0072] Unless otherwise defined herein, scientific and technical terms used in conjunction with the present invention shall have the meanings commonly understood by those of ordinary skill in the art. The meaning and scope of the terms should be clear, however, in the case of any potential ambiguity, the definitions provided herein take precedence over any dictionary or external definitions. In this application, unless otherwise stated, the use of "or" means "and / or". In addition, the use of the term "including" and other forms is non-limiting.

[0073] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0074] The present invention is further described below by way of examples. Unless otherwise specified, the materials in the examples are prepared according to existing methods or directly purchased from the market.

[0075] Example 1

[0076] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0077] Fuel: Paraffin 90 parts

[0078] Strong reducing substance: 10 parts sodium borohydride

[0079] The solid-liquid rocket engine grain is prepared by the following steps:

[0080] Paraffin wax and sodium borohydride are weighed according to the formula amount and mixed at a speed of 1500 rpm, the temperature is raised to 80° C., and then poured through a mold, and then the temperature is lowered to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine grain.

[0081] Example 2

[0082] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0083] Fuel: 80 parts paraffin

[0084] Strong reducing substance: 20 parts of sodium borohydride

[0085] The solid-liquid rocket engine grain is prepared by the following steps:

[0086] Paraffin wax and sodium borohydride are weighed according to the formula amount and mixed at a speed of 1200 rpm, the temperature is raised to 80° C., and then poured through a mold, and then the temperature is lowered to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine grain.

[0087] Example 3

[0088] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0089] Fuel: 70 parts paraffin

[0090] Strong reducing substance: 30 parts of lithium aluminum hydride

[0091] The solid-liquid rocket engine grain is prepared by the following steps:

[0092] Paraffin wax and lithium aluminum hydride are weighed according to the formula amount and mixed at a speed of 1000 rpm, the temperature is raised to 80° C., and then poured through a mold, and then the temperature is lowered to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine grain.

[0093] Example 4

[0094] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0095]

[0096] The solid-liquid rocket engine grain is prepared by the following steps:

[0097] Paraffin wax, lithium aluminum hydride, isophorone diisocyanate and triethanolamine were weighed according to the formula and mixed at a speed of 1000 rpm, heated to 80° C., poured through a mold, and then cooled to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0098] Example 5

[0099] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0100] Fuel: 68 parts paraffin

[0101] Strong reducing substance: 30 parts of lithium aluminum hydride

[0102] Burning rate catalyst: 2 parts of ferric oxide

[0103] The solid-liquid rocket engine grain is prepared by the following steps:

[0104] Paraffin wax, lithium aluminum hydride and ferric oxide are weighed according to the formula and mixed at a speed of 1000 rpm, heated to 80° C., poured through a mold, and then cooled to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine grain.

[0105] Example 6

[0106] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0107]

[0110] The solid-liquid rocket engine grain is prepared by the following steps:

[0111] Paraffin wax, lithium aluminum hydride and sodium borohydride are weighed according to the formula amount and mixed at a speed of 1200 rpm, heated to 80° C., poured through a mold, and then cooled to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine grain.

[0112] Example 7

[0113] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0114]

[0117] The solid-liquid rocket engine grain is prepared by the following steps:

[0118] Paraffin wax, lithium aluminum hydride and sodium borohydride are weighed according to the formula amount and mixed at a speed of 1000 rpm, heated to 80° C., poured through a mold, and then cooled to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine grain.

[0119] Example 8

[0120] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0121] Fuel: 80 parts paraffin

[0122] Strong reducing substance: 20 parts of ammonia borane

[0123] The solid-liquid rocket engine grain is prepared by the following steps:

[0124] Paraffin wax and ammonia borane are weighed according to the formula amount and mixed at a speed of 1200 rpm, the temperature is raised to 80° C., and then poured through a mold, and then the temperature is lowered to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine grain.

[0125] Example 9

[0126] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0127] Fuel: 80 parts paraffin

[0128] Strong reducing substance: 19 parts of ammonia borane

[0129] Catalytic combustion aid: Palladium carbon (20% Pd) 1 part

[0130] The solid-liquid rocket engine grain is prepared by the following steps:

[0131] Paraffin wax, ammonia borane and palladium carbon are weighed according to the formula amount and mixed at a speed of 1200 rpm, heated to 80° C., poured through a mold, and then cooled to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0132] Example 10

[0133] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0134] Fuel: 60 parts paraffin

[0135] Strong reducing substance: 39 parts of ammonia borane

[0136] Catalytic combustion aid: Palladium carbon (20% Pd) 1 part

[0137] The solid-liquid rocket engine grain is prepared by the following steps:

[0138] Paraffin wax, ammonia borane and palladium carbon are weighed according to the formula amount and mixed at a speed of 800 rpm, the temperature is raised to 80° C., and then poured through a mold, and then the temperature is lowered to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0139] Embodiment 11

[0140] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0141]

[0142] The solid-liquid rocket engine grain is prepared by the following steps:

[0143] Paraffin, lithium aluminum hydride, magnesium, isophorone diisocyanate, triethanolamine, dibutyl phthalate, chromite, diphenylamine and boron powder are weighed according to the formula, mixed at a speed of 900 rpm, heated to 80° C., poured through a mold, and then cooled to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine grain.

[0144] Example 12

[0145] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0146] Fuel: 75 parts of polyethylene

[0147] Strong reducing substance: 25 parts of sodium borohydride

[0148] The solid-liquid rocket engine grain is prepared by the following steps:

[0149] Polyethylene and sodium borohydride are weighed according to the formula amount and mixed at a speed of 1100 rpm, the temperature is raised to 120° C., and then poured through a mold, and then the temperature is lowered to 30° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0150] Embodiment 13

[0151] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0152] Fuel: 67 parts of polyethylene

[0153] Strong reducing substance: 33 parts of sodium borohydride

[0154] The solid-liquid rocket engine grain is prepared by the following steps:

[0155] Polyethylene and sodium borohydride were weighed according to the formula and mixed at a speed of 900 rpm, heated to 120° C., poured through a mold, and then cooled to 30° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0156] Embodiment 14

[0157] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0158]

[0159] The solid-liquid rocket engine grain is prepared by the following steps:

[0160] Polyethylene, sodium borohydride, toluene diisocyanate and triethanolamine are weighed according to the formula and mixed at a speed of 900 rpm, heated to 120° C., poured through a mold, and then cooled to 30° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0161] Embodiment 15

[0162] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0163] Fuel: 65 parts of polyethylene

[0164] Strong reducing substance: 33 parts of sodium borohydride

[0165] Burning rate catalyst: 2 parts of ferric oxide

[0166] The solid-liquid rocket engine grain is prepared by the following steps:

[0167] Polyethylene, sodium borohydride and ferric oxide are weighed according to the formula and mixed at a speed of 900 rpm, heated to 120° C., poured through a mold, and then cooled to 30° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0168] Example 16

[0169] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0170]

[0173] The solid-liquid rocket engine grain is prepared by the following steps:

[0174] Polyethylene, sodium borohydride and lithium aluminum hydride are weighed according to the formula and mixed at a speed of 900 rpm, the temperature is raised to 120° C., and then poured through a mold, and then the temperature is lowered to 30° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0175] Embodiment 17

[0176] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0177] Fuel: 80 parts of polyethylene

[0178] Strong reducing substance: 19 parts of ammonia borane

[0179] Catalytic combustion aid: Palladium carbon (20% Pd) 1 part

[0180] The solid-liquid rocket engine grain is prepared by the following steps:

[0181] Polyethylene, ammonia borane and palladium carbon are weighed according to the formula amount and mixed at a speed of 1200 rpm, the temperature is raised to 120° C., and then poured through a mold, and then the temperature is lowered to 30° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0182] Embodiment 18

[0183] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0184] Fuel: 60 parts of polyethylene

[0185] Strong reducing substance: 39 parts of ammonia borane

[0186] Catalytic combustion aid: Palladium carbon (20% Pd) 1 part

[0187] The solid-liquid rocket engine grain is prepared by the following steps:

[0188] Polyethylene, ammonia borane and palladium carbon are weighed according to the formula amount and mixed at a speed of 800 rpm, the temperature is raised to 120° C., and then poured through a mold, and then the temperature is lowered to 30° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0189] Embodiment 19

[0190] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0191]

[0192] The solid-liquid rocket engine grain is prepared by the following steps:

[0193] Polyethylene, sodium borohydride, aluminum, toluene diisocyanate, triethanolamine, dibutyl phthalate, carbon black, phenylnaphthylamine and carbon powder are weighed according to the formula, mixed at a speed of 900 rpm, heated to 120° C., poured through a mold, and then cooled to 30° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0194] Embodiment 20

[0195] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0196] Fuel: 50 parts of dicyclopentadiene

[0197] Strong reducing substance: 50 parts of lithium aluminum hydride

[0198] The solid-liquid rocket engine grain is prepared by the following steps:

[0199] Dicyclopentadiene and lithium aluminum hydride are weighed according to the formula amount and mixed at a rotation speed of 800 rpm, the temperature is raised to 80° C., and then poured through a mold, and then the temperature is lowered to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine grain.

[0200] Embodiment 21

[0201] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0202] Fuel: 60 parts of dicyclopentadiene

[0203] Strong reducing substance: 40 parts of lithium aluminum hydride

[0204] The solid-liquid rocket engine grain is prepared by the following steps:

[0205] Dicyclopentadiene and lithium aluminum hydride are weighed according to the formula amount and mixed at a rotation speed of 800 rpm, the temperature is raised to 80° C., and then poured through a mold, and then the temperature is lowered to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine grain.

[0206] Embodiment 22

[0207] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0208]

[0209] The solid-liquid rocket engine grain is prepared by the following steps:

[0210] Dicyclopentadiene, lithium aluminum hydride, dimer fatty acid diisocyanate and triethanolamine were weighed according to the formula and mixed at a speed of 800 rpm, heated to 80° C., poured through a mold, and then cooled to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0211] Embodiment 23

[0212] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0213] Fuel: 58 parts of dicyclopentadiene

[0214] Strong reducing substance: 40 parts of sodium borohydride

[0215] Burning rate catalyst: 2 parts of ferric oxide

[0216] The solid-liquid rocket engine grain is prepared by the following steps:

[0217] Dicyclopentadiene, sodium borohydride and ferric oxide were weighed according to the formula and mixed at a speed of 800 rpm, heated to 80° C., poured through a mold, and then cooled to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0218] Embodiment 24

[0219] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0220]

[0221]

[0222] The solid-liquid rocket engine grain is prepared by the following steps:

[0223] Dicyclopentadiene, sodium borohydride, beryllium, dimer fatty acid diisocyanate, triethanolamine, dibutyl phthalate, carbon black, phenylnaphthylamine and carbon powder are weighed according to the formula amount and mixed at a speed of 1000 rpm, the temperature is raised to 80° C., and then poured through a mold, and then the temperature is lowered to 10° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0224] Embodiment 25

[0225] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0226] Fuel: 67 parts of hydroxy-terminated polybutadiene

[0227] Strong reducing substance: 33 parts of sodium borohydride

[0228] The solid-liquid rocket engine grain is prepared by the following steps:

[0229] The terminal hydroxyl polybutadiene and sodium borohydride were weighed according to the formula amount and mixed at a rotation speed of 900 rpm, heated to 120° C., poured through a mold, and then cooled to 30° C. for solidification to obtain the solid-liquid rocket engine grain.

[0230] Embodiment 26

[0231] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0232]

[0233]

[0234] The solid-liquid rocket engine grain is prepared by the following steps:

[0235] The terminal hydroxyl polybutadiene, sodium borohydride, dimer fatty acid diisocyanate and triethanolamine are weighed according to the formula amount and mixed at a rotation speed of 900 rpm, heated to 120° C., poured through a mold, and then cooled to 30° C. for solidification to obtain the solid-liquid rocket engine powder column.

[0236] Embodiment 27

[0237] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0238] Fuel: 65 parts of hydroxy-terminated polybutadiene

[0239] Strong reducing substance: 33 parts of sodium borohydride

[0240] Burning rate catalyst: 2 parts of ferric oxide

[0241] The solid-liquid rocket engine grain is prepared by the following steps:

[0242] The terminal hydroxyl polybutadiene, sodium borohydride and ferric oxide are weighed according to the formula amount and mixed at a speed of 900 rpm, the temperature is raised to 120° C., and then poured through a mold, and then the temperature is lowered to 30° C. to solidify, thereby obtaining the solid-liquid rocket engine grain.

[0243] Embodiment 28

[0244] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0245]

[0248] The solid-liquid rocket engine grain is prepared by the following steps:

[0249] The terminal hydroxyl polybutadiene, sodium borohydride and lithium aluminum hydride are weighed according to the formula amount and mixed at a rotation speed of 900 rpm, the temperature is raised to 120° C., and then poured through a mold, and then the temperature is lowered to 30° C. to solidify, thereby obtaining the solid-liquid rocket engine grain.

[0250] Embodiment 29

[0251] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0252] Fuel: 60 parts of hydroxyl-terminated polybutadiene

[0253] Strong reducing substance: 39 parts of ammonia borane

[0254] Catalytic combustion aid: Palladium carbon (20% Pd) 1 part

[0255] The solid-liquid rocket engine grain is prepared by the following steps:

[0256] The terminal hydroxyl polybutadiene, ammonia borane and palladium carbon are weighed according to the formula amount and mixed at a rotation speed of 900 rpm, the temperature is raised to 120° C., and then poured through a mold, and then the temperature is lowered to 30° C. to solidify, thereby obtaining the solid-liquid rocket engine powder column.

[0257] Embodiment 30

[0258] This embodiment provides a self-igniting solid-liquid rocket engine grain. The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight:

[0259]

[0260] The solid-liquid rocket engine grain is prepared by the following steps:

[0261] The terminal hydroxyl polybutadiene, sodium borohydride, lithium, isophorone diisocyanate, triethanolamine, dibutyl phthalate, carbon black, phenylnaphthylamine and carbon powder are weighed according to the formula amount and mixed at a speed of 800 rpm, the temperature is raised to 120° C., and then poured through a mold, and then the temperature is lowered to 30° C. to solidify, so as to obtain the solid-liquid rocket engine grain.

[0262] Comparative Example 1

[0263] This comparative example provides a solid-liquid rocket engine powder column, which is different from Example 1 only in that no strong reducing substance is added, and the contents of other components and the preparation method are consistent with those of Example 1.

[0264] Comparative Example 2

[0265] This comparative example provides a solid-liquid rocket engine powder column, which is different from Example 1 only in that sodium borohydride is replaced with an equal mass of sodium thiosulfate, and the contents of other components and the preparation method are consistent with Example 1.

[0266] Comparative Example 3

[0267] This comparative example provides a solid-liquid rocket engine grain, which differs from Example 1 only in that sodium borohydride is replaced with an equal mass of sodium sulfite, and the contents of other components and the preparation method are consistent with those of Example 1.

[0268] Comparative Example 4

[0269] This comparative example provides a solid-liquid rocket engine propellant, which differs from Example 1 only in that sodium borohydride is replaced with an equal mass of carbon powder, and the contents of other components and the preparation method are consistent with those of Example 1.

[0270] Performance Testing

[0271] Test samples: the self-igniting solid-liquid rocket engine grains provided in Examples 1 to 30, and the solid-liquid rocket engine grains provided in Comparative Examples 1 to 4; the oxidant is 90% hydrogen peroxide.

[0272] The specific test results are shown in Table 1 (the data in Table 1 are calculated under a combustion chamber pressure of 1 MPa):

[0273] Table 1

[0274]

[0275]

[0276]

[0277] It can be seen from the test in Table 1 that the present invention provides a low ignition delay self-igniting powder column formula for hydrogen peroxide solid-liquid rocket engines, and the powder column formula includes common fuels, strong reducing substances, metal fuels and other additives for solid-liquid rocket engines. The powder column can achieve rapid ignition, multiple starts, thrust adjustability, long-term storage of fuel, large thrust, etc. The ignition delay of the self-igniting powder column is extremely low, and can be between a few milliseconds and tens of milliseconds depending on the ratio. And the performance of this self-igniting powder column is good, and it will hardly change the specific impulse and adiabatic flame temperature of the solid-liquid rocket engine. In addition, this self-igniting powder column also has the ability to ignite repeatedly.

[0278] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A self-igniting solid-liquid rocket engine grain, characterized in that: The raw materials for preparing the self-igniting solid-liquid rocket engine grain include, by weight: 50 to 90 parts of solid-liquid rocket engine fuel and 5 to 50 parts of strong reducing substances; The strong reducing substance is selected from any one of alkali metal borohydrides, alkali metal aluminum hydrides or boron nitrogen compounds, or a combination of at least two thereof.

2. The self-igniting solid-liquid rocket engine grain according to claim 1, characterized in that: The solid-liquid rocket engine fuel is selected from any one or a combination of at least two of polyethylene, hydroxyl-terminated polybutadiene, carboxyl-terminated polybutadiene, polymethyl methacrylate, paraffin, polysulfide rubber, coal powder or dicyclopentadiene, preferably any one or a combination of at least two of paraffin, polyethylene, dicyclopentadiene or hydroxyl-terminated polybutadiene; Preferably, the alkali metal borohydride is selected from any one of lithium borohydride, sodium borohydride or potassium borohydride, or a combination of at least two thereof; Preferably, the alkali metal aluminum hydride is lithium aluminum hydride; Preferably, the boron-nitrogen compound is selected from ammonia borane and / or ethylenediaminebisborane.

3. The self-igniting solid-liquid rocket engine grain according to claim 1, characterized in that: The raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of metal fuel; Preferably, the metal fuel is selected from any one of magnesium, aluminum, beryllium, lithium or zirconium, or a combination of at least two thereof.

4. The self-igniting solid-liquid rocket engine grain according to claim 1 or 2, characterized in that: The raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 10 parts of additives; Preferably, the additive is selected from any one or a combination of at least two of a curing agent, a cross-linking agent, a plasticizer, a combustion rate catalyst, a catalytic combustion aid, an anti-aging agent or a non-metallic powder; Preferably, the particle size of the additive is 10 to 240 μm.

5. The self-igniting solid-liquid rocket engine grain according to claim 4, characterized in that: The raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of a curing agent; Preferably, the curing agent is diisocyanate; Preferably, the diisocyanate is selected from any one or a combination of at least two of isophorone diisocyanate, toluene diisocyanate, 1,6-hexamethylene diisocyanate, dimer fatty acid diisocyanate or multifunctional isocyanate; Preferably, the raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of a cross-linking agent; Preferably, the cross-linking agent is selected from triethanolamine.

6. The self-igniting solid-liquid rocket engine grain according to claim 4, characterized in that: The raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of a plasticizer; Preferably, the plasticizer is selected from dibutyl phthalate; Preferably, the raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of a burning rate catalyst; Preferably, the burning rate catalyst is selected from any one or a combination of at least two of ferric oxide, chromite or carbon black; Preferably, the raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of a catalytic combustion aid; Preferably, the catalytic combustion improver is selected from palladium-carbon powder; Preferably, the raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of an anti-aging agent; Preferably, the anti-aging agent is selected from any one or a combination of at least two of diphenylamine, phenylnaphthylamine or magnesium oxide; Preferably, the raw materials for preparing the self-igniting solid-liquid rocket engine grain include 0.05 to 5 parts of non-metallic powder; Preferably, the non-metallic powder is selected from boron powder and / or carbon powder.

7. A method for preparing a self-igniting solid-liquid rocket engine grain according to any one of claims 1 to 6, characterized in that: The preparation method specifically comprises the following steps: The raw materials for preparing the self-igniting solid-liquid rocket engine grain are mixed, poured through a mold, cooled and solidified, and the self-igniting solid-liquid rocket engine grain is prepared.

8. The method for preparing a self-igniting solid-liquid rocket engine grain according to claim 7, characterized in that: The mixing temperature is 60-180°C, and the mixing speed is 500-2000rpm; Preferably, the pouring temperature is 60-160°C; Preferably, the cooling and solidification temperature is 0-50°C.

9. Use of the self-igniting solid-liquid rocket engine grain according to any one of claims 1 to 6 in the preparation of a self-igniting hydrogen peroxide-catalyzed solid-liquid rocket engine.

10. A hydrogen peroxide solid-liquid rocket engine, characterized in that: The hydrogen peroxide solid-liquid rocket engine comprises a hydrogen peroxide delivery system and an engine main body system, and the hydrogen peroxide solid-liquid rocket engine has no ignition device; Wherein, the engine main body system includes a combustion chamber, and the combustion chamber includes the self-igniting solid-liquid rocket engine charge according to any one of claims 1 to 6.

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