Solid propellant containing liquid metal

Abstract

The invention relates to the technical field of solid propellants, and particularly discloses a solid propellant containing liquid metal, which comprises the following components by mass: 10%-20% of an adhesive system; 10%-50% of an oxidizing agent; 20-70% of a cooling agent; 2%-8% of liquid metal; 0%-2% of a combustion regulator; and 0.5%-2% of a performance regulator. The solid propellant containing the liquid metal is obtained by bonding and loading the liquid metal particles on a three-dimensional network structure of an adhesive system, the liquid metal particles with metal embrittlement ability are released after the propellant is combusted, and a new way is expected to be provided for the solid propellant integrating a propelling function and a damage function.

Description

Technical Field

[0001] The present invention relates to the technical field of solid propellants, and in particular to a solid propellant containing liquid metal. Background Art

[0002] Solid propellant is a type of energetic composite material composed of fillers (oxidizers, energetic materials, etc.) as dispersed phases and polymer adhesives as continuous phases. In working state, solid propellant generates a large amount of high-temperature, high-pressure gas through combustion and provides power for the system. It has the characteristics of high working reliability and excellent quality ratio, and is widely used as the power source for missile main engines and auxiliary systems such as servo and roll control. With the continuous increase in the demand for the development of modern warfare, solid propellants with a single propulsion function can no longer meet the functional requirements of advanced weapons and equipment.

[0003] The integration of propulsion and damage is an important area for the expansion of solid propellant functions. Currently, the unburned residual propellant in the engine is mainly controlled to detonate in order to fully exert the missile damage effect. To achieve the above purpose, it is necessary to accurately control the propellant combustion, detonation and other processes, which places extremely high demands on the solid propellant performance and engine design. At present, there is no mature technology to achieve this capability. Therefore, it is urgent to find a new technical approach to give solid propellants the new function of efficient damage and expand the application range of solid propellants. Summary of the invention

[0004] In order to realize the integrated propulsion and damage technology of solid propellant, the present invention discloses a solid propellant containing liquid metal. By typing liquid metal particles into the binder network structure, a low combustion temperature solid propellant containing liquid metal is obtained. When the solid propellant is working, the lower combustion temperature is not enough to completely oxidize the liquid metal, so that the liquid metal with metal embrittlement function is released in the form of products, and then the function of efficient damage is exerted, causing the weapon system to be damaged, and a solid propellant integrating propulsion function and damage function is obtained.

[0005] To achieve the purpose of the present invention, the present invention provides the following technical solutions:

[0006] The invention provides a solid propellant containing liquid metal. The liquid metal is dispersed in a binder system to obtain the solid propellant containing liquid metal and having a low combustion temperature.

[0007] In some optional embodiments, the liquid metal includes at least one of gallium, gallium-indium alloy, gallium-indium-tin alloy, and mercury.

[0008] In some optional embodiments, the particle size of the liquid metal particles ranges from 0.5 μm to 300 μm.

[0009] In some optional embodiments, the combustion temperature of the low combustion temperature solid propellant is lower than 900°C.

[0010] In some optional embodiments, the following components are included in weight percentage:

[0011] Adhesive system: 10% to 20%;

[0012] Oxidant: 10% to 50%;

[0013] Cooling agent: 20% to 70%;

[0014] Liquid metal: 2% to 8%;

[0015] Combustion regulator: 0%~2%;

[0016] Performance regulator: 0.5%~2%.

[0017] In some optional embodiments, the adhesive system includes an adhesive, a plasticizer and a curing agent.

[0018] In some optional embodiments, the adhesive in the adhesive system is selected from a combination of one or more of terminal hydroxyl polybutadiene, polyterminal hydroxyl ethylene oxide-tetrahydrofuran copolyether, polyethylene glycol and 3,3-diazidemethyl-oxacyclobutane-tetrahydrofuran copolyether; the plasticizer in the adhesive system is selected from a combination of one or more of dioctyl sebacate, dibutyl phthalate, butanetriol trinitrate and trimethylolethane trinitrate, and the curing agent in the adhesive system is one or more of isophorone diisocyanate and toluene diisocyanate.

[0019] In some optional embodiments, the cooling agent includes at least one of ammonium nitrate, dihydroxyglyoxime, ammonium sulfate, and ammonium oxalate.

[0020] The present invention has the following beneficial effects:

[0021] The present invention provides a solid propellant containing liquid metal. By bonding liquid metal particles to a three-dimensional network structure loaded in a binder system, a low-ignition-temperature solid propellant containing liquid metal is obtained, which is expected to provide a new approach for solid propellants that integrate propulsion and destructive functions. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the present invention are clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0023] Example 1

[0024] A solid propellant containing liquid metal, the formula composition of which is shown in Table 1, and the performance is shown in Table 2.

[0025] Table 1 Composition of solid propellant containing liquid metal

[0026] Recipe composition content / % Adhesive system PET, TEGDN, TDI 17.5 Oxidants AP 39.5 Cooling agent AS 38.0 Liquid Metal Ga 2.0 Combustion regulator <![CDATA[Fe2O3]]> 2.0 Performance Conditioner MAPO, MNA 1.0

[0027] The raw materials were prepared according to the composition of the solid propellant containing liquid metal shown in Table 1, and then added to the mixer in order and mixed evenly. After vacuum casting and solidification, the low combustion temperature solid propellant containing liquid metal was obtained. The performance of the prepared solid propellant was tested, and the test results are shown in Table 2. After the propellant is burned, 1.7wt% of liquid metal particles with metal embrittlement ability can be released.

[0028] Table 2 shows the properties of the propellant obtained from the formula in Table 1

[0029] project performance Combustion temperature (6.86MPa), ℃ 890 <![CDATA[Density, g / cm 3 > 1.611 Liquid metal content in the product, % 1.7 <![CDATA[Maximum tensile strength σ m (at 20 °C), MPa]]> 1.18 <![CDATA[Maximum elongation ε m (20 °C),%]]> 27.7

[0030] Example 2

[0031] A solid propellant containing liquid metal, the formula composition of which is shown in Table 3, and the performance is shown in Table 4. 75 In 25 (gallium-indium alloy), the propellant can release 4.2wt% of liquid metal particles with metal embrittlement ability after combustion.

[0032] Table 3 Composition of solid propellant containing liquid metal

[0033]

[0034]

[0035] Table 4 shows the properties of the propellant obtained from the formula in Table 3

[0036] project performance Combustion temperature (6.86MPa), ℃ 900 <![CDATA[Density, g / cm 3 > 1.531 Liquid metal content in the product, % 4.2 <![CDATA[Maximum tensile strength σ m (at 20 °C), MPa]]> 1.24 <![CDATA[Maximum elongation ε m (at 20 °C), %]]> 34.1

[0037] Example 3

[0038] A solid propellant containing liquid metal, the formula composition of which is shown in Table 5, and the performance is shown in Table 6. Using GaInSn (gallium indium tin alloy), the propellant can release 2.6wt% of liquid metal particles with metal embrittlement ability after combustion.

[0039] Table 5 Composition of solid propellant containing liquid metal

[0040]

[0041]

[0042] Table 6 shows the properties of the propellant obtained from the formulation in Table 5

[0043] project performance Combustion temperature (6.86MPa), ℃ 880 <![CDATA[Density, g / cm 3 > 1.562 Liquid metal content in the product, % 2.6 <![CDATA[Maximum tensile strength σ m (at 20 °C), MPa]]> 1.08 <![CDATA[Maximum elongation ε m (at 20 °C),%]]> 30.2

[0044] Example 4

[0045] A solid propellant containing liquid metal, the formula composition of which is shown in Table 7, and the performance is shown in Table 8. Two liquid metal particles of Ga and GaInSn are used, and after the propellant is burned, 2.7wt% of liquid metal particles with metal embrittlement ability can be released.

[0046] Table 7 Composition of solid propellant containing liquid metal

[0047]

[0048]

[0049] Table 8 shows the properties of the propellant obtained from the formulation in Table 7

[0050] project performance Combustion temperature (6.86MPa), ℃ 876 <![CDATA[Density, g / cm 3 > 1.590 Liquid metal content in the product, % 2.7 <![CDATA[Maximum tensile strength σ m (at 20 °C), MPa]]> 1.31 <![CDATA[Maximum elongation ε m (at 20°C), %]]> 32.0

[0051] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A solid propellant containing liquid metal, characterized in that: The low combustion temperature solid propellant containing liquid metal is obtained by dispersing liquid metal in a binder system.

2. The solid propellant containing liquid metal according to claim 1, characterized in that: The liquid metal includes at least one of gallium, gallium-indium alloy, gallium-indium-tin alloy and mercury.

3. The solid propellant containing liquid metal according to claim 2, characterized in that: The particle size of the liquid metal particles ranges from 0.5 μm to 300 μm.

4. The solid propellant containing liquid metal according to claim 1, characterized in that: The combustion temperature of the low combustion temperature solid propellant is lower than 900°C.

5. The solid propellant containing liquid metal according to any one of claims 1 to 4, characterized in that: Contains the following components by mass percentage: Adhesive system: 10% to 20%; Oxidant: 10% to 50%; Cooling agent: 20% to 70%; Liquid metal: 2% to 8%; Combustion regulator: 0%~2%; Performance regulator: 0.5%~2%.

6. The solid propellant containing liquid metal according to claim 5, characterized in that: The adhesive system comprises an adhesive, a plasticizer and a curing agent.

7. The solid propellant containing liquid metal according to claim 6, characterized in that: The adhesive in the adhesive system is selected from a combination of one or more of terminal hydroxyl polybutadiene, polyterminal hydroxyl ethylene oxide-tetrahydrofuran copolyether, polyethylene glycol and 3,3-diazidemethyl-oxetane-tetrahydrofuran copolyether; the plasticizer in the adhesive system is selected from a combination of one or more of dioctyl sebacate, dibutyl phthalate, butanetriol trinitrate and trimethylolethane trinitrate; the curing agent in the adhesive system is one or more of isophorone diisocyanate and toluene diisocyanate.

8. The solid propellant containing liquid metal according to claim 5, characterized in that: The cooling agent includes at least one of ammonium nitrate, dihydroxyglyoxime, ammonium sulfate and ammonium oxalate.

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