CN110981665B - Boron-containing fuel-rich propellant for platform combustion - Google Patents
Boron-containing fuel-rich propellant for platform combustion Download PDFInfo
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- CN110981665B CN110981665B CN201911346385.6A CN201911346385A CN110981665B CN 110981665 B CN110981665 B CN 110981665B CN 201911346385 A CN201911346385 A CN 201911346385A CN 110981665 B CN110981665 B CN 110981665B
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- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B33/00—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide
- C06B33/06—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide the material being an inorganic oxygen-halogen salt
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- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06D—MEANS FOR GENERATING SMOKE OR MIST; GAS-ATTACK COMPOSITIONS; GENERATION OF GAS FOR BLASTING OR PROPULSION (CHEMICAL PART)
- C06D5/00—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets
- C06D5/06—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more solids
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Abstract
The invention relates to a platform combustion boron-containing fuel-rich propellant, which effectively reduces the pressure index of the propellant through technical approaches of adjusting the type and the gradation of an oxidant, introducing a novel additive and the like, and solves the problems of unstable ballistic performance and reduced working reliability of an engine caused by large combustion speed change of the boron-containing propellant when the working pressure of a ramjet engine is changed sharply. The combustion speed of the propellant is basically kept unchanged when the working pressure of the ramjet engine is changed sharply on the premise of not influencing the comprehensive performance of the propellant, the platform combustion of the propellant is realized, the ballistic performance and the working reliability of the propellant are improved, an important technical support is provided for the application of the solid ramjet engine, and the solid ramjet engine has a wide application prospect.
Description
Technical Field
The invention belongs to the field of fuel-rich propellants for solid ramjet engines, and particularly relates to a boron-containing fuel-rich propellant for platform combustion.
Background
The solid rocket ramjet organically combines the advantages of the solid rocket engine and the air-breathing engine. Compared with a solid rocket engine, the energy of the propellant is greatly improved by using oxygen in the air as an oxidant, and the specific impulse is 2-4 times that of the solid rocket engine; compared with an air suction type engine, the internal profile compression air inlet principle is adopted, so that complex structures such as rotating parts are omitted, and the structure of the engine is simplified. Therefore, the missile taking the solid impact engine as power has the characteristics of small volume, light weight and long range, can realize the whole-course powered flight, and enhances the penetration resistance and the tail-end attack capability of the missile.
The development of ammunition weapons has been around the three goals of range, accuracy and power, and the requirements for range of conventional ammunition weapons have become more stringent and more prominent in modern war patterns. The long-range weapon can greatly enhance the firepower suppressing capability, increase the striking range and improve the survival capability in wartime. The ramjet is widely applied to missile and rocket weapons such as missiles, shells, rocket projectiles and the like as a range-extending power device. With the same charge quality, ramjets have a higher specific impulse. The ramjet is applied to the traditional rocket projectile weapon, and the range of the rocket projectile can be greatly improved.
The stroke is increased by adopting the ramjet technology, and compared with other stroke increasing technologies, the stroke increasing technology has the advantages of simple structural design, higher stroke increasing efficiency, higher terminal kinetic energy and the like, and has become the key point of military expert research of all countries. According to the current development situation of the stroke-increasing ammunition of the foreign ramjet, the range-increasing efficiency of the medium-diameter and large-diameter ammunition reaches 100 percent after the stroke-increasing technology is adopted, and the ramjet is applied to the traditional artillery and rocket weapon systems to meet the requirements of the current national defense situation.
The burning rate and pressure index are important indicators of the ballistic performance of a propellant, and the combustion process in which the pressure index is approximately 0 is called platform combustion. In order to ensure stable ballistic performance and reliable engine operation, the solid propellant used by general rocket artillery and extended-range artillery requires stable combustion in a wide pressure range, so that the solid propellant is required to have a low pressure index and maintain platform combustion.
However, the combustion speed of the boron-containing propellant adopted by the solid ramjet is greatly influenced by the change of working pressure, has a high pressure index, and is unstable in a complex working environment, so that the application of the boron-containing propellant is limited.
The pressure index of the boron-containing fuel-rich propellant is reduced, the propellant can be stably combusted in a wide working pressure range, the problem of the requirement of a future long-distance rocket projectile range-extending power device on a high-performance fuel-rich propellant is solved, and the application prospect is wide.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a boron-containing fuel-rich propellant, which effectively reduces the pressure index of the propellant without changing other performances of the propellant by adjusting the type and the gradation of an oxidizer, introducing a novel additive and other technical approaches. The problems that the combustion speed of the boron-containing propellant is changed greatly when the working pressure of the ramjet engine is changed sharply, so that the ballistic performance is unstable and the working reliability of the ramjet engine is reduced are solved. On the premise of not influencing the comprehensive performance of the propellant, the burning speed of the propellant is basically kept unchanged when the working pressure of the ramjet engine is changed sharply, the platform combustion of the propellant is realized, and the ballistic performance of the propellant and the working reliability of the engine are improved.
The invention relates to the following technical scheme that a boron-containing fuel-rich propellant comprises the following components in parts by mass: adhesive system: 17% -28%; oxidizing agent: 28% -37%; fuel: 30% -40%; auxiliary metal fuel: 3% -8%; performance modifier: 2% -5%; the oxidant is Ammonium Perchlorate (AP) and potassium perchlorate (KP); the oxidizing agent comprises a combination of class IV and one or more other classes of the following classes classified by particle size: one or a combination of type I (280-360 μm), type III (90-140 μm), type IV (5-15 μm), type V (0.5-2 μm). The IV oxidant is beneficial to reducing the pressure index of the propellant, the higher the content is, the lower the pressure index is relatively, but other performances of the propellant can be influenced, so that the dosage of the functional additives TEPE and MAPO is required to be increased; the performance regulator in the propellant comprises polyethylene glycol single-end ether (TEPE), the performance regulator polyethylene glycol single-end ether (TEPE) is a performance regulator with multiple functions, the patent ZL201611127349.7 discloses a synthesis method of the performance regulator, and experiments prove that the TEPE participates in reaction in the propellant, so that the bonding effect of IV oxidants and a propellant matrix can be improved, and the catalytic action of the combustion regulator can be delayed under the condition of not influencing the combustion performance.
Furthermore, the adhesive system comprises an adhesive, a curing agent and a plasticizer, wherein the adhesive is hydroxyl-terminated polybutadiene, the curing agent is one or a combination of Hexamethylene Diisocyanate (HDI), isophorone diisocyanate (IPDI) and Toluene Diisocyanate (TDI), the plasticizer is one or a combination of diisooctyl sebacate (DOS) and triethyl acetyl citrate (ATC), the content of the plasticizer is 1-5%, and if the content of the plasticizer exceeds 5.5%, the mechanical property of the propellant is reduced sharply, and the plasticizer has no use value.
Further, the fuel is boron and/or boron carbide, and the particle size is 1-10 μm.
Further, the auxiliary metal fuel is one or a combination of magnesium (Mg), aluminum (Al) and titanium (Ti). The auxiliary metal fuel is spherical and has a particle size of 1-30 μm.
Further, the performance regulator also comprises a mixture of a combustion regulator and one or more of lecithin, polyethylene glycol single-end ether (TEPE), tris [1- (2-methyl) aziridinyl ] phosphine oxide (MAPO), N-methyl-p-nitroaniline (MNA), N-diphenyl-p-phenylenediamine (DPPD), N-phenyl-2-naphthylamine (anti-aging agent D) and N-phenyl-N-cyclohexyl-p-phenylenediamine (anti-aging agent 4010).
Further, the combustion regulator is iron oxide (Fe)2O3) Ferroferric oxide (Fe)3O4) Vanadium pentoxide (V)2O5) One or a combination of the above components, wherein the content of the propellant is 1-2.8% of the total mass of the propellant.
Compared with the prior art, the invention has the beneficial effects that:
1. through technical approaches of adjusting the type and the gradation of the oxidant, introducing a novel additive and the like, the pressure index of the propellant is effectively reduced, and the platform combustion of the propellant is realized.
2. The problems that the combustion speed of the boron-containing propellant is changed greatly when the working pressure of the ramjet engine is changed sharply, so that the ballistic performance is unstable and the working reliability of the ramjet engine is reduced are solved. On the premise of not influencing the comprehensive performance of the propellant, the burning speed of the propellant is basically kept unchanged when the working pressure of the ramjet engine is changed sharply, and the ballistic performance of the propellant and the working reliability of the engine are improved.
Detailed Description
The following will explain details with reference to specific examples.
Example 1
A boron-containing fuel-rich propellant has a formula composition and content shown in Table 1.
Table 1: propellant formulations of example 1
The properties of the propellant formulations are shown in Table 2.
Table 2: TABLE 1 Properties of the propellants of the formulations
Example 2
A boron-containing fuel-rich propellant has a formulation composition and contents as shown in Table 3.
Table 3: propellant formulations of example 2
The properties of the propellant formulations are shown in Table 4.
Table 4: TABLE 3 Properties of the formulated propellants
Example 3
A boron-containing fuel-rich propellant has a formulation composition and contents as shown in Table 5.
Table 5: propellant formulations of example 3
The properties of the propellant formulations are shown in Table 6.
Table 6: EXAMPLE 3 Properties of the formulated propellants
Example 4
A boron-containing fuel-rich propellant has a formulation composition and contents as shown in Table 7.
Table 7: propellant formulation of example 4
The properties of the propellant formulations are shown in Table 8.
Table 8: EXAMPLE 4 Properties of the formulated propellants
Example 5
A boron-containing fuel-rich propellant having the formulation composition and content shown in table 9.
Table 9: propellant formulation of example 5
Table 10: EXAMPLE 5 Properties of the formulated propellants
In the above examples 1 to 5, the propellant pressure index is effectively reduced by means of adjusting the amount of the IV-type oxidizer and the amount of the combustion regulator, and the like, and the platform combustion is realized. The introduction of the novel performance regulator polyethylene glycol single-terminal ether (TEPE) improves the bonding effect of the IV-class oxidizing agent and the propellant matrix, delays the catalytic action of the combustion regulator under the condition of not influencing the combustion performance, and ensures that the mechanical performance of the propellant is not influenced.
Comparative examples
Comparative example 1
A formulation with 6% plasticizer was designed, the other ingredients and levels are shown in Table 11, and the properties of the resulting formulated propellant are shown in Table 12.
Table 11: propellant formulation of comparative example 1
Table 12: comparative example 1 Properties of the formulated propellant
As can be seen from the comparison of the test results of the example 1 and the comparative example 1, the formula with 6% of the plasticizer has extremely poor mechanical properties, cannot meet the use requirements of the ramjet engine, and has no use value.
Comparative example 2
The formulation composition and the contents of comparative example 2 are shown in Table 13, and the properties of the resulting propellant are shown in Table 14.
Table 13: propellant formulation of comparative example 2
Table 14: comparative example 2 Properties of the formulated propellant
As can be seen from the comparison of the test results of example 1 and comparative example 2, the pressure index is greatly improved by replacing class IV AP with ultrafine AP.
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (1)
1. The boron-containing fuel-rich propellant for platform combustion is characterized by comprising the following components in percentage by mass:
adhesive system: 17% -28%;
oxidizing agent: 28% -37%;
fuel: 30% -40%;
auxiliary metal fuel: 3% -8%;
performance modifier: 2% -5%;
the oxidant is one or a combination of ammonium perchlorate and potassium perchlorate;
the oxidant comprises the following combinations of the IV class and one or more other classes classified according to the particle size: 280-360 μm for type I, 90-140 μm for type III, 5-15 μm for type IV and 0.5-2 μm for type V;
the performance regulator comprises polyethylene glycol single-end ether;
the adhesive system comprises an adhesive, a curing agent, and a plasticizer; wherein the adhesive is hydroxyl-terminated polybutadiene; the curing agent is one or a combination of hexamethylene diisocyanate, isophorone diisocyanate and toluene diisocyanate; the plasticizer is one or a combination of diisooctyl sebacate and acetyl triethyl citrate, wherein the mass percentage of the plasticizer in the propellant is 1-5%;
the fuel is boron and/or boron carbide, and the particle size of the fuel is 1-10 mu m;
the auxiliary metal fuel is one or a combination of magnesium, aluminum and titanium, and is spherical, and the particle size of the auxiliary metal fuel is 1-30 mu m;
the performance modifier further comprises a mixture of a combustion modifier in combination with one or more of lecithin tris [1- (2-methyl) aziridinyl ] phosphine oxide, N-methyl p-nitroaniline, N-diphenyl-p-phenylenediamine, N-phenyl-2-naphthylamine, N-phenyl-N-cyclohexane-based-p-phenylenediamine;
the combustion regulator comprises one or more of ferric oxide, ferroferric oxide and vanadium pentoxide, and the mass percentage of the combustion regulator in the propellant is 1-2.8%.
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| CN111892466A (en) * | 2020-07-24 | 2020-11-06 | 北京理工大学 | High-density high-energy metal fuel |
| CN112898106B (en) * | 2021-01-18 | 2022-04-08 | 湖北航天化学技术研究所 | High-burning-rate propellant for platform combustion and preparation method thereof |
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| US8465607B1 (en) * | 2008-09-18 | 2013-06-18 | The United States Of America As Represented By The Secretary Of The Navy | Higher-performance solid-rocket propellants and methods of utilizing them |
| CN106750240B (en) * | 2016-12-09 | 2019-02-22 | 湖北航天化学技术研究所 | A kind of synthetic method of the single-ended ether series compound of polyethylene glycol |
| CN108727146A (en) * | 2018-06-13 | 2018-11-02 | 湖北航天化学技术研究所 | A kind of fuel-rich propellant of boracic based composite metal powder |
| CN109574773B (en) * | 2019-01-14 | 2021-01-22 | 湖北航天化学技术研究所 | Boron-containing fuel-rich propellant |
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Inventor after: Pang Aimin Inventor after: Xiao Jinwu Inventor after: Chen Tao Inventor after: Zhang Xianrui Inventor after: Liu Jianhong Inventor after: Huang Ling Inventor after: Li Jianhua Inventor after: Wang Yuanyuan Inventor after: Wang Rui Inventor before: Pang Aimin Inventor before: Xiao Jinwu Inventor before: Chen Tao Inventor before: Zhang Xianrui Inventor before: Liu Jianjiang Inventor before: Huang Ling Inventor before: Li Jianhua Inventor before: Wang Yuanyuan Inventor before: Wang Rui |
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