CN105130720B - A kind of high energy low burning rate temperature-sensitivity coefficient propellant - Google Patents

A kind of high energy low burning rate temperature-sensitivity coefficient propellant Download PDF

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CN105130720B
CN105130720B CN201410237990.0A CN201410237990A CN105130720B CN 105130720 B CN105130720 B CN 105130720B CN 201410237990 A CN201410237990 A CN 201410237990A CN 105130720 B CN105130720 B CN 105130720B
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propellant
burning rate
temperature
energy
oxidant
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CN105130720A (en
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徐海元
唐根
周立
罗传志
倪凤翔
冯勇
吴芳
包玺
李伟
徐星星
王伟
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Hubei Institute of Aerospace Chemical Technology
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Hubei Institute of Aerospace Chemical Technology
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Abstract

A kind of high energy low burning rate temperature-sensitivity coefficient propellant, includes following component：Adhesive 12% ~ 15%；Plasticizer 10% ~ 13%；Oxidant 15% ~ 18%；The explosive 38% ~ 50% containing energy；Metal fuel 10% ~ 18%；Small component：1.5%~2.0%.Wherein adhesive is glycidyl azide polymer；Plasticizer is triethylene glycol dinitrate or the diaza alkane of 2,4 dinitro 2,4；Oxidant is ammonium perchlorate；The explosive containing energy is HMX;Metal fuel is aluminium powder.The present invention has propellant energy higher（Standard actual measurement specific impulse is more than 2450N.s/kg）, temperature sensitivity of burning rate is low（Temperature sensitivity of burning rate is not more than 0.15%K‑1）The characteristics of, suitable for requiring that far firing range, penetration ability are strong, reliability is high and the tactical missile engine of precise guidance.

Description

A kind of high energy low burning rate temperature-sensitivity coefficient propellant
Technical field
It is applied to require that far firing range, penetration ability are strong, reliability is high and the tactics of precise guidance are led the present invention relates to a kind of The GAP high energy low burning rate temperature-sensitivity coefficient propellants of bullet.
Background technology
Temperature sensitivity of burning rate is one of very important performance indications of solid propellant, characterizes the change of propellant initial temperature Influence to burn rate or combustion chamber pressure.Under the conditions of certain pressure intensity, propellant temperature change 1K is drawn in the range of a certain initial temperature The burn rate relative variation risen, its mathematic(al) representation are：
The progress of military technology proposes higher requirement to the performance of missile armament, informatized service there is an urgent need to The long distance precision strike capacity of tactical missile weapon is improved, to give full play to the fighting efficiency of high-tech weapons.Solid propellant propulsion Power source of the agent as various missile armaments and spacecraft rocket engine and KKV etc., its distinctive energy Amount, combustibility decide the important war skill index such as range, precision, penetration ability and the maneuverability of missile armament, are high property The technical foundation of energy missile weapon system development.
The development that energetic and high workload pressure have turned into following advanced tactical missile weapon solid propellant rocket becomes Gesture.There is the high-energy solid propellant of low temperature sensitivity coefficient in a wide range, due to following characteristics, following work can be met Technical requirements of the war condition to advanced tactical missile weapon：
（1）The burn rate of low temperature sensitivity coefficient solid propellant varies less in certain temperature range, solid-rocket hair Motivation burning intraventricular pressure changes very little by force, so as to which the jet pipe size tolerance requirements to engine are extremely low；Simultaneously by temperature change and The influence of pressure oscillation is small, is advantageous to reduce missile trajectory deviation, improves the fire accuracy and closeness of guided missile；
（2）Solid-rocket and missile propulsive plant and powder charge design adjustment to high energy high workload pressure is extremely advantageous；Favorably In improving engine operating pressure, scope and maneuverability are improved；
（3）When solid propellant rocket burns, balance pressure oscillation is small, so as to make combustion chamber wall thickness reduction, engine Case weight mitigates, and maximum can obtain the specific impulse gain more than 5%.
To ensure the work of the normal table of missile propulsive plant, tactical weapon model typically requires the burn rate of used propellant Temperature-sensitivity coefficient should be less than 0.20%K-1。
Develop with the technology of tactical weapon model, it is imperative to improve the energy level of propellant, and this is high energy propulsion Application of the agent in tactical weapon proposes powerful demand pull.Although the high-energy propellant energy level developed at present Height, but temperature sensitivity of burning rate is typically in 0.35%K-1More than, it is impossible to meet tactical weapon model complex environment temperature It is required that.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of high energy low burning rate temperature-sensitivity coefficient propellant, particularly Suitable for requiring that far firing range, penetration ability are strong, reliability is high and the GAP high energy low burning rate temperature of the tactical missile of precise guidance is quick Feel coefficient propellant.
The technical solution adopted by the present invention includes following component and content（Mass percent %）：
Adhesive：12%~15%；
Plasticizer：10%~13%；
Oxidant：15%~18%
The explosive containing energy：38%~50%
Metal fuel：10%~18%
Small component：1.5%~2.0%（Wherein curing agent 0.8% ~ 1.3%：Curing catalysts 0.1%, age resistor 0.2% ~ 0.4%, NPBA 0.2% ~ 0.4%）.
Adhesive of the present invention is glycidyl azide polymer（GAP）.
Plasticizer of the present invention is triethylene glycol dinitrate（TEGDN）Or 2,4- dinitro -2,4- diazas Alkane（DNDA）.
Oxidant of the present invention is ammonium perchlorate（AP）.
The explosive of the present invention containing energy is HMX（HMX）.
Metal fuel of the present invention is aluminium powder（Al）.
The curing agent of small component of the present invention is six methine polyisocyanates（LM-100）Or and toluene diisocynate Ester（TDI）Combination；Curing catalysts are triphenyl bismuth（TPB）；Age resistor is N- methyl paranitroanilines（MNA）；Neutrality is poly- Compound bonding agent is BAG, BAG-78C.It is mainly used in adjusting the mechanical property of propellant, to Propellant warp and flammability It can influence little.
The preparation technology of the present invention includes the following aspects：
Mixed using vertical or flat mixer, it is molten that adhesive and plasticizer are made into mixing according to proportioning in advance Liquid, the components such as mixed solution, small component, metal fuel, oxidant, the explosive containing energy are then sequentially added into mixer, mixing one The uniform medicine slurry of component is formed after fixing time, motor grain is realized using vacuum pouring system and tests the production of test specimen.
By the present invention in that and decomposable process temperature-resistant energetic binder high with energy level, containing can aoxidize The technological means such as agent, energetic plasticiser improve the energy level of propellant, while reduce the temperature sensitivity of burning rate of propellant, So as to form a high energy low burning rate temperature-sensitivity coefficient propellant formulation.So as to solve common biradical and HTPB propellant energy The problem of low and high-energy propellant temperature sensitivity of burning rate of level is high.The present invention compared with prior art the advantages of it is as follows：
（1）Energy level is high：By introduce GAP, TEGDN, DNDA, HMX etc. containing can material, it is real under propellant 6.86MPa Survey specific impulse and be more than 2450N.s/kg.
（2）Temperature sensitivity of burning rate is low：By using the temperature-resistant material of decomposable process such as HMX, DNDA etc., And formula is rationally designed, propellant burning rate temperature-sensitivity coefficient is not more than 0.15% K-1。
High energy low burning rate temperature-sensitivity coefficient propellant has higher energy level, low temperature sensitivity of burning rate, Range, penetration ability, reliability and the precision strike capability of guided missile can be significantly improved after being applied in weapon model.
Embodiment
With reference to embodiment, the present invention is described in detail.
Embodiment 1
（1）Propellant forms
Component GAP TEGDN AP HMX Al
Content (%wt) 13.5 10 15 50 10
Component TPB MNA BAG-78C LM-100 TDI
Content (%wt) 0.1 0.3 0.3 0.5 0.3
（2）The performance of propellant
Survey specific impulse：2451N.s/kg（6.86MPa, survey specific efficiency 0.944）
Density：1.76g/cm3
Temperature sensitivity of burning rate：0.13% K-1（-30℃~40℃）.
Embodiment 2
（1）Propellant forms
Component GAP TEGDN AP HMX Al
Content (%wt) 12 12 18 38 18
Component TPB MNA BAG-78C LM-100
Content (%wt) 0.1 0.2 0.4 1.3
（2）The performance of propellant
Survey specific impulse：2480N.s/kg（6.86MPa, survey specific efficiency 0.938）
Density：1.79g/cm3
Temperature sensitivity of burning rate：0.15% K-1（-30℃~40℃）.
Embodiment 3
（1）Propellant forms
Component GAP TEGDN AP HMX Al
Content (%wt) 13 13 16 42.3 14
Component TPB MNA BAG-78C LM-100
Content (%wt) 0.1 0.3 0.4 0.9
（2）The performance of propellant
Survey specific impulse：2474N.s/kg（6.86MPa, survey specific efficiency 0.940）
Density：1.77g/cm3
Temperature sensitivity of burning rate：0.14 %K-1（-30℃~40℃）.
Embodiment 4
（1）Propellant forms
Component GAP TEGDN AP HMX Al
Content (%wt) 12 12 17 45 12
Component TPB MNA BAG-78C LM-100
Content (%wt) 0.1 0.4 0.2 1.3
（2）The performance of propellant
Estimate actual measurement specific impulse：2466N.s/kg（6.86MPa, calculated according to specific efficiency 0.940）
Density：1.77g/cm3
Temperature sensitivity of burning rate：0.15 %K-1（-30℃~40℃）.
Embodiment 5
（1）Propellant forms
Component GAP TEGDN AP HMX Al
Content (%wt) 15 11 17 39.5 16
Component TPB MNA BAG-78C LM-100 TDI
Content (%wt) 0.1 0.3 0.3 0.5 0.3
（2）The performance of propellant
Estimate actual measurement specific impulse：2477N.s/kg（6.86MPa, calculated according to specific efficiency 0.938）
Density：1.78g/cm3
Temperature sensitivity of burning rate：0.15% K-1（-30℃~40℃）.
Embodiment 6
（1）Propellant forms
Component GAP DNDA AP HMX Al
Content (%wt) 12.5 12.5 18 38 17.5
Component TPB MNA BAG-78C LM-100 TDI
Content (%wt) 0.1 0.3 0.3 0.5 0.3
（2）The performance of propellant
Estimate actual measurement specific impulse：2475N.s/kg（6.86MPa, calculated according to specific efficiency 0.938）
Density：1.78g/cm3
Temperature sensitivity of burning rate：0.13 %K-1（-30℃~40℃）.
Embodiment 7
（1）Propellant forms
Component GAP DNDA AP HMX Al
Content (%wt) 12 12 17 42 15
Component TPB MNA BAG-78C LM-100
Content (%wt) 0.1 0.3 0.3 1.3
（2）The performance of propellant
Estimate actual measurement specific impulse：2470N.s/kg（6.86MPa, calculated according to specific efficiency 0.940）
Density：1.77g/cm3
Temperature sensitivity of burning rate：0.12 %K-1（-30℃~40℃）.
Embodiment 8
（1）Propellant forms
Component GAP DNDA AP HMX Al
Content (%wt) 14 10 15 48 11
Component TPB MNA BAG-78C LM-100
Content (%wt) 0.1 0.3 0.3 1.3
（2）The performance of propellant
Estimate actual measurement specific impulse：2451N.s/kg（6.86MPa, calculated according to specific efficiency 0.941）
Density：1.75g/cm3
Temperature sensitivity of burning rate：0.10 %K-1（-30℃~40℃）.
The method of testing of propellant formulation properties of the present invention：
Specific impulse：Made energy calculation according to energy characteristics theoretical calculation software RAMJ, select representative formula to carry out engine Actual measurement checking, calculates actual measurement specific efficiency, the test run specific impulse of other formulas is then estimated by specific efficiency.
Density：Relative density method, propellant is made to the medicinal strip of about standard specification, accurate weighing promotes at a temperature of 20 DEG C Medicinal strip, is then put into normal fluid by the quality of agent, measures the volume of medicinal strip, so as to calculate the density of medicinal strip.
Temperature sensitivity of burning rate：Underwater acoustic-emission, pressure be 8MPa under test medicinal strip -30 DEG C, 0 DEG C, 20 DEG C, Burn rate at 40 DEG C, under each temperature spot test be no less than 4 medicinal strips, according to temperature sensitivity of burning rate accounting equation, pass through Index return method obtains temperature-sensitivity coefficient.

Claims (1)

1. a kind of high energy low burning rate temperature-sensitivity coefficient propellant, it is characterised in that include following masses percentage % component：
Adhesive：12%~15%；
Plasticizer：10%~13%；
Oxidant：15%~18%；
The explosive containing energy：38%~50%；
Metal fuel：10%~18%；
Small component：1.5%~2.0%；
The plasticizer is 2,4- dinitro -2,4- diaza alkane；
The group is divided into curing agent, curing catalysts triphenyl bismuth, age resistor N- methyl paranitroanilines, neutral polymer key Mixture；
The curing agent is six methine polyisocyanates or the combination with toluene di-isocyanate(TDI)；
The proportioning of the small component is：Curing agent 0.8% ~ 1.3%：Curing catalysts 0.1%, age resistor 0.2% ~ 0.4%, neutrality are poly- Compound bonding agent 0.2% ~ 0.4%；
Described adhesive is glycidyl azide polymer；
The oxidant is ammonium perchlorate；
The explosive containing energy is HMX；
The metal fuel is aluminium powder.
CN201410237990.0A 2014-05-30 2014-05-30 A kind of high energy low burning rate temperature-sensitivity coefficient propellant Active CN105130720B (en)

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