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1.
    
Nitramines are known to produce lower burning rates and higher pressure exponent (η) values. Studies on the burning rate and combustion behavior of advanced high‐energy NG/PE‐PCP/HMX/AP/Al based solid propellant processed by slurry cast route were carried out using varying percentages of HMX and AP. It was observed that propellant compositions containing only AP and Al loaded (total solids 75 %) in NG plasticized PE‐PCP binder produce comparatively lower pressure exponent (η) values similar to AP‐Al filled HTPB based composite propellants. However, energetic propellants containing high level of nitramine (40–60 %) produce high pressure exponent (0.8–0.9) values in the same pressure range. Incorporation of fine particle size AP (ca. 6 μm) and change in its concentration in the propellant composition reduces η value marginally and influences the burning rate. However, such compositions have higher friction sensitivity.  相似文献   

2.
    
Different propellant compositions were prepared by incorporating nano‐sized cobalt oxide from 0.25 % to 1 % in HTPB/AP/Al‐based composite propellant formulations with 86 % solid loading. The effects on viscosity build‐up, thermal, mechanical and ballistic properties were studied. The findings revealed that by increasing the percentage of nano‐Co3O4 in the composition, the end of mix viscosity, the modulus and the tensile strength increased, whereas the elongation decreased accordingly. The thermal property data envisaged a reduction in the decomposition temperature of ammonium perchlorate (AP) as well as formulations based on AP. The ballistic property data revealed an enhanced burning rate from 6.11 mm s−1 (reference composition) to 8.99 mm s−1 at 6.86 MPa and a marginal increase in pressure exponent from 0.35 (reference composition) to 0.42 with 1 % nano‐cobalt oxide.  相似文献   

3.
    
High burning rate composite propellants are achieved by incorporation of fine particles of oxidizer, transition metal oxides, and liquid ballistic modifiers. However, they pose processing problems, inertness to the composition and migration related issues. To overcome such problems, an attempt was made to incorporate ferrocenyl grafted HTPB as a burning rate modifier by partly replacing HTPB from 10 % to 50 % using TDI/ IPDI bicurative system and to study their processability in terms of viscosity, mechanical, thermal, sensitivity, and ballistic properties. The data on viscosity reveal that there is a marginal enhancement in end of mix viscosity as percentage of ferrocenyl grafted HTPB increases. The mechanical data reveal that tensile strength and elastic modulus increases, whereas percentage elongation decreases compared to base composition. The results on thermal properties infer that, as the percentage of ferrocenyl grafted HTPB increases, onset decomposition temperature decreases. The impact and friction sensitivity data also envisage that sensitivity increases in comparison to base composition. The data on ballistic properties revealed that there is ca. 53 % increase in burning rate, while decrease in “n” value from 0.39 to 0.2 was obtained compared to base composition.  相似文献   

4.
研究了硼氢化合物 B1 2 H1 2 [N(C2 H5 ) 4] 2 对 NEPE推进剂燃烧性能的影响 ,采用 DSC分析了 B1 2 H1 2 [N(C2 H5 ) 4] 2 与 NEPE推进剂主要组分硝酸酯的相容性以及对推进剂固化反应的催化作用和对高氯酸铵、硝胺常压热分解的催化作用 ,并利用恒压静态燃速仪测试了推进剂在 4~ 1 1 MPa的燃烧速度和燃速压力指数  相似文献   

5.
纳米氧化铅为燃烧催化剂的应用研究   总被引:20,自引:3,他引:20  
运用红外光谱法研究纳米氧化铅对 HMX固相热分解的影响 ,通过静态靶线法燃速测试仪考察纳米氧化铅在推进剂中的实际应用效果。红外谱峰的变化表明 :氧化铅对 HMX的固相热分解直接起催化作用。通过纳米氧化铅在 NEPE推进剂中的实际应用效果表明 :纳米氧化铅可有效的降低 NEPE推进剂的燃速压力指数。  相似文献   

6.
镁铝中能贫氧推进剂燃烧性能初探   总被引:3,自引:0,他引:3  
系统地研究了镁铝中能贫氧推进剂的燃烧特性,并对该类推进剂的配方进行了初步的优化设计。研究发现,高氯酸铵含量和镁铝比对贫氧推进剂燃烧特性有显著影响。增加AP含量和金属添加剂中镁粉含量均有助于提高推进剂的燃速和拓宽其低压可燃极限。另外,采用超细组分或添加燃速催化剂也是提高推进剂燃速和拓宽低压可燃极限的重要途径。  相似文献   

7.
潘文达  冯伟 《火炸药》1996,19(3):36-40
利用俄国Flame数据库中若干个具有100℃(初温)燃速值的双基系推进剂配方及其它数据资料,分析了初温为100℃时双基及改性双基推进剂的燃烧特性及组分对燃烧特性的影响。  相似文献   

8.
    
By means of DNDA nitramine fractions in the formulation, it is hoped to produce gun propellants that have an almost temperature‐independent burning behavior. The reason for this behavior is not clear yet. In the last years, it has become known that pressure oscillations may occur in the hole channels of gun propellant grains that may lead to a modification of the burning. To analyze the impact of such oscillations on the burning behavior of DNDA powders, tests with two different DNDA powders were performed in a closed vessel. In both cases, it could be demonstrated that the oscillations have a determining influence on the temperature behavior.  相似文献   

9.
    
The initial viscosities of propellants based on yellow iron oxide and red iron oxide were similar. Furthermore, it was confirmed that the thermal decomposition rate of the material to which yellow iron oxide was added was higher than that of the material to which red iron oxide was added; in particular, the pressure index at high pressure was low. From analyzing the combustion properties of the actual test motor, it was concluded that erosion and combustion mainly occur in the initial stage of operation of the rocket motor, and are mitigated due to the low initial pressure in the propellant containing yellow iron oxide. The mechanical properties of the propellant with yellow iron oxide were slightly better compared to those of the propellants with red iron oxide. The analysis revealed that the crystallinity, volatility, thermal decomposition, and mechanical properties of yellow iron oxide were unchanged with natural aging for 10 years. Thus, yellow iron oxide can exhibit the same performance even after prolonged aging for 10 years when applied in a rocket motor.  相似文献   

10.
    
In a systematic study to compare the effects of the values of burning rate and pressure exponent in RDX‐AP based composite propellant, various compositions with varying percentages of zirconium carbide (ZrC) and zirconium silicate (ZrSiO4) were formulated to select a suitable candidate. Various rocket parameters of each formulation were theoretically predicted by the NASA CEC‐71 program and the burning rate was evaluated in pressure range of 3–11 MPa. In addition, density, sensitivity, and thermal properties of compositions having maximum effects on pressure exponent’s values were also evaluated. It was concluded that ZrSiO4 enhances the pressure exponent “n” value substantially, whereas ZrC doesn’t have significant effects on it as compared to base composition and also provides higher density values of composite propellant formulated.  相似文献   

11.
It has been well established that sustained combustion in ammonium nitrate water‐based emulsions (AWEs) can only occur if the ambient pressure is held above some threshold value, usually referred to as the ‘minimum burning pressure’ (MBP). For the commercial explosives industry, a good knowledge of the MBP for particular AWE formulations is essential to estimate safe operating pressures for the associated manufacturing and handling processes. In these processes, AWE products are most often pumped in closed systems and at elevated temperature. While previous studies have established that the MBP can depend critically on major ingredients, its dependence on physical characteristics such as temperature and viscosity had never been investigated. Moreover, the consequences of alterations in measurement methodologies on the resulting measured MBP values had not been studied.  相似文献   

12.
It is well known that water‐based commercial explosives locally ignited in closed vessels do not undergo self‐sustained combustion when the pressure is lower than some threshold value. The latter is usually referred to as the Minimum Burning Pressure (MBP) of the explosive and is now being used by some manufacturers as a basis of safety for many associated manufacture, transport, and handling processes. In the present work, both an apparatus based on hot‐wire ignition and an associated methodology were developed to measure the MBP of water‐based explosives. Typical results for various emulsion and water‐gel explosives are also reported and discussed. It is also shown that the technique could be used to characterize very insensitive explosive substances normally used as explosive precursors.  相似文献   

13.
Emulsions based on ammonium nitrate (AN) and water locally ignited by a heat source do not undergo sustained combustion when the pressure is lower than some threshold value usually called the Minimum Burning Pressure (MBP). This concept is now being used by some manufacturers as a basis of safety. However, before a technique to reliably measure MBP values can be designed, one must have a better understanding of the ignition mechanism. Clearly, this is required to avoid under ignitions which could lead to the erroneous interpretation of failures to ignite as failures to propagate. In the present work, facilities to prepare and characterize emulsions were implemented at the Canadian Explosives Research Laboratory. A calibrated hot‐wire ignition system operated in a high‐pressure vessel was also built. The system was used to study the ignition characteristics of five emulsion formulations as a function of pressure and ignition source current. It was found that these mixtures exhibit complicated pre‐ignition stages and that the appearance of endotherms when the pressure is lowered below some threshold value correlates with the MBP. Thermal conductivity measurements using this hot‐wire system are also reported.  相似文献   

14.
聚乙烯压力管材的生产过程控制   总被引:2,自引:0,他引:2  
聚乙烯压力管材的生产过程中,原料的选择和预处理、管材挤出设备和工艺参数的选择以及生产中实际问题的解决是三个重要方面,对平衡管材的质量和经济效益具有重要意义。本文根据我公司的实际生产情况对这些问题进行探讨。  相似文献   

15.
    
Fine and ultra‐fine powders are actively studied in pyrotechnics, explosives and propellants. The important questions are how to produce a powder with specified characteristics and how to use the powder produced.  相似文献   

16.
    
The thermal decomposition behavior and combustion characteristics of mixtures of ammonium dinitramide (ADN) with additives were studied. Micrometer‐sized particles of Al, Fe2O3, TiO2, NiO, Cu(OH)NO3, copper, CuO, and nanometer‐sized particles of aluminum (Alex) and CuO (nano‐CuO) were employed. The thermal decomposition was measured by TG‐DTA and DSC. The copper compounds and NiO lowered the onset temperature of ADN decomposition. The heat value of ADN with Alex was larger than that of pure ADN in closed conditions. The burning rates and temperature of the pure ADN and ADN/additives mixtures were measured. CuO and NiO enhance the burning rate, particularly at pressures lower than 1 MPa, because of the catalyzed decomposition in the condensed phase; the other additives lower the burning rate. This negative effect on the burning rate is explained based on the surface temperature measurements by a physicochemical mechanism, which involves a chemical reaction, a phase change of the ammonium nitrate, and the blown‐off droplets of the condensed phase.  相似文献   

17.
高能硝胺发射药的膛内基本燃烧特征   总被引:1,自引:1,他引:1  
针对高能硝胺发射药在静态下燃速压力指数大的特殊燃烧性能,通过30mm高压模拟炮试验,采用与制式单基药相对比的研究分析方法,对高能硝胺发射药在火炮膛内条件下的基本燃烧特征进行了研究分析。  相似文献   

18.
干熄焦烧损率的统计方法及烧损因素探讨   总被引:1,自引:0,他引:1  
干熄焦烧损率的计算目前都采用碳平衡法,碳平衡法能确定干熄焦稳定运行时的烧损率,但进行生产统计时碳平衡法是不可取的。文中介绍了用干熄焦产汽率计算、统计干熄焦焦炭烧损的方法,该方法不需要进行碳排放量的测定,可随时进行统计计算,方便简单,精度能够满足生产统计需要,同时对干熄焦系统运行过程焦炭烧损的原因进行了分析和探讨。  相似文献   

19.
    
In the present research, an experimental and numerical investigation has been performed to study initial pressure rise in multi grain solid rocket motor. A cluster of seven uninhibited tubular grains of double base propellant is analysed to get near neutral pressure in rocket motor. It is experimentally observed that in some static firings initial pressure rise in first 100 ms is higher than the predicted value of ∼7.5 MPa. The average pressure in the rocket motor is ∼7 MPa and total burning time of these grains is ∼2 s. ANSYS software is used for numerical analysis to investigate the effects of various % openings of nozzle end (NE) metal grid on pressure rise in the rocket motor with and without peripheral opening. The analysed results are compared with experiments. It is found that, as the %opening of NE metal grid increases, the initial pressure in the rocket motor decreases. The peripheral opening is also important to reduce pressure rise in rocket motor. This study helps in reducing the initial pressure rise in the combustion chamber which is essential for safe working of the rocket motor.  相似文献   

20.
    
The effect of N‐methyl‐2‐(3‐nitrophenyl)pyrrolidino[3′,4′:1,2]fullerene (mNPF) on the decomposition characteristics of hexogen (RDX) was investigated using differential scanning calorimetry (DSC). The results show that mNPF can accelerate the decomposition of RDX, the peak temperature (Tp) of the exothermal decomposition is reduced by 6.4 K, and the corresponding apparent activation energy (Ea) is decreased by 8.7 kJ mol−1. N‐methyl‐2‐(3‐nitrophenyl)pyrrolidino[3′,4′:1,2]fullerene (mNPF), carbon black (CB), and C60 were used as combustion catalysts to improve the combustion performance of a composite modified double‐base propellant containing RDX (RDX‐CMDB). The burning rate experimental results show that mNPF has a stronger catalytic effect than C60 and CB. The magnitude of the effect of the three carbon substances on the enhancement of the burning rate is as follows: mNPF>C60>CB. The catalytic effects of different contents of mNPF on the burning rates of RDX‐CMDB propellants were also studied, and the results show that the burning rates of RDX‐CMDB propellants are improved with increasing mNPF content. The plateau burning rate of a RDX‐CMDB propellant can be increased to 19.6 mm s−1 when 1.0 % mNPF is added, and the corresponding plateau combustion region occurs at 8–22 MPa.  相似文献   

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