液体推进剂爆炸火球热传递参数的试验测量技术

介绍了液体推进剂爆炸火球的内部温度,辐射温升和辐射热流密度的试验测量方法,试验测量的计算机数据采集系统,并给出了５０ｋｇ,１００ｋｇ,３００ｋｇ液体推进剂（Ｎ２Ｏ４／ＵＤＭＨ）爆炸火球的热传递参数的部分测量结果。     

Research on the influences of confining pressure and strain rate on NEPE propellant: Experimental assessment and constitutive model

In order to study the influences of confining pressure and strain rate on the mechanical properties of the Nitrate Ester Plasticized Polyether (NEPE) propellant, uniaxial tensile tests were conducted using the self-made confining pressure system and material testing machine. The stress-strain responses of the NEPE propellant under different confining pressure conditions and strain rates were obtained and analyzed. The results show that confining pressure and strain rate have a remarkably influence on the mechanical responses of the NEPE propellant. As confining pressure increases (from 0 to 5.4 MPa), the maximum tensile stress and ultimate strain increase gradually. With the coupled effects of confining pressure and strain rate, the value of the maximum tensile stress and ultimate strain at 5.4 MPa and 0.0667 s⁻¹ is 2.03 times and 2.19 times of their values under 0 MPa and 0.00333 s⁻¹, respectively. Afterwards, the influence mechanism of confining pressure on the NEPE propellant was analyzed. Finally, based on the viscoelastic theory and continuous damage theory, a nonlinear constitutive model considering confining pressure and strain rate was developed. The damage was considered to be rate-dependent and pressure-dependent. The constitutive model was validated by comparing experimental data with predictions of the constitutive model. The whole maximum stress errors of the model predictions are lower than 4% and the corresponding strain errors are lower than 7%. The results show that confining pressure can suppress the damage initiation and evolution of the NEPE propellant and the nonlinear constitutive model can describe the mechanical responses of the NEPE propellant under various confining pressure conditions and strain rates. This research can lay a theoretical foundation for analyzing the structural integrity of propellant grain accurately under working pressure loading.     

嵌银丝贫氧推进剂燃烧特性

采用试验发动机法 ,对嵌银丝铝镁贫氧推进剂的燃烧特性进行了研究 ,得到了低压下嵌银丝铝镁贫氧推进剂的燃烧规律 ,研究了银丝直径和贫氧推进剂配方对嵌银丝发动机燃速的影响。结果表明 ,嵌银丝贫氧推进剂的燃烧过程由初始工作段、稳定工作段和结束段组成 ;采用较粗的银丝 (0 3mm和0 4mm)可以显著提高贫氧推进剂的燃速 ;提高贫氧推进剂的基础燃速也是提高嵌银丝贫氧推进剂燃速的有效方法之一。     

航天器推进系统气液路故障仿真

为了研究和分析航天器推进系统气液路故障的发展变化规律及对整个推进系统性能的影响,在某挤压式航天器推进系统仿真模型的基础上,分别采用Realizable k-ε湍流模型和一维可压缩流模型对气路泄漏和堵塞故障进行动态仿真,采用一维不可压瞬变管流模型与变流量系数模型对液路泄漏和堵塞故障进行仿真分析。仿真结果表明:推进系统增压气路堵塞和泄漏故障,会导致增压不足,使推进剂供应管路压强下降;推进剂供应管路堵塞故障和泄漏故障会导致混合比偏离设计值,使推进系统性能降低。两类故障都会引起推力不足,致使系统性能降低。两者的不同之处在于:堵塞故障下,故障组件上游压强高于额定工况,推进剂消耗低于额定工况;泄漏故障下,故障组件上游压强低于额定工况,推进剂消耗高于额定工况。     

两种单基发射药灌注成型为凝胶炸药研究

对14／7和22／1两种单基发射药灌注成型为凝胶炸药进行了初步的试验研究,并对生成的凝胶炸药进行了威力和猛度测试。结果表明,可以利用高分子含水材料与氧化剂将废弃的发射药转化为凝胶民用炸药,通过调整装药直径,可获得一定的威力和猛度。     

点火具参数对RLPG点火过程的影响

采用考虑固体点火药燃烧过程的再生式液体发射药火炮(RLPG)膛内再生喷射燃烧过程的零维数学模型,研究了点火具参数对RLPGG点火过程的影响,分析并揭示了点火具参数对点火性能的影响规律.     

非壅塞固体火箭冲压发动机及其贫氧推进剂

研究了非壅塞固体火箭冲压发动机的工作特性。研制出了能量高、燃速高、燃速压强指数高、低压燃烧性能好的铝镁贫氧推进剂配方。采用连管式试验与数值分析相结合的方法 ,对非壅塞固体火箭冲压发动机性能进行了系统的研究     

先进的低特征信号推进剂研制

为了进一步提高导弹的突防能力和生存能力 ,扼要概括了国外战术导弹用低特征信号推进剂的现状 ;重点介绍了航天系统研制的几种不同能量梯次的低特征信号推进剂     

弹药长期贮存后发射药剩余能量的计算

对弹药在长期贮存过程中其发射药剩余能量的变化情况进行了研究。首先建立了箱装弹药中发射药放热规律的数学模型 ,然后利用数值模拟的方法计算了其在贮存过程中的剩余能量 ,最后对计算结果进行了分析与讨论     

不同海拔地区发射药安定性试验数据差异分析

按照同一试验方法,同一发射药分别在高原地区和内陆地区两地进行安定性试验对比。结果表明：同海拔高差测得的CO2体积分数差别为36％左右。因此,在对不同海拔地区发射药安定性试验数据进行处理时,需考虑气压因素影响,进行气压校正。