复合固体推进剂装药侧面包覆层贮存试验

叙述了复合固体推进剂壳体粘结式装药侧面包覆层及其作用。总结了ＰＳ－１和ＰＳ－２两种壳体粘结式复合固体推进剂装药侧面包覆层ＢＫ－１和ＢＫ－２长期贮存试验情况。实验结果表明,在室内无控条件下,ＢＫ－１包覆层贮存８年,ＢＫ－２包覆层贮存６年,性能基本上稳定。对于装复合固体推进剂的钢壳体发动机必须研究防腐问题。     

导弹续航药有效使用年限研究

选择某导弹续航发动机推进剂装药在使用中发现质量最差的批次作为代表批，经过长期贮存及数次实际内弹道性能静止试验，通过对试验数据的分析，研究该导弹续航药的有效使用年限。     

含硝酸酯螺压推进剂装药贮存性能评估研究

为得到含硝酸酯螺压推进剂装药在自然贮存过程中性能变化规律,对贮存于某库房(贮存温度–10～35℃,相对湿度≤85%)12年的装药进行了系统性能测试与研究。结果表明,推进剂药柱的药形尺寸、理化性能、化学安定性、内部质量、力学性能、燃速及感度等性能未发生明显变化,装药的内弹道性能略有降低,但满足技术要求,表明该装药使用寿命至少能达12年。     

某型导弹弹射发动机装药的安全贮存寿命预估

为了准确预估某型导弹弹射发动机装药的安全贮存寿命,对自然贮存10年后的发动机装药进行了X射线检测、燃烧性能、物理化学性能、化学安定性能、力学性能、内弹道性能等测试.结果表明,该导弹弹射发动机装药的安全贮存寿命至少为10年.     

贮存条件对导弹发动机装药的影响及分析

分析了目前国内在导弹发动机装药贮存中存在的问题，以及贮存条件对固体推进剂装药力学性能的影响，提出了合理、实用的贮存条件，经某型导弹实际贮存验证效果良好。     

界面粘接结构贮存过程中的脱粘分析

介绍了固体火箭发动机贮存过程中衬层/推进剂界面脱粘的机理和影响因素,着重分析了老化、组分迁移和贮存环境对衬层/推进剂界面脱粘的影响,并提出了缓解界面脱粘的主要措施,认为在衬层和推进剂间增设阻挡层和改进衬层的抗迁移能力是缓解界面脱粘的有效途径。     

双基火箭装药的热老化研究

固体火箭装药是由固体推进剂及其表面上覆盖的包覆层构成。火箭装药在成型加工、贮存过程中,都会受到内外因素的综合作用,在包覆层及推进剂药柱的各自内部及其粘接界面上将发生物理或化学反应,从而使装药的性能逐渐变坏,以致最后丧失使用寿命,此即称之谓火箭装药的“老化”。本文对某一种双基火箭装药的成品进行了热老化研究。分析研究了该装药的包覆层及双基推进剂的热老化进程与变化程度。讨论了本课题所设计及采用的热老化实验与分析方法的特点,很适用于火箭装药的老化问题的科学研究,可以使研究工作简化,使一些难于开展研究的课题可以进行。另外,本文阐述了以单位装药试样的与其热值相对应的面积值表示装药的老化变化程度的合理性。     

双基火箭装药的热老化研究

固体火箭装药是由固体推进剂及其表面上覆盖的包覆层构成。火箭装药在成型加工、贮存过程中,都会受到内外因素的综合作用,在包覆层及推进剂药柱的各自内部及其粘接界面上将发生物理或化学反应,从而使装药的性能逐渐变坏,以致最后丧失使用寿命,此即称之谓火箭装药的“老化”。本文对某一种双基火箭装药的成品进行了热老化研究。分析研究了该装药的包覆层及双基推进剂的热老化进程与变化程度。讨论了本课题所设计及采用的热老化实验与分析方法的特点,很适用于火箭装药的老化问题的科学研究,可以使研究工作简化,使一些难于开展研究的课题可以进行。另外,本文阐述了以单位装药试样的与其热值相对应的面积值表示装药的老化变化程度的合理性。     

湿度对丁羟推进剂及其粘接性能的影响研究

固体火箭发动机燃烧室内绝热层、人工脱黏层及推进剂药柱,均为高分子材料复合体系。在成型及贮存过程中,湿度是影响丁羟推进剂药柱性能及各界面的联合粘接强度的首要因素。探讨了绝热层、衬层及推进剂药柱在不同环境湿度下的吸湿特性,通过模拟实际生产过程的环境湿度,研究了丁羟推进剂药柱性能及各界面的联合粘接强度变化状况。     

HTPB推进剂贮存老化建模及寿命预估研究综述

HTPB复合固体推进剂是火箭发动机的动力之源,其贮存寿命和性能优劣决定了火箭发动机的寿命和作战性能的发挥,因而研究HTPB复合固体推进剂的贮存老化模型及寿命预估具有重要的军事和经济意义。本文对复合固体推进剂贮存老化性能的研究方法进行了介绍,并综述了国内外贮存寿命老化建模的研究进展,针对推进剂实际贮存可能出现的问题对未来贮存寿命预估的发展趋势进行了预测。研究结果表明,现代仪器的运用可以弥补传统仪器在固体推进剂老化性能研究上的不足,但是还存在研究手段单一、测试方法存在误差、没有形成统一的系统等缺点;推进剂的老化过程比较复杂,结构完整性分析和老化试验相结合的方法可以对推进剂贮存性能和寿命预估进行系统性的研究,得到的结果更准确,可靠性更高。分段老化建模作为推进剂寿命预估研究的新方向,具有很大的发展空间。     

Applying modified hyperbranched polyester in hydroxyl‐terminated polyether/ammonium perchlorate/aluminium/cyclotrimethylenetrinitramine (HTPE/AP/Al/RDX) composite solid propellant

Composite solid propellants demand fine and stable mechanical properties, creep resistance and stress relaxation performance during their long storage and usage time. In this study, modified hyperbranched polyester (MHBPE) was prepared and introduced into HTPE/AP/Al/RDX (HTPE, hydroxyl‐terminated polyether; AP, ammonium perchlorate; RDX, cyclotrimethylenetrinitramine) solid propellant as an effective additive. The static tensile and dynamic mechanical properties of this propellant before and after the introduction of MHBPE were evaluated. The elevated interfacial interaction by using MHBPE between the binder and RDX fillers improved the toughness and elasticity of the propellant. The enhancement mechanisms were also confirmed by the influence on the fracture surface morphology of the binder which was investigated by SEM. In addition, some influence on the dynamic mechanical properties of HTPE/AP/Al/RDX propellant caused by MHBPE was investigated by dynamic mechanical analysis. The creep behaviors of the HTPE/AP/Al/RDX propellants with and without MHBPE were also investigated at different stresses and temperatures. Reduced creep strain rate and strain were obtained for the modified propellant, implying enhanced creep resistance performance. The creep properties were quantitatively evaluated using a six‐element model and the long‐term creep performance of the propellant was predicted using the time–temperature superposition principle. A creep behavior of nearly 10⁶ s at 30 °C could be acquired in a short‐term experiment (800 s) at 30–70 °C. Moreover, the stress relaxation investigation of the propellants with and without MHBPE at ?40 °C, 20 °C and 70 °C suggested that MHBPE/HTPE/AP/Al/RDX propellant possessed better response ability to deformation. Thus, the application of MHBPE provides an efficient route of reinforcement to enhance the creep resistance and stress relaxation properties. © 2020 Society of Chemical Industry     

胶黏固结发射药的燃烧性能

以变燃速发射药为基体,用含能胶黏剂对其药粒表面微胶化处理,压实固结,制成胶黏固结整体变燃速发射药,解决固结装药的燃烧渐增性问题。将高装填密度和变燃速发射药的燃速渐增特性结合在一起,可有效控制高装填密度发射药的燃气释放。由密闭爆发器实验得出变燃速发射药和胶黏固结药的p-t和L-B曲线,并对两种发射药曲线进行对比分析。结果表明,胶黏固结发射药基本保持变燃速发射药的高燃烧渐增性,具有高装填密度和燃烧再现性。     

含废弃丁羟推进剂的凝胶炸药

为安全处理和再利用废弃固体推进剂,通过添加单基药将丁羟推进剂再利用制备了灌注式凝胶炸药.采用验证板试验及电离探针法研究了不同装药配比、推进剂颗粒尺寸及装药直径对炸药爆轰性能的影响.结果表明,丁羟推进剂难以发生爆轰,若添加适量单基药,能显著提高炸药的爆轰感度,并降低其临界直径;该凝胶炸药密度为1.6 g/cm3,直径为7...     

基于TDLAS技术的双基系推进剂装药排气羽流流速特性研究

基于可调谐半导体激光吸收光谱(TDLAS)技术,利用吸收光谱中1392nm附近的H2O吸收谱线,测量了双基推进剂和改性双基推进剂装药在Ф50mm标准缩比发动机中燃烧后产生的排气羽流的流速。结果表明,双基推进剂装药的流速在达到第1个峰值后有稍许下降,随后缓慢上升,进入位于0.90~1.39s的平台区;而改性双基推进剂装药的流速在达到1100m/s后直接进入位于0.33~0.88s的平台区,而流速在该区域内呈现下降趋势;上述两种装药的排气羽流流速曲线的变化趋势与燃烧室内压强曲线一致,但由于流速测量点距喷口有一定距离,导致其与压强曲线相比有一定程度的滞后;双基和改性双基两种推进剂装药在距发动机喷口30cm处的平均羽流流速分别为831.8和1057.5m/s。     

Performance optimization of a standard-flow hybrid rocket engine

A method for performance optimization of a standard-flow hybrid rocket engine is considered. The method is based on inserting an additional amount of an oxidizer into a solid propellant with a prescribed distribution of the oxidizer mass fraction along the solid propellant charge. An analytical dependence is derived for the oxidizer fraction distribution that ensures uniform combustion and high efficiency of the solid propellant charge.     

膏体推进剂火箭发动机研究进展

膏体推进剂是由固体推进剂衍变而成的一种新型化学推进剂。简要介绍膏体推进剂组成、制造工艺及性能。着重介绍膏体推进剂火箭发动机国内外研究进展及其结构特征。     

Weathering of recycled photo‐degraded polyethylene

The increased use of recycled plastics in a wide range of outdoor applications depends on the long‐term performance of the material. However, to date most research has been concerned with the effects that recycling has on the immediate mechanical properties of the polymer. The following paper examines the effects that recycling photo‐degraded polymer has on the long‐term photo‐stability of the recycled material. Two identical high‐density polyethylene wheelie‐bins were used in this study, one of which had been kept in a controlled indoor environment and the other kept outdoors for 12years in the United Kingdom. Material removed from each wheelie‐bin was reprocessed and molded into specimens, which were artificially weathered in a Xenon arc chamber. Infrared spectroscopy and nanoindentation revealed that although the properties of each set of specimens were similar immediately after reprocessing, those that had been subjected to outdoor exposure prior to reprocessing degraded more rapidly. This accelerated degradation is believed to be due to the photo‐degraded products in the recycled material accelerating the degradation process. The consequences of this accelerated degradation raise issues regarding the vulnerability of recycled material to the long‐term effects of outdoor exposure. POLYM. ENG. SCI., 2008. © 2007 Society of Plastics Engineers     

复合固体推进剂老化研究

针对复合固体推进剂的老化问题,探讨了复合固体推进剂老化的主要因素;从复合固体推进剂组分的影响、环境湿度、储存温度等方面分析了其影响复合固体推进剂老化的机理;综述了复合固体推进剂贮存寿命的几种预估方法:力学性能法、阿累尼乌斯方程式法、凝胶含量法、傅里叶红外光谱法和动态粘弹法,并对这些研究方法的内容和结果可信度进行了分析。最后对复合固体推进剂老化研究的发展趋势进行了展望。     

一种评估库存发射药安全贮存寿命的方法

为了科学评估库存发射药的安全贮存寿命,通过对库存弹药(发射药)长期贮存试验研究,得到了在库存环境下贮存30多年部分发射药的DPA含量试验数据,建立了相应的数据处理数学模型和安全贮存寿命预测方法。依据试验结果和该数据处理方法,计算出该发射药在置信水平为90％的条件下,安全贮存寿命不低于56年。经试验验证,该评估结果与实际情况基本相符,表明提出的估算库存发射药安全寿命的方法是可以接受的。     

Review of the Adhesively Bonded Interface in a Solid Rocket Motor

One of the most challenging requirements in a solid rocket motor (SRM) is the integrity of the charge structure which is a multilayer adhesive joint involving the propellant, liner, and insulation. The propellant/liner/insulation interface is considered to be the weakest part of the whole structure. This interface has some of the usual features of an adhesively bonded interface, as well as its own special characteristics: the co-cured process, ingredient migration between interfaces, and complicated damage mechanisms. We give a technical and critical review of the past 50 years of existing research on many aspects of the propellant/liner/insulation interface in terms of the adhesive properties and adhesive mechanisms, ingredients migration, damage determination, and fracture analysis. To present a comprehensive outline of this interface we also clarify some remaining problems which should be addressed in the future. With significant improvements in the theoretical and experimental studies of the propellant/liner/insulation interface, the problem of integrity failure of the charge structure in SRM will be well resolved.