热塑型聚氨酯复合体系力学性能研究

采用压延机，在加工温度不高于１２０°Ｃ的条件下，成功地制备出热塑型聚氨酯弹性体（ＴＰＵ）与高氯酸铵、铝粉及增塑剂邻苯二甲酸二丁酯（ＤＢＰ）等组成的复合胶片，拉伸实验结果指出了所制备的热塑性弹性体复合体系具有良好的力学性能，完全达到或超过推进剂体系的要求指标。     

Active Sensing for Monitoring the Properties of Solid Rocket Motor Propellant Grains

Aging induced changes in the mechanical properties of solid propellant can lead to defects, such as cracks and grain‐liner separations, that limit the service lifetime of solid rocket motors. The use of embedded sensors is one approach that is being explored by various researchers to augment legacy inspection and prediction methods. We present herein an active sensing technique that is particularly suited for monitoring the properties of solid propellant, as it does not introduce electrical wires into the motor. Based on the use of magnetic induction for excitation and an optical fiber Bragg grating sensor to measure deformation, the method can be used to characterize the properties of a material with which it is in contact. In this paper, we first present proof‐of‐principal experiments demonstrating the utility of the method in characterizing the visco‐elastic properties of an adhesive, and in following changes in viscosity of an epoxy resin during cure. We next apply the method to solid propellant, and present data demonstrating that the method can be used to measure a deflection‐load curve of an aluminized HTPB propellant. In addition, we also show that the observed strain rate sensitivity matches that found in the literature and that the method had more than adequate resolution to observe the expected changes in material properties due to aging.     

单级入轨飞行器水平发射的优势

建立了可用于描述单级入轨飞行任务的动力学模型.选取了一种升力体外形的单级入轨飞行器作为算例,对水平发射的优势进行了论证.结合英国HOTOL的起飞参数对算例的水平发射过程进行了仿真,验证了地面助推发射对减少起飞段推进剂消耗的贡献.简要回顾并分析了美国X-33计划曾面临的技术困难,对算例在不同发射方式下所获得的入轨质量及其组成进行了比较,表明了降低起飞推重比对提高单级入轨飞行器运载效率的重要意义.选择相同的起飞参数,对采用不同发射方式时算例的飞行过程进行了对比.结果表明,水平起飞飞行器由于能够更好地利用其自身的升力体效应,在大气层内消耗的推进剂较垂直发射时少.     

抗化学介质润滑脂7804号在加注系统中的应用

抗化学介质润滑脂7804号在加注系统中得到了广泛应用,但抗化学介质润滑脂在连续加注工况下对加注系统的影响目前尚无相关研究.在对抗化学介质润滑脂7804号的成分和性能以及与推进剂的相容性研究的基础上,分析了连续多次和长时间加注条件下润滑脂对加注系统及加注过程的影响,并模拟实际情况进行了介质加注试验验证.根据研究结果从设计、工艺和使用上提出了减小润滑脂对加注系统影响的技术途径.     

基于凝胶百分数的推进剂贮存寿命及其可靠性分析

选择凝胶百分数作为老化性能评定参数,根据凝胶百分数与老化时间的关系,建立了推进剂贮存寿命预估模型;采用Monte-Carlo法分析了某固体推进剂贮存的寿命及其可靠性问题.结果表明:在常温下该推进剂的贮存寿命为5.93a,可靠度为0.83.     

热分解数据对研究火药临界工艺温度的指导意义

用示差量热法（ＤＳＣ）研究了药料初温、升温速率对火药热分解温度的影响,作为研究临界工艺温度的基础。     

基于ANSYS的随机场仿真及其应用

对于复杂几何形状及材料非线性结构的随机场仿真,为了提高效率,利用有限元软件ANSYS提供的概率设计系统(PDS)和随机场的局部平均理论,文中提出了随机场仿真的实施方法,用离散后数个特征值较大的随机变量代替原随机场建立相应的分析文件和概率设计文件.最后在此基础上通过一个算例分析了固体推进剂药柱在泊松比为随机情况下的结构响应,得到了较为详尽的分析结果.结果表明,该方法能为结构随机性分析提供一种简洁、方便的途径.     

便携式推进剂泄漏检测仪

介绍了一台用于航天器推进剂泄漏检测的便携式小型谱检测仪,详细阐述了仪器的设计,结构及特性,给出仪器的性能实验结果及卫星的推进剂的检测实例。     

HPFP,a model propellant for pMDIs

A novel model propellant for the study of the properties of pMDIs (pressurized metered-dose inhalers) at atmospheric pressure is proposed and extensively characterized. The reasons for the choice of this liquid, with its advantages and drawbacks, are explained and justified. Comparison with existing fluorinated propellants is also documented.     

Investigation of the Failure Mechanism of HTPB/AP/Al Propellant by In‐situ Uniaxial Tensile Experimentation in SEM

The failure mechanism of a propellant consisting of hydroxyl terminated poly‐butadiene filled with ammonium perchlorate and aluminum (HTPB/AP/Al) was determined by performing in‐situ uniaxial tensile tests in a scanning electron microscope (SEM). The experimental test plan contained uniaxial tensile test experiments performed at room temperature (25 °C) at three different strain rates (30, 150 and 750 μm min⁻¹). The in‐situ images and in‐situ videos collected by the SEM were correlated with the stress‐strain diagrams created with the tensile experiments, in order to relate the failure mechanism to the features found in the stress‐strain diagram. No significant strain rate dependency of the failure mechanism was observed when working with strain rates up to 750 μm min⁻¹ and working at room temperature. The stress‐strain diagram showed indications of existing cracks and voids opening up prior to the creation of new cracks and/or voids in the sample, debonding of binder with AP particles as well as nucleation and coalescence of voids. On the fracture surfaces of the samples, it was apparent that the binder cleanly separated from the large AP particles but had a better bond with the aluminum particles. However, a difference in the appearance of a short drawing phase in the stress‐strain diagram of the propellant is observed at different strain rates. The presented results clearly demonstrate the major advantage of the combination of microscopic tensile tests with microscopic observations, linking the stress‐strain behavior to the mechanical deformation processes taking place in these propellant samples at the microscopic level.