复合固体推进剂拉伸/压缩性能对比研究(英文)

为了获得药柱受压状态的模量参数,开展了推进剂压缩性能的探索测试。参照拉伸标准试件,进行了压缩试件尺寸的设计与调试,通过不同高度试件的测试结果及破坏形貌分析,确定了试件尺寸。在此基础上进行了不同应变下的推进剂拉/压对比测试。相同应变率下,压缩模量较拉伸模量高,压缩模量随压缩速度的变化规律与拉伸模量一致,随着速度的提高,模量随之提高。     

航天用纤维增强金属层合板

迄今铝合金仍是航空航天产品的主要结构材料,但它目前正受到纤维增强聚合物和新近崛起的纤维增强金属层合板(FRML)的强有力的挑战。这些新颖材料具有强度高、质量轻、模量高、膨胀系数低和耐疲劳性能好等优点。因而自它们一出世,就受到航空航天界的重视,文中对纤维增强金属层合板的制作方法和它的力学性能作了简要介绍。     

复合材料油气管路多目标设计法模糊物元评估分析

对复合材料油气管路多目标设计法，用模糊物元评估法进行了分析，结论与其他方法相符。     

用CTS试件及不连续位移法研究复合材料板裂纹

用ＣＴＳ试件研究了带裂纹的Ｆ１２有机纤维／环氧基体复合材料板裂纹法端附近的应力，介绍了该方法的原理、试验手续、加载方式数据处理；用不连续位移法对该 年进行了数值分析，试验和数值分析计算结果相近。     

三体随动跟踪式重力卫星姿态与无拖曳控制方法

采用非接触洛伦兹力执行器代替微推进系统,提出一种“质量块—载荷舱—平台舱”三体随动跟踪式重力卫星总体架构,避免传统低低跟踪重力场测量卫星设计中的质心波动与执行机构带来的动力学不确定性影响。其次,建立了该架构下的卫星姿轨耦合动力学模型,并在此基础上针对动力学非线性耦合项的影响,构建了一种基于带宽参数化自适应补偿的复合自抗扰控制方法,提升姿态与无拖曳控制性能。最后,采用数学仿真验证了所提出的重力卫星总体架构及其控制方法的有效性。仿真结果表明,该方法有效提升了系统的频域性能。     

Study on an automatic multi-pin insertion system for preparing Z-pin composite laminates

As a three-dimensional layer enhancement technology, the Z-pin technology is suitable for manufacturing composite prepreg laminates and can also effectively improve their interlaminar properties. In order to manufacture Z-pin composite parts efficiently, this paper proposes a transi- tional insertion system, and according to the technical requirements of the transitional insertion process and the functional requirements of the transitional insertion platform, proposes a transition insertion plan which can insert multiple Z-pins into a carrier. A prototype machine has been designed and made, and a series of function debugging and verification experiments have been car- ried out on the machine. Some problems show up during the experiments, but based on the analysis of the reasons, this paper provides lots of solutions, and finally demonstrates the feasibility and practical value of the system. The results show that the system meets all technical requirements of the Z-pin insertion process. It is capable to insert multiple Z-pins into a foam carrier; as a result, the system is as much as 5 times more efficient than existing equipment, and the deviation for the insertion distance can be controlled within 0.3 mm. This Z-pin transitional insertion platform pro- motes the use of Z-pins in national defense and lays the foundation for commercializing the Z-pin technology.     

Material parameter modeling and solution technique using birth–death element for notched metallic panel repaired with bonded composite patch

This paper seeks to outline a novel three-layer model and a new birth–death element solution technique to evaluate static strength of notched metallic panel repaired with bonded composite patch and to optimize material parameters. The higher order 3D, 8-node isotropic solid element and 8-node anisotropic layered solid element with three degrees of freedom per node are respectively implemented to model substrate panel, adhesive layer and composite patch to establish three-layer model of repaired panel. The new solving technique based on birth–death element is developed to allow solution of the stress pattern of repaired panel for identifying failure mode. The new model and its solution are used to model failure mode and residual strength of repaired panel, and the obtained results have a good agreement with the experimental findings. Finally, the influences of material parameter of adhesive layer and composite patch on the residual strength of repaired panel are investigated for optimizing material properties to meet operational and environmental constraints.     

基于COMPRO 模型的复合材料热压罐成型工艺仿真

有效利用热压罐技术来实现复合材料成型的关键在于选择合适的工艺参数和制定合理的工艺
方案,虚拟热压罐工艺仿真可以有助于对固化过程进行预测,提高工艺设计效率,降低生产成本。本文介绍了
热压罐工艺仿真软件COMPRO 以及典型的固化过程分析模型(热化学模型、流动压实模型和应力变形模型)。
最后给出了影响COMPRO 数值模拟的关键参数及翼梁样件试验数据与数值模拟对比,COMPRO 可以较为准
确的预测固化工艺。     

碳纤维复合材料的屏蔽效能

碳纤维复合材料的屏蔽效能对系统抗电磁脉冲设计具有重要影响。本文通过理论分析建立了碳

纤维复合材料的屏蔽效能模型,研究了频率、厚度等因素对碳纤维复合材料屏蔽效能的影响。结果表明,碳纤

维复合材料具有较为良好的屏蔽效能,屏蔽效能在频率拐点以下随频率变化较小,在频率拐点以上随频率增大

迅速增大,并通过了试验验证。

     

某型飞机复合材料后机身闪电防护设计及应用研究

飞机的防雷击设计是现代飞机设计的一个重要组成部分,由于复合材料的抗雷击损伤能力比铝合金差,所以必须有可靠的防雷击系统才能保证飞机的飞行安全。以复合材料后机身作为研究对象,详细探讨了闪电防护的方案设计和应用研究及其适航符合性说明。