空间索杆铰接式伸展臂性能参数分析与设计

提出了评价空间索杆铰接式伸展臂性能的主要参数,分析研究了空间索杆铰接式伸展臂的主要性能参数与伸展臂几何特征参数的相互关系.推导了伸展臂线密度、收拢率、弯曲刚度和抗弯强度等性能参数的表达式.分析了伸展臂材料特性对伸展臂性能参数的影响,讨论了空间索杆铰接式伸展臂的稳定性问题,分析了局部失稳与整体失稳的条件.基于抗弯强度约束、弯曲刚度和抗弯强度共同约束两种约束模式对伸展臂进行了设计,建立了伸展臂几何参数和线密度与抗弯强度和弯曲刚度之间的关系方程,并将设计结果与美国ADAM(Able Deployable Articulated Mast)伸展臂参数进行了对比分析.      

便携式坐标测量系统在航空发动机关键部件检测中的应用

介绍了激光跟踪仪和关节臂坐标测量机在航空发动机关键部件检测中的应用,根据发动机部件的特点,对几类共性的检测问题提出了计量解决方案.     

TC11钛合金焊接接头低周疲劳分形损伤演化研究

基于损伤力学和分形理论,在金属材料疲劳断口的形貌特征具有统计自相似性的基础上建立了表征焊接接头断口损伤的面分形损伤演化模型.利用TC11合金低周疲劳试验后所得到的断口测得其面分维数,结合试验数据拟合获得该材料损伤演化方程参数;从而建立了TC11合金焊接接头三级载荷下的疲劳损伤演化方程;同时将该模型与基于断口表面裂纹扩展的线分形损伤演化模型加以比较.      

缝合连接三维编织复合材料弯曲性能试验研究

研究了缝合密度、搭接长度和编织角对缝合连接三维编织复合材料弯曲性能的影响.实验结果表明,搭接长度和缝合密度对弯曲性能影响较大,不同缝合密度试件的弯曲强度均与搭接长度成正比;搭接长度25、40、55 mm试件的弯曲强度随缝合密度的增加而增大,但编织角35°、搭接长度70 mm试件的弯曲强度随缝合密度的增加而减小,编织角20°、搭接长度70 mm试件的弯曲强度随缝合密度的增大呈现先增大后减小的规律;编织角对搭接长度70 mm试件的弯曲性能影响显著,对于中密度和高密度缝合试件,编织角20°的试件弯曲强度大于编织角35°的试件,而在低密度缝合试件中表现出相反的规律.     

Determining effects of impact loading on residual strength of fiber-metal laminates with grid-characteristic numerical method

The Grid-Characteristic numerical Method (GCM) that is quite common in solving aero and hydrodynamic problems can also be applied for mechanics of solids. It allows to implement complex border and contact conditions, including the non-reflecting border and the destructible contact. Both this conditions are very important for the precise and effective modeling of Low-Velocity Impacts (LVI) on fiber and Fiber-Metal Laminates (FML) and the resulting Barely Visible Impact Damage (BVID) that influences the residual strength of a composite aircraft part. BVID is the type of damage that is not visible by the naked eye and can be hardly detected by a standard ultrasound equipment that is used for regular maintenance. It can appear during any weak impacts like bird strike or hail. Determining its influence on the residual strength of the part is very important to define the priorities of development of ultrasound diagnostics. In this paper, the GCM was applied for a full cycle of loading of an FML aircraft cover part. The FML consisted of a Carbon Fiber Reinforced Polymer (CFRP) and a single titanium layer on the upper surface. The cycle of loading in a single calculation consisted of an LVI caused by a small striker and a comparatively slow compressive in-plane loading. Three-dimensional patterns of velocity and stress distributions over the time of calculation are given. Destruction patterns, obtained via the Hashin failure criterion are given and analyzed.     

基于广义线性模型的固体推进剂贮存寿命评估

研究了固体推进剂在贮存过程中性能退化对贮存寿命与可靠性的影响,提出了一种基于广义线性模型的固体推进剂贮存寿命与可靠性评估方法.首先结合固体推进剂退化数据的特点,利用位置刻度模型来描述固体推进剂抗拉强度与贮存时间的关系,建立了固体推进剂的贮存寿命模型.然后利用广义线性模型,给出了贮存寿命模型系数的极大似然估计.根据极大似然估计的渐近正态性,利用Fisher信息矩阵,给出了贮存寿命与可靠度近似置信下限.结合算例表明该方法综合利用固体推进剂在不同贮存时间下的性能数据,改善了固体推进剂贮存寿命与可靠性评估精度.      

带有柔性补偿的柔性关节空间机器人的增广自适应控制及关节振动抑制

The problems of joint motion control and flexible vibration suppression of a flexible joint space based robot for manipulating an unknown payload are studied. Based on the system linear momentum conservation and the Lagrange method, the under actuated dynamics model of the space robot is established. For convenience of the design of its control system, the system is divided into both fast and slow subsystems by using the joint flexibility compensation technique and the singular perturbation theory. A torque differential feedback controller is proposed for the fast subsystem to suppress the joints’ flexible vibration, meanwhile an adaptive control scheme based on the augmentation approach is designed for the slow subsystem to realize the joint trajectory asymptotic tracking under the condition of unknown payload parameters. Because of introduction of the flexibility compensation technique, the presented control scheme can equivalently increase the joint stiffness, and it is suitable to control the space robot systems with low joint stiffness. Moreover, the effect of unknown parameters is real time compensated by its adaptive controller, and then the specified joint motion task is achieved precisely. The effectiveness of the scheme is verified by the corresponding simulation results.     

热熔型聚酰亚胺薄膜的热封性能研究

针对现有商用聚酰亚胺（PI）薄膜无法采用热熔工艺进行粘接的问题,采用异构化二酐单体、2,3,3’,4’-二苯醚四酸二酐（a-ODPA）分别与7种芳香族二胺单体通过化学亚胺化工艺制备了PI薄膜（PI-1～PI-7）,系统研究了这些PI薄膜的结构与性能的关系。结果表明:a-ODPA的不对称结构赋予了PI薄膜良好的热塑性特征,使之可以采用热熔工艺进行粘接,薄膜间的热封强度最高可达660 N/m;此外,制备的PI薄膜还具有良好的耐热性能与力学性能,5%失重的温度超过500℃,玻璃化转变温度超过230℃,薄膜拉伸强度超过89 MPa。     

超低温处理对T700碳纤维/环氧复合材料拉—压疲劳性能的影响

对T700碳纤维/环氧复合材料在超低温处理前后的拉—压疲劳性能进行了的研究。采用真空袋—热压罐成型工艺,制备了T700碳纤维/环氧复合材料单向板,在液氮中对试样进行超低温浸泡和超低温/室温循环处理,利用光学显微镜观测了试样在超低温处理过程中产生的微裂纹情况,并测试了超低温处理后试样的静强度和拉—压疲劳1000次、10000次及130000次后的剩余强度。对T700碳纤维/环氧复合材料超低温损伤机理进行了分析,并讨论了超低温处理和拉—压疲劳对复合材料剩余强度的影响。结果表明,超低温处理和拉—压疲劳处理都会使试样产生微裂纹,并引起试样内的残余应力释放和试样的剩余强度降低;经历不同的超低温处理之后,试样的剩余强度达到最高值时所对应的拉—压疲劳次数不同;随着超低温处理和拉—压疲劳的作用,试样的剩余强度会经历先升高—再降低的过程。     

复合材料结构机械连接设计分析与试验研究

以某型机复合材料机身与主减后接头局部连接结构为研究对象,针对结构承面外载荷较大的特殊受载形式进行复合材料-金属接头机械连接技术研究。通过有限元仿真分析,确定了复合材料-金属接头的连接形式,并对复合材料机身结构连接区的局部铺层进行了优化,随后开展复合材料-金属接头连接结构的力学试验。结果表明,在给定载荷下,复合材料-金属接头机械连接结构具有足够的强度和刚度,满足设计要求。