航天器姿态容错控制技术研究现状与发展

更远、更复杂的人类空间探测任务要求航天器具有更高的可靠性,因此航天器的容错控制技术受到了广泛关注。对航天器姿态系统的容错控制技术发展现状进行了分析,总结了国内外近年来航天器姿态容错控制的成果,重点分析了利用自适应控制、滑模控制、模糊控制、神经网络控制等理论开展容错控制的进展,并分别阐述了采用不同技术途径发展容错控制的优缺点。最后,展望了航天器姿态容错控制技术未来的发展。     

导弹敏捷转弯段的新型非奇异终端滑模控制

针对具有快时变性、不确定性、强非线性和系统初始状态远离平衡点等特点的敏捷导弹的直接力/气动力复合控制律设计问题,提出了一种新型非奇异终端滑模控制方法。为缩短到达平衡态的时间,设计了一种组合非奇异终端滑模面,提高了系统状态在滑模面上的收敛速度,设计了改进的变系数双幂次趋近律,提高了系统状态到达滑模面的速度,并利用扩张状态观测器实时估计系统内外扰动,消除了观测误差对系统造成的干扰,抑制了抖振。最后,证明了所提方法的有限时间收敛特性,通过仿真对比校验了所提方法的有效性。     

小型薄片零件高速铣削加工试验研究

针对小型薄片结构零件切削过程中的变形问题,以薄片"一"字电极高速铣削加工试验为例,从编程方式、切削参数选用、工序安排、走刀路线等方面展开研究。控制其变形量达到最小,以满足产品设计要求。     

Stress analysis and damage evolution in individual plies of notched composite laminates subjected to in-plane loads

This work aims to investigate local stress distribution, damage evolution and failure of notched composite laminates under in-plane loads. An analytic method containing uniformed boundary equations using a complex variable approach is developed to present layer-by-layer stresses around the notch. The uniformed boundary equations established in series together with conformal mapping functions are capable of dealing with irregular boundary issues around the notch and at infinity. Stress results are employed to evaluate the damage initiation and propagation of notched composites by progressive damage analysis(PDA). A user-defined subroutine is developed in the finite element(FE) model based on coupling theories for mixed failure criteria and damage mechanics to efficiently investigate damage evolution as well as failure modes. Carbon/epoxy laminates with a stacking sequence of [45°/0°/ 60°/90°]sare used to investigate surface strains, in-plane load capacity and microstructure of failure zones to provide analytic and FE methods with strong validation. Good agreement is observed between the analytic method, the FE model and experiments in terms of the stress(strain) distributions, damage evaluation and ultimate strength, and the layerby-layer stress components vary according to a combination effect of fiber orientation and loading type, causing diverse failure modes in individuals.     

Evaluation of tensile properties of a compositemetal joint with a novel metal insert design by experimental and numerical methods

Composite-metal joints with a metal insert are one kind of connecting structure.In this paper,tensile experimental tests were carried out to investigate tensile properties of a composite metal joint with a novel metal insert design.Finite element models of the joint were established,and strain distribution and tensile strength were analyzed.The numerical results are in good agree ment with the experimental results.Results show that the joint failure is dominated by shear properties of the resin layer.Increasing the resin layer thickness in a certain range will improve the tensile strength of the joint,while increasing the radius of the fillet on the ending side of the metal insert will decrease the joint strength.Increasing the resin layer plasticity will improve the joint strength.The effect of the embedded depth of the metal insert can be ignored.     

足球教学与校园文化和谐发展模式的构建与实验研究

通过对足球与校园文化的研究,探索符合高校大学生体育学习的新的足球教学模式,为解决足球在高校的发展问题提供策略。三级足球教学的新模式,能够丰富校园体育文化内容,满足学生提高足球技战术水平的需要,最大限度地把学生吸引到足球运动中来,努力营造踊跃参与的校园足球文化氛围,实现足球与校园体育文化的完美结合,促进足球在高校校园的和谐发展。     

航空维修工程训练全程评估模式的研究

在现行航空工程机务维修考核评分标准的基础上,应用CDIO的工程教育理念,结合航空维修的特点,提出了对训练的全过程进行指导、记录、考核、评估的航空维修工程训练全程考核评估标准模式,应用于维修基础实习、系统实习、维修工程实习中,取得了良好的成效。     

Adaptive sliding mode control of the A-axis used for blisk manufacturing

As a key assembly in the 5-axis CNC machine tools, positioning precision of the A-axis directly affects the machining accuracy and surface quality of the parts. First of all, mechanical structure and control system of the A-axis are designed. Then, considering the influence of nonlin- ear friction, backlash, unmodeled dynamics, uncertain cutting force and other external disturbance on the control precision of the A-axis, an adaptive sliding mode control （ASMC） based on extended state observer （ESO） is proposed. ESO is employed to estimate the state variables of the unknown system and an adaptive law is adopted to compensate for the input dead-zone caused by friction, backlash and other nonlinear characteristics. Finally, stability of the closed-loop system is guaran- teed by the Lyapunov theory. Positioning experiments illustrate the perfect estimation of ESO and the stronger anti-interference and robustness of ASMC, which can improve the control precision of the A-axis by about 40 times. Processing experiments show that the ASMC can reduce the waviness, averaKe error and roughness of the nrocessed surface by 35.63%, 31.31% and 30.35%, respectively.     

基于原理的飞机机载系统故障诊断技术研究

以飞机系统设计原理为出发点,依据某支线飞机机载系统功能组成,分析各组成部件的失效模式和部件间失效影响模式,并进一步得到可能的故障征兆或故障现象;结合飞机维修类手册和历史维护案例数据,建立了有助于飞机排故支持及维修任务决策的辅助诊断系统。     

复合材料加筋筒段压载荷承载能力优化

复合材料加筋筒段是航空航天领域广泛采用的结构构形,其结构形式决定了重量及承压能力。为了研究加筋筒壁的承载能力,分析筋条间距、筒段长度和四种典型工程筋条截面的影响;以结构轻重量为目标函数,结构临界屈曲载荷、筋条局部屈曲载荷为约束,采用梁轴惯性矩平移模型,对复合材料筒壁0°、±45°、90°各铺层总厚度和筋条截面尺寸进行优化。结果表明结构轻重量设计中τ型桁条最有利,并得到其设计曲线,为工程设计应用提供参考。