螺纹紧固件耐久性分析方法的实验研究

本文在实验的基础上，提出了应用于螺栓螺纹表面裂纹上一种抗疲劳分裂研究方法－－耐久性损伤分析方法，考虑了一个新的耐久性损伤模型，螺纹圆角处开裂，把适用于紧固孔上小裂纹模型上的理论方法发展延伸至螺纹圆角模型大裂纹上，并通过实验得到了验证。同时给出了一个例子，预测结果与实验结果拟合得很好，为带螺纹紧固件的耐久性分析方法的研究提供了一种可行的方法。     

烟丝配料单片机控制系统

本文介绍了配料生产过程中单片机控制系统的硬件结构及软件流程。由于硬件和软件设计上都采用了模块化的结构，所以便于安装调试，整个系统可推广到诸如水泥、矿产、食品加工等生产中。     

某型号机襟翼机构摩擦磨损可靠性分析与计算(英文)

本文应用空间机构的建模方法建立了某型号机襟翼机构运动的数学模型。当给出输入参数时，可通过此数学模型求出襟翼机构的理论输出参数。输入参数相同时，通过引入摩擦磨损量至数学模型可获得襟翼机构的实际输出参数，并在此基础上求得襟翼机构的摩擦磨损可靠性。     

中国核电厂操作员反应时认知模型的应用(英文)

讨论了一些有关人员行为与时间有依赖关系的可靠性模型；给出了中国核电厂操作员在清华大学培训模型机上的一些可靠性实验结果。此外，还根据已获得的实验数据计算了在ＡＴＷＳ事故条件下人的失误概率。     

A formal approach using SysML for capturing functional requirements in avionics domain

In this work, a Model-Based Systems Engineering approach based on SysML is proposed. This approach is used for the capture and the definition of functional requirements in avionics domain. The motivation of this work is triple: guide the capture of functional requirements, validate these functional requirements through functional simulation, and verify efficiently the consistency of these functional requirements. The proposed approach is decomposed into several steps that are detailed to go from conceptual model of avionics domain to a formal functional model that can be simulated in its operating context. To achieve this work, a subset of SysML has been used as an intermediate modelling language to ensure progressive transformation that can be understood and agreed by system stakeholders. Formal concepts are introduced to ensure theoretical consistency of the approach. In addition, transformation rules are defined and the mappings between concepts of ARP4754A civil aircraft guidelines and SysML are formalized through meta-model. The resulting formalization enables engineers to perform functional simulation of the top-level functional architecture extracted from operational scenarios. Finally, the approach has been tested on an industrial avionics system called the Onboard Maintenance System.     

Reconfigurable Flight Control Design for Combat Flying Wing with Multiple Control Surfaces

With control using redundant multiple control surface arrangement and large-deflection drag rudders,a combat flying wing has a higher probability for control surface failures.Therefore,its flight control system must be able to reconfigure after such failures.Considering three types of typical control surface failures(lock-in-place(LIP),loss-of-effectiveness(LOE) and float),flight control reconfiguration characteristic and capability of such aircraft types are analyzed.Because of the control surface redundancy,the aircraft using the dynamic inversion flight control law already has a control allocation block.In this paper,its flight control configuration during the above failures is achieved by modifying this block.It is shown that such a reconfigurable flight control design is valid,through numerical simulations of flight attitude control task.Results indicate that,in the circumstances of control surface failures with limited degree and the degradation of the flying quality level,a combat flying wing adopting this flight control reconfiguration approach based on control allocation could guarantee its flight safety and perform some flight combat missions.     

飞机机身近区电磁散射建模研究

采用物理光学法和一致性几何绕射理论，分析机身各 球面波照射下的近场电磁散射特性几何绕射并建立其雷达散射截面（ＲＣＳ）数学模型，同时对于复杂机身的前部，采用面元油、即采用双三次Ｂ样条技术对机外形进行拟合，然后再用一致性几何绕射理论进行计算。种方法具有一定的可信度。     

Controlling factors of Region 2 field-aligned current and its relationship to the ring current: Model results

One essential component of magnetosphere and ionosphere coupling is the closure of the ring current through Region 2 field-aligned current (FAC). Using the Comprehensive Ring Current Model (CRCM), which includes magnetosphere and ionosphere coupling by solving the kinetic equation of ring current particles and the closure of the electric currents between the two regions, we have investigated the effects of high latitude potential, ionospheric conductivity, plasma sheet density and different magnetic field models on the development of Region 2 field-aligned currents, and the relationship between R2 FACs and the ring current. It is shown that an increase in high latitude potential, ionospheric conductivity or plasma sheet density generally results in an increase in Region 2 FACs’ intensity, but R2 FACs display different local time and latitudinal distributions for changes in each parameter due to the different mechanisms involved. Our simulation results show that the magnetic field configuration of the inner magnetosphere is also an important factor in the development of Region 2 field-aligned current. More numerical experiments and observational results are needed in further our understanding of the complex relationship of the two current systems.     

Reliable flight performance assessment of multirotor based on interacting multiple model particle filter and health degree

Multirotor has been applied to many military and civilian mission scenarios. From the perspective of reliability, it is difficult to ensure that multirotors do not generate hardware and software failures or performance anomalies during the flight process. These failures and anomalies may result in mission interruptions, crashes, and even threats to the lives and property of human beings. Thus, the study of flight reliability problems of multirotors is conductive to the development of the drone industry and has theoretical significance and engineering value. This paper proposes a reliable flight performance assessment method of multirotors based on an Interacting Multiple Model Particle Filter (IMMPF) algorithm and health degree as the performance indicator. First, the multirotor is modeled by the Stochastic Hybrid System (SHS) model, and the problem of reliable flight performance assessment is formulated. In order to solve the problem, the IMMPF algorithm is presented to estimate the real-time probability distribution of hybrid state of the established SHS-based multirotor model, since it can decrease estimation errors compared with the standard interacting multiple model algorithm based on extended Kalman filter. Then, the reliable flight performance is assessed with health degree based on the estimation result. Finally, a case study of a multirotor suffering from sensor anomalies is presented to validate the effectiveness of the proposed method.     

同伦法在现代飞机尾旋预测中的应用

在利用ＢＡＣＴＭ法对高性动性能飞机尾旋预测中，首先要求解平衡解，为此需要使用静态，强迫振荡天平气动模型和旋转天平气动模型，而在两气动模型转换过程中，常常遇到难找或不断得到平衡解的问题，针对这一问题，利用同伦法对气动模型进行处理，有效地了解决了该问题，同时，结合某战斗机进行了有关尾旋的计算和预测，结果表明，所提出的方法是可靠和切实可行的。