战斗机瞬态敏捷性试飞技术研究

对飞机瞬态敏捷性尺度作了介绍和分析.在此基础上,对敏捷性尺度的试飞技术进行了研究,并提出了在敏捷性试飞过程中的注意事项、驾驶技术及计算方法,为以后的飞机敏捷性试飞提供了参考.     

基于参数辨识的直升机姿态敏捷试飞技术

基于不同的规范要求、试飞方法及响应类型,通过参数辨识方法对直升机的姿态敏捷特性进行研究,得到了二阶响应直升机姿态敏捷响应曲线,通过辨识结果能够更准确快捷地得到直升机姿态敏捷的考核指标。最后,结合某型直升机试飞结果对相关结论进行了具体分析,对后续直升机飞行品质试飞具有一定的指导意义。     

频率捷变雷达信号源实时校准技术研究

分析了原有频率捷变雷达信号源中频率校准方法存在的缺陷,在此基础上设计了实时校准的频率校准电路,提高了信号源的频率跟踪精度和稳定工作时间。     

基于多态性的UML时序图度量研究

目前对于时序图度量的研究没有考虑到面向对象软件的多态性特点,度量不够准确。本文结合面向对象多态性的特点和UML(Unified mode ling language)类图、时序图,运用图论的方法构建了有向无环图,并在此基础上提出了相适应的度量集,最后通过实例分析说明时序图的多态性扩展和度量集的有效性。同时,本文的研究也为软件测试用例的设计提供了指导。     

红外多光谱扫描仪在发射段的结构可靠性

用Ｇ莱希纳和Ｂ贝尔契（德）提出的结构系统可靠性分析通用方法（以下简称ＧＢ法），详细分析了某多光谱扫描仪的结构特点、工作环境与受力情况，并根据航天器受载特点建立了遥感器部分在发射阶段的可靠度数学模型，以一次二阶矩法为主要算法对红外扫描仪主体在发射阶段的结构可靠性进行了分析和评估。     

完备度量空间上的不动点定理

1922年,Banach证明了压缩映射的不动点的存在性。不动点理论对于解决一些实际问题诸如代数方程、微分方程、积分方程中都有应用。B ranc iari[1]提出了完备度量空间上的边值压缩,并证明了边值压缩映射的不动点定理。本文给出了完备度量空间上的三个不动点定理,推广了B ranc iari[1]中的结果,并且举例说明本文的结果是对Banach压缩定理的推广。     

敏捷性导弹的双网络逆动态模糊神经网络控制

新疆敏捷性导弹为了获得更高的机动性、敏捷性和好的导引精度，许多采用推力矢量控制方案，本文讨论了一类带推力矢量控制导弹的数学建模，在此基础上提出了一种适用于此类新型导弹的模糊神经网络控制方案，采用双网络逆动态学控制结构，数字仿真表明所提出的控制方案对于系统内参数不确定性和非线性变化具有强的适应性。     

Structure-aware fusion network for 3D scene understanding

In this paper, we propose a Structure-Aware Fusion Network(SAFNet) for 3D scene understanding. As 2D images present more detailed information while 3D point clouds convey more geometric information, fusing the two complementary data can improve the discriminative ability of the model. Fusion is a very challenging task since 2D and 3D data are essentially different and show different formats. The existing methods first extract 2D multi-view image features and then aggregate them into sparse 3D po...     

适用于航天软件开发的可靠性度量

介绍了软件可靠性和软件度量的概念 ,阐述了航天控制软件的特点 ,提出了可靠性度量的选择准则 ,推荐了 14种适用于航天控制软件的可靠性度量     

Investigation Into Cost-Effective Propulsion System Options for Small Satellites

The paper summarizes research into cost-effective propulsion system options for small satellites. Research into the primary cost drivers for propulsion systems is discussed and a process for resolving them is advanced. From this analysis, a new paradigm for understanding the total cost of propulsion systems is defined that encompasses nine dimensions – mass, volume, time, power, system price, integration, logistics, safety and technical risk. This paradigm is used to characterize all near-term propulsion technology options. From this effort, hybrid rockets emerges as a promising but underdeveloped technology with great potential for cost-effective application. A dedicated research program was completed to characterize this potential. This research demonstrated that hybrid rockets offer a safe, reliable upper stage option that is a versatile, cost-effective alternative to solid rocket motors. Finally, an innovative technique was derived to parametrically combine the diverse cost dimensions into a useful, quantifiable figure of merit for mission and research planning. Overall, it is shown that the most cost-effective solution is found by weighing all options along the nine dimensions of the cost paradigm within the context of a specific mission.