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排序方式: 共有91条查询结果,搜索用时 468 毫秒
81.
针对JL8型飞机尾旋振荡模态特性,结合几种尾旋试飞操纵规律对JL8型飞机翼刀腹鳍进行了探索性地研究和计算。结果表明,带翼刀腹鳍构型并不是对所有尾旋模态都会有影响,而是在一定的操纵规律下有影响尾旋运动振荡特性的作用。 相似文献
82.
一种星载计算机操作系统容错引导算法研究 总被引:1,自引:0,他引:1
将软件冗余备份与SPARC V8构架芯片EDAC相结合,提出了一种新型星载计算机操作系统容错引导算法。该算法首先在EEPROM中备份三份操作系统文件,星载机上电或复位后,利用硬件EDAC功能对引导的操作系统文件进行错误检测及纠错,当检测主操作系统文件错误并且无法纠错时,则屏蔽错误操作系统文件自动引导备份操作系统文件,星载机仍可正常启动。与目前采用的硬件编码容错技术及软件冗余容错算法相比,该算法在有效降低硬件成本和软件消耗的同时,实现了对操作系统文件的检错纠错及错误屏蔽功能,提高了操作系统数据的可靠性。该算法可以为星载机容错设计提供参考。 相似文献
83.
本文简要介绍JT8D—17A发动机燃油调节器故障分析课题所做的一些工作及进展。通过对燃油调节器的理论分析、实验研究、经验积累,初步掌握了一些调试规律,并使燃调拆换率下降。 相似文献
84.
基于TDRSS的高速数传信号载波捕获及跟踪算法研究 总被引:1,自引:0,他引:1
以TDRSS数传系统为研究背景,针对TDRSS数传信号的特点,以实现高速8PSK调制信号的载波同步与跟踪为研究前提。提出了一种采用二叉树(BinarySearchTree)频率搜索方法实现捕获及采用平均"滑动窗"递推最小二乘(RLS)一步预测方法实现频率跟踪的算法,并针对此方法进行了理论推导和蒙特卡洛(MonteCarlo)仿真。结果表明:该方法适用于全数字高速数传8PSK调制信号接收系统,同时也可移植、推广至全数字雷达接收机中。 相似文献
85.
86.
本文介绍了水杨醛缩-5-碘-8-氨基喹啉新西夫碱的合成、提纯与鉴定。特别对其性质及其与镓金属离子显色反应的光度特性作了研究,其配合物3.49×104L·mol(-1)·cm(-1). 相似文献
87.
采用等离子体浸没离子注人(PⅢ)技术对9Cr18轴承钢表面进行了双注入及共注入Ti+N工艺处理.测试了处理前后试样的显微硬度及真空摩擦因数,并表征分析了表面磨损形貌.结果表明:处理后试样的显微硬度都有大幅提高,最大增幅达68.7%;表面真空摩擦因数由0.15下降到0.08;磨斑尺寸及粗糙度分别减少了54.4%和37.4%.双注入与共注入方式在相同参数下,双注入处理后的试样表面综合性能更加优异. 相似文献
88.
Landsat系列卫星热波段具有60~120m的空间分辨率,对各种环境监测起到了重要的作用。随着Landsat系列卫星在全球范围内地表温度(land surface temperature,LST)产品的发布,其验证工作也随之展开,然而对于长时间序列的精度验证工作仍然缺乏。以黑河流域中游为研究区,利用研究区内湿地站(SD)、戈壁站(GB)和大满超级站(CJZ)三个气象站的地面测量数据对2013-2016年清晰无云的31景Landsat 8地表温度产品进行了验证与分析,并将Landsat 8地表温度产品与广泛使用的普适性单通道算法(JMS)反演结果进行了对比。结果表明,Landsat 8地表温度产品与普适性单通道算法反演结果精度均较高,在各个站点处R2均优于0.949。基于所有站点分析,Landsat 8地表温度产品精度稍高于普适性单通道算法反演结果。 相似文献
89.
Effect of Isothermal Forging on the Microstructure and Mechanical Properties of Mg-8Gd-3Y-0.5Zr Alloy 下载免费PDF全文
HOU Xiangwu WANG Yanbo ZHOU Haitao SUN Xin GONG Zhengxuan JIANG Shanyao XIAO Lü 《上海航天》2022,39(1):186-195
Aiming at the problems of poor plastic forming ability, narrow forging temperature range, and strain rate sensitivity of rare earth magnesium alloys, a study on the microstructure and mechanical properties of Mg-8Gd-3Y-0.5Zr alloy with different isothermal forging processes is carried out. The microstructure and properties of the alloy in the as-cast, isothermal forged, and post-aging states after forging are studied with optical microscope (OM), scanning electron microscope (SEM), and tensile testing. The results show that significant dynamic recrystallization occurs during the isothermal forging process, a fine equiaxed grain structure is formed, and the mechanical properties of the alloy are greatly improved. When the isothermal forging temperature is 460 ºC and the strain rate is 0.02 s-1, the alloy structure performance is the best, the room temperature tensile yield strength (TYS) is 218 MPa, the ultimate tensile strength (UTS) is 299 MPa, and the fracture elongation (FE) is 19.2%. When the alloy is post-forging artificial aged, the α-Mg matrix is dispersed, the Mg5(Gd,Y) phase is precipitated, the UTS of the alloy is increased to 392 MPa, and the FE is reduced to 12.0%. 相似文献
90.
《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2023,71(6):2702-2710
The European Stratospheric Balloon Observatory (ESBO) initiative aims at simplifying the access to stratospheric balloon missions. We plan to provide platforms and support with instrument design in order to support scientists. During the design process, the inevitable question of qualification for the harsh flight conditions arises. Unfortunately, there is no existing standard for qualification of stratospheric ballooning hardware. Thus, we developed a qualification procedure for use within ESBO and similar projects.In this paper, we present our analysis of the environmental conditions in the stratosphere. While conditions at typical balloon float altitudes are similar to the space environment, there are also some relevant differences. For example, the thermal environment is dominated by radiation and thermal conduction, but the remaining atmosphere still supports a certain amount of convection. The remaining atmospheric pressure in the stratosphere also leads to reduced arcing distances. Vibrational loads are far less than for space missions, but quasi-static or shock loads may occur. The criticality of radiation increases with mission duration.Based on the environmental conditions, we present the qualification procedures for ESBO, which are based on the European Cooperation for Space Standardization (ECSS) standards for space systems. Overtesting against too high requirements leads to overengineering, driving mission cost and mitigating the advantages of balloons over space missions. Therefore, we modified the ECSS standards to fit typical scientific ballooning missions over several days at altitudes up to 40 km. Furthermore, we analyzed design rules for space systems with regard to their relevance for scientific ballooning, including material and component selection. We present the experience from the hardware qualification process for the ESBO prototype STUDIO (Stratospheric UV Demonstrator of an Imaging Observatory). Even though boundary conditions are different for each individual mission, we aimed for a broader approach: We investigated more general requirements for scientific ballooning missions to support future flights. 相似文献