基于模型拼接技术的四旋翼无人机全飞行包线建模

四旋翼无人机在军事和民用领域都有广泛的应用前景。然而，四旋翼无人机具有机载传感器准确性低与可靠性差、不同飞行条件下动力学模型差异大等特点。本文以四旋翼无人机为研究对象，系统地开展了飞行路径重构、频率域系统辨识、全飞行包线建模的相关研究工作。针对机载低成本传感器存在显著常值偏差与量测噪声统计学特性未知的缺点，采用基于EKF的飞行路径重构技术对在飞行试验中无人机的机体空速进行重构；针对不同飞行速度下四旋翼无人机动力学模型差异大的特点，采用频域法辨识得到不同飞行条件下的本体动力学模型；针对四旋翼无人机大跨域的高精度控制需求，利用模型拼接技术，系统性地提出了全飞行包线建模方案，经过验证，所提出模型拼接技术是准确可靠的。     

Solar polar magnetic field dependency of geomagnetic activity semiannual variation indicated in the Aa index

Three major hypotheses have been proposed to explain the well-known semiannual variation of geomagnetic activity, maxima at equinoxes and minima at solstices. This study examined whether the seasonal variation of equinoctial geomagnetic activity is different in periods of opposite solar magnetic polarity in order to understand the contribution of the interplanetary magnetic field (IMF) in the Sun-Earth connection. Solar magnetic polarity is parallel to the Earth’s polarity in solar minimum years of odd/even cycles but antiparallel in solar minimum years of even/odd cycles. The daily mean of the aa, Aa indices during each solar minimum was compared for periods when the solar magnetic polarity remained in opposite dipole conditions. The Aa index values were used for each of the three years surrounding the solar minimum years of the 14 solar cycles recorded since 1856. The Aa index reflects seasonal variation in geomagnetic activity, which is greater at the equinoxes than at the solstices. The Aa index reveals solar magnetic polarity dependency in which the geomagnetic activity is stronger in the antiparallel solar magnetic polarity condition than in the parallel one. The periodicity in semiannual variation of the Aa index is stronger in the antiparallel solar polar magnetic field period than in the parallel period. Additionally, we suggest the favorable IMF condition of the semiannual variation in geomagnetic activity. The orientation of IMF toward the Sun in spring and away from the Sun in fall mainly contributes to the semiannual variation of geomagnetic activity in both antiparallel and parallel solar minimum years.     

空间太阳能电站姿态运动-结构振动耦合建模与分析

针对多旋转关节空间太阳能电站构型，利用基于能量等效原理的连续体等效方法将其等效为柔性梁模型，并考虑重力梯度影响，建立了姿态运动与结构振动的耦合动力学模型；结合Runge-Kutta 法和Newmark法的优点，提出了适用于求解姿态运动与结构振动耦合动力学方程的改进算法，相比于经典Runge-Kutta 法大幅提高了效率；利用改进算法得到了不同参数下的动力学响应。在此基础上，推导了结构振动量级随结构尺寸的六次方量级增加的规律，仿真结果表明尺寸过大引发不稳定现象；分析了姿态运动和重力梯度对结构振动频率和振幅的影响；发现了姿态运动周期受结构柔性影响而增大的现象，这种现象在低轨以及大初始姿态角下影响更为明显。     

Sealing reliability modeling of aviation seal based on interval uncertainty method and multidimensional response surface

Many variables affect the sealing performance, and their distribution characteristics are difficult to obtain with probabilistic methods owing to the high cost involved. Numerous problems in engineering are similar due to the appearance of small-sample parameters. In this study, the sealing reliability of an aviation seal was defined as the research object, and an interval uncertainty method and multidimensional response surface were proposed to calculate the sealing reliability.Based on this, we first analyzed the failure mechanism of the aviation seal and established a leakage rate model. Then, based on the non-probabilistic interval model, an interval uncertainty method was proposed to construct the analytical model. With reference to the limit state equation from the structural reliability theory, the multidimensional response surface was used for fast calculation.Then, we chose the single-cylinder gas steering gear used in aircraft as the case study, its sealing reliability in working and non-working statuses were calculated, and the results were verified with the actual maintenance records. By analyzing the sensitivity of some variables, we can improve the sealing reliability of the aviation seal by improving the surface roughness only if the cost allows.Finally, we consider that the method proposed in this study realizes the application of smallsample uncertainty analysis in reliability analysis, and could provide a feasible way to solve the similar problems in engineering with multidimensional and small-sample parameters.     

北京平原地区VS30估算模型适用性研究

本文使用基于钻孔测井数据的3类模型,即常速度外推模型、速度梯度模型、双深度参数外推模型,通过对北京地区460个深度超过30m的钻孔剪切波速资料进行分析,详细探究了V_(S30)估算模型在本研究区的适用性。研究结果表明双深度参数外推模型在估算V_(S30)上准确度很高,其不需要大量的数据进行回归分析,且不具有区域独立性,可以为全球包括北京地区场地类别划分提供依据,进而在震害快速评估中用于确定场地影响,是一种值得推广的估算模型。     

风云二号卫星地面控制系统自适应同步控制方法

针对风云二号07星测控实施过程中部分姿章联控参数未能正常执行的系统间时序控制不同步问题,研究提出一种地面控制系统自适应同步控制方法,分析卫星历史数据得到有效接收时间区间,取所有有效接收时间区间的交集得到最终有效接收时间区间。经验证,方法可有效解决系统间时序不同步的问题,精度高,控制效果好。     

Simulated microgravity inhibits cell wall regeneration of Penicillium decumbens protoplasts

This work compares cell wall regeneration from protoplasts of the fungus Penicillium decumbens under rotary culture (simulated microgravity) and stationary cultures. Using an optimized lytic enzyme mixture, protoplasts were successfully released with a yield of 5.3 × 10⁵ cells/mL. Under simulated microgravity conditions, the protoplast regeneration efficiency was 33.8%, lower than 44.9% under stationary conditions. Laser scanning confocal microscopy gave direct evidence for reduced formation of polysaccharides under simulated conditions. Scanning electron microscopy showed the delayed process of cell wall regeneration by simulated microgravity. The delayed regeneration of P. decumbens cell wall under simulated microgravity was likely caused by the inhibition of polysaccharide synthesis. This research contributes to the understanding of how gravitational loads affect morphological and physiological processes of fungi.     

分布式卫星嵌入式计算机系统结构设计方法

针对分布式卫星的运行环境和任务特点,综合考虑分布式卫星嵌入式计算机系统在可靠性、安全性和实时性方面的要求,提出了一种基于三级容错的主辅式双系统体系结构设计方法。论文分析了分布式卫星的特点和星上嵌入式计算机系统的设计要求,对三级容错设计、主辅式双系统安全设计以及基于可信平台模块(TPM)的辅系统设计进行了详细的阐述。该设计方法已成功应用于地面原理验证系统中,结果表明其可以很好地解决分布式卫星嵌入式计算机系统的可靠性、安全性和实时性问题。     

月球探测器软着陆机构

综述了月球探测器软着陆机构的应用与发展现状。介绍了软着陆机构的性能要求和组成,并根据着陆腿结构和缓冲器种类对软着陆机构进行了分类。讨论了着陆器主体设计、着陆腿结构和缓冲器的模块化设计。阐述了着陆器发射、在轨飞行、着陆和着陆后阶段的动力学研究内容。分析了缓冲器设计、着陆机构基本构型设计,以及缓冲器与基本构型主要参数配置等关键技术,对月球探测器软着陆机构设计有一定的参考意义。