高压大口径油气管道跨长计算

基于几何非线性,考虑当量轴向力(S₀)对管道挠曲的影响,提出了有或无固定墩单跨无补偿器管道强度计算方程。有固定墩跨越管道的设计计算是显式的。对于无固定墩两端埋地跨越管道,认为埋地管道的横向反力和轴向摩擦力分别与其横、轴向位移成正比,内力和变形计算最终可归结为两个非线性方程的求解,管道的自振固有频率可由特征方程数值解求得。提出了S₀为压力或拉力的显式判别式。并区分S₀为压力、零、拉力,列出内力、挠度、频率计算方程。介绍了静强度验算和动力设计的方法,给出了算例。     

不同威胁情况下无人机实时航路规划算法研究

针对无人机实时航路规划问题,分析安全影响威胁,建立了改进的威胁概率模型。在安全回避突发威胁的前提上,增加考虑了偏离预定航路飞行代价影响;以飞行总航程最短为目标建立了新的飞行模型。针对当前飞行航段出现单个突发威胁和多个处于不同排列情况的突发威胁(组)情况,给出了相应的最优航路分析;并设计了基于最短路思想的启发式算法。对三种场景进行算例仿真。仿真结果表明,模型和算法具有有效性和可行性,可以实时分析突发威胁,并规划出相对安全经济的实时航路。     

Dissipation and Distribution of Picarbutrazox Residue Following Spraying with an Unmanned Aerial Vehicle on Chinese Cabbage (Brassica campestris var. pekinensis)

We assessed the residual distribution and temporal trend of picarbutrazox sprayed by agricultural multicopters on Chinese cabbage and considered fortification levels and flying speeds. In plot 2, 14 days after the last spraying, the residues decreased by ~91.3% compared with those in the samples on day 0. The residues in the crops decreased by ~40.8% of the initial concentration owing to growth (dilution effect) and by ~50.6% after excluding the dilution effect. As the flight speed increased, picarbutrazox residues decreased (p < 0.05, least significant deviation [LSD]). At 2 m s⁻¹ flight speed, the residual distribution differed from the dilution rate of the spraying solution. The average range of picarbutrazox residues at all sampling points was 0.007 to 0.486, below the limit of quantitation −0.395, 0.005–0.316, and 0.005–0.289 mg kg⁻¹ in plots 1, 2, 3, and 4, respectively, showing significant differences (p < 0.05, LSD). These results indicated that the residual distribution of picarbutrazox sprayed by using a multicopter on the Chinese cabbages was not uniform. However, the residues were less than the maximum residue limit in all plots. Accordingly, picarbutrazox was considered to have a low risk to human health if it was sprayed on cabbage according to the recommended spraying conditions.     

Structure and Cytotoxicity of Novel Lignans and Lignan Glycosides from the Aerial Parts of Larrea tridentata

Previously, the authors conducted phytochemical investigations of the aerial parts of Larrea tridentata and reported triterpene glycosides and lignan derivatives. In continuation of the preceding studies, 17 lignans and lignan glycosides (1–17) were isolated, including seven new compounds (1–7). Herein, the structure of the new compounds was determined based on spectroscopic analysis and enzymatic hydrolysis. The cytotoxicity of 1–17 against HL-60 human promyelocytic leukemia cells was examined. Compounds 4–11 and 14–16 were cytotoxic to HL-60 cells, with IC₅₀ values in the range of 2.7–17 μM. Compound 6, which was the most cytotoxic among the unprecedented compounds, was shown to induce apoptotic cell death in HL-60 cells.     

基于无人机的超宽带通信链

在无人机通信中继模型的基础上,结合无人机的特殊工作环境,构建了无人机超宽带通信链路模型,并对其性能进行了Monte—Carlo仿真。重点分析了无人机中继模型中,由于无人机间的相互运动造成的多谱勒频移对超宽带通信链路性能的影响。     

基于数字摄影测量的结构面信息表征及应用研究

结构面的存在直接影响岩体的强度、变形特征及破坏机制。为探究夏甸金矿矿区结构面的存在对岩体力学参数和岩体质量情况的影响,利用数字摄影测量技术快速获取研究区域结构面几何信息,并通过三维建模、激光扫描技术以及VR-Platform虚拟现实平台实现了结构面二维几何信息的真三维表征。基于此,利用广义Hoek-Brown强度准则分析计算了各研究区域的岩体力学参数,并根据岩体基本质量指标BQ值进行了岩体质量分级评价。结果表明,夏甸金矿岩体力学参数指标和岩体质量指标均较好;矿体下盘距离矿体方向越远,岩体完整性系数和岩体力学参数越低;利用广义Hoek-Brown强度准则计算所得岩体力学参数除内摩擦角外数值均与前期试验所得数据基本一致,计算所得岩体内摩擦角度偏大的原因,可能是其未考虑结构面自身的颗粒直径和形态等对岩体内摩擦角的影响。     

基于Geolord-AT软件系统的数字空中三角测量

通过对Geolord-AT软件系统在自动空中三角测量中的应用研究,有效地降低了构网的系统误差,提高了加密的可靠性和精度。     

一种新的无人机系统级电磁兼容测试法

 分析了实际电磁环境对无人机的影响,得到对无人机造成伤害的电磁环境场强极限值在0.1~ 8×10³ MHz频段中为60～200 V/m。根据无人机中存在的辐射干扰和传导干扰的共性特征,得到无人机系统级电磁辐射极限场强在0.1～2×10³ MHz频段中为10～60 V/m。由此提出了一种具有实际可操作性的无人机电磁兼容测试法。依照军标GJB3567-99以及在实际飞行场地中进行测试,结果显示,通过该测试的无人机各机载设备工作正常。     

柔性膜微型扑翼飞行器气动力的数值研究

采用数值法计算了膜扑翼飞行器的气动力,并与实验结果进行了对比.将惯性力和刚性扑翼产生的气动力作为原始载荷,采用有限元法计算了膜扑翼的变形,分析了此变形引起的气动力的变化.与实验结果的对照表明,该计算结果有较好的可靠性.与刚性扑翼相比,膜扑翼对升力的影响不大,但是大大地增大了推力的正峰值,使得推力有较大的增加,从而改善了扑翼飞行器的气动性能.     

膜扑翼飞行器的变形研究

最近昆虫翼的变形成了研究热点,而扑翼飞行器的变形力学研究却几乎无人问津.然而,无论昆虫、鸟类还是扑翼飞行器在飞行时,翼的变形都是存在的,要精确计算翼扑动产生的气动力,必须考虑其变形.本文比较了导致变形产生的膜扑翼飞行器的惯性力和气动力在一个周期中的变化情况,发现它们的峰值比值为2左右,然后提出了在随体坐标系中的固支边界条件,采用有限元法计算了惯性力和气动力分别对变形的影响,发现扑翼飞行器的气动力对变形的影响是不可忽略的重要因素,而惯性力与气动力的合力引起的最大正变形发生在下扑初始阶段,最大负变形发生在上扑初始阶段.本文为扑翼飞行器的设计提供了力学分析基础.