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不等边基四边形的等距曲线设计

根据等距曲线的成形原理和几何特性,讨论了在有条件下的不等边基四边形等距曲线设计以及基四边形边长和形状的变化对等距曲线的影响,阐述了等距曲线的图形设计原则、轮廓曲线作图方法并加以证明,从而确定了不等边基四边形的设计作图范围和应用特性,扩展了机械传动机构型面联接中的等距曲线设计途径和方法。     

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??GNSS??????????У??轫GNSS?????????????????????????????????????????GNSS???????????????????????????????????????????????????????????????????????????????????????????????????????????????е???????????????????????е????λ???ó????????????????????????????????????????????????????????????????о???GNSS????????????????????????????????????????????????????????????????????????????????????????????????????????????     

A tangential wind profile for simulating strong tropical cyclones with MM5

A new tangential wind profile for simulating strong tropical cyclones is put forward and planted into the NCARAFWA tropical cyclone bogussing scheme in MM5. The scheme for the new profile can make full use of the information from routine typhoon reports, including not only the maximum wind, but also the additional information of the wind speeds of 25.7 and 15.4 ms^-1 and their corresponding radii, which are usually provided for strong cyclones. Thus, the new profile can be used to describe the outer structure of cyclones more accurately than by using the earlier scheme of MM5 in which only the maximum wind speed is considered. Numerical experimental forecasts of two strong tropical cyclones are performed to examine the new profile. Results show that by using the new profile the prediction of both cyclones‘ intensity can be obviously improved, but the effects on the track prediction of the two cyclones are different. It seems that the new profile might be more suitable for strong cyclones with shifted tracks. However, the conclusion is drawn from only two typhoon cases, so more cases are needed to evaluate the new profile.     

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谱线分析法测定ζAur型系统的 红巨星星风物质损失

用双星技术（Binary-technique）的谱线分析方法来测定双星系统中的红巨星或红超巨星的星风物质损失率是目前最为精确的。扼要介绍了此类方法的一般原理以及在ζAur/VVCep双星系统的物质损失测量中的应用。同时介绍了该方法的最新进展,并展开与此有关的一些简要讨论。     

研究太阳分离活动体光谱不对称轮廓的“多云模型”方法和应用

本文提出了处理分离的太阳活动体光谱不对称轮廓的一种方法──“多云模型”方法。在某些假设和一定的近似条件下利用本文提出的方法可同时得到太阳多个分离活动体的视向速度Ｖ，多普勒线宽△λ_Ｄ和线心光学深度τ_０，源函数Ｓ的近似值。文章给出了该方法的几个应用实例并进行了讨论。研究表明，计算所得的Ｖ和△λ_Ｄ的值是较为可靠的，二云模型是处理由两个分离活动体沿视线重叠而产生的不对称轮廓较为有效的方法。     

Effect of perturbation on the location of libration point in the robe restricted problem of three bodies

The effect of small perturbation in the Coriolis and centrifugal forces on the location of libration point in the ‘Robe (1977) restricted problem of three bodies’ has been studied. In this problem one body,m ₁, is a rigid spherical shell filled with an homogeneous incompressible fluid of densityϱ ₁. The second one,m ₂, is a mass point outside the shell andm ₃ is a small solid sphere of densityϱ ₃ supposed to be moving inside the shell subject to the attraction ofm ₂ and buoyancy force due to fluidϱ ₁. Here we assumem ₃ to be an infinitesimal mass and the orbit of the massm ₂ to be circular, and we also suppose the densitiesϱ ₁, andϱ ₃ to be equal. Then there exists an equilibrium point (−μ + (ɛ′μ)/(1 + 2μ), 0, 0).     

Artificial halo orbits for low-thrust propulsion spacecraft

We consider periodic halo orbits about artificial equilibrium points (AEP) near to the Lagrange points L ₁ and L ₂ in the circular restricted three body problem, where the third body is a low-thrust propulsion spacecraft in the Sun–Earth system. Although such halo orbits about artificial equilibrium points can be generated using a solar sail, there are points inside L ₁ and beyond L ₂ where a solar sail cannot be placed, so low-thrust, such as solar electric propulsion, is the only option to generate artificial halo orbits around points inaccessible to a solar sail. Analytical and numerical halo orbits for such low-thrust propulsion systems are obtained by using the Lindstedt Poincaré and differential corrector method respectively. Both the period and minimum amplitude of halo orbits about artificial equilibrium points inside L ₁ decreases with an increase in low-thrust acceleration. The halo orbits about artificial equilibrium points beyond L ₂ in contrast show an increase in period with an increase in low-thrust acceleration. However, the minimum amplitude first increases and then decreases after the thrust acceleration exceeds 0.415 mm/s². Using a continuation method, we also find stable artificial halo orbits which can be sustained for long integration times and require a reasonably small low-thrust acceleration 0.0593 mm/s².