Powered-descent trajectory optimization scheme for Mars landing

This paper presents a trajectory optimization scheme for powered-descent phase of Mars landing with considerations of disturbance. Firstly, θ–D$\theta ''–''D$ method is applied to design a suboptimal control law with descent model in the absence of disturbance. Secondly, disturbance is estimated by disturbance observer, and the disturbance estimation is as feedforward compensation. Then, semi-global stability analysis of the composite controller consisting of the nonlinear suboptimal controller and the disturbance feedforward compensation is proposed. Finally, to verify the effectiveness of proposed control scheme, an application including relevant simulations on a Mars landing mission is demonstrated.     

基于符号计算的风洞试验测量不确定度评估

基于符号计算进行风洞试验测量不确定度分析可以实现实验数据处理公式及误差灵敏度系数的自动推导 ,采用该方法对ZSDD 1导弹标模风洞试验结果进行了定量的试验不确定度评估 ,计算得到的气动力系数精度极限与重复性试验得出的试验精度吻合良好 ,气动力系数偏离极限计算值通常是其精度极限的 3～ 4倍 ,其不确定度大约是其精度极限的 4倍。笔者所述分析方法和分析程序为定量评估风洞试验数据的可靠性提供了一种有效手段。     

Nonlinear H∞ based underactuated attitude control for small satellites with two reaction wheels

Underactuated attitude control is supposed to be used on spacecraft when failure happens with onboard actuators. One main problem with existing underactuated attitude control designs is their limited capabilities against disturbances. In order to solve this problem, an approach based on the theory of H∞$H\infty$ is proposed in this paper. Two propositions are derived from the H∞$H\infty$ theory to improve the robustness of one popular underactuated attitude control design, which was presented by Tsiotras et al. It is proved mathematically that the controller satisfying these two propositions respectively can stabilize the underactuated attitude system locally or globally. The numerical simulations show that the improved controllers based on the H∞$H\infty$ theory could provide higher pointing accuracy for small satellites against disturbances. This validates the effectiveness of the proposed H∞$H\infty$ based approach to improve existing underactuated attitude control designs.     

情报研究成果的AHP-F评价

本文采用层次分析法与模糊数学综合译判法相结合的方法——AHP-F法,提出了综合情报评判研究成果指标体系和方法,旨在实现对情报研究成果的科学有效的管理。     

计算物理中的数学实验方法

论述了计算物理与数学实验的关系,以及数学实验对计算物理的重要性,并通过实例说明,利用数学实验方法可以简化计算,突出物理概念,使问题得到更好的解决。     

基于因子分析和模糊数学方法的公司内在价值评价的实证研究

本文对公司内在价值作了定义 ,系统分析了影响公司内在价值的因素 ,并建立了评价指标体系 ;设计了两种分别基于因子分析法和模糊数学方法的内在价值综合评价方法 ;最后选择了纺织板块上市公司作实证分析 ,比较了两种方法的优劣     

Global electric circuit modulation of winter cyclone vorticity in the northern high latitudes

Small changes in extended winter (November–March) 500 hPa vorticity area index (VAI) values for the 60–80°N latitude band are shown to be positively correlated with changes in a proxy for the high latitude ionosphere-to-surface current density _Jz$J_z$.     

Physics of ion acceleration in the solar flare on 2005 September 7 determines γ-ray and neutron production

Relativistic neutrons were observed by the neutron monitors at Mt. Chacaltaya and Mexico City and by the solar neutron telescopes at Chacaltaya and Mt. Sierra Negra in association with an X17.0 flare on 2005 September 7. The neutron signal continued for more than 20 min with high statistical significance. Intense emissions of γ-rays were also registered by INTEGRAL, and during the decay phase by RHESSI. We analyzed these data using the solar-flare magnetic-loop transport and interaction model of Hua et al. [Hua, X.-M., Kozlovsky, B., Lingenfelter, R.E. et al. Angular and energy-dependent neutron emission from solar flare magnetic loops, Astrophys. J. Suppl. Ser. 140, 563–579, 2002], and found that the model could successfully fit the data with intermediate values of loop magnetic convergence and pitch-angle scattering parameters. These results indicate that solar neutrons were produced at the same time as the γ-ray line emission and that ions were continuously accelerated at the emission site.     

考虑弹体弹性的导弹半物理仿真方法与影响分析

随着对导弹速度和精度等性能要求的提高,弹性特性已成为导弹动力学分析与设计中不可忽略的因素。弹性振动将对导弹的飞行特性和控制精度产生较大的影响。因此,在对弹性体导弹进行半物理仿真时,考虑弹体弹性振动所产生的影响,有利于提高仿真的真实度。本文发展了考虑弹体弹性的导弹飞行动力学数学仿真框架,建立了弹性体导弹半物理仿真系统各环节的数学模型,实现了半物理环节动力学模型在数学仿真框架中的集成与一体化仿真,并在此基础上分析了弹性振动和仿真设备在弹性体导弹半物理仿真中的影响,数值仿真结果表明,研究结果可以为考虑弹体弹性的导弹半物理仿真提供一定的理论基础。