高超声速飞行器攻角特性数值研究

采用二维耦合隐式欧拉方程对高超声速飞行器内定常无粘流场进行了数值仿真,离散采用二阶迎风格式,分析了攻角变化(-10°~7°)对高超声速飞行器分别处于进气道关闭、发动机通流及发动机点火3种不同工作状态下飞行性能的影响。结果表明,当攻角在-10°~7°之间变化时,飞行器的升力系数和升阻比都是随着攻角的增大而不断增加;而俯仰力矩系数却是随着攻角的变化,先增大后减小;在进气道关闭时,随着攻角的不断增大,飞行器的阻力系数亦不断增加,在其他2种工作状态下,随着攻角的增大,飞行器的阻力系数是先减小,后增加,且变化较缓慢,但阻力系数在3种工况下总的趋势是随着攻角的增大而增大。     

卫星热设计中β角在不同轨道下的变化规律分析

阳光矢量与卫星轨道平面之间夹角是卫星热控设计中至关重要的一个设计参数,其不仅与到达卫星表面的阳光热流密度密切相关,也与到达卫星表面的地球反射热流密度密切相关。文章根据β角的变化规律将传统意义上的轨道分为了同步轨道和非同步轨道两种,并结合升黄赤经夹角的变化规律分析了不同轨道下β角的变化规律,以及相应的热设计特点。     

乘波器的参数化设计研究

开展变楔角参数化乘波器的研究.研究中考虑了粘性效应,分析了不同设计参数对乘波器气动性能的影响.对比MAXWARP乘波器设计结果和数值求解NS方程的结果,验证了变楔角参数化乘波器设计方法的正确性.分析了不同的设计参数对乘波器气动性能的影响,为研究复杂的乘波器设计和优化规律提供了一个途径.参数化乘波器设计可方便的控制乘波器的外形尺寸,使乘波器的应用性大大提高.     

Element and Isotopic Fractionation in Closed Magnetic Structures

Recent papers have suggested that the slow solar wind is a super-position of material which is released by reconnection from large coronal loops. This reconnection process is driven by large-scale motions of solar magnetic flux driven by the non-radial expansion of the solar wind from the differentially rotating photosphere into more rigidly rotating coronal holes. The elemental composition of the slow solar wind material is observed to be fractionated and more variable than the fast solar wind from coronal holes. Recently, it has also been reported that fractionation also occurs in 3He/4He. This may be interpreted in the frame-work of an existing model for fractionation on large coronal loops in which wave-particle interactions preferentially heat ions thereby modifying their scale-heights. This revised version was published online in June 2006 with corrections to the Cover Date.     

刚体飞行器大角度机动的反馈非线性化控制

研究了刚体飞行器大角度的姿态控制问题,采用四元数描述刚体姿态,建立了刚体姿态运动的数学模型。基于反馈非线性化技术,通过构造李雅普诺夫函数推导出标量增益的线性控制律和矩阵增益的非线性控制律。两种控制律不需要知道系统参数,对模型误差具有鲁棒性。理论分析和仿真结果表明,所求控制律对闭环系统具有全局渐近稳定性。     

卫星表面原子氧通量和遭遇量的计算及讨论

建立了一个较为理想情况下卫星表面原子氧通量和遭遇量的计算模式。在此基础上,着重讨论了轨道高度、太阳活动、飞行攻角及轨道倾角等因素对原子氧通量和遭遇量的影响。      

太阳能火箭发动机吸热/推力室流场及性能计算

首先对某大型太阳能火箭发动机(Solar Thermal Propulsion:STP)的实验情况,进行了结构分析和基本实验条件估算.然后利用FLUENT计算软件,采用等壁温模型,对其吸热/推力室的内部流动、传 热情况,以及STP的性能特征等进行了计算,计算结果与实验数据一致,这对STP的设计有重要的指导意义.     

1996-2003年大耀斑事件引起的TEC突然增强的统计分析

利用1996—2003年期间GOES卫星耀斑观测资料和国际GPS观测网的GPS—TEC资料分析X级大耀斑事件引起的电离层电子浓度总含量(TEC)的突然增强(SITEC)现象．对X射线耀斑等级、耀斑日面位置与SITEC的关系进行了分析．结果表明,两者都与SITEC现象的强弱有着一定的正相关性．在消除X射线耀斑等级、耀斑日面位置对电离层SITEC现象的影响后,进而分析了日地距离以及耀斑持续时间对电离层SITEC现象的影响．结果表明,日地距离和耀斑持续时间都是影响SITEC现象的重要参数,日地距离较近时发生的耀斑事件引起的SITEC现象较为强烈．另外,耀斑持续时间越长,SITEC现象越微弱,但是当耀斑持续时间继续延长时,SITEC现象的强弱逐渐趋于不再改变,最后在某值附近达到平衡．还对某些没有在电离层中引起明显SITEC现象的耀斑事件进行了讨论,发现了这类耀斑的一些特征．     

扩大并联机床工作空间方法的研究

针对机床坐标系和工件坐标系的关系,采用一致坐标系转台转角分解和非一致坐标系转台转角分解方法,从而达到扩大并联机床工作空间的目的。     

Artificial equilibrium points and bi-impulsive maneuvers to observe 243 Ida

In the restricted three-body problem, the traditional Lagrange points L₁ and L₂ are the only equilibrium points near the asteroid 243 Ida. The thrust generated by a solar sail over a spacecraft enables the existence of new artificial equilibrium points, which depend on the position of the spacecraft with respect to the asteroid and the attitude of the solar sail. Such equilibrium points generate new spots to observe the body from above or below the plane of motion. Such points are very good observational locations due to their stationary condition. This work provides a preliminary analysis to observe Ida through the use of artificial equilibrium points as spots combined with transfer maneuvers between them. Such combination can be used to observe the asteroid from more different points of view in comparison to fixed ones. The analyses are made for a spacecraft equipped with a solar sail and capable of performing bi-impulsive maneuvers. The solar radiation pressure is used both to maintain the equilibrium condition and to reduce the costs of the transfers and/or to create transfers with longer duration. This is a new aspect of the present research, because it combines the continuous thrust with initial and final small impulses, which are feasible for most of the spacecraft, because the magnitudes of the impulses are very low. These combined maneuvers may reduce the transfer times of the maneuvers in most of the cases, compared with the maneuvers based only on continuous thrust. Several options involved in these transfers are shown, like to minimize the fuel spent ($\mathrm{\Delta }\mathit{v}$) as a function of the transfer time or to extend the duration of the travel between the points. Extended transfer times can be useful when observations are required during the transfers.