高分七号卫星结构尺寸稳定性设计与验证

尺寸稳定性是高分七号卫星(GF-7)结构设计的重要使命。针对GF 7结构尺寸稳定性设计需求,开展了影响因素分析,并针对分解指标给出了适用于航天器结构的尺寸稳定性设计和验证流程。首先,在整星结构构型设计的基础上,通过灵敏度分析确定了结构选材方案。随后,针对尺寸稳定性关键件一体化支架,提出了热控设计和结构设计方案。最终,通过舱段级热稳定性试验获得了结构平均热膨胀系数等结构稳定性关键参数,利用经试验结果修正后的有限元模型开展了卫星在轨热变形分析并验证了指标的可实现性。结果表明,GF-7结构设计满足载荷安装面指向变化亚角秒级的尺寸稳定性指标要求。     

深空天文测角测速组合自主导航可观测性分析方法

导航系统的性能与其可观测性密切相关,而可观测矩阵是分析导航系统可观测性能的重要依据。本文基于分段线性定常系统(PWCS)方法给出导航系统的可观测矩阵,进而针对测角测速组合导航系统开展可观测性分析。通过分析测角测速组合导航系统可观测矩阵的秩和条件数,得到导航系统的可观测性和整体可观测度,并研究导航系统的可观测阶数对导航系统的影响;同时基于奇异值分解(SVD)方法给出测角测速组合导航系统各个状态分量的可观测性分析方法。最后,以小行星探测工程任务巡航段为背景,系统地给出了不同量测模型的导航系统可观测性结果,分析了不同可观测性分析方法对导航系统可观测性刻画的适用性。本文所提出的可观测性分析方法,对导航系统可观测性分析具有很好的参考性,可为组合导航系统量测模型的优选提供参考,具有良好的理论和应用价值。     

精密离心机动态半径采集系统的设计

本文介绍了精密离心机动态半径采集与处理系统的设计。该系统通过串口接收下位机采集的数据,经过处理的数据在上位机界面以实时曲线的方式显示。本系统基于VC环境下设计实现,可实现离心机动态半径的在线检测,具有良好的实用性和直观性。     

Sq(H) field variations at Sonmiani geomagnetic observatory,Pakistan for solar cycle 24

In this study, Sq(H) field results for Sonmiani geomagnetic observatory (SON), Pakistan are presented first time for solar cycle i.e., Solar Cycle 24. Sonmiani observatory was established in 2008 and was included in the list of INTERMAGNET Magnetic Observatory (IMO) in 2012. The analysis of Sq(H) field is performed to examine diurnal, annual and seasonal behaviour of Sq(H) field at Sonmiani along with Honolulu which is used as reference observatory. Both the observatories lie at the Equatorial Ionisation Anomaly (EIA) crest. In general strong dependency of Sq(H) field on solar cycle has been observed. First peak of SC24 was visible in Sq(H) field at both observatories. However, at HON maximum Sq(H) was observed in 2015 instead of 2014, a year later than the year of solar maximum. Prominent longitudinal difference has been noted between both observatories. At HON, maximum Sq(H) was observed during equinox while at SON it was noted during equinox and summer as a consequence of shift in latitude of Sq focus. Phase shift of Sq(H) at SON followed a general trend, that is maximum Sq(H) shifted to later hours in solar maximum as compared to solar minimum. Whereas, an opposite trend was noted at HON which might be due to coastal effect. In case of seasonal phase shift, at both observatories maximum Sq(H) occurred at later hours in summer than in winter which is opposite to the results obtained by many workers. These points need further investigation and geomagnetic as well as wind, and electric field data of other observatories situated at the EIA crest region is required to interpret the Sq(H) phase shift extensively.     

Encounter trajectories for deep space mission ASTER to the triple near Earth asteroid 2001-SN263. The laser altimeter (ALR) point of view

In cooperation with Russia, the Brazilian deep space mission ASTER plans to send a small spacecraft to investigate the triple asteroid 2001-SN263. The nearest launch opportunities for this project include June 2022 and June 2025. One main exploration campaign is being planned with focus on the largest asteroid (Alpha). Among the instruments under development, a laser altimeter (named ALR) was preliminarily designed and presented in 2010–2011. Many studies to define mission and instruments requirements were performed aiming at the characterization of important issues for the successful realization of the mission. Among them, the identification of a suitable trajectory that could be followed by the ASTER spacecraft in the encounter phase, when the main campaign will take place. This paper describes the effort undertaken with focus on the laser altimeter operation. Possible encounter trajectories were modelled and simulated to identify suitable approach parameters and conditions allowing the accomplishment of the intended investigation. The simulation also involves the instrument operation, considering approach geometry, attitude, relative motion, time/date, and the dynamics of the main asteroid. From the laser altimeter point of view, keeping in mind the desired coverage results (50% minimum surface coverage of asteroid Alpha, complying with horizontal and vertical resolution requirements), results point out crucial features for the encounter trajectory, like the need for a small inclination (10^-6 degrees; with respect to the asteroid's orbit), the most favourable spacecraft positioning (between the Sun and the asteroid) and pointing condition (back to the Sun), the minimum amount of achievable surface coverage (58%, focused on central areas), and the most proper time to conduct the main campaign (January 2025). Concerning the instrument, results offer refined values for divergence angle (500 to 650 μrad, half-cone), pulse repetition frequencies (from 1/20 to 1 Hz), and consequent data generation rates. A simulation tool that can use any 3D generated trajectories as input data was created for the analyses presented here. Although created for the ALR in this mission, this simple analysis tool can be adapted to other instruments in this or other missions.     

基于FAA25-131修正案的飞机告警系统适航问题分析

FAA25.1322规定了飞机警告灯、戒备灯和提示灯颜色的使用要求。FAA25-131修正案在原有14CFR25.1322条款的基础上,对飞行显示与机组告警系统提出了新的要求。本文对该修正案进行分解与分析,明确了修正案要求的重点考虑事项,简单、客观地呈现了与这些条款项关联的技术问题的矛盾性争辩过程,进行了基于型号研制实践的符合性方法总结,为验证民用飞机飞行显示与机组告警系统对FAR25-131修正案的符合性提供了有效途径,具有工程实践意义。     

Spatial asymmetry in topside ion density and vertical E × B plasma drift velocity within 75°E–95°E

The ion density measured by the Ionospheric Plasma and Electrodynamics Instrument (IPEI) on board the ROCSAT -1 over the 75°E and 95°E meridian at 600km altitude has been utilized to examine the latitudinal and longitudinal distribution within the Indian sector, in particular, the north-south and east-west asymmetries of the equatorial ionization anomaly (EIA). A longitudinal gradient in ion density at 600?km higher towards 95°E develops during the noontime and afternoon hours when the EIA is at its peak. The density gradient persists till evening hours when pre-reversal enhancements occur. The vertical E?×?B plasma drift velocity measured simultaneously by ROCSAT -1 for the same space-time configuration has also been studied. In addition to diurnal, seasonal and solar activity variations in E?×?B drift velocity, the longitudinal gradient is also observed. The EIA at the altitude of 600?km peaks at different latitudes and are mostly asymmetric about the magnetic equator. From midnight till 0800 LT, the ion density across the equator is nearly uniform in the equinoxes. But in the solstices, the density exhibits a north-south gradient. In the June solstice, density is higher in the northern hemisphere and decreases gradually towards south. The gradient in density reverses in December solstice. Normally, the EIA peaks within 1200 LT and 1600 LT while around 2000 LT, pre-reversal enhancement of ionization occurs affecting the EIA evening structure. The strength of the EIA also exhibits seasonal, year-to-year and hemispheric variations. The longitudinal asymmetry of drift velocity along 75°E and 95°E longitude sectors is the contributing factor behind the observed longitudinal asymmetry in ion density. Significant positive correlation between the strength of the EIA and E?×?B drift is observed in both longitudes.     

集装箱甩挂运输模型与应用

描述了集装箱甩挂运输的作业流程.从车辆等待时间的角度及集装箱甩挂运输的特点,分析了集装箱甩挂运输在不同情况的适用性问题.使用0-1决策变量来描述集装箱甩挂运输的各个操作流程,建立了以提箱次数、放箱次数、行驶次数、等待时间及各项操作流程的发生顺序为约束条件、以完成全部作业的总时间最短为目标函数的集装箱甩挂运输模型.通过算例分析,算出传统集装箱运输与集装箱甩挂运输的车辆等待时间,验证了集装箱甩挂运输模型的可操作性.     

农业转移人口市民化过程中地方政府行为激励问题研究——基于多任务委托代理模型

推进农业转移人口市民化的过程从本质上看是实现基本公共服务均等化的过程,而事实上,农业转移人口在享受公共福利方面与城市居民有着巨大的差别。现有体制下,地方政府作为提供公共产品的主要主体,同时面临着财政能力与体制的双重约束,从而在提供公共产品时表现出财力不足和意愿不足。文章主要是在已有研究的基础上,从地方政府意愿方面,基于一个多任务委托代理分析框架,研究在推进农业转移人口市民化过程中如何激励地方政府做出合理行为的问题,并尝试给出政策建议。     

C/C喉衬近净尺寸制备及性能

采用径向针刺工艺制备了近净尺寸针刺C/C喉衬预制体,通过热梯度CVI和树脂浸渍碳化复合工艺对预制体进行了致密,利用μ-CT、光学显微仪表征了C/C喉衬材料微观孔隙和热解碳织构,分析了喉衬材料的弯曲性能。结果表明,径向针刺过程形成的损伤型孔隙通道与碳源气体传输方向一致,提高了碳源气体传输效率,使径向针刺喉衬CVI增密效率比传统轴向针刺喉衬提高10.9%。预制体近净尺寸成型缩短了烧蚀区域碳源气体的渗透距离,喉衬材料烧蚀区域形成了高织构热解碳,有利于喉衬烧蚀性能的提高。径向针刺喉衬的轴向弯曲强度比轴向针刺喉衬提高150%。