应用OptiStruct软件的太阳翼基板结构优化

应用Altair OptiStruct软件独有的复合材料优化技术,针对非连续铺层复合材料,对某卫星太阳翼基板结构进行了优化设计。整个基板结构优化设计过程包括两个阶段：概念设计阶段和系统设计阶段。首先,在概念设计阶段利用自由尺寸优化模块,对太阳翼基板结构进行了拓扑优化;然后,在系统设计阶段利用尺寸优化模块完成了铺层厚度的优化。在经验设计方案中,太阳翼基板面板质量为3.6kg,经优化设计后,基板面板质量为1.7kg,减少了53%。     

Comment on “Subsurface water detection on Mars by astronauts using a seismic refraction method: Tests during a manned Mars simulation,” by V. Pletser et al.

Pletser et al. performed a seismic-refraction survey on Devon Island with the goal of assessing the feasibility of astronauts carrying out such operations on Mars to detect subsurface water. We demonstrate that the seismic analysis is fundamentally flawed. The survey performed in this test will likely bear little resemblance to future crewed geophysical surface operations, and better methods exist to detect subsurface water.     

亚燃燃烧室稳态工作过程数值研究

采用Fluent流场计算软件,对液体亚燃冲压发动机燃烧室的稳态工作过程,包括点火前的冷流场与点火后的两相反应流场进行数值模拟研究。首先,通过二维计算,对比研究两种不同阻塞比燃烧室方案的冷流损失特性与回流区特性,进行方案初选。随后,对选型后方案进行两相反应流场计算,研究燃烧室热态工作过程的温度场、燃油分布与燃烧效率的一般规律,比较并选择适合的燃油供应方案;最后,对燃烧室进行三维详细结构的建模并计算。计算结果很好地揭示了燃烧室内的流动和燃烧过程,与试验数据吻合较好。     

Biofeedback monitoring-devices for astronauts in space environment

After a reconsideration of the state-of-the-art in biofeedback research the implementation of biofeedback systems is envisioned as a countermeasure of stress for the psychoprophylaxis of the astronaut. A one-session experiment performed on two groups of subjects to assess the interference from EMG-feedback on the performance in a simultaneous psychomotor trial with a view to expanding biofeedback application is described. The results show that the experimental group performed in the same way as the control without feedback, but with less CNS activation. Some general conclusions are drawn from the advances in technology.     

火箭仪器舱仪器安装板的振动控制试验研究

本文在对长Ⅲ甲运载火箭仪器舱进行了试验模态分析的基础上，对长Ⅲ甲运载火箭仪器舱进行了可控约束阻尼层主被动一体化振动控制试验研究，研究结果表明，可控约束阻尼层结构对火箭仪器舱这一大型复杂结构进行振动控制是非常有效的。     

Geomagnetic effect of launches and flights of large spacecraft

The results of observations of variations in the geomagnetic field that accompanied launches and flights of rockets of different types have been analyzed. The launches were performed in 2002–2010 from different space launch facilities of the world (237 events in total), and variations in the range of periods 1–1000 s were studied. Measurements were performed near the city of Kharkov (distance from the spaceports ranges from 1500 to 9500 km). Statistical analysis and spectral estimations have been made, and three groups of disturbances were revealed. Time delays and disturbance durations increased with increasing distance from spaceports. Typical periods were equal to 6 to 14 min, while amplitudes varied in the range 1–3 nT.     

Thermomechanical behaviour of CFRP tubes for space structures

Carbon fiber reinforced plastic (CFRP) tubes, with the increasing dimensions and performances requested for space structures, are becoming a basic building element of boom-type structures for large precision reflectors, towers and payload support structures such as the Modular Payload Support Structure, the Shuttle Pallet Satellite or the European Retrievable Carrier. It is very important for such applications that the CFRP tubes have minimum thermal distortions and very high stiffness.An extensive test program was performed to characterise the CFRP tubes that are used for such applications. Measurements of coefficient of thermal expansions, thermal conductivity, thermal cycling, microstructure behaviour, as well as mechanical tests and outgassing tests were performed. The main purpose was to correlate the microcracking with the thermal cycling and the coefficient of thermal expansion and thermal conductivity.These types of activities for the CFRP tubes were performed for the first time in Europe and important results were found, especially in the area of microcracking generation and correlation with engineering parameters. The influence of the thermal cycling speed on the microcracking was also studied. Most of the tests were conducted at ESTEC (European Space Research & Technology Centre, Holland) by the European Space Agency in the frame of the technology research activities.     

基于嵌入式MATLAB函数编程的火星车能量平衡仿真系统

在以往航天器研制过程中,电源系统能量平衡分析是基于表格化计算的方法,其运算效率低、显示不直观。文章提出了一种可视性强、易编程、更通用的能量平衡分析方法,即采用嵌入式MATLAB函数对电源系统能量平衡分析的功能模块进行编程实现,以火星车电源系统为应用背景,在MATLAB/SIMULINK平台上搭建了一套用于能量平衡分析的仿真系统,并在特定实例下进行仿真分析,仿真结果采用图表曲线形式显示,能清晰、直观地反映能源利用的动态变化趋势,可为电源系统方案优化设计提供参考依据。     

SFMEA方法在飞行控制软件中的应用

为提高飞行控制软件的安全性,分析了飞行控制软件的安全性薄弱环节,探讨了影响飞行控制软件安全性的隐患。简要阐述了软件失效模式、影响(SFMEA)方法,给出软件失效模式分类的方法以及飞行控制软件常见的失效模式,给出适用于航天飞行控制软件的软件危害性等级,结合某型号飞行控制软件进行了SFMEA方法的尝试性应用,分析了软件失效的局部影响和最终影响,形成了52个SFMEA的分析表格,总结了302个飞行控制软件的失效模式,发现了部分安全性薄弱环节,并提出了相应的改进措施,结果表明,SFMEA方法对提高飞行控制软件的安全性有一定的工程价值。     

锥面共形阵列相干源DOA和极化参数的联合估计算法

针对共形阵列中的多参数联合估计问题,用交叉电偶极子对天线单元在锥面共形载体上构造极化敏感阵列并建立了快拍数据模型,在此基础上提出一种适用于相干源的多参数联合估计算法。该算法充分挖掘阵列中隐含的多个空域旋转不变结构,首先通过空间平滑预处理恢复子阵协方差矩阵的秩,实现信源的解相干,然后根据旋转不变子空间思想完成多个相干信源二维到达角和极化参数的联合估计。Monte Carlo仿真结果表明了算法的有效性。     

宽频带垂直极化天线的研究

为适应跳频通信等宽频带系统的要求 ,设计一种仙人掌式的宽频带天线。用多端口网络理论分析该天线的阻抗特性 ,阐明该天线能够实现宽频带工作的原理。利用 Ansoft公司的 HFSS仿真工具对天线进行仿真设计 ,并对天线进行了测试 ,实测结果与仿真结果相吻合。研究了地对天线性能的影响。地的直径分别为 3 0 mm、2 0 0 mm、3 0 0 mm时 ,该天线 VSWR小于 2的相对阻抗带宽超过 3 4%。地对天线辐射方向图有着显著影响 ,通过选择地的大小可以获得所需的方向图     

周边式桁架可展开天线的形面调整

本文针对周边式桁架可展开天线进行了基于优化方法的网面调整。以纵向调节索调节力的大小为设计变量，网状反射面的均方根误差为目标函数，应力和频率为约束条件，建立了形面调整的优化数学模型，并用遗传算法对网面调整进行了优化、仿真。数值结果表明：基于优化方法的网面调整是可行的，对工程应用具有一定的指导意义。     

仿真软件YHSIM中“集中－混合”式数值积分技术

连续系统实时仿真软件ＹＨＳＩＭ中所采用的运用多种数值积分方法进行“集中一混合”式数值积分的积分程序的工作原理和实现技术,在本文中作了介绍。     

Study of vibration microaccelerations onboard the International Space Station

The results of studying vibration microaccelerations aboard the International Space Station are presented. The study was performed using the measurement data of the MAMS low-frequency and the SAMS high-frequency accelerometers. For the study, six intervals of measurements were selected, performed in 2005. During these intervals the station was flying in the standard orbital orientation, attitude control engines were not switched on, and the crew rested. Discrete and continuous spectra were analyzed on selected intervals. The most significant disturbances with the discrete spectrum (cyclic trends) have been found. Using the second order autoregression model, parameters of the most significant disturbances with the continuous spectrum were determined. This study was carried out as a part of the technical experiment “The ISS environment”.     

Numerical modeling of RadioAstron SRT temperature deformations

The results of modeling the thermal deformations of a space radio telescope’s reflecting surface are presented in the paper. Calculations were performed for the versions of the most unfavorable telescope illumination by the Sun.     

复杂形状壳体数控加工研究

应用UGCAM对复杂形状壳体进行机床仿真加工，避免了实际加工中存在的问题，提高了产品加工效率和质量，解决了以往壳体加工变形的问题。同时，为保证产品批次质量的稳定性，提出了采用可视化工艺文件的建议。     

提高电子仪器电磁屏蔽性能的方法

要提高电子仪器可靠性，对电磁干扰和抗干扰技术需要进一步研究。有关电子仪器电磁屏蔽的机理和设计方法在本文中作了介绍。     

Development of thermal protective seal for hot structure control surface actuator rod

For the Intermediate eXperimental Vehicle (IXV) the deflection of the highly loaded body flap is performed by an actuator system which is connected to the body flap by a rod. Besides the thermal and mechanical loads the sealing of the inner vehicle against the possible leaking hot plasma is an important issue whereby the special challenge for the design results from the spatial movement of the rod. This requires a design consisting of different parts and various materials in order to satisfy the mechanical flexibility and the resistance to the thermal and mechanical loads under the aspect of reusability. This paper describes the MT Aerospace approach for the thermal protection system for the actuator as presented for the critical design review of IXV. The design is presented and described including all necessary performed analysis steps toward such a design.     

载入航天器的热真空试验

文章概述了美国 NASA 约翰逊航天中心(JSC)进行“阿波罗”飞船热真空试验的经验,介绍了近年来中心在热真空试验设施(容器 B)中进行载人热真空试验的经验和有关技术问题。     

一种基于逆动力学极点配置的空间拦截末制导律

在本文中用逆动力学理论研究了一种空间末制导模型，用极点配置综合了伪线性系统，提出了一种非线性末制导律，并进行了数学仿真。