O2 evolution and cyclic electron flow around photosystem I in long-term ground batch culture of Euglena gracilis

Based on the purpose of better exploring the function of green producers in the closed aquatic biological life support system, the condition of dynamic O₂ evolution and performance of cyclic electron flow around photosystem I (CEF-PSI) in long-term ground batch culture of Euglena gracilis were studied, the relationship between linear electron flow (LEF) and CEF-PSI was revealed, the function of CEF-PSI was investigated. Excellent consistency in O₂ evolution pattern was observed in cultures grown in both closed and open containers, O₂ evolution was strictly suppressed in phase 1, but the rate of it increased significantly in phase 2. CEF-PSI was proposed to be active during the whole course of cultivation, even in the declining phase 3, it still operated at the extent of 47–55%. It is suggested that the relationship between LEF and CEF-PSI is not only competition but also reciprocity. CEF-PSI was proposed to contribute to the considerable growth in phase 1; it was also suggested to play an important protective role against photosystem II (PSII) photoinhibition at the greatly enhanced level (approximately 80–95%) on the 2nd day. Our results in this research suggest that E. gracilis had very particular photosynthetic characteristics, the strict O₂ evolution suppression in the initial culture phase might be a special light acclimation behavior, and CEF-PSI could be an important mechanism involved in this kind of adaptation to the changeable light environment.     

Orbit determination by genetic algorithm and application to GEO observation

This paper demonstrates an initial orbit determination method that solves the problem by a genetic algorithm using two well-known solutions for the Lambert’s problem: universal variable method and Battin method. This paper also suggests an intuitive error evaluation method in terms of rotational angle and orbit shape by separating orbit elements into two groups. As reference orbit, mean orbit elements (original two-lines elements) and osculating orbit elements considering the J2 effect are adopted and compared. Our proposed orbit determination method has been tested with actual optical observations of a geosynchronous spacecraft. It should be noted that this demonstration of the orbit determination is limited to one test case. This observation was conducted during approximately 70 min on 2013/05/15 UT. Our method was compared with the orbit elements propagated by SGP4 using the TLE of the spacecraft. The result indicates that our proposed method had a slightly better performance on estimating orbit shape than Gauss’s methods and Escobal’s method by 120 km. In addition, the result of the rotational angle is closer to the osculating orbit elements than the mean orbit elements by 0.02°, which supports that the estimated orbit is valid.     

Simulation software for the spiral trajectory of our Moon

At 4.56 Ga, the accretion of the slowly rotating Solar Nebula led to the formation of Sun and its Planets in the plane of disc of accretion. Moon was formed by accretion from a circumterrestrial disk of debris generated by the glancing angle impact of the young Earth by a Mars size planetary embryo at about 4.5 Ga at a distance of 15,000 km. The Moon since then has migrated to the present position of 384,400 km from the center of the Earth. In course of this outward migration it has slowed down the spin rate of Earth and caused the lengthening of diurnal day length from 5 h initially to 24 h presently. The basic mechanics of Earth–Moon System has been worked out and theoretical determination of lengthening of day curve is carried out. This theoretical lengthening of day curve is compared with the observed lengthening of day curve based on paleobotanical evidences, ancient tidalites and Australian Banded Iron Formation. There is a remarkable correspondence between the two curves except for intermittent deviations due to geographical and geophysical factors. Based on the theoretical curve of lengthening of day, an empirical formula for the lunar orbital radius expansion is determined. Based on this empirical formula, simulation software is developed that gives the correct evolution of the semi-major axis (a) of our Moon for any time span from the inception to the time chosen under study. For mathematical simplicity the system is considered to be a two body rotating system throughout its evolutionary history of 4.5 Gyrs. This simulation draws the Moon’s spiral trajectory from its inception to any subsequent epoch. The terminal epoch is an input to the simulation software to arrive at the spiral trajectory of the Moon from the inception to the given epoch. The basic mechanics of Earth–Moon System and this simulation can be generalized to lay the foundation of simulation software for any Planet–Satellite pair or any Sun-Planet pair in our Solar System or Star-Planet pair in any Extra-Solar System. The basic dynamics has been found to be valid for Star–Planet pair also. So this Simulation Methodology can as well be applied to study the migratory evolution of Gas Giants also.     

树脂交联结构特征对复合材料纵向压缩性能的影响

通过选择不同官能度的环氧树脂,调节树脂单体配比,获得了不同固化交联结构的环氧树脂基体,并与国产T800级碳纤维复合制备成碳纤维复合材料;研究不同交联结构的环氧树脂基体对其 T800级碳纤维复合材料纵向压缩性能的影响。研究结果表明,随着三官能团树脂含量升高,树脂基体的交联密度增大,树脂基体模量增大,其对应碳纤维复合材料单向层合板泊松比降低;碳纤维复合材料的纵向压缩强度随着树脂基体交联密度的增大而增大;树脂基体交联密度对单向复合材料层合板纵向压缩模量的影响不明显。     

基于Kane方法的直升机-柔性绳索-吊挂系统动力学建模

完成了基于Kane方法的直升机-柔性绳索-吊挂系统的动力学建模.通过运动学描述,将系统分为直升机本体、吊挂绳索和吊挂载荷三部分.直升机本体为六自由度刚体;吊挂绳索模拟为集中质点模型,质点间用弹簧连接;吊挂载荷模拟为三自由度质点.考虑重力、气动力和弹性力的影响,建立直升机-吊挂系统的Kane动力学方程.针对直升机本体和考虑吊挂绳索柔性的直升机-柔性绳索-吊挂系统这两种模型,计算了它们在不同前飞速度下的配平状态,分析了其运动模态并进行对比.仿真结果表明:外吊挂引入后,直升机需要额外的总距操纵;考虑吊挂绳索柔性后,直升机长周期运动的收敛/发散速度变慢;Kane方法适用于直升机-柔性绳索-吊挂系统的动力学建模,方程整齐简洁,编程求解方便.      

BA9916-Ⅱ/CCF300复合材料加筋板吸湿特性

为研究BA9916-II/CCF300复合材料加筋板的吸湿特性,在70℃/85%RH湿热环境中开展了吸湿实验,提出了基于厚度划分的Fick吸湿模型M_t=∑ni=1v_i[G_iM_(∞i)+M_(0i)(1-G_i)],并采用质量扩散模块进行了吸湿行为的有限元仿真。结果表明:提出的基于厚度划分的Fick吸湿模型能较好地描述该型结构的吸湿行为,具有较高的分析精度;但由于复合材料加筋板在吸湿后期存在阶段吸湿现象,Fick吸湿模型在该结构吸湿行为后期的描述上存在一定偏差;有限元仿真得到的吸湿动力曲线和水浓度分布结果验证了基于厚度划分吸湿模型的合理性,更好地还原了真实的吸湿过程与水分分布情况。     

基于Kane方法的双旋弹飞行动力学建模及仿真

针对双旋弹飞行动力学建模,提出了基于Kane方法建立树形多刚体系统动力学方程的方法.分析了双旋弹后体和前体的运动,并分别建立了其动力学方程,综合得到了双旋弹的七自由度飞行动力学方程.基于四元数转换,建立了双旋弹转动运动学方程.通过编程对双旋弹的无控和有控运动特性进行了仿真分析.结果表明,双旋弹无控时以小迎角稳定飞行;有控飞行时弹体产生配平迎角,且纵向和横向修正会出现交叉耦合.     

X-ray, γ-emission and energetic particles in near-Earth space as measured by CORONAS-F satellite: From maximum to minimum of the last solar cycle

The Russian solar observatory CORONAS-F was launched into a circular orbit on July 31, 2001 and operated until December 12, 2005. Two main aims of this experiment were: (1) simultaneous study of solar hard X-ray and γ-ray emission and charged solar energetic particles, (2) detailed investigation of how solar energetic particles influence the near-Earth space environment. The CORONAS-F satellite orbit allows one to measure both solar energetic particle dynamics and variations of the solar particle boundary penetration as well as relativistic electrons of the Earth’s outer radiation belt during and after magnetic storms. We have found that significant enhancements of relativistic electron flux in the outer radiation belt were observed not only during strong magnetic storms near solar maximum but also after weak storms caused by high speed solar wind streams. Relativistic electrons of the Earth’s outer radiation belt cause volumetric ionization in the microcircuits of spacecraft causing them to malfunction, and solar energetic particles form an important source of radiation damage in near-Earth space. Therefore, the present results and future research in relativistic electron flux dynamics are very important.     

飞必冲天 学行世界——飞院精神探讨

大学精神是一所大学的灵魂和根基,是大学文化的积淀和提炼。飞院精神传承自飞院特殊历史,滋养于飞院长期文化积淀。"飞必冲天,学行世界"是飞院精神基于大学精神共性——科学精神与人文精神的个性表达,蕴涵着飞院人的共同理想信念、价值追求、精神传统、行为规范和文化特色,将飞院精神特有的使命元素(勇敢担当,科学践行)、安全元素(人本关怀,科技保障)、飞行元素(和谐美善,执着求真)、时代元素(开放创新,卓立民航)融为一体,表达了飞院精神是科学精神和人文精神的融合,是科学精神和人文精神的实践的深刻内涵,体现了飞院精神是大学精神的本质。     

基于随机与区间分析的状态方程不确定性比较

基于现代控制理论中状态方程的求解算法,对具有参数不确定性的控制系统采用非概率区间分析方法与随机控制理论进行研究。首先明确实际工程应用中不确定性的概念和影响,分别建立了区间值和随机过程2种描述方法,求解系统的响应区间,并分为与初始条件和输入相关的零输入和零状态两部分不确定量。根据区间数学中的区间函数扩张原理和概率统计理论中的切比雪夫不等式,从数学证明和数值计算2个方面,分别用非概率区间分析和概率统计方法求解不确定系统的响应,并对二者进行比较,分析其相容性。结果表明,在由概率统计信息得到不确定性变量的区间向量为系统输入的情况下,非概率区间分析方法得到的响应区间包含由随机控制理论得到的响应区间。