天宫一号目标飞行器氢镍蓄电池压力-容量充电控制研究

作为在轨管理的关键部分,良好的充电控制是保证蓄电池长寿命的重要因素。对于氢镍蓄电池,压力-容量充电控制是最理想的充电控制方式,但存在压力检测难度大、控制策略复杂等困难。天宫一号目标飞行器氢镍蓄电池通过大量的压力测量地面可靠性试验,解决了压力传感器的测量稳定性及一致性问题;同时提出柔性充电控制策略,给出了压力-容量标准曲线、不同荷电态下的充电电流及压力控制点修正系数。在轨数据表明,天宫一号目标飞行器氢镍蓄电池压力-容量充电控制稳定,满足设计要求。     

周建平:天宫二号空间实验室将于2016年发射

<正>全国政协委员、中国载人航天工程总设计师、《载人航夭》主编周建平近日接受新华社记者专访时表示,天宫二号空间实验室将于2016年发射。天宫二号是在天宫一号目标飞行器备份的基础上,根据天宫二号的任务需要改装研制而成。周建平介绍说,天宫二号的发射准备工作进展顺利,它将用于验证空间站的技术,也将接受航天员的访问。他表示:"天宫二号入轨并完成在轨测试后,将与之后发射的神舟十一号飞船完成交会对接。航天员在天宫二号上生活的时间将比在神舟九号、神舟十号生活的时间更长。"     

天宫一号技术状态管理方法及工程实践

介绍了天宫一号地面研制和在轨飞行的技术状态管理方法,结合天宫一号工程实践,对该方法的应用进行了分析。结果表明,天宫一号研制过程中的技术状态管理方法适应工程实践的需要,在轨技术状态管理方法确保了飞行任务的成功。在天宫一号技术状态控制信息化及技术状态审核表格化管理的成果基础上,提出了后续载人航天器技术状态管理微观化和项目关联自动化的建议。     

天宫飞行器低轨控空气动力特性一体化建模与计算研究

对非规则板舱组合体天宫飞行器300~200 km低轨道飞行过程空气动力特性一体化计算建模,提出考虑复杂构型物面遮盖效应面元解析法与经修正的Boettcher/Legge非对称桥函数,发展基于三角形面元逼近复杂外形通用处理方法,建立适于天宫飞行器复杂物形处理与面元气动力系数计算规则;将DSMC方法与求解Boltzmann模型方程气体运动论统一算法应用于天宫飞行器简化外形,进行气动力当地化关联参数计算修正,建立针对大型复杂结构天宫飞行器低轨道飞行控制过程空气动力特性一体化快速算法与程序软件。对大尺度圆柱体外形与天宫飞行器300~200 km不同高度变轨飞行过程不同迎角与侧滑角及帆板平面与本体主轴不同夹角复杂构型气动力特性计算分析验证,表明天宫飞行器在200 km以上低轨道飞行控制过程中所受空气动力系数随飞行高度发生显著变化(8%~50%),证实长期在轨运行的大型航天器若采用统一固定的气动力系数,误差累积巨大,需要采取防护措施,低轨道飞控大气阻力仍是制约航天器定轨预报精度最关键因素。     

简讯

“神八”与“天宫”顺利对接 11月1日清晨，携带神舟八号飞船的长征二号F火箭顺利升空。两天之后，神舟八号飞船和天宫一号目标飞行器实现了刚性连接，形成组合体，这标志着中国突破了载人航天三大基础性技术的最后一项——空间交会对接。     

国际重要航天器交会对接记录

2011年11月3日凌晨,"天宫一号"目标飞行器与"神舟八号"飞船首次在太空成功进行了无人交会对接试验,使中国成为世界上第3个自主掌握并成功实施航天器空间交会对接技术的国家。     

类天宫飞行器轨道衰降过程空气动力特性一体化建模并行优化设计

针对天宫一号目标飞行器无控飞行轨道衰降数值预报需要快速确定轨道积分高精度计算模型中的空气动力,在发展基于修正Boettcher/Legge非对称桥函数的天宫一号空气动力特性当地化算法基础上,对当地化算法的运算流程及对应程序代码进行了整体分析,根据原程序热点代码集中、数据独立性强及传输需求少等特点,发展了多核处理单元的并行优化方法。引入CUDA架构的GPU设备同时,开展了系统、算法以及语句三个层次的并行优化,设计了GPU内存对齐访问方案,使用数据传输函数,将算法求解部分内循环经过展开与合并,整理为整体移植入核函数的一个循环,利用GPU较强的并行计算能力提升运算效率,对函数、循环、指令等代码语句进行级别优化。使用设计的并行计算方案对类天宫飞行器空气动力特性当地化串行算法程序进行CPU+GPU移植优化,达到了近5倍的并行加速比,且使单次求解中GPU数据传输时间缩减为原来的23%,证实了并行方案和优化设计手段的高效实用性。在类天宫飞行器空气动力特性GPU并行算法程序验证基础上,使用GPU并行程序对天宫飞行器轨道衰降飞行340～120 km过程的气动特性进行了不同迎角、侧滑角等飞行姿态计算分析,提供了大量可供轨道飞行力学数值预报的空气动力计算数据。     

天宫二号对地观测应用研究进展

天宫二号空间实验室在轨运行两年多的时间内,对地表、海洋和临近空间大气进行探测,获取了大批高质量遥感数据。针对天宫二号遥感数据的应用研究进展,总结了天宫二号3个对地观测载荷的主要应用技术指标,分析了所获取的多载荷遥感数据在国土资源、海洋及海岸带应用、湖泊监测、农业应用、生态环境和大气环境探测等多个领域的应用研究成果;对天宫二号遥感数据进一步扩大应用研究范围、数据定量化应用、多源遥感数据融合应用与智能化分析等进行了展望。     

交会对接平移靠拢段手控策略设计

以载人飞船与目标飞行器进行交会对接为背景,探讨了平移靠拢段的手动控制策略。载人飞船作为追踪飞行器,姿态控制采用自动控制的方式,而平移控制则以控制效能指标为依据,结合飞船轨道运动特性,采用手动控制的方式操纵飞船与目标飞行器对接,以此给出了轨道面内和垂直于轨道面方向的控制策略。仿真结果表明,使用平移手动控制策略,对接精度高、时间短、燃料消耗量少,可完成交会对接任务。     

为实现中华民族伟大复兴的中国梦谱写载人航天新篇章

2013年6月11日至26日,我国成功组织实施天宫一号与神舟十号载人飞行任务,圆满实现了“准确进入轨道,精准操控对接,稳定组合运行,健康在轨驻留,安全顺利返回”的任务目标,标志着我国载人航天工程第二步战略目标取得了重大阶段性胜利. 航天梦是中国梦的重要组成部分.我国载人航天工程的历史发展和成功业绩,是沿着中国特色社会主义道路正确前进的又一光辉印证.党中央、国务院和中央军委始终高度重视、十分关心载人航天工程,对工程建设给予了亲切关怀、倾注了大量心血.     

基于直流微电网的混合储能协调控制策略仿真研究

针对直流微电网中光伏发电单元出力的波动性和间歇性造成系统内部功率不平衡的问题,混合储能系统可以同时发挥蓄电池高能量密度和超级电容高功率密度的优势,根据直流母线电压进行混合储能单元间的协调控制策略。该策略将直流母线电压进行分层控制,采用四个电压阈值共分成五个控制区域,以直流母线电压为信息载体,决定储能系统的运行状态,实现对混合储能单元的充电、放电模式间自主切换。电压分层控制有效地避免了蓄电池由于电压波动而频繁进行充放电切换,从而延长了电池的使用寿命。最后,MATLAB/Simulink的仿真结果验证了所提控制策略的可行性。     

Fast intelligent battery charging: neural-fuzzy approach

This paper focuses on the design of a super fast battery charger based on National's proprietary neural network based NeuFuz technology. In this application, we have used a NiCd battery pack as the test vehicle. However, this technology can be extended to other chemistries such as Ni-MH, Li-ion, etc. This technology allows the designer to accurately model the charge controller using a neural network, based on battery charge characteristics provided by the manufacturer. This approach continuously monitors the battery status, and modifies the charge current accordingly. It also eliminates the need for standard charge termination methods used in today's conventional chargers. The result is super fast charging in 20 to 30 minutes, and increased battery life. A low cost embedded controller (COP8) performs all the fuel-gauging and charge control functions by processing data obtained from the battery circuitry     

Battery charge controller characteristics in photovoltaic systems

Typical strategies for battery charge regulation and load control in stand-alone photovoltaic (PV) systems are presented. Several charge algorithms (methods of controlling current to the battery) are presented, along with terminology used by the PV industry for battery charge controllers. Information gained from an extensive evaluation of commercially available charge controllers and data collected from tests on PV systems in the field are discussed. An overview of battery performance characteristics needed for the successful design and long-term operation of PV systems is presented with the intent of soliciting feedback on the information presented from the battery industry     

Hubble performance on-orbit

A summary of the Hubble Space Telescope (HST) nickel-hydrogen (NiH/sub 2/) battery performance from launch to the present. Over the life of HST vehicle configuration, charge system degradation and failures, together with thermal design limitations, have had a significant effect on the capacity of HST batteries. Changes made to the charge system configuration to protect against power system failures and to maintain battery thermal stability resulted in undercharging of the batteries. This undercharging resulted in decreased usable battery capacity as well as battery cell voltage/capacity divergence. This cell divergence was made evident during on-orbit battery capacity measurements by a relatively shallow slope of the discharge curve following the discharge knee. Early efforts to improve battery performance have been successful. On-orbit capacity measurement data indicates increases in the usable battery capacity of all six batteries as well as improvements in the battery cell voltage/capacity divergence. Additional measures have been implemented to improve battery performance, however, failures within the HST Power Control Unit (PCU) have prevented verification of battery status.     

Charge equalization for an electric vehicle battery system

Charge equalization for series connected battery strings has important ramifications on battery life. It enhances the uniformity of the battery cells and hence improves the life of the battery as a whole. A new charge equalization technique for a series string of battery cells has been recently proposed by the authors. The basic technique utilizes a simple isolated dc-to-dc converter with a capacitive output filter along with a multiwinding transformer. The possibility of integrating the trickle charge function with the charge equalization function is potentially very attractive, as it can lead to an efficient and low cost implementation     

Charge equalization for series-connected batteries

A novel nondissipative charge equalization circuit is proposed for charge equalization control of series-connected batteries. Each battery associates with a subcircuit, which is essentially a buck-boost converter acting as a current diverter to redistribute the excessive energy from more affluent batteries to the hungry ones. By dynamically redistributing the charging current, charge equalization can be achieved more quickly and efficiently. The applicability of this approach is confirmed by experiments.     

Integral Electronic Charge Controls for High Performance Secondary Batteries

Requirements and constraints of unattended secondary batteryapplications are outlined and translated into battery charge control designcriteria. Attention is given to battery performance and reliabilityrequirements and power system interfaces. Charge control requirementsents are defined. Implementation analyses and selection of integralcell-level electronic charge controls are detailed. Feasibility of thecharge control concepts are demonstrated and merits of integralelectronic cell-level battery controls are summarized.     

燃料电池无人机能源管理与飞行状态耦合

开展了燃料电池/锂电池（简称燃锂）混合动力无人机的能源管理与飞行状态耦合研究。综合顶层飞行任务规划与底层能源系统管理，以动力系统模型为耦合点联立能源系统与无人机运动方程，建立能源状态与运动状态耦合模型。针对燃锂混合最紧密的爬升过程，以迎角、转速和燃料电池的放电功率作为控制变量，建立了燃料消耗最小的能源管理与航迹规划耦合最优控制问题，研究不同爬升高度对最优控制过程的影响，并与模糊控制能源管理策略进行对比分析。针对大功率短时爬升和小功率长时巡航的典型任务特点，建立了燃锂最优混合问题。研究了最优的锂电池容量和燃料电池功率水平的混合量，以及爬升和巡航两阶段最优功率分配和飞行状态，分析了不同巡航目标高度对最优混合量和飞行状态的影响。结果表明：采用能源与航迹耦合的最优控制策略在给出最优功率流分配的同时，能够很好地兼顾飞行状态控制；对燃锂混合和飞行状态的综合优化可以有效地处理爬升和巡航阶段的能源需求矛盾，在给出最优燃锂混合量和飞行状态的同时，降低整个任务过程的燃料消耗。     

A microcontroller-based intelligent battery system

State-of-charge indication for a secondary battery is becoming increasingly important for battery-operated electronics. Consumers are demanding fast charging times, increased battery lifetime, and fuel gauge capabilities. All of these demands require that the state of charge within a battery be known. One of the simplest methods employed to determine state of charge is to monitor the voltage of the battery. However, this method alone is not a good indicator of battery energy, since both NiMH and NiCd batteries have voltage-versus-energy curves that are essentially flat. This paper presents a more effective method of determining the state of charge in secondary cell batteries. A NiMH battery is used as our test vehicle, since it is one of the more difficult batteries to determine state of charge. This method monitors the battery's temperature, voltage, and discharge/charge rate. A microcontroller then manipulates the information, using look-up tables to determine the state of charge. Also, by modifying the look-up tables, this technique can be employed in many other battery technologies and is not limited to NiMH     

Flight strategy optimization for high-altitude long-endurance solar-powered aircraft based on Gauss pseudo-spectral method

Solar-powered aircraft have attracted great attention owing to their potential for longendurance flight and wide application prospects.Due to the particularity of energy system, flight strategy optimization is a significant way to enhance the flight performance for solar-powered aircraft.In this study, a flight strategy optimization model for high-altitude long-endurance solar-powered aircraft was proposed.This model consists of three-dimensional kinematic model,aerodynamic model, energy collection model, energy store model and energy loss model.To solve the nonlinear optimal control problem with process constraints and terminal constraints, Gauss pseudo-spectral method was employed to discretize the state equations and constraint equations.Then a typical mission flying from given initial point to given final point within a time interval was considered.Results indicate that proper changes of the attitude angle contribute to increasing the energy gained by photovoltaic cells.Utilization of gravitational potential energy can partly take the role of battery pack.Integrating these two measures, the optimized flight strategy can improve the final state of charge compared with current constant-altitude constant-velocity strategy.The optimized strategy brings more profits on condition of lower sunlight intensity and shorter daytime.