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蓄电池发热量是航天器蓄电池热控设计的重要参数,其测试准确度直接影响热控设计状态和在轨工作温度。文章采用真空绝热量热法对蓄电池发热量测试系统进行了漏热分析,并给出了修正方法;以模拟蓄电池为研究对象,分析了蓄电池发热量测试误差,并提出了改善系统测量准确度的解决方案。结果表明,当放电时间大于1 h,航天器蓄电池发热功率在2~25 W范围内时,测试误差不超过6%,且发热功率越大误差越小;当发热功率大于10 W时,测试误差不超过3%,可以满足工程要求;对于发热功率较小(绝对值小于0.5 W)的小电流放电或充电,测试误差较大,但绝对值仍然较小,对实际工程影响不大。 相似文献
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馈源阵作为星载天线的核心部件,其馈源辐射杯圆度误差显著影响天线的馈电性能,因此,探究馈源单元电性能与圆度误差的关联性极为重要。以某卫星天线馈源阵三维单馈源为例,基于几何绕射理论,将圆度误差引入方向图函数,建立了电磁耦合模型;基于FEKO电磁软件,分析了圆度误差对馈源单体最大增益、波束宽度等主要馈电性能指标的影响规律。研究结果表明,频率越大,增益与波束宽度对圆度误差越敏感。当馈源杯直径存在尺寸误差时,圆度误差导致的电性能变化与尺寸误差之间为振荡关系。文章研究工作可为探求天线制造误差与电性能的关联性提供一定的借鉴与指引。 相似文献
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PLZT光致伸缩层合梁的非接触形状控制 总被引:1,自引:0,他引:1
以光电层合梁非接触形状控制问题为研究对象,阐述了PLZT光致伸缩驱动器的工作机理,建立了光-电-力-热耦合情况下的光电有限元模型,通过引入加强假定应变模式和假定自然应变法改善了单元的性能。在此基础上,以光致伸缩驱动器所受到的光强大小为设计变量,以光电层合梁的期望形状与控制形状的差值函数为目标函数,应用有限元法和遗传算法建立了求解基于PLZT光致伸缩驱动器层合梁非接触形状控制问题的一般方法。数值模拟的结果验证了该方法有效,表明该方法能够很好地实现光电层合梁结构的非接触形状控制。 相似文献
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A.S. Gvamichava V.I. Buyakas N.S. Kardashev N.P. Melnikov A.S. Sokolov G.S. Tsarevsky V.I. Usyukin 《Acta Astronautica》1981,8(4):337-348
Large space antennas can solve some actual problems of fundamental and applied investigations. Mirror antennas of large diameters (up to tens or hundreds of meters) are designed using an automatically deployed truss frame as a base onto which the radioreflecting surface is pulled (long-wave version) or precisely controllable panels are mounted (shortwave version). The reasons are discussed why antennas of millimeter range can be promptly developed. The factors are considered that influence on the resultant precision of the reflecting surface of the space antenna: technological errors in the process of frame manufacturing; technological errors during manufacturing of the reflecting surface; deformations due to thermal or force effects. To operate in the millimeter wavelength range, it is required to design antennas with automatic control of the reflecting surface. The analysis of the mathematical model of a modular mirror leads to the conclusion about the basic possibility of its adjustment. 相似文献
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以直径0.6 m开口筒壳为例,分析了装配误差对仿真结果产生的影响,表明高精度量化试验系统装配方法研究的必要性。传统装配方法采用直尺等机械工具开展试验系统装配,导致实际装配误差较大且难以精准定量。因此提出一种试验系统装配误差精准测量与调控方法,该方法通过测量标识点获取装配件实际位置,并计算实际与理论位置的装配误差,结合机械推动以及位移测量等设备实现位置精确调控。为验证方法的可行性与精度,基于自研的强度试验高精度装配软件,分别开展了直径0.6 m和1.6 m圆柱筒壳装配调控试验。相比传统方法,最大位移误差从15.00 mm降至0.75 mm,最大角度误差从0.93°降至0.04°,数值分析承载力误差从1.67%降到了0.04%,降低了装配误差对承载力的影响,提高了试验系统装配精度。 相似文献
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基于测角信息的测量数据折射误差修正方法研究 总被引:1,自引:0,他引:1
光学设备测量数据因精度高而一般成为雷达精度校飞、实测数据固定偏差估计的比较标准。然而,受各种因素干扰,光测数据同样地包含一定误差,其中光、电波折射误差是其最主要误差之一。因此,如何精确修正测量信号的大气折射误差,往往成为影响数据处理精度的主要因素。首先给出了利用测角信息交会计算目标坐标的方法,并从大气模型入手,针对光学测量数据的特点,建立了精确的光波折射误差修正模型,并给出了在线算法。仿真证明,该方法在保证计算速度前提下,可极大地提高数据处理的精度。 相似文献
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系统误差模型的建立方法 总被引:3,自引:0,他引:3
为了提高制导控制系统的精度 ,需要对误差进行预测和补偿 ,而根据预测的实验数据建立准确的数学模型是提高补偿效果的必要步骤。阐述了根据试验测出的系统误差数据或曲线 ,利用估计理论建立误差模型的方法 ,尤其是多维系统误差模型的建立方法 ,为误差补偿提供数学模型。结果表明 :采用估计理论建立的系统误差模型可以达到所需要的精度 ,在工程上是可行的 相似文献
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刘培培 《华北航天工业学院学报》2009,(1):1-3
本文介绍了利用VHDL语言,在MAXPLUSⅡ平台上,使用CPLD实现串行、并行两种信源方式的CRC码的设计及其模型验证结果。无论是串行,还是并行的信源要想实现CRC码设计必须建立校验、纠错两个模块,完成数据传输中的差错控制。同时在用硬件实现CRC码传输的过程中,比较了串、并两种方式的优缺点。 相似文献
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A P Nechaev 《Acta Astronautica》2001,49(3-10):271-278
Human error prevention is very important to support the safety and efficiency of human-machine systems. The approach to space crew member management error is considered in this paper. The data collected during 14 "Mir" station missions were analyzed to substantiate this approach. As a result of data processing, the significant (p<0.05) correlation of crew member errors with work and rest schedule tensity has been revealed. This finding was used to work out the mathematical model describing the dependence between the frequency (the probability) of crew member errors and work and rest schedule tensity. Based on the model, the algorithm of error management by means of efficient planning of crew members' work has been developed. The suggested approach may be used equally with other methods to raise the reliability of human-operator performance. Grant numbers: NAS-15-10110. 相似文献
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针对侧滑转弯(STT)导弹带有攻击角度约束的机动目标拦截问题,提出一种基于自适应终端滑模动态面控制的三维部分制导控制一体化(PIGC)设计方法。首先,建立了针对机动目标拦截的侧滑转弯导弹三维部分制导控制一体化设计模型,且不需要导弹速度微分体轴系分量信息。然后,使用终端滑模控制理论构建误差向量与虚拟控制量,达成精确拦截与攻击角度约束的控制目的;引入有限时间非线性收敛扩张状态观测器(ESO)来在线估计系统不确定性;设计自适应算子与自适应更新律对观测器的估计误差进行补偿,以提高方法的鲁棒性。最后,三维空间拦截仿真校验了方法在提高拦截精度与增强角度约束收敛性能的有效性。 相似文献
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As one of the most critical issues for high-accuracy satellite attitude determination, the relative installation error of star tracker usually leads to inconsistency of the output attitude information. In this paper, an approach named regularized robust filter algorithm is proposed to control the relative installation error of star tracker in the attitude measurement data. Based on the uncertainty model established for the attitude measurement system, the weighted least square solution is presented and the regularized robust filter is deduced firstly. The algorithm parameters are then optimized with the design indices in order to minimize the upper boundary for the variance of the estimated error. Compared with the traditional Kalman filter, the regularized robust filter takes into consideration the effects of model uncertainty, which can be used to optimize the filter parameters during its design stage. Thus, the information of both the system model and the measurement data can be applied effectively. Moreover, the existence conditions need not be validated in the proposed filter algorithm, which is convenient for on-orbit application. Finally, simulation results demonstrate the validity and efficiency of the proposed method. The relative installation error of attitude determination is mostly reduced and the estimation precision is improved greatly. 相似文献