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用现代谱估计法实现导弹系统仿真模型的高可信度确认 总被引:1,自引:0,他引:1
本文概述导弹仿真模型的确认方法和各自的优缺点及应用范围。分析了导弹系统仿真过程输出序列的特点,并根据现代谱估计方法对短序列、低信噪比序列进行谱估计时分辩力高的特点,提出了一种导弹系统仿真模型有效性确认的新方法,并结合某型号半实物仿真过程给出应用结果。 相似文献
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空间原子氧环境效应模拟方法 总被引:1,自引:1,他引:0
原子氧是近地轨道中一种极为恶劣的空间环境,地面模拟与数值模拟是进行原子氧环境效应研究的常用方法。文章调研分析了国内外在空间原子氧地面模拟与数值模拟方面的最新进展及所采用的关键技术,提出国内今后在地面模拟方面应着力建立有效的试验方法与寿命预示方法,为今后航天器选材试验提供技术基础;在数值模拟方面应以工程应用为指导,以试验结果为基础,逐步建立起合理有效的数值模拟方法。 相似文献
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现代仿真技术对仿真机提出更高要求,传统的混合计算机相应也要发展。本文针对国内的实际情况,提出改进现有混合机的设想:1.补足模拟容量;2.仿制ECSSL;3.增强专用计算能力。这些都是切实可行的措施。第1项已经实现,第2、3项正在着手进行。 相似文献
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本文介绍用YH-F_1仿真机进行固体火箭姿态控制系统半实物仿真试验的系统配置、仿真程序设计和仿真模型检验. 相似文献
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凝胶模拟液直圆管流动特性数值模拟 总被引:2,自引:0,他引:2
采用POLYFLOW软件,对幂律型凝胶模拟液在直圆管内的流动和流变特性进行了数值模拟研究。结果表明:在流速和管径不变时,压降随管长的增加成线性增加;在流速和管长不变时,压降随管径的增大急剧减小;随着流变指数的减小,直圆管轴线附近出现明显的柱塞流动区,在此区域内,速度和剪切速率变化较小,剪切粘度值趋于最大;在管壁附近.速度和剪切速率变化较大。剪切粘度降低明显。 相似文献
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本文对三维隅角机翼声速喷流与超声速主流的干扰流扬进行了数值模拟。三维欧拉方程的求解采用非结构网络有限体积伽辽金法(Finite Volume Galerkin Method)。引入了总体结点积分域的概念,简化了从单元矩阵到总体矩阵的汇总过程。通量的分裂采用Osher格式,通过外差使其由一阶精度上升为二阶精度。发展了一种基于线化流量的逆风非结构网格隐式有限元格式以提高求解精度及效率。最后给出了三维隅角机翼流场的算例。 相似文献
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Two major treaties define the legal framework of space, the Outer Space and Moon Treaties. The former prevents conflict and ensures free access in space, in part by preventing property claims in space, while the latter in part established the need for sharing space resources between the developed and less developed nations. Several groups argue that this has unintentionally restrained space commerce. Discussions supporting or expanding the current legal regime are contrasted with allowing individual property rights. A normative solution is suggested for establishing property rights and establishing equity between the developed and less developed nations. 相似文献
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In this study, a novel reliability-corrected cost model for estimating the development cost of highly agile small EO (Earth Observation) satellites is presented. In order to develop the cost model of highly agile small EO satellites, a database has been constructed consisting of 49 satellites carrying electro-optical payloads and having a launch mass between 100 kg and 1,000 kg that have either been developed or being developed within a time frame from 1991 to 2011. The cost model of top-down type was developed by analyzing the database statistically. The reliability-corrected CER (Cost Estimating Relationships) developed in this study implement multiple parameters-based complexity indexes. In addition, the Cost Correction Factor (CCF) and Low Cost Small Satellite (LCSS) adjustment factor were newly introduced as additional parameters for cost estimation. The reliability-corrected CERs for 26 EO satellites were used for verification of the cost model developed in this study. It was observed that there are approximately 7% of absolute average errors in the reliability-corrected CER. It is concluded that this cost model can provide cost estimates with a higher accuracy, as compared to conventional cost models such as USCM and SSCM. Finally, this paper also describes the results of cost estimation obtained by applying the developed cost model to highly agile small electro-optical satellites having specific performance requirements. 相似文献
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The Space Systems Research Laboratory (SSRL) at Saint Louis University is developing SLUCUBE nanosatellite as part of the space mission design program. The objective of the mission is to demonstrate space capability of high performance nanosatellite components that has been developed at SSRL for the past three years. The objective of the program is to provide extremely low-cost and rapid access to space for scientists and commercial exploitation using commercial-off-the-shelf components. SLUCUBE is a double CubeSat with dimensions 10×10×20 cm and a mass of 2 kg. This nanosatellite features suite of technology demonstration components to enlarge the capability of space mission for such class of spacecrafts. The primary mission of SLUCUBE is to test and demonstrate several enabling technologies by flying a number of university developed high performance components. This paper describes the new developed technologies by providing details of specific components developed along with the R&D efforts and laboratory facilities. A brief discussion about the student involvement and educational benefits will also be presented. 相似文献
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《Acta Astronautica》2010,66(11-12):1804-1812
The Space Systems Research Laboratory (SSRL) at Saint Louis University is developing SLUCUBE nanosatellite as part of the space mission design program. The objective of the mission is to demonstrate space capability of high performance nanosatellite components that has been developed at SSRL for the past three years. The objective of the program is to provide extremely low-cost and rapid access to space for scientists and commercial exploitation using commercial-off-the-shelf components. SLUCUBE is a double CubeSat with dimensions 10×10×20 cm and a mass of 2 kg. This nanosatellite features suite of technology demonstration components to enlarge the capability of space mission for such class of spacecrafts. The primary mission of SLUCUBE is to test and demonstrate several enabling technologies by flying a number of university developed high performance components. This paper describes the new developed technologies by providing details of specific components developed along with the R&D efforts and laboratory facilities. A brief discussion about the student involvement and educational benefits will also be presented. 相似文献
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为了解决过程噪声和测量噪声为高斯有色噪声且反馈控制器未知情况下的闭环系统辨识问题,给出了基于子空间辨识框架下的闭环辨识算法。算法通过选择适当的辅助变量,构造出噪声过程的高阶累积量,并利用高阶累积量对高斯噪声不敏感的特性来抑制噪声的影响,最后再使用子空间算法辨识系统的状态空间模型。数值仿真表明,对于存在高斯有色噪声的闭环系统,该辨识算法可以得到无偏的系统状态空间模型。 相似文献
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Dong-Young Rew Gwanghyeok Ju Sangchul Lee Kwangjin Kim Sang-Wook Kang Sang-Ryool Lee 《Acta Astronautica》2014
In preparation for the lunar exploration program scheduled to be launched during the early 2020s in Korea, a lunar lander demonstrator, which will be used for developing and demonstrating lunar landing technologies, is being developed. The control configuration of the lunar lander demonstrator is determined with the consideration of available technologies and flight requirements. It is suggested that altitude control be achieved by clustering five 200 N monopropellant thrusters and attitude control with eight 3 N thrusters. A control algorithm designed to follow a predefined trajectory is developed using quaternion feedback. Control system configuration and control logic are verified by using computer simulations. Simulation results show that a soft landing with a touchdown velocity of less than 3 m/s is achieved. Attitude control performance is also verified using computer simulations. The developed control configuration will be further tested by hardware in the loop simulations and ground based firing tests during the next phase of the study. 相似文献