Finite element reconstruction approach for on-orbit spacecraft breakup dynamics simulation and fragment analysis

Breakup model is the key area of space debris environment modeling. NASA standard breakup model is currently the most widely used for general-purpose. It is a statistical model found based on space surveillance data and a few ground-based test data. NASA model takes the mass, impact velocity magnitude for input and provides the fragment size, area-to-mass ratio, velocity magnitude distributions for output. A more precise approach for spacecraft disintegration fragment analysis is presented in this paper. This approach is based on hypervelocity impact dynamics and takes the shape, material, internal structure and impact location etc. of spacecraft and impactor, which might greatly affect the fragment distribution, into consideration. The approach is a combination of finite element and particle methods, entitled finite element reconstruction (FER). By reconstructing elements from the particle debris cloud, reliable individual fragments are identified. Fragment distribution is generated with undirected graph conversion and connected component analysis. Ground-based test from literature is introduced for verification. In the simulation satellite targets and impactors are modeled in detail including the shape, material, internal structure and so on. FER output includes the total number of fragments and the mass, size and velocity vector of each fragment. The reported fragment distribution of FER shows good agreement with the test, and has good accuracy for small fragments.     

Experimental investigation on deformation behavior of TJ-1 lunar soil simulant subjected to principal stress rotation

The knowledge of mechanical properties of lunar soil is of fundamental importance for the coming exploration of the Moon. This paper aims to investigate the fundamental deformation behavior of lunar soil and the effects of the intermediate principal stress coefficient, deviatoric stress ratio, and mean stress during the principal stress rotation. First, an improved technique was proposed to generate homogeneous samples based on the Multi-layer Undercompaction Method. Second, three series of tests on TJ-1 lunar soil simulant under the principal stress rotation were performed with a hollow cylinder apparatus at Tongji University, China. In each series of tests, only one value of the three variables mentioned above was changed while the others were kept constant. The test results demonstrate that the rotation of principal stress can result in significant plastic deformation, volumetric strain, and non-coaxiality (non-coincidence of the increment direction of principal plastic strain with the principal stress direction) of TJ-1 lunar soil simulant. In addition, it is found that the intermediate principal stress coefficient, deviatoric stress ratio, and mean stress have different influences on the four strain components, i.e. _εz,_εr,_εθ${\epsilon }_z\text{,}{\epsilon }_{\text{r}}\text{,}{\epsilon }_{\theta }$ and _γzθ${\gamma }_{z\theta }$, volumetric strain, and non-coaxiality during the principal stress rotation. The influence of deviatoric stress ratio is relatively stronger than the others. Therefore, the influence of principal stress rotation on the deformation behavior of lunar soil should be taken into account carefully in the design and construction of facilities on the lunar surface in the future.     

An improved approach to model regional ionosphere and accelerate convergence for precise point positioning

Given the severe effects of the ionosphere on global navigation satellite system (GNSS) signals, single-frequency (SF) precise point positioning (PPP) users can only achieve decimeter-level positioning results. Ionosphere-free combinations can eliminate the majority of ionospheric delay, but increase observation noise and slow down dual-frequency (DF) PPP convergence. In this paper, we develop a regional ionosphere modeling and rapid convergence approach to improve SF PPP (SFPPP) accuracy and accelerate DF PPP (DFPPP) convergence speed. Instead of area model, ionospheric delay is modeled for each satellite to be used as a priori correction. With the ionospheric, wide-lane uncalibrated phase delay (UPD) and residuals satellite DCBs product, the wide-lane observations for DF users change to be high-precision pseudorange observations. The validation of a continuously operating reference station (CORS) network was analyzed. The experimental results confirm that the approach considerably improves the accuracy of SFPPP. For DF users, convergence time is substantially reduced.     

电子照射对硅漂移探测器性能的影响

由于高能电子辐射的长期照射,新一代太阳X射线探测器硅漂移传感器的探测性能可能发生变化.通过用电子放射源模拟空间电子对硅漂移探测器进行辐射照射试验,以测试电子照射对传感器能量分辨率、效率、信号幅度等性能的影响.试验结果表明,长期的电子照射造成硅漂移探测器面损伤和体损伤,使其漏电流增大,信号幅度减小,能量分辨率也受到照射的影响,而探测效率未发生变化.     

基于小波变换的光纤周界定位系统

为提高基于双Mach-Zehnder干涉仪结构的光纤周界定位系统的定位精度,对信号频率范围及信噪比对系统定位精度的影响进行了理论分析和仿真研究.在此基础上,提出在选用光缆时需要兼顾对外界振动的敏感性和对外场复杂环境的适应性,以确保在长期可靠运行的前提下,扩展采集信号的频率范围;使用小波阈值降噪算法,提取振动信号的有效频率成分,滤除噪声,提高信噪比.最后进行了监测距离31 km的外场实验,验证了所选用光缆的优良性能和小波降噪算法的有效性.     

非对称受损飞机多变量模型参考自适应控制

针对非对称受损的常规布局飞机,对其自适应控制设计方法与适用条件进行了研究.建立了非对称结构受损飞机的非线性模型,详细讨论了模型的线性化过程以及受损造成的纵、横向间动态耦合项;结合常规布局非对称结构受损飞机的物理特性,对多变量模型参考自适应控制器设计的关键条件：关联矩阵和高频增益矩阵顺序主子式符号的不变性做出了证明,确立了该方法在非对称结构受损飞机上应用的理论可行性;通过仿真验证了MRAC（Model Reference Adaptive Control）方法对非对称结构受损飞机控制的有效性.     

地地弹道导弹可用性仿真评估系统构建

阐述了地地弹道导弹可用性评估的重要性,并以此为需求牵引,提出了以MTMC-RDEDS(Mission Time Monte Carlo Random Discrete Event Dynamic Systems)为核心的可用性建模与仿真一体化框架,结合实际应用,以模型重用技术为基础,构建了拥有丰富建模与仿真知识库、模块化设计与开放式接口的导弹可用性仿真评估系统总体框架及软件层次结构,并给出了涉及工作状态、维修保障、统计优化在内的核心仿真模型与算法,探讨了系统实现的关键技术,包括:随机变量建模、武器系统建模、仿真系统可信度评估.利用VC++和相关软件开发了地地弹道导弹可用性仿真评估系统,给出了仿真运行界面,并进行实例分析,验证模型和系统的有效性.仿真的结果与实际试验情况吻合较好,表明该动态评估方法快捷有效,评估系统建设方案合理可行,适用于工程分析,不失为地地弹道导弹可用性评估的一种有效手段.     

无人机集群路径规划算法研究综述

无人机集群路径规划算法是无人机集群控制的重要研究方向之一.多无人机路径规划相较于单无人机路径规划,会考虑空间协同和时间协同约束、飞行安全等问题.首先对无人机集群路径规划算法进行分类,分为传统路径规划算法、智能优化算法和深度强化学习算法.其次对各类算法进行简要分析和总结,针对缺陷,给出相应的改进思路及例子.再着重对深度强...     

非圆形截面复合材料机身屈曲优化设计研究

为了降低BWB机身弯曲应力、提高屈曲稳定性,在150座BWB民机复合材料三舱室机身结构的基础上,提出了改进的Y形和弧形加强三舱室机身设计模型;利用零阶参数优化算法,对3种机身结构进行了静力与线性屈曲优化分析,获得了较为合理的三舱室机身布局方案,为BWB民机机身设计提供了重要技术参考.