Biomechanical analysis of an absorbable material for treating fractures of the inferior orbital wall

AIM:To investigate the biomechanical properties and practical application of absorbable materials in orbital fracture repair.METHODS:The three-dimensional(3D)model of orbital blowout fractures was reconstructed using Mimics21.0 software.The repair guide plate model for inferior orbital wall fracture was designed using 3-matic13.0 and Geomagic wrap 21.0 software.The finite element model of orbital blowout fracture and absorbable repair plate was established using 3-matic13.0 and ANSYS Workbench 21.0 software.The mechanical response of absorbable plates,with thicknesses of 0.6 and 1.2 mm,was modeled after their placement in the orbit.Two patients with inferior orbital wall fractures volunteered to receive single-layer and double-layer absorbable plates combined with 3D printing technology to facilitate surgical treatment of orbital wall fractures.RESULTS:The finite element models of orbital blowout fracture and absorbable plate were successfully established.Finite element analysis(FEA)showed that when the Young’s modulus of the absorbable plate decreases to 3.15 MPa,the repair material with a thickness of 0.6 mm was influenced by the gravitational forces of the orbital contents,resulting in a maximum total deformation of approximately 3.3 mm.Conversely,when the absorbable plate was 1.2 mm thick,the overall maximum total deformation was around 0.4 mm.The half-year follow-up results of the clinical cases confirmed that the absorbable plate with a thickness of 1.2 mm had smaller maximum total deformation and better clinical efficacy.CONCLUSION:The biomechanical analysis observations in this study are largely consistent with the clinical situation.The use of double-layer absorbable plates in conjunction with 3D printing technology is recommended to support surgical treatment of infraorbital wall blowout fractures.

Modified filter for mean elements estimation with state jumping

To investigate the real-time mean orbital elements(MOEs)estimation problem under the influence of state jumping caused by non-fatal spacecraft collision or protective orbit trans-fer,a modified augmented square-root unscented Kalman filter(MASUKF)is proposed.The MASUKF is composed of sigma points calculation,time update,modified state jumping detec-tion,and measurement update.Compared with the filters used in the existing literature on MOEs estimation,it has three main characteristics.Firstly,the state vector is augmented from six to nine by the added thrust acceleration terms,which makes the fil-ter additionally give the state-jumping-thrust-acceleration esti-mation.Secondly,the normalized innovation is used for state jumping detection to set detection threshold concisely and make the filter detect various state jumping with low latency.Thirdly,when sate jumping is detected,the covariance matrix inflation will be done,and then an extra time update process will be con-ducted at this time instance before measurement update.In this way,the relatively large estimation error at the detection moment can significantly decrease.Finally,typical simulations are per-formed to illustrated the effectiveness of the method.

Calculation of Orbital Elements for Released Tethered Satellite

The tethered satellite system has a great potential and one of its very useful applications is momentum transfer. Raising a payload by deploying it upward from an orbitor on a long tether and then releasing it represents a rather important possible application with significant fael economy. This paper presents a dynamic model set up for a two body tethered satellite system and two control laws of deployment used to simulate the deployment of the system, gives calculation formulas for six orbital elements of two sub satellites and discusses calculation examples.

Efficient Orbit Propagation of Orbital Elements Using Modified Chebyshev Picard Iteration Method

This paper focuses on propagating perturbed two-body motion using orbital elements combined with a novel integration technique.While previous studies show that Modified Chebyshev Picard Iteration(MCPI)is a powerful tool used to propagate position and velocity,the present results show that using orbital elements to propagate the state vector reduces the number of MCPI iterations and nodes required,which is especially useful for reducing the computation time when including computationally-intensive calculations such as Spherical Harmonic gravity,and it also converges for>5.5x as many revolutions using a single segment when compared with cartesian propagation.Results for the Classical Orbital Elements and the Modified Equinoctial Orbital Elements(the latter provides singularity-free solutions)show that state propagation using these variables is inherently well-suited to the propagation method chosen.Additional benefits are achieved using a segmentation scheme,while future expansion to the two-point boundary value problem is expected to increase the domain of convergence compared with the cartesian case.MCPI is an iterative numerical method used to solve linear and nonlinear,ordinary differential equations(ODEs).It is a fusion of orthogonal Chebyshev function approximation with Picard iteration that approximates a long-arc trajectory at every iteration.Previous studies have shown that it outperforms the state of the practice numerical integrators of ODEs in a serial computing environment;since MCPI is inherently massively parallelizable,this capability is expected to increase the computational efficiency of the method presented.

Short-Term Orbit Prediction with J₂and Mean Orbital Elements

An analytical theory for calculating perturbations of the orbital elements of a satellite due to J2 to accuracy up to fourth power in eccentricity is developed. It is observed that there is significant improvement in all the orbital elements with the present theory over second-order theory. The theory is used for computing the mean orbital elements, which are found to be more accurate than provided by Bhatnagar and taqvi’s theory (up to second power in eccentricity). Mean elements have a large number of practical applications.

Orbital Elements Ephemerides and Interfaces Design of LEO Satellites

Low earth orbit satellites,with unique advantages,are prosperous types of navigation augmentation satellites for the GNSS satellites constellations.The broadcast ephemeris element needs to be designed as an important index of the augmented LEOs.The GPS ephemerides of 16/18 elements cannot be directly applied to the LEOs because of the poor fitting accuracies in along-track positional component.Besides,the ill-conditioned problem of the normal-matrix exists in fitting algorithm due to the small eccentricity of the LEO orbits.Based on the nonsingular orbital elements,5 sets of ephemerides with element numbers from 16 to 19 were designed respectively by adding or modifying orbital elements magnifying the along-track and radial positional components.The fitting experiments based on the LEO of 300 to 1500 km altitudes show that the fitting UREs of the proposed 16/17/18/18*/19-element ephemerides are better than 10/6/4/5/2.5 cm,respectively.According to the dynamical range of the fitting elements,the interfaces were designed for the 5 sets of ephemerides.The effects of data truncation on fitting UREs are at millimeter level.The total bits are 329/343/376/379/396,respectively.29/15 bits are saved for the 16/17-element ephemerides compared with the GPS16 ephemeris,while 64/61/41 bits can be saved for the 18/18*/19-element ephemerides compared with the GPS18 elements ephemeris.

Study on relative orbital configuration in satellite formation flying

In this paper, the relative orbital configurations of satellites in formation flying with non-perturbation and J2 perturbation are studied, and an orbital elements method is proposed to obtain the relative orbital configurations of satellites in formation. Firstly, under the condition of non-perturbation, we obtain many shapes of relative orbital configurations when the semi-major axes of satellites are equal. These shapes can be lines, ellipses or distorted closed curves. Secondly, on the basis of the analysis of J2 effect on relative orbital configurations, we find out that J2 effect can induce two kinds of changes of relative orbital configurations. They are distortion and drifting, respectively. In addition, when J2 perturbation is concerned, we also find that the semi-major axes of the leading and following satellites should not be the same exactly in order to decrease the J2 effect. The relationship of relative orbital elements and J2 effect is obtained through simulations. Finally, the minimum relation perturbation conditions are established in order to reduce the influence of the J2 effect. The results show that the minimum relation perturbation conditions can reduce the J2 effect significantly when the orbital element differences are small enough, and they can become rules for the design of satellite formation flying.

Three-dimensional finite element analysis of hyperbaric oxygen therapy on the optic nerve from a damaged orbit

A middle-aged male patient with a right orbital comminuted fracture underwent computer tomography scanning, and a three-dimensional finite element model of the eyes and relevant tissues was established. Optic nerve stress in a hyperbaric oxygen environment was simulated and analyzed by changing the elastic modulus and external pressure of the skull at the damage side. Results showed that stress maximized at the contact site of the optic nerve and the eyeball in the damaged and intact eye orbits. Optic nerve stress at the damaged orbit significantly increased; however, stress in the intact orbit only slightly changed with decreased elastic modulus of the skull while external pressure remained unchanged. Maximum optic nerve stress increased in the damaged and intact side, along with increased external pressure, while elastic modulus remained unchanged. These experimental findings suggested that the optic nerve was compressed under hyperbaric oxygen and optic nerve stress was greater in the damaged orbit than in the intact orbit.

TLE orbit determination using simplex method

Two-Line Element(TLE)datasets are the only orbital data source of Earth-orbiting space objects for many civil users for their research and applications.The datasets have uneven qualities that may affect the reliability of the propagated positions of space objects using a single TLE.The least squares approach to use multiple TLEs also suffers from the poor quality of some TLEs,and reliable error information cannot be available.This paper proposes a simplex algorithm to estimate an optimal TLE from multiple TLEs and obtain the uncertainty of each element.It is a derivative-free technique that can deal with various orbit types.Experiments have demonstrated that using the TLE estimated from the simplex method is more reliable,stable,and effective than those from the batch least squares method.As an application example,the optimal TLE and its uncertainty are used for predicting the fallen area,keeping the actual fallen site in the prediction areas.

高阶轨道角动量传输光纤设计及传输特性研究(内封底文章)

为解决一般轨道角动量传输光纤传输轨道角动量模式数量少、质量差的问题,提出了一种基于正六边形空气孔排列的新型光子晶体光纤结构。该光纤引入了空气填充率高的矩形空气孔以及采用高折射率材料填充环形传输区域,能够有效提高环形传输区域和包层间的折射率差,且正六边形排列空气孔有利于提高模间有效折射率差。经过结构优化得到最优光纤结构,有限元法的分析结果表明,最优结构下,该光纤在常用波段S+C+L+U波段上能够支持142种轨道角动量模式的传输,最高阶数达到36阶。且所提出光纤具有良好的传输特性,本征模式的最高限制性损耗为10−9 dB/m量级,与典型轨道角动量传输光子晶体光纤相比至少降低了一个数量级;最大有效模场面积能够达到206.18μm^(2),最小非线性系数低至0.397 W^(−1)∙km^(−1);色散平坦且最小色散变化低至1.4578 ps/(nm∙km);所有本征模式纯度均在93.4%~96.8%范围内。且该光纤具有较好的制备可行性,对制造精度要求不高。因此,该光纤在基于轨道角动量光纤的复用系统中具有广阔的应用前景,为提高通信容量提供了一种有效手段。

航空圆柱直齿轮热摆辗成形工艺分析

为研究航空圆柱直齿轮热摆辗成形过程中金属变形规律和齿形充填特点,利用DEFORM-3D软件建立了圆柱直齿轮热摆辗成形三维刚塑性有限元模型,模拟了其热摆辗成形过程。结果表明,圆柱直齿轮热摆辗成形过程中,坯料变形区分为主动变形区和被动变形区,并随着摆头的运动而呈周期性变化;随着变形的进行,主动变形区金属流动方向从径向转变为轴向充填模具型腔,齿形从上端到下端逐渐成形,坯料呈蘑菇状;齿根区域等效应变与等效应力值最大,齿顶温度高于齿根温度;轴向载荷随塑性变形的进行逐渐增大,最大值约为2500 kN,径向载荷呈周期性变化,径向载荷远小于轴向载荷。开展了圆柱直齿轮热摆辗工艺实验,实验结果与模拟结果吻合。

井下带式输送机智能巡检机器人结构的设计

为解决带式输送机采用传统人工检测故障效率低等问题,针对问题设计出一种适用于井下输送机故障自动巡检机器人系统,区别于其他带式输送机巡检机器人。该巡检机器人可以实现大坡度和大转弯半径的运动,首先利用ADAMS分析现在主流的巡检机器人模型,分析其优劣性;利用SOLIDWORKS软件建立巡检机器人的三维模型,提出了摩擦驱动与齿轮齿条驱动的两用机器人模型;再利用ANSYS软件对轨道和机架进行了有限元分析,仿真结果表明巡检轨道与机器人本体的应力小于许用应力,能够平稳地检测输送机的故障;最后再利用ADAMS软件对巡检机器人进行动力学分析,得出巡检机器人可以进行无障碍的水平和爬坡运动。

有限元方法在眼眶生物力学中的应用进展

有限元方法(FEM)是力学研究中常用的数学方法,将物体划分为离散且相互作用的有限单元。在医学研究中,有限元分析(FEA)可模拟难以开展的生物力学实验。眼眶手术极具挑战性且具有陡峭的学习曲线,给眼科医生带来了巨大挑战。FEM可模拟分析眼眶组织的力学特性,为眼眶相关疾病的诊断和治疗提供了新的方法。随着技术的发展,FEM在眼眶疾病的诊疗中愈发成熟,并成为眼眶生物力学研究的热门领域。本文综述了眼眶FEM的最新进展,包括建立眼眶FEA模型、模拟眼眶结构以及在眼眶相关疾病中的应用情况。此外,还讨论了FEM的局限性和未来的研究方向。眼眶FEA作为一种辅助诊疗数字化工具,将随着技术的发展逐渐释放其在眼眶疾病诊疗方面的潜力。

低轨卫星轨道根数型广播星历预报

基于第一类无奇点轨道根数的参数模型设计了17~23参数的8种模型,通过拟合参数外推得到预报轨道,研究拟合轨道与预报轨道间的关系,并探究预报精度的影响因素。实验结果表明:增加参数个数对拟合精度有明显提升。相对于全球定位系统(GPS)的16参数模型,20参数模型的预报精度提升26.2%,拟合精度提升71.2%。同时,使用蜂群(Swarm)卫星、重力反演和气候实验(GRACE)卫星、贾森2号卫星及通信、导航预测中断系统(C/NOFS)卫星的实测数据分析了轨道倾角、轨道高度、偏心率和拟合弧长对预报精度的影响。

半解析卫星轨道不确定性快速估计方法

基于半解析法和球形单边采样无迹变换提出一种轨道不确定性快速估计方法。首先在考虑J2摄动和大气阻力摄动的基础上,构建轨道要素解析模型用于瞬时轨道要素快速估计。随后基于该轨道要素快速估计方法,结合球形单边采样无迹变换传播初始轨道不确定性,依据高斯摄动方程和球形单边采样点的特性对传播后的采样点进行修正,估计传播后的轨道不确定性。最后将提出的半解析法与高斯和模型相结合,以提高精度。数值仿真分析了所提出的轨道不确定性估计方法相较无迹变换法的计算效率提升程度,并依据似然一致性度量将所提出的方法与蒙特卡洛法、无迹变换法等进行了精度比较。结果表明,所提方法的计算效率相较于传统无迹变换法有较大提升,且具有合适的精度。

基于CEI测量的GEO目标快速轨道恢复

连线干涉测量(Connected Element Interferometry,CEI)是一种全天时全天候的被动测角技术,已用于空间目标的跟踪监视.地球静止轨道(Geostationary Earth Orbit,GEO)卫星需要频繁机动以保持轨位或完成其他任务,其机动后的快速轨道恢复能力对于监视预警极为重要.针对基于CEI的GEO短弧定轨和预报,分析了定轨算法的形亏和数亏,在附加先验轨道约束的短弧定轨基础上,提出了轨道半长轴初值的自适应优化方法.利用亚太七号卫星的CEI仿真和实测数据进行了短弧定轨和预报,实验结果表明,采用优化后的半长轴初值,30min短弧定轨和10min预报的卫星位置分量精度均优于4km,能够满足非合作GEO目标机动后快速轨道恢复的需求.

一种基于CEI的GEO目标滑窗式机动探测方法

为了进一步提升地面跟踪站的监视预警能力,提出一种基于连线相位干涉测量(CEI)的地球静止轨道(GEO)目标滑窗式机动探测方法:立足于CEI的GEO短弧段定轨和预报,基于GEO卫星位保机动的持续小推力和轨道缓慢渐变特性,提出一种针对GEO目标尤其是非合作GEO目标的滑窗式准实时机动探测方法;并利用亚太七号和中星十号卫星的CEI仿真和实测数据进行机动探测。结果表明,东西机动和南北机动捕获与卫星发动机的点火时刻基本保持一致,机动探测延迟量均小于10 min;能够实现GEO目标的准实时机动告警。

特征融合的卷积神经网络材料性质预测模型

针对目前大多数机器学习模型预测材料性质时需要大量的先验知识以及特征向量筛选困难的问题,基于电子轨道矩阵和元素周期表法两种描述符,通过特征融合的方式,设计了一种卷积神经网络模型OPCNN(Orbital of electron and Periodic table CNN)。实验数据表明,OPCNN与其他预测模型相比,在带隙、生成热以及形成能数据集上都有着更好的性能,平均绝对误差分别为0.26 eV、0.037 KJ/mol和0.073 eV/atom,且R^(2)都达到了91%以上。OPCNN在保证了预测准确性的同时对先验知识的要求更低,只需要元素周期表中的信息即可预测材料性质,特征融合的思想可以让特征设计更加灵活,有利于新材料体系快速和准确的预测。

面向SOT-MRAM的磁屏蔽仿真设计与优化

磁随机存储器由于其高读写速度、接近无限次的读写次数和低功耗等优异特性受到越来越多的关注。磁随机存储器采用磁场方向来操作存储位,外部磁场很容易对磁结产生干扰导致读写错误的发生。因此采用磁屏蔽封装结构来减小外部磁场对存储器的影响具有重要意义。本文针对第四代自旋轨道矩磁随机存储器的磁屏蔽优化设计进行研究,根据自旋轨道矩磁随机存储器的面内磁场敏感特性,采用平行式磁屏蔽封装形式,建立了磁屏蔽有限元模型,分析了磁屏蔽结构因素(间距,面积和厚度)和磁饱和现象对磁屏蔽效果的影响,为磁存储器磁屏蔽设计提供了新思路。

基于TLE双行根数的航天器机动检测方法

由于不同功能的航天器承担的任务不尽相同、轨道亦不相同等原因,航天器不时需要变轨机动以确保完成任务.对于非合作航天器,其可能的变轨信息预先未知且难以预测,故需要准确快速判断航天器的变轨事件,以及时调整轨道探测策略.由于美国公布的双行根数具有来源稳定、更新频率快和容易获取等特点,本文结合航天器轨道动力学及变轨控制的特点,提出了基于TLE双行根数的航天器变轨机动检测方法,通过检测半长轴的变化量和相对距离最小值实现了在轨航天器轨道面内机动的检测.以METOP-A1和IRNSS 1G两个航天器在2019年6-9月的TLE根数为例,说明使用该方法开展机动检测的操作流程和步骤.同时大量仿真计算结果表明,该方法能够有效解决航天器在轨运行过程中面内机动时间和半长轴改变量的检测以及多次变轨识别的问题,检测精度与TLE根数自身精度及机动量大小相关.