The adjusted optical properties for Galileo/BeiDou-2/QZS-1 satellites and initial results on BeiDou-3e and QZS-2 satellites

Solar Radiation Pressure (SRP) is the dominant non-gravitational perturbation for GNSS (Global Navigation Satellite System) satellites. In the absence of precise surface models, the Empirical CODE Orbit Models (ECOM, ECOM2) are widely used in GNSS satellite orbit determination. Based on previous studies, the use of an a priori box-wing model enhances the ECOM model, especially if the spacecraft is a stretched body satellite. However, so far not all the GNSS system providers have published their metadata. To ensure a precise use of the a priori box-wing model, we estimate the optical parameters of all the Galileo, BeiDou-2, and QZS-1 (Quasi Zenith Satellite System) satellites based on the physical processes from SRP to acceleration. Validation using orbit prediction proves that the adjusted parameters of Galileo and QZS-1 satellites exhibit almost the same performance as the corresponding published and “best guess” values. Whereas, the estimated parameters of BeiDou-2 satellites demonstrate an improvement of more than 60% over the initial “guess” values. The resulting optical parameters of all the satellites are introduced into an a priori box-wing model, which is jointly used with ECOM and ECOM2 model in the orbit determination. Results show that the pure ECOM2 model exhibits better performance than the pure ECOM model for Galileo, BeiDou-2 GEO and QZS-1 orbits. Combined with the a priori box-wing model the ECOM model (ECOM+BW) results in the best Galileo, BeiDou-2 GEO and QZS-1 orbits. The standard deviation (STD) of satellite laser ranging residuals reduce by about 20% and 5% with respect to the pure ECOM2 model for Galileo and BeiDou-2 GEO orbits, while the reductions are about 40% and 60% for QZS-1 orbits in yaw-steering and orbit-normal mode respectively. BeiDou-2 IGSO and MEO satellite orbits do not benefit much from the a priori box-wing model. In summary, we suggest setting up a unified SRP model of ECOM+BW for Galileo, QZS-1, and BeiDou-2 orbits based on the adjusted metadata. In addition, we estimate the optical parameters of BeiDou-3e and QZS-2 satellites using a limited number of tracking stations. Results regarding the unified SRP model indicate the same advantages, the STD of satellite laser ranging residuals reduces by about 30% and 20% for QZS-2 and BeiDou-3e orbits respectively over orbit products without a priori model. The estimation procedure is effective and easy to apply to the new emerging satellites in the future.     

Comparison of observed ionospheric vertical TEC over the sea in Indian region with IRI-2016 model

The vertical ionospheric TEC values obtained from GAGAN grid based ionospheric delay correction values over the sea in the Indian equatorial region have been compared with the corresponding values derived from the International Reference Ionosphere model, IRI-2016. The objective of this work is to study the deviation of the vertical TEC derived from the IRI model from ground truths over the sea for different conditions. This will serve the basic intention of assessing the candidature of the IRI model as an alternative ionospheric correction model in navigation receivers in terms of accuracy. We have chosen different solar activity periods, seasons, geomagnetic conditions, locations etc. for our comparison and analysis. The TEC values by the IRI-2016 were compared with the actual measured values for the given conditions and errors were obtained. The measured vertical TEC values at the ionospheric grid points were derived from the GAGAN broadcast ionospheric delay data and used as reference. The IRI model with standard internal functions was used in estimating the TEC at the same ionospheric grid points. The errors in the model derived values are statistically analysed. Broadly, the results show that, for the Indian sector over the sea, the IRI model performs better on quiet days in off equatorial regions, particularly in the northern region. The overall performance degrades for other conditions with the model generally underestimating the true TEC values and most severely in the equatorial region. The performance is worst in this region for the disturbed days of the equinoctial period. The comparison study is also done with the TEC data measured directly by dual frequency GPS receivers. The results were found to be in general agreement with those obtained by comparing the model with GAGAN broadcast data as reference. This study will be useful in considering the IRI-2016 model for real time estimates of TEC as an alternative to the current parametric model in a satellite navigation receiver in absence of other options.     

基于数字孪生的智能脉动管控

为提升飞机总装脉动生产线智能化水平,开展了基于数字孪生的智能脉动管控研究。基于数字孪生五维模型理论构建了飞机总装脉动生产线数字孪生应用架构,从反应式计划调度、物流精准配送、智能作业指导、产线健康监视、资源迭代优化配置5个方面开展了技术研究,为复杂产品装配的智能制造应用提供参考。     

多梁复合结构的动力学建模及全局解析振型分析

多梁复合结构广泛用于工程领域，其动力学特性对相关装备的工作状况有着重要影响，建立准确适用的动力学模型对后续的动力学响应参数影响规律研究有决定性作用。针对工程中常见的多梁复合结构，给出了位移场的一般表达式，利用哈密顿原理得出多梁复合结构的运动控制方程和边界条件，对其全局解析振型进行理论计算，给出了计算多梁复合结构数值振型的一般过程，基于数值分析和实验分析以L型梁和Z型梁为例利用频率相对误差、振型定性比较和MAC定量分析说明了全局解析振型的求解验证方法，利用伽辽金方法和全局解析振型给出了截断原系统得到离散系统运动方程的一般形式。提出的多梁复合结构的建模方法和全局解析振型求解验证方法，对工程中此类结构动力学响应的参数影响规律研究有重要意义。     

新型柔索式杆束结构压紧释放装置

针对空间机械臂、空间可展开天线等空间机构在收拢状态的杆束结构压紧与释放问题，提出一种基于柔性索捆绑压紧与热刀释放的新型压紧释放装置。建立了柔索式压紧释放装置锁紧状态的力学模型，分析了静态压紧和考虑惯性载荷情况下的绳索预紧力变化情况，得到了满足可靠压紧的绳索预紧力设计值。基于质量和刚度等效，设计了机械臂杆束结构力学等效件，并进行了正弦与随机振动力学试验。试验结果验证了所设计的柔索式杆束结构压紧释放装置的可行性，并可以推广到具有复杂包络的杆束结构压紧释放中。     

Applications of structural efficiency assessment method on structural-mechanical characteristics integrated design in aero-engines

In the design process of advanced aero-engines, it is necessary to carry out an effective analysis method between structural features and mechanical characteristics for a better structural optimization. Based on the structural composition and functions of aero-engines, the concept and contents of structural efficiency can reflect the relation between structural features and mechanical characteristics. In order to achieve the integrated design of structural and mechanical characteristics, one quantitative analysis method called Structural Efficiency Assessment Method (SEAM) was put forward. The structural efficiency coefficient was obtained by synthesizing the parameters to quantitatively evaluate the aero-engine structure design level. Parameterization method to evaluate structural design quality was realized. After analyzing the structural features of an actual dual-rotor system in typical high bypass ratio turbofan engines, the mechanical characteristics and structural efficiency coefficient were calculated. Structural efficiency coefficient of high-pressure rotor (0.43) is higher than that of low-pressure rotor (0.29), which directly shows the performance of the former is better, there is room for improvement in structural design of the low-pressure rotor. Thus the direction of structural optimization was pointed out. The applications of SEAM shows that the method is operational and effective in the evaluation and improvement of structural design.     

某航天器输氢管道系统结构完整性评估

为保障某航天器在服役年限内不发生事故，针对航天器上采用插入焊接技术的精密管道系统进行结构完整性评估。在考虑到系统存在整圈的环形未焊透缺陷基础上，结合工程实践，假设在焊接区域存在更危险的平面缺陷。首先，开展高压气相热充氢试验下的标准拉伸和三点弯试验得到管道系统材料"J-75"在临氢环境下应力应变曲线和断裂韧性。其次，采用有限元程序计算系统在内压、惯性载荷与离面位移作用下的应力分布，考虑到间隙配合中的不确定性，改变模型中的最大间隙多次模拟计算，发现最大应力位置基本不变，以此区域作为假想缺陷的具体萌生区域。最后，采用失效评估图（FAD）方法对存在4种缺陷模式的系统分别进行结构完整性评估。通过引入安全裕度的概念，发现系统在含有初始尺寸（0.15 mm）的4种平面缺陷时，均处于安全状态，并且安全裕度都在2倍以上；通过工程临界分析（ECA）发现随着缺陷尺寸的增大，系统中含有缺陷2（位于管道焊接区域最大应力处的轴对称平面且沿焊深方向扩展的缺陷）时最为危险，且当缺陷深度超过0.61 mm时将断裂失效；考虑到测试数据的弥散性，针对系统最危险的模式，以安全裕度为可靠性指标，将失效评估图方法与可靠性评价相结合，得到系统在含有尺寸为0.15 mm的缺陷2情况下保有足够安全裕度的可靠性下限值超过0.999 5。     

反推力装置运动学与动力学仿真

为了研究叶栅式反推力装置各部件在工作过程中的运动学与动力学特性,根据机构运动原理对反推力装置进行简化并建立了运动学与动力学数学模型。以滑动整流罩位移与阻流门所受气动负荷为输入进行运动学与动力学仿真,得到了反推力装置各部件的位移、速度及受力特性曲线,并对比分析了在不同尺寸参数下各部件特征点的运动轨迹和反推力装置负载力变化。结果表明:运动学及动力学仿真结果与工程实际相符；反推力装置机构参数选择不合理时,各设计点会发生干涉现象并导致机构无法运动;机构参数变化对负载力最大值影响尤为突出,在阻流门AC段长度值增大6%,阻流门CB段长度值减小9%的情况下,负载力正向最大值将增大19.53%,负向最大值增大12.67%。研究方法及研究结果可为反推力装置运动学及动力学分析,以及为反推力装置机构优化设计提供参考。      

航天器姿态预设性能控制方法综述

针对存在不确定惯量矩阵及其它未知不确定性(如执行器故障、航天器结构发生突变等)下的航天器姿态控制问题，综述了预设性能控制及其应用的研究进展。首先阐释了预设性能控制方法的基本内涵及其关键步骤；然后分析总结了现有航天器姿态控制以及预设性能控制研究的基本概况与发展趋势；最后面向未来复杂化、智能化的空间任务对航天器控制系统提出的新需求，提出航天器预设性能控制值得研究的问题和方向。     

Evaluation of SARAL/AltiKa performance using GNSS/IMU equipped buoy in Sajafi,Imam Hassan and Kangan Ports

Performance of SARAL/AltiKa mission has been evaluated within 2016 altimeter calibration/validation framework in Persian Gulf through three campaigns conducted in the offshore waters of Sajafi, Imam Hassan and Kangan Ports, while the altimeter overflew the passes 470, 111 and 25 on 13 Feb, 7 March and 17 June 2016, respectively. As the preparation, a lightweight buoy was equipped with a GNSS receiver/choke-ring antenna and a MEMS-based IMU to measure independent datasets in the field operations. To obtain accurate sea surface height (SSH) time series, the offset of the onboard antenna from the equilibrium sea level was predetermined through surveying operations as the buoy was deploying in the onshore waters of Kangan Port. Accordingly, the double-difference carrier phase observations have been processed via the Bernese GPS Software v. 5.0 so as to provide the GNSS-derived time series at the comparison points of the calibration campaigns, once the disturbing effects due to the platform tilt and heave have been eliminated. Owing to comparing of the SSH time series and the associating altimetry 1?Hz GDR-T datasets, the calibration/validation of the SARAL/AltiKa has been performed in the both cases of radiometer and ECMWF wet troposphere corrections so as to identify potential land contamination. An agreement of the present findings in comparison with those attained in other international calibrations sites confirms the promising feasibility of Persian Gulf as a new dedicated site for calibration/validation of ongoing and future altimetry missions.