基于会切场推力器无拖曳系统建模及参数优化

随着卫星重力测量技术的突破性进展,对航天器试验环境要求也在不断提高,航天器受到的残余扰动必须尽可能减小。作为中国将来重力场测量卫星备选主推力器的会切场推力器,其推力器的控制精度直接决定了测量的准确性。文章首先通过PID方法设计了位移模式下的无拖曳控制器,该控制器在预估阻力系数、参考质量与卫星本体的位移差、速度差等性能方面有良好的表现,在应对卫星运行时的突发情况时表现出很强的稳定性。但PID参数没有达到最优解,在此基础上对于该模型的控制精度进行优化,用遗传算法对PID控制的参数进行筛选。结果分析表明,会切场推力器的控制精度有所改善,NTW方向上的速度和位移误差均减小;推力阻力和显著减少;控制精度提高,更好地满足使用需求。     

BeiDou-3 orbit and clock quality of the IGS Multi-GNSS Pilot Project

Within the Multi-GNSS Pilot Project (MGEX) of the International GNSS Service (IGS), precise orbit and clock products for the BeiDou-3 global navigation satellite system (BDS-3) are routinely generated by a total of five analysis centers. The processing standards and specific properties of the individual products are reviewed and the BDS-3 orbit and clock product performance is assessed through direct inter-comparison, satellite laser ranging (SLR) residuals, clock stability analysis, and precise point positioning solutions. The orbit consistency evaluated by the signal-in-space range error is on the level of 4–8 cm for the medium Earth orbit satellites whereas SLR residuals have RMS values between 3 and 9 cm. The clock analysis reveals sytematic effects related to the elevation of the Sun above the orbital plane for all ACs pointing to deficiencies in solar radiation pressure modeling. Nevertheless, precise point positioning with the BDS-3 MGEX orbit and clock products results in 3D RMS values between 7 and 8 mm.     

灵巧型大孔径四反星敏感器镜头设计

星敏感器镜头是星敏感器姿态轨道控制系统的重要组成部分，具有相对孔径大、工作谱段宽、绝对畸变低的特点，针对这些特点，在四反射镜初始结构的基础上，分析了镜头探测能力和相对孔径的关系，明确了镜头设计指标，利用非球面反射镜强大的像差校正能力，优化设计得到了全反射4反星敏感器镜头。镜头焦距170mm，轴向长度50mm，镜头F数2，等效入瞳直径51.2mm，圆视场±2.25°。镜头工作波段可由膜系决定，无色差，空间频率35lp/mm处传递函数优于0.6，畸变优于0.01%，弥散斑直径优于13μm，系统15μm范围内能量集中度优于80%，渐晕系数小于0.95，该镜头可用于亚像素精度的飞船姿态轨道控制系统，为星敏感器导航光学系统设计提供了参考。     

Refined modeling and experimental verification of a torque motor for an electro-hydraulic servo valve

The Permanent Magnet Torque Motor (PMTM) is the key electro-mechanical conversion device in an Electro-Hydraulic Servo Valve (EHSV). In this work, a refined model of a PMTM is developed, considering the non-working air-gaps between the upper or lower yoke and the armature, the fringing effect at the limiting holes, and the nonlinear permeability of soft magnetic material. Based on the refined model, the influences of various factors on the calculation accuracy of the magnetic flux at the pole surfaces of the armature and the output torque are investigated. For verifying the validity of the refined model, a Finite Element Analysis (FEA) of the PMTM is conducted, and a test platform is constructed. Compared with existing models, the refined model can better reveal the intrinsic mechanism of the PMTM, and its calculations are more consistent with the FEA results. The experimental results of the armature deflection displacement show that the refined model can accurately describe the output characteristics of the PMTM.     

芯片级光钟技术综述

芯片级光钟是一种基于热原子中光频跃迁的新型光钟,近年来随着光子集成技术、激光技术和微机电技术的发展,该类光钟可以实现较小的体积和较高的精度,有望广泛应用于对体积、质量、功耗和精度敏感的各种国防装备中.介绍了国内外芯片级光钟技术的进展情况,阐述了芯片级光钟的相关技术,包括基于双光子跃迁的光频标技术、微制造气室技术和微腔光频梳技术等,分析了影响频率稳定度和准确度的主要因素,最后对芯片级光钟面临的机遇和挑战进行了简要的展望.     

挠性空间机械臂伪速率增量反馈控制

针对空间机械臂平台中挠性机械臂与平台的耦合情况,采用伪速率反馈控制方法对机械臂平台的姿态控制系统进行设计和分析,使机械臂平台的姿态控制系统满足稳定性、控制精度等性能,并采用描述函数法对所设计线性控制系统的方法中,描述函数法是较为有效的方.η率脉冲调制喷气控制方案。本文在原有的伪速率脉.η的姿态控制系统进行稳定性分析。     

Comprehensive performance review of BDS-3 after one-year official operation

On July 31, 2020, the third generation BeiDou Global Satellite Navigation System (BDS-3) was officially put into service. Here we first reviewed the development history of BDS-3, and described the status of BDS-3 constellation, satellite signals, and ground tracking network. Then we expounded the 10 innovations in which BDS-3 differs from the other global satellite navigation systems. In addition, the latest service performance status of BDS-3 was displayed from a comprehensive perspective. The performance of BDS-3 was analyzed and evaluated from five aspects: constellation performance, observation data quality, spatial signal performance, PNT (Positioning, Navigation, and Timing) service performance, and precision positioning application. We used 14 indices to conduct comprehensive assessment of the BDS-3 service performance. Finally, the main direction of the next development of BDS was prospected.     

卫星在轨推进剂补加量测量方法精度研究

卫星在轨推进剂补加量的精确测量技术是在轨补加任务的关键技术之一。本文结合型号攻关结果，提出2种在轨推进剂补加量测量方法数学模型，分别是压力-体积-温度(PVT)法和超声波流量计法。首先，PVT法是一种通过补加前后受体卫星贮箱剩余量反算补加量的间接测量方法，而超声波流量计法是利用超声波顺逆流相位差进行测量的直接测量方法;其次，在推进剂补加量测量模型的基础上，进一步通过取变分的手段提出2种模型的精度分析解析模型，解析的精度分析模型不仅可用于定性分析影响测量精度的因素，还可量化评价各个因素对测量精度的影响;最后，利用现有在研单机的精度水平及精度分析解析模型分析了2种方法的测量精度，验证了方法的有效性。     

Analysis on navigation accuracy of high orbit spacecraft based on BDS GEO and IGSO satellites

To make up for the insufficiency of earth-based TT&C systems, the use of GNSS technology for high-orbit spacecraft navigation and orbit determination has become a new technology. It is of great value to applying Geosynchronous Earth Orbit (GEO) and Inclined GeoStationary Orbit (IGSO) navigation satellites for supporting the navigation of high-orbit spacecraft since there are three different types of navigation satellites in BeiDou Navigation Satellite System (BDS): Medium Earth Orbit (MEO), GEO and IGSO. This paper conducts simulation experiments based on Two-Line Orbital Element (TLE) data to analyze and demonstrate the role of these satellites in the navigation of high-orbit spacecraft. Firstly, the spacecraft in GEO was used as the target satellite to conduct navigation experiments. Experiments show that for the spacecraft on the GEO orbit, after adding GEO and IGSO respectively on the basis of receiving MEO navigation satellite signals, the accuracies were improved by 7.22 % and 6.06 % respectively. When adding both GEO and IGSO navigation satellites at the same time, the accuracy can reach 16 m. In the second place, navigation and positioning experiments were carried out on three high elliptical orbit (HEO) satellites with different semimajor axis (32037.2 km, 42385.9 km, 67509.6 km). The experiments show that the number of visible satellites has been improved significantly after adding GEO and IGSO navigation satellites at the same time. The visible satellites in these three orbits were improved by 32.84 %, 41.12 % and 37.68 %, respectively compared with only observing MEO satellites.The RMS values of the navigation positioning errors of these three orbits are 25.59 m, 87.58 m and 712.48 m, respectively.