A guidance strategy for rendezvous and docking to the space station in the Earth-Moon NRHO orbit

With the development of space technology,it is possible to build a space station in Earth-Moon space as a transit for Earth-Moon round-trip and entering in the deep space.Rendezvous and docking is one of the key technologies for building an Earth-Moon space station.A guidance strategy for rendezvous and docking from the Earth orbit to the space station in the Earth-Moon NRHO orbit is proposed in this paper,which is suitable for engineering applications.Firstly,the rendezvous and docking process is divided into three sections,i.e.,the large-range orbit transfer section,far-range guidance section,and close-range approaching section.The suitable terminal of large-range orbit transfer is selected according to the eigenvalue of NRHO orbit state transition matrix.The two-impulse guidance method based on the relative motion equation in the three-body problem is adopted for the far-range guidance section.The impulse time and amplitude are solved with the optimization algorithm.The linear constant three-body relative motion equation is proposed for the close-range approaching section,and the rendezvous and docking is completed by a two-stage linear approximation.Finally,a simulation analysis is carried out,and the simulation results show that the adopted dynamics equations and the designed guidance law are effective,and the three flight phases are naturally connected to accomplish the rendezvous and docking mission from the Earth orbit to the space station on the Earth-Moon NRHO.

Predictive Modeling and Parameter Optimization of Cutting Forces During Orbital Drilling

To optimize cutting control parameters and provide scientific evidence for controlling cutting forces,cutting force modeling and cutting control parameter optimization are researched with one tool adopted to orbital drill holes in aluminum alloy 6061.Firstly,four cutting control parameters(tool rotation speed,tool revolution speed,axial feeding pitch and tool revolution radius)and affecting cutting forces are identified after orbital drilling kinematics analysis.Secondly,hybrid level orthogonal experiment method is utilized in modeling experiment.By nonlinear regression analysis,two quadratic prediction models for axial and radial forces are established,where the above four control parameters are used as input variables.Then,model accuracy and cutting control parameters are analyzed.Upon axial and radial forces models,two optimal combinations of cutting control parameters are obtained for processing a13mm hole,corresponding to the minimum axial force and the radial force respectively.Finally,each optimal combination is applied in verification experiment.The verification experiment results of cutting force are in good agreement with prediction model,which confirms accracy of the research method in practical production.

THE IMPACTS OF ORBITAL PARAMETERS ON SUMMER PRECIPITATION OVER CHINA IN THE HOLOCENE

The impact of orbital parameters on the climate of China in the Holocene is simulated from 11kaBP to 0kaBP with an interval of 1ka using National Center for Atmospheric Research (NCAR) Community Atmosphere Model version 2 (CAM2). The geographic distributions of summer precipitation around both 9kaBP and 4kaBP were realistically captured by CAM2, compared to the proxy data collected from 80 stations. Among all orbital parameters, the precession plays a major role in computing solar radiation, which dominates the variations of summer precipitation over China during the Holocene. The summers around 9kaBP were the wettest in China. Later on, the precipitation gradually reduced to the minimum around 0kaBP by about 10%. This tremendous change occurred from the Northeast China and the eastern Inner Mongolia extending southwestwards to the Qinghai-Tibet Plateau, especially over the Qinghai-Tibet Plateau.

Simulation of the Impacts of Single LEO Satellite Orbit Parameters on the Distribution and Number of Occultation Events

Focusing on carrying out GPS occultation observat io ns with a receiver set on LEO satellite, this paper develops the LEO orbit simul ation system based on which the occultation events can be simulated taking into account the geometric relationship of the satellites and the field of view of th e receiver antenna. In this paper, the impacts of 4 types of LEO orbit parameter s including argument of latitude (AOL), right ascension of ascending node (RAAN) , orbit height and orbit inclination on the distribution and number of occultati on events observed with a single LEO satellite are discussed through simulat ion and some conclusions are drawn.

CONTROLLING HYPERCHAOS IN PLANAR SYSTEMS BY ADJUSTING PARAMETERS

For the two_parameter family of planar mapping, a method to stabilize an unstable fixed point without stable manifold embedding in hyperchaos is introduced. It works by adjusting the two parameters in each iteration of the map. The explicit expressions for the parameter adjustments are derived, and strict proof of convergence for method is given.

A 16-parameter GEO Broadcast Ephemeris

Currently,the broadcast ephemerides used in GEOs are same as those of the MEOs and IGSOs in the BeiDou navigation constellation.However,a trade-off strategy,i.e.an orbital inclination of 5°rotation,is needed in the fitting algorithm to solve the ephemeris parameters as well as the user satellite position computation for GEOs.Based on the standard broadcast ephemerides,the representations of both the orbit and its perturbation were revised according to the second class of nonsingular orbital elements.In this research,a 16-parameter broadcast ephemeris is presented specifically for GEOs,and user satellite position computation formulas were derived correspondingly.Fit simulations show that the root of mean squares(RMS)of user range error(URE)with two hour and three hour data sets are better than 0.05 m and 0.1 m,respectively.

The Orbital Error Analysis and Study of Space Vehicle Active Phase

In this paper we solve the three-dimensional coordinate that the satellite is relative to the geocentric coordinate under certain conditions, making use of the satellite orbit standard trajectory differential equations. By means of the method of tri-parametric equation fitting, we confirm the three-dimensional trajectory function of target flying object to geocentric coordinate in double satellites observation conditions, and analyze theoretical errors.

Theoretical investigations of the local distortion and electron paramagnetic resonance parameter for CdCl_2:V^(2+) and CsMgX_3:V_^(2+)(X=Cl,Br) systems

This paper systematically investigates the local distortion and electron paramagnetic resonance （EPR） parameter for CdCl2：V^2＋ and CsMgX3：V^2＋ （X=Cl, Br） systems on the basis of the complete energy matrix, in which not only the contributions due to the spin-orbit coupling of the central ions but also that of the ligands are considered. To describe the difference of overlapping between d-orbits and p orbit, two spin-orbit coupling coefficients are introduced. By simulating the crystal field parameter and EPR parameter, the local distortion parameters are studied and the relationships between the EPR parameter and the spin-orbit coupling coefficients as well as divergent parameter are discussed. These results show that the local structures exhibit compression distortion for CdCl2：V^2＋ and elongation distortions for CsMgX3：V^2＋ （X：Cl, Br）, respectively. It notes that the empirical formula R≈RH T （ri - rh）/2 is not suitable for CdCl2：V^2＋ and CsMgX3：V^2＋ （X=Cl, Br） systems. The contributions of ligand to spin-orbit coupling interaction cannot be neglected for strong covalent systems, especially for V^2＋ doped in CsMgBr3：V^2＋.

The Figure and Dynamical Parameters of Io Inferred from Internal Structure Models

The recent Galileo spacecraft explored Jupiter and its satellite system and provided us with new geodetic data. In order to discuss the dynamical parameters and secular tidal effect of Io, the theory of synchronous satellite is described in detail. Using the new geodetic data of Io, two sets of Io's internal structure models are constructed based on the asthenosphere assumption. The liberation parameters α,β,γ and dynamical flattening H are calculated for the models of Io. A comparison of Io with the Moon indicates that they are quite different in many characteristics in spite of the fact that they are approximately equal in mass and size and that they both orbit synchronously.

航天器入轨状态与偏差传播分析

本文研究了航天器入轨状态和入轨偏差传播问题。推导了火箭熄火时的入轨速度平方比率及速度仰角与主要轨道参数之间的关系,从而分析航天器的入轨状态。建立了航天器转移轨道的偏差传播矩阵,得到入轨偏差对转移轨道的影响。将本文的偏差传播分析方法与传统轨道误差分析方法进行对比以验证本文方法的正确性。最后,通过仿真算例分析了航天器入轨状态和入轨偏差对转移轨道的影响。

参量共振单摆的理论与实验研究

为了将参量共振引入基础物理实验教学,搭建了参量驱动单摆实验系统,并从理论和实验上研究了平衡点附近的运动.理论上,利用微扰方法计算了轨道的一般形式,在此基础上确定了参量共振带的边界,并得到了轨道特征量与驱动参量(频率与幅度)的依赖关系.实验上,利用2个一维激光位移传感器组装成二维位移传感器,实现了单摆轨迹的实时测量.在参量共振带内,测量了不同驱动频率下的轨道发散指数和振子-驱动相位差;在参量共振带的中心,测量了发散指数与驱动幅度之间的关系;在参量共振带的外边缘,测量了轨道包络的拍频和调制深度与驱动频率的关系.所有测量结果都与一阶微扰计算符合良好.

星基并置轨道配置对地球自转参数解算的影响

为了进一步研究全球卫星导航系统(GNSS)和卫星激光测距(SLR)低轨卫星(LEO)星基并置对于地球自转参数(ERP)解算的贡献,综合评估星基并置轨道配置和空间连接误差对地球自转参数解算的影响:通过仿真实验,联合地面全球定位系统(GPS)、低轨卫星星载GPS,以及低轨卫星激光测距观测数据,分析低轨卫星轨道配置、空间连接误差对地球自转参数解算精度的影响。结果表明,ERP的估计精度受低轨星基并置站的轨道高度和倾角影响较为明显;相比于低轨道、低倾角卫星,高轨道、高倾角卫星对于极移参数的解算精度提升效果更为显著,这主要是得益于该轨道配置可提供更多的SLR观测数据;此外,空间连接误差分析结果表明,ERP对于低轨卫星SLR棱镜质心改正的误差更加敏感,特别是在Z向,2 cm的Z向SLR棱镜质心改正误差可使得极移X分量和Y分量的估计精度分别下降24%和14%。

基于失效卫星轨道数据的空间环境评估方法

卫星姿轨控系统失效后,在空间自由漂浮,空间环境的长期影响及其变化将直接在失效卫星的轨道参数的微弱变化中体现。本文研究了失效卫星轨道根数数据用于原位溯源空间环境长周期扰动影响的可行性及方法,基于非均匀采样傅里叶变换手段,实现公开卫星轨道数据的长周期频率特征提取,并与太阳活动相关的空间环境影响周期匹配。通过大数据分析多颗失效卫星公开轨道数据,以卫星轨道倾角为例,识别出太阳活动相关的空间环境对低轨卫星轨道摄动的周期400、89和13.5 d。该方法为失效卫星轨道数据的利用挖掘提供了新思路。

LEO星载GPS实时精密定轨伪模糊度随机过程参数优化

提出在定轨策略及其他变量不变的情况下,使用一种数值步进的搜索比较方法,以确定伪模糊度随机过程参数的最优设置。使用GRACE-C、SWARM-A两颗LEO卫星2021年doy92~101共10 d的GPS数据及同时段的CNT、MADOCA两种实时精密星历产品,以模拟在轨实时精密定轨的方式,对伪模糊度随机过程参数开展优化实验。结果表明,在伪模糊度参数最优值方案下,两颗LEO卫星的实时精密定轨三维位置误差(RMS)约为4.62~7.56 cm,相比于传统模糊度浮点解方案,使用CNT和MADOCA产品的实时定轨精度分别平均提升约39.15%和29.61%。

Ion-acoustic waves with non-planar wavefronts

The ion-acoustic(IA) mode exhibiting various orbital angular momentum(OAM) states is examined in a plasma with drifting electrons.The constituent plasma species are modeled with a non-gyrotropic Maxwellian distribution and discussion of dispersion relation and growth rate of twisted IA waves under various conditions is presented.In the domain of kinetic model,the twisted IA waves are characterized by Laguerre-Gaussian(LG) solutions,where plasma distribution function and electric field are decomposed into axial and azimuthal components.The plasma response function is obtained under paraxial approximations and investigated for threshold condition of instability growth rate with helical electric field structures.The impact of an extra electron specie on the instability is demonstrated through a comparison of twisted waves for single and double electron species.

沁水盆地左权地区山西组米氏旋回识别及其天文年代标尺

依据地层序列的旋回信号进行地球轨道参数周期的识别,是确定深时时间尺度的有效方法之一。以沁水盆地左权地区山西组为例,使用时间序列分析法与相关系数法对钻孔剖面自然伽马测井曲线进行旋回性分析,并据此建立山西组年代地层标尺。使用频谱分析,在区内山西组识别出7.13 m、1.62~2.23 m的优势沉积旋回,分别对应405 kyr的长偏心率周期和91.9~126.4 kyr的短偏心率周期,经过天文检验,证实沁水盆地山西组受到天文周期驱动。通过高斯带通滤波,建立沁水盆地山西组“浮动”天文年代标尺,确定出9个405 kyr长偏心率旋回,据此获得山西组沉积时限为3.82 Myr。建立的天文年代标尺可为沁水盆地山西组古环境、古气候和各种地质事件的演化提供年代学依据。

Ka波段大回旋电子注介质加载回旋行波管输入耦合器研究

针对Ka波段大回旋电子注回旋行波管设计了一个TE 21模式输入耦合器。该输入耦合器结构为Y形功分器,将输入的矩形波导TE 10模式转换为圆波导的TE 21模式进行输出。本文对其转换原理进行了简要介绍,通过仿真确定了输入耦合器模型的参数,并加工出部件,并进行了实际测试,测试的结果满足Ka波段大回旋行波管的信号输入要求。

定量研究地球轨道参数和温室气体浓度变化对中全新世气候的影响

依据最新的古气候耦合模式比较计划(PMIP4)协议,利用完全耦合的气候模式CESM1.0,研究中全新世与工业革命前气候的差异,量化地球轨道参数(ORB)和温室气体(GHG)对中全新世气候变化的影响。3个模拟试验结果表明,与工业革命前相比,中全新世北半球高纬度地区气候偏温,全球其他地区气候偏冷,北半球大部分地区更湿润,南半球则较为干燥;ORB导致全球中高纬度地区升温,GHG在降低全球气温和减少中高纬度地区降水方面发挥作用;这种差异引起大气和海洋环流的变化,导致地球经向热量输送的差异;就总经向热量输送的变化范围而言,ORB对气候的影响大约是GHG的5倍。研究结果对深入了解中全新世气候及其对不同外部强迫的响应有积极意义。

Artificial Sun synchronous frozen orbit control scheme design based on J_2 perturbation

Sun synchronous orbit and frozen orbit formed due to J 2 perturbation have very strict constraints on orbital parameters,which have restricted the application a lot.In this paper,several control strategies were illustrated to realize Sun synchronous frozen orbit with arbitrary orbital elements using continuous low-thrust.Firstly,according to mean element method,the averaged rate of change of the orbital elements,originating from disturbing constant accelerations over one orbital period,was derived from Gauss＇ variation of parameters equations.Then,we proposed that binormal acceleration could be used to realize Sun synchronous orbit,and radial or transverse acceleration could be adopted to eliminate the rotation of the argument of the perigee.Finally,amending methods on the control strategies mentioned above were presented to eliminate the residual secular growth.Simulation results showed that the control strategies illustrated in this paper could realize Sun synchronous frozen orbit with arbitrary orbital elements,and can save much more energy than the schemes presented in previous studies,and have no side effect on other orbital parameters＇ secular motion.

Consistency of MGEX Orbit and Clock Products

The analysis centers of the Multi-GNSS Pilot Project of the International GNSS Service provide orbit and clock products for the global navigation satellite systems(GNSSs)Global Positioning System(GPS),GLONASS,Galileo,and BeiDou,as well as for the Japanese regional Quasi-Zenith Satellite System(QZSS).Due to improved solar radiation pressure modeling and other more sophisticated models,the consistency of these products has improved in recent years.The current orbit consistency between different analysis centers is on the level of a few centimeters for GPS,around one decimeter for GLONASS and Galileo,a few decimeters for BeiDou-2,and several decimeters for QZSS.The clock consistency is about 2 cm for GPS,5 cm for GLONASS and Galileo,and 10 cm for BeiDou-2.In terms of carrier phase modeling error for precise point positioning,the various products exhibit consistencies of 2–3 cm for GPS,6–14 cm for GLONASS,3–10 cm for Galileo,and 10–17 cm for BeiDou-2.