Visualization of Traveling Vortices in the Boundary Layer on a Rotating Disk under Orbital Motion

The objective of this study is to experimentally visualize traveling vortices in the boundary layer on a rotating disk under orbital motion. The orbital radius is half of the disk’s diameter (200 mm) and the maximum speed of orbital motion is 500 revolutions per minute. The Reynolds number in the pure-rotation case is 2.77 × 105. The characteristics of two types of traveling vortices are visualized by a smoke-wire method. The first type is transition vortices. In the pure-rotation case, they arise at circumferentially equal intervals, and are not traveling but stationary relative to the rotational disk. The result of visualization of this type shows that the intervals between transient vortices change in a circumferential direction, or in an orbital radial direction, on the rotating disk under orbital motion. The second type is new arc-shaped vortices that correspond to low-frequency disturbances. As orbital speed increases, the radial traveling velocities of the low-frequency disturbances increase and the intervals between low-frequency disturbances decrease.

Averaging analyses for spacecraft orbital motions around asteroids

This paper summarizes a few cases of spacecraft orbital motion around asteroid for which averaging method can be applied, i.e., when central body rotates slowly, fast, and when a spacecraft is near to the resonant orbits between the spacecraft mean motion and the central body＇s rotation. Averaging conditions for these cases are given. As a major extension, a few classes of near resonant orbits are analyzed by the averaging method. Then some resulted conclusions of these averaging analyses are applied to understand the stabil- ity regions in a numerical experiment. Some stability conclu- sions are obtained. As a typical example, it is shown in detail that near circular 1 ： 2 resonant orbit is always unstable.

NONGRAVITATIONAL EFFECT ON ORBITAL MOTIONS OF COMETS

Since the concept of Nongravitational Force (hereafter NF) was first proposed a century and a half ago, different models of it have been suggested and being modified. Its effect on the orbital motions of comets has been studied. Especially, some researchers have attempted to draw some inclues of the physical nature of the cometary nucleus from the NF parameters. In this paper, we try to give a concise review about the different models of NF and their effects on orbit computation. And then, we will try to detect whether there is nongravitational effect on Comet Hale-Bopp’s orbital motion using Style II NF model.

Orbital Spin: A New Hypothesis to Explain Precession of Equinox—The Third Motion of Earth

In this paper, the phenomena of Earth’s motion about its own axis, the ecliptic plane of the Earth’s orbit around the Sun, the definitions of equinoxes, the precession of equinoxes, Earth’s wobble and other astronomical terminology are briefly described. Some of the existing theories explaining the precession of equinox and their inadequacies are brought out. New Hypothesis is that precession of equinoxes is a direct result of Orbital spin of Earth in a retrograde direction—a celestial phenomenon similar to that of Moon’s Orbital spin around the Earth. The study of Moon’s orbit round the Earth reveals the exact movement of Earth’s orbit, which causes precession of equinoxes without any ambiguity. The analogy presented herein demonstrates the plausible hypothesis.

Determination of the Proper Motions and Membership of the Globular Cluster M3 and of its Orbit in the Galaxy

We examine 14 plates of the globular cluster M3 (NGC 5272) taken with the 40 cm refractor at the Sheshan station of Shanghai Astronomical Observatory. The plates span over a period of about 77 years. The positions and absolute proper motions of eight stars in the Hipparcos Catalogue and of 49 stars in the Tycho-2 Catalogue are used as the reference frame. The astrometric reduction is made with the central overlapping principle. The absolute proper motions of 534 stars in a region of about 100' × 100' around the cluster are measured. With the new proper motion data the membership probabilities of the stars are determined. The average absolute proper motion obtained for the cluster is -0.06±0.30 mas yr-1 in R.A. and -2.6±0.30 mas yr-1 in Decl. By combining this result with the known distance and radial velocity of the cluster, we also obtained the Galactic orbit of M3 for a chosen three-component Galactic potential.

The Absolute Proper Motion of M3 and Its Galactic Orbit

We have obtained the absolute proper motion of globular cluster M3 from measurements of 14 plates taken with the 40cm refractor at Sheshan station of Shanghai observatory, spanning epoch is about 80 years. The positions and absolute proper motions of 24 stars in ACT catalogue are used as the reference frame. The reduction was made with the central overlapping principle. The absolute proper motions of 534 stars in the region of about 1° 5×1° 5 around the cluster M3 are determined. With the new data of proper motions, the membership probabilities of the stars are determined. The mean absolute proper motions for the cluster of -0 3±0 3 mas/yr in R.A. and -3 1±0 3 mas/yr in Dec. were obtained.Combining our results with the known distance and radial velocity of the cluster, we obtained its space motions and Galactic orbits in two different three component Galactic potentials.

航天器相对运动的教学设计与思政实践

航天器相对运动研究两个及以上航天器在太空中相对彼此的运动特性,在空间交会对接和空间站建设运营等领域有着广泛的应用。相对运动的教学工作面临理论公式繁多、运动特性反直觉、思政案例难设计等挑战。课程负责人设计了“历史背景—基础理论—思想实验—课堂讨论—编程实践—工程案例”的教学流程和方法,并在其中穿插融入了人类交会对接成就史和月球采样返回的中国方案等思政案例。教学实践表明,该教学和思政设计能有效提升学生的学习成效,使得思想政治教育与专业知识教育相辅相成。

航天器受控绕飞任务规划与自主通用软件实现

针对日益复杂的太空安全形势和空间在轨服务需求,基于自研的自主航天任务设计工具箱研究了航天器受控绕飞轨迹设计及规划方法。假设航天器采用多脉冲机动完成受控绕飞任务,首先分析受控绕飞的任务流程,并给出进入绕飞段和快速绕飞段的轨迹设计方案;然后,针对目标航天器轨道为圆轨道和非圆轨道的情况,计算了多脉冲拱线抵近和多脉冲圆形绕飞过程中各导航点位置和所包含瞄准序列段的参数;最后,通过自主航天任务设计软件实现了受控绕飞任务的轨迹规划,对绕飞参数进行了分析。仿真结果表明:受控绕飞所需总的速度脉冲随进入绕飞段的任务时间和最大转移飞行角的增大而减小,随快速绕飞段绕飞半径、绕飞点数、绕飞周期时间比例的增加而增加。

空间桁架在轨装配机器人的运动规划方法

提出一种利用机器人完成空间桁架在轨装配的设计方案,并针对其中机器人的无碰运动规划问题,提出一种引入启发信息的运动规划方法。首先,设计了装配机器人和空间桁架系统;随后,引入基于距离场的碰撞检测算法进行空间中的障碍检测,并利用随机轨迹优化框架下的运动规划(stochastic trajectory optimization for motion planning,STOMP)算法进行机器人无碰运动规划;针对其中随机叠加轨迹方向不确定导致的规划效率低的问题提出了启发式STOMP(heuristically STOMP,hSTOMP)运动规划算法。仿真结果表明该算法能够快速得到机器人的无碰平滑关节轨迹,其中启发信息的引入大大提高了原算法的规划效率,具有一定的理论意义和应用价值。

一种面向限制性三体问题的轨道-姿态运动模态构建方法

针对平动点附近的具有强非线性和耦合性的轨道-姿态动力学机理分析,以及如何利用其动力学特性完成相关任务操作等问题,提出了基于Floquet理论的轨道-姿态运动模态构建方法,并探讨了所构建模态的典型应用。首先,在平动点轨道-姿态周期解的基础上,对轨道-姿态状态转移矩阵进行分块,根据分块矩阵特征值特点,建立了姿态模态和姿轨耦合模态,与轨道模态共同构成完整的轨道-姿态运动模态。然后,对模态特性进行了相空间分析。最后,以平动点相对轨道-姿态运动解析、平动点轨道-姿态稳定性控制和平动点轨道附近姿轨编队设计为应用案例,相应数值仿真表明了所提出模态的正确性,以及在典型航天任务设计与控制中的应用价值。

Starlink卫星运动仿真分析

基于开普勒第三定律,研究Starlink卫星轨道运行轨迹,分析其轨道运行特征,建立轨道仿真模型,使用高阶的Runge-Kutta方法求解方程,并利用STK对中国东南地区以及中国低纬度地区的Starlink卫星覆盖情况进行分析。仿真结果表明:随着Starlink卫星发射数量的增加,整体覆盖能力稳步提升。最开始1000颗卫星的覆盖范围在北纬54°至南纬54°之间,中国低纬地区的覆盖程度要比中纬地区低;2000颗卫星在此范围之间的覆盖达到了100%,3000颗卫星的覆盖水平明显提高,并且向两极方向延伸,但是一直无法覆盖两极地区。

低轨互联网星座发展研究

近年来,随着互联网用户激增,SpaceX、OneWeb等创新型企业纷纷计划打造低轨互联网星座,引发全球低轨卫星互联网星座的发展热潮。因此,研究国内外低轨互联网星座的发展情况及当前面临的技术难题有着很重要的意义。基于此,介绍了国外具有代表性的3个低轨互联网星座计划(Starlink、OneWeb、Lightspeed)及国内星座的最新发展情况;根据低轨互联网星座的特点,着重分析了低轨互联网星座面临的五大技术挑战:星座相对运动演化预报、星座自主导航与定轨、星座构型重构的路径规划、星座自组织协同构型控制、星座通信与网络服务;根据当前低轨互联网星座的发展趋势,对中国在低轨互联网星座的发展给出了建议。

Particle Motion in Surface Gravity Waves

Fluid particles in translating surface gravity waves have an orbital motion which decreases in size with increasing mean depth. These wave characteristics came from observations and were not forecast theoretically. The classical potential flow model is incapable of explaining the particle movement due to the irrotational assumption and to a flaw in carrying out the method. When a wave passes by an observer from left to right, the particles move clockwise under a crest and a trough. This correct conclusion is consistent with what the incorrect standard theory implies but should not be considered to have been derived from it.

Formation around planetary displaced orbit

The paper investigates the relative motion around the planetary displaced orbit. Several kinds of displaced orbits for geocentric and martian cases were discussed. First, the relative motion was linearized around the displaced orbits. Then, two seminatural control laws were investigated for each kind of orbit and the stable regions were obtained for each case. One of the two control laws is the passive control law that is very attractive for engineering practice. However, the two control laws are not very suitable for the Martian mission. Another special semi-natural control law is designed based on the requirement of the Martian mission. The results show that large stable regions exist for the control law.

Design and control of multiple spacecraft formation flying in elliptical orbits

Spacecraft formation flying is an attractive new concept in international aeronautic fields because of its powerful functions and low cost. In this paper, the formation design and PD closed-loop control of spacecraft formation flying in elliptical orbits are discussed. Based on two-body relative dynamics, the true anomaly is applied as independent variable instead of the variable of time. Since the apogee is considered as the starting point, the six integrating constants are calculated. Therefore, the algebraic solution is obtained for the relative motion in elliptical orbits. Moreover, the formation design is presented and both circular formation and line formation are provided in terms of an algebraic solution. This paper also discusses the PD-closed loop control for precise formation control in elliptical orbits. In this part, the error-type state equation is put forward and the linear quadratic regulator （LQR） method is used to calculate PD parameters. Though the gain matrix calculated from LQR is time-variable because the error-type state equation is time variable, the PD parameters are also considered as constants because of their small changes in simulation. Finally, taking circular formation as an example, the initial orbital elements are achieved for three secondary spacecraft. And the numerical simulation is analyzed under PD formation control with initial errors and J2 perturbation. The simulation results demonstrate the validity of PD closed-loop control scheme.

HETEROCLINIC ORBIT AND SUBHARMONIC BIFURCATIONS AND CHAOS OF NONLINEAR OSCILLATOR

Dynamical behavior of nonlinear oscillator under combined parametric and forcing excitation, which includes yon der Pol damping, is very complex. In this paper, Melnikov's method is used to study the heteroclinic orbit bifurcations, subharmonic bifurcations and chaos in this system. Smale horseshoes and chaotic motions can occur from odd subharmonic bifurcation of infinite order in this system-far various resonant cases finally the numerical computing method is used to study chaotic motions of this system. The results achieved reveal some new phenomena.

Analytical Solution for Formation Flying Problem near Equatorial-Circular Reference Orbit

The relative motion between multiple satellites is a developed technique with many applications. Formation-flying missions use the relative motion dynamics in their design. In this work, the motion in invariant relative orbits is considered under the effects of second-order zonal harmonics in an equatorial orbit. The Hamiltonian framework is used to formulate the problem. All the possible conditions of the invariant relative motion are obtained with different inclinations of the follower satellite orbits. These second-order conditions warrantee the drift rates keeping two, or more, neighboring orbits from drifting apart. The conditions have been modeled. All the possibilities of choosing mean elements of the leader satellite orbit and differences in momenta between leader and follower satellites’ orbits are presented.

Study and Analysis of the Orbital and Physical Properties of 2010 TK₇

In this paper we calculate the volume, mass, gravitational attraction to the Earth, angular momentum the orbit of the Trojan asteroid (TK7) [1]. In this paper, we use classical Newtonian mechanics to analyse some of the physical and orbital properties of the Trojan asteroid, which are still experimentally unknown. The asteroid should remain in Earth’s orbit for the next 100 years. We conclude by providing informed estimates of 2010 TK7’s yet unknown physical properties: i.e. mass, volume, gravitational attraction to Earth and angular momentum.

论太阳轨道运动不绕过太阳系质心的准2400年周期成因

K指数越大表明行星系统在某一径向方向会合的程度越大.K指数极值标定的太阳轨道运动半径的变化具有凸显的准20 a、179 a、2400 a周期嵌套关系.随时间尺度的增大,K指数极大值不但呈现出显著的准2400 a周期,而且太阳系质心在太阳本体内外持续的时间长度的变化也具有准2400 a周期.这其中隐含太阳轨道运动不绕过太阳系质心的准2400 a周期特殊规律.本文以木星和太阳连线为基准方向,创建了行星会合向量指数K.K向量指数图像清晰地呈现出由13~14个准179 a包络线周期(其中3~4个周期谷值出现K<0)构成的太阳轨道运动不绕过太阳系质心的准2400a周期.这一发现为科学辨识太阳轨道运动特征的复杂性又向前推进一步.

Spatiotemporal Bloch states of a spin–orbit coupled Bose–Einstein condensate in an optical lattice

We study the spatiotemporal Bloch states of a high-frequency driven two-component Bose–Einstein condensate(BEC)with spin–orbit coupling(SOC) in an optical lattice. By adopting the rotating-wave approximation(RWA) and applying an exact trial-solution to the corresponding quasistationary system, we establish a different method for tuning SOC via external field such that the existence conditions of the exact particular solutions are fitted. Several novel features related to the exact states are demonstrated; for example, SOC leads to spin–motion entanglement for the spatiotemporal Bloch states, SOC increases the population imbalance of the two-component BEC, and SOC can be applied to manipulate the stable atomic flow which is conducive to control quantum transport of the BEC for different application purposes.