旋转三角形绳系卫星编队系统动态稳定性分析

本文研究了平动点附近的旋转三角形绳系卫星编队系统的动态稳定性问题.为了便于分析,假设系绳始终保持张紧状态,且不计系绳的质量.为了建立更加符合实际的数学模型,考虑了姿态运动和轨道运动的相互影响,即姿轨耦合,并在此基础上推导出了考虑姿轨耦合的非线性动力学方程.最后用数值方法模拟了在不同的旋转速度情况下系统的动态稳定性,模拟结果表明旋转速率越大系统稳定性越好.     

空间绳系太阳能电站初始姿态误差影响分析

针对地球同步轨道绳系太阳能电站在轨运行的动力学问题,建立复杂绳系编队系统的动力学模型。此模型考虑了系绳的柔性、太阳能子板的姿态运动、编队系统构型与轨道运动之间相互耦合的特性。在无扰动及存在初始太阳能子板姿态误差的情况下对系统进行动力学仿真,分析了系统的稳定性。结果表明:不同方向上的初始太阳能子板姿态误差对系统的影响不同,指向地心方向上的初始姿态误差不会引起系统的运动,另外两方向上初始姿态误差会引起柔性系绳内力变化从而对系统产生影响,其中轨道运行方向上的初始姿态误差对系统的影响最明显;较小的初始姿态误差所引起的系统运动主要为太阳能子板在其平衡位置附近的小幅往复转动;初始姿态误差较大时,平台系统会大幅偏离其平衡位置,影响空间绳系太阳能电站的构型保持。     

时变自由度绳系卫星系统动力学

建立了针对无限维的黏弹性两体绳系卫星系统的时变动力学模型.当系绳释放时,卫星中系绳所对应的离散集中质量由星内移至星外,导致绳系卫星系统的自由度发生改变,成为时变的多自由度绳系卫星系统.基于改进的有限差分法,研究了判定系统自由度发生变化的方法及时变自由度绳系卫星系统动力学响应的计算方法.结果表明,所提出的计算时变自由度系统动力学响应的方法,实现了绳系卫星系统释放动力学行为的数值模拟.     

空间电动绳系推进的动力学建模与分析

为分析空间电动绳系的运动特性，从一般力学角度出发，结合电动力学知识，建立了近地轨道空间电动绳系推进飞行的动力学模型，得出了多种初始条件下的数值计算结果，并据此对电动绳系航天器的轨道机动过程进行了详尽的讨论，阐明了系统在轨道高度变化的同时，其轨道面也会发生变化，而且导电系绳还会旋转与弯曲变形等规律. 此外，还对电动绳系推进系统的效率和地球自转的影响进行了估计.     

考虑姿态的绳系卫星后退时域回收控制

建立了计入子星姿态运动的绳系卫星非线性动力学模型,研究了子星回收过程的非线性后退时域控制问题.将非线性后退时域控制问题伪线性化为一系列线性最优控制,并在Legendre-Gauss点离散,作为该复杂受控绳系卫星系统的数值求解策略.结果表明,通过调节系绳张力和作用于子星上的力矩,可实现子星的稳定回收,所设计的控制律对初始状态扰动、模型误差和外扰力等扰动均有良好的抑制作用.     

带有姿态的绳系航天器混沌运动实验研究

利用地面物理仿真平台研究了绳系航天器的混沌动力学行为. 首先, 根据天地动力学相似原理, 通过对卫星仿真器施加喷气力和动量轮力矩来模拟空间动力学环境, 提出了两种等效方案, 给出了它们各自适用的实验工况. 数值结果表明, 在轨绳系航天器在一定的参数条件下系绳摆动为周期或概周期运动、航天器姿态发生混沌运动. 物理仿真验证了等效方案的有效性, 揭示了绳系航天器的混沌运动特征, 表明在阻尼力矩的作用下可以避免绳系航天器混沌运动的发生.      

基于微分包含的绳系卫星时间最优释放控制

考虑系绳弹性的影响,建立了绳系卫星系统三维动力学模型,研究了在状态和控制约束下的绳系卫星非线性时间最优控制问题. 为缩减系统变量,控制律设计没有采用通常的状态空间模型,而是基于二阶微分包含,将连续时间最优控制问题离散为大规模动态规化问题,最后通过数值模拟验证了该方法的有效性.      

双小行星探测轨道动力学研究进展

双小行星系统由在万有引力作用下彼此环绕的两颗小行星组成, 对研究太阳系起源、行星系统演化和行星防御都具有重要的价值, 近年来成为行星科学和航天动力学研究的热门对象, 对双小行星系统的原位探测也即将迎来热潮. 双小行星系统的独特构型和附近的复杂动力学环境为探测器轨道动力学和任务设计带来了全新的挑战, 为应对这些挑战所进行的研究也推动了轨道动力学基础理论的发展. 本文对双小行星探测轨道动力学的研究进展进行综述, 首先介绍了双小行星研究和探测的背景及意义, 简要阐述了双小行星系统形成理论及其附近轨道动力学的研究概况. 其次, 介绍了双小行星系统不规则引力场和相互引力势的建模方法, 进而展示了双星的姿态轨道耦合动力学, 即完全二体问题, 包括双星相对运动的平衡构型和稳定性. 接着, 介绍了描述双星附近探测器轨道运动的限制性完全三体问题的动力学模型, 以及该模型下的平动点、平动点周期轨道、大范围周期轨道、转移轨道和轨道维持等方面的研究进展. 第四部分综述了环绕双小行星系统单颗星的受摄二体问题, 以轨道摄动理论和行星系统中受摄二体问题的研究现状为背景, 介绍了环绕双小行星系统主星的半解析轨道动力学建模与轨道稳定性分析. 之后, 介绍了目前面向探测任务需求和考虑实际约束的轨道动力学研究和轨道设计. 最后, 基于目前研究进展, 分析了面临的若干问题, 对未来双小行星探测轨道动力学及相关技术的发展进行了讨论和展望.      

绳系卫星在轨试验及地面物理仿真进展

通过系绳释放、运行和回收的在轨卫星称为绳系卫星. 绳系卫星功能独特, 在人工重力梯度、空间传送、电动力推进等方面应用广泛. 本文以绳系卫星为对象, 概述了全世界历年来绳系卫星的在轨飞行试验, 包括试验背景、目的、步骤以及结果等; 介绍了近年来绳系卫星的地面物理仿真实验技术, 分析了系统结构、仿真原理以及实验结果; 对未来我国空间绳系卫星技术的发展提出建议.     

倾斜轨道电动力绳系卫星回收控制

考虑电动力影响,建立了倾斜轨道绳系卫星系统的动力学模型,研究了子星回收过程的非线性最优控制. 应用Legendre伪谱算法,将连续时间最优控制问题离散化,进而利用非线性规划方法进行求解,通过数值模拟验证了方法的有效性. 结果表明,在满足相关约束的条件下,通过调节系绳张力和电动力,可将子星回收到靠近主星的指定位置.      

Libration suppression of tethered space system with a moving climber in circular orbit

This paper studies the dynamics and libration suppression of a tethered system with a moving climber in circular orbits. The tethered system is modeled by a two-piece dumbbell model that consists of one main satellite, one climber and one end-body connected by two straight, massless and inextensible tethers. A new tension control strategy to suppress the libration of the tethered system due to the moving climber is proposed by reeling in-out tether at the end-body without thrust. The control strategy is implemented with the sliding mode control to suppress the libration angle of the climber to zero by the end of climber’s transfer phase. The numerical results show that the proposed control strategy is very effective in suppressing the libration of the climber in the three-body tethered system with tension control only. Furthermore, cases with limited tension control are examined. It reveals that a longer tether between the climber and the end-body is required to supplement the limited tension in suppressing the libration of the climber.     

A new control law based on characteristic exponent assignment for libration point orbit maintenance

A new method is developed for stabilizing motion on collinear libration point orbits using the formalism of the circular restricted three body problem. Linearization about the collinear libration point orbits yields an unstable linear parameter-varying system with periodic coefficients. Given the variational equations, an innovative control law based on characteristic exponent assignment is introduced for libration point orbit maintenance. A numerical simulation choosing the Richardson＇s third order approximation for a halo orbit as a nominal orbit is conducted, and the results demonstrate the effectiveness of this control law.     

A station-keeping strategy for collinear libration point orbits

Spacecrafts in periodic or quasi-periodic orbits near the collinear libration points are proved to be excellent platforms for scientific investigations of various phenomena. Since such periodic or quasi-periodic orbits are exponentially unstable, the station-keeping maneuver is needed. A station-keeping strategy which is found by an analytical method is presented to eradicate the dominant unstable component of the libration point trajectories. The inhibit force transforms the unstable component to a stable component. In this method, it is not necessary to determine a nominal orbit as a reference path.     

基于多项式约束的三角平动点平面周期轨道设计方法1）

平动点是圆型限制性三体问题中的五个平衡解.其中,三角平动点在平面问题中具有“中心×中心”的动力学特性,其附近存在着大量的周期轨道,研究这些周期轨道的构建方法在深空探测中具有理论及工程意义.本文从振动角度分析周期轨道,通过多项式展开法构建出主坐标下周期轨道两个运动方向之间的渐近关系.从新的角度分析了系统的动力学特性和平面周期运动两个方向内在关联以及物理规律.这种多项式形式的关系式,可以作为约束条件用于数值微分修正算法中,通过迭代的方式寻找周期轨道.数值仿真算例验证了方法的正确性及精确性.文章从振动的角度对周期轨道进行分析,改进了微分修正算法.提出的方法可以被拓展至圆型/椭圆型限制性三体问题的三维周期轨道构建中.     

Periodic motion around libration points in the Elliptic Restricted Three-Body Problem

Periodicity of motion around the collinear libration point associated with the Elliptic Restricted Three-Body Problem is studied. A survey of periodic solutions in the Circular Restricted Three-Body Problem is presented considering both Sun–Earth and Earth–Moon systems. Halo, Lyapunov and Vertical families around L1, L2 and L3 points are investigated, and their orbital period ranges through the entire family are reported. Resonant motions within the orbit families in the circular problem are identified and selected as suitable initial guess to find periodic orbits in the elliptic problem, which are targeted using a differential correction algorithm. Periodic solutions found are cataloged depending on the number of revolutions around libration points. Geometry, dynamical behavior and stability properties of single-revolution orbits are shown, as well as double-, triple- and quadruple-revolution solutions.     

COLLINEAR LIBRATION POINTS WITH CONTINUOUS LOW THRUST

研究了圆型限制性三体问题的平动点在连续小推力作用下的具体位置和动力学特征的变化. 研究表明,随着小推力方向在空间中的变化,平动点的具体位置也会发生相应的变化,文章详细阐述了这些变化的特征.针对航天任务中应用较多的共线平动点L1和L2,研究了其附近运动的稳定性状态,给出了线性条件稳定解,并在此基础上,构造了条件稳定解的高阶形式,将其结果与数值积分轨道进行了比对,两者符合得很好. 最后,进一步研究了共线平动点附近周期轨道族的演化状态,由于连续小推力引入的非对称性,周期轨道族会发生分岔现象.     

Dynamic analysis of a tethered satellite system with a moving mass

This paper presents a dynamic analysis of a tethered satellite system with a moving mass. A dynamic model with four degrees of freedom, i.e., a two-piece dumbbell model, is established for tethered satellites conveying a mass between them along the tether length. This model includes two satellites and a moving mass, treated as particles in a single orbital plane, which are connected by massless, straight tethers. The equations of motion are derived by using Lagrange’s equations. From the equations of motion, the dynamic response of the system when the moving mass travels along the tether connecting the two satellites is computed and analyzed. We investigate the global tendencies of the libration angle difference (between the two sections of tether) with respect to the changes in the system parameters, such as the initial libration angle, size (i.e. mass) of the moving mass, velocity of the moving mass, and tether length. We also present an elliptic orbit case and show that the libration angles and their difference increase as orbital eccentricity increases. Finally, our results show that a one-piece dumbbell model is qualitatively valid for studying the system under certain conditions, such as when the initial libration angles, moving mass velocity, and moving mass size are small, the tether length is large, and the mass ratio of the two satellites is large.     

基于混合Lie算子辛算法的不变流形计算

平动点附近周期轨道的不变流形因其在低能轨道转移中起着重要作用而受到广泛关注.在设计低能轨道过程中不变流形要实时进行能量匹配,但利用传统数值积分方法进行积分时能量会耗散.显式辛算法具有比隐式辛算法计算效率高的优势,但其要求Hamilton系统必须分成两个可积的部分,而旋转坐标系下的圆型限制性三体问题是不可分的,因而显式辛算法难以用于求解旋转坐标系下的圆型限制性三体问题.本文通过引入混合Lie算子,成功实现了带三阶导数项的力梯度辛算法对圆型限制性三体问题的求解,并将基于混合Lie算子的带三阶导数项的辛算法与Runge-Kutta78算法和Runge-Kutta45算法进行仿真对比,仿真结果表明基于混合Lie算子的含有三阶导数项的辛算法位置精度高、能量误差小且计算效率高.利用基于混合Lie算子的带三阶导数项的辛算法计算不变流形,可以实现低能轨道转移过程中轨道拼接点的能量精准匹配.     

Complex dynamics of perfect discrete systems under partial follower forces

Equilibrium points, primary and secondary static bifurcation branches, and periodic orbits with their bifurcations of discrete systems under partial follower forces and no initial imperfections are examined. Equilibrium points are computed by solving sets of simultaneous, non-linear algebraic equations, whilst periodic orbits are determined numerically by solving 2- or 4-dimensional non-linear boundary value problems. A specific application is given with Ziegler's 2-DOF cantilever model. Numerous, complicated static bifurcation paths are computed as well as complicated series of periodic orbit bifurcations of relatively large periods. Numerical simulations indicate that chaotic-like transient motions of the system may appear when a forcing parameter increases above the divergence state. At these forcing parameter values, there co-exist numerous branches of bifurcating periodic orbits of the system; it is conjectured that sensitive dependence on initial conditions due to the large number of co-existing periodic orbits causes the chaotic-like transients observed in the numerical simulations.     

Subharmonic Melnikov method of six-dimensional nonlinear systems and application to a laminated composite piezoelectric rectangular plate

In this paper, the bifurcations of subharmonic orbits are investigated for six-dimensional non-autonomous nonlinear systems using the improved subharmonic Melnikov method. The unperturbed system is composed of three independent planar Hamiltonian systems such that the unperturbed system has a family of periodic orbits. The key problem at hand is the determination of the sufficient conditions on some of the periodic orbits for the unperturbed system to generate the subharmonic orbits after the periodic perturbations. Using the periodic transformations and the Poincaré map, an improved subharmonic Melnikov method is presented. Two theorems are obtained and can be used to analyze the subharmonic dynamic responses of six-dimensional non-autonomous nonlinear systems. The subharmonic Melnikov method is directly utilized to investigate the subharmonic orbits of the six-dimensional non-autonomous nonlinear system for a laminated composite piezoelectric rectangular plate. Using the subharmonic Melnikov method, the bifurcation function of the subharmonic orbit is obtained. Numerical simulations are used to verify the analytical predictions. The results of the numerical simulation also indicate the existence of the subharmonic orbits for the laminated composite piezoelectric rectangular plate.