小行星捕获轨道优化研究综述

小行星捕获对研究行星起源、地球生命来源、防御小行星撞击地球和开采行星矿产资源具有重要的意义。由于现有的推进器能力不足,小行星捕获任务中优化小行星捕获所需要的速度增量是任务成败的关键。本文分别从利用引力辅助轨道优化、连续小推力轨迹优化、小行星捕获任务轨道优化设计及小行星临时捕获等4 个方向介绍小行星捕获轨道优化方面国内外研究进展及现状。基于对上述研究现状的分析,尝试展望小行星捕获轨道优化研究的未来发展趋势。     

小行星的奇特动力学

小行星数以百万计,有着千奇百怪的外形.无论是小行星自身长期演化、还是它们附近的绕飞物体,都有着奇特的动力学现象.介绍小行星研究现状和发展趋势,阐明影响小行星姿态轨道长期演化的重要作用——雅科夫斯基效应和YORP效应.概述小行星不规则引力场描述方法与其中复杂的周期轨道,尝试提炼其中的科学问题和研究方向.     

小行星的奇特动力学1）

小行星数以百万计,有着千奇百怪的外形.无论是小行星自身长期演化、还是它们附近的绕飞物体,都有着奇特的动力学现象.介绍小行星研究现状和发展趋势,阐明影响小行星姿态轨道长期演化的重要作用--雅科夫斯基效应和YORP效应.概述小行星不规则引力场描述方法与其中复杂的周期轨道,尝试提炼其中的科学问题和研究方向.     

Resonance Capture in a Three Degree-of-Freedom Mechanical System

We study the phenomena of resonance capture in a three degree-of-freedom dynamical system modeling the dynamics of an unbalanced rotor, subject to a small constant torque, supported by orthogonal, linearly elastic supports, which is constrained to move in the plane. In the physical system the resonance exists between translational motions of the frame and the angular velocity of the unbalanced rotor. These equations, valid in the neighborhood of the resonance, possess a small parameter which is related to the imbalance. In the limit 0, the unperturbed system possesses a homoclinic orbit which separates bounded periodic motion corresponding to resonant solutions from unbounded motion which corresponds to solutions passing through the resonance. Using a generalized Melnikov integral, we characterize the splitting distance between the invariant manifolds which govern capture and escape from resonance for 0. It is shown that as certain slowly varying parameters evolve, the separation distance alternates sign, indicating that both capture into, and escape from resonance occur. We find that although a measurable set of initial conditions enter into a sustained resonance, as the system further evolves the orientation of the manifolds reverses and many of these captured solutions will subsequently escape.     

Optimal design of near-Earth asteroid sample-return trajectories in the Sun–Earth–Moon system

In the 6th edition of the Chinese Space Trajectory Design Competition held in 2014, a near-Earth asteroid sample-return trajectory design problem was released, in which the motion of the spacecraft is modeled in multi-body dynamics, considering the gravitational forces of the Sun,Earth, and Moon. It is proposed that an electric-propulsion spacecraft initially parking in a circular 200-km-altitude low Earth orbit is expected to rendezvous with an asteroid and carry as much sample as possible back to the Earth in a10-year time frame. The team from the Technology and Engineering Center for Space Utilization, Chinese Academy of Sciences has reported a solution with an asteroid sample mass of 328 tons, which is ranked first in the competition.In this article, we will present our design and optimization methods, primarily including overall analysis, target selection, escape from and capture by the Earth–Moon system,and optimization of impulsive and low-thrust trajectories that are modeled in multi-body dynamics. The orbital resonance concept and lunar gravity assists are considered key techniques employed for trajectory design. The reported solution, preliminarily revealing the feasibility of returning a hundreds-of-tons asteroid or asteroid sample, envisions future space missions relating to near-Earth asteroid exploration.     

基于偏转距离近似模型的动能撞击小行星防御任务脉冲轨道优化研究

小行星撞击对地球上的生命存在重大潜在威胁,动能撞击是目前最易实现且成熟度最高的防御方案.动能撞击任务的一种轨道优化指标为最大化偏转距离(即小行星被偏转前后近地距的改变量),若用数值积分的方法精确计算偏转距离, 会导致优化效率较低.在动能撞击任务的设计初期, 可以对动力学模型及偏转距离的计算方法进行简化,以提升优化效率. 本文首先将高精度模型简化为二体模型,分析了两种经典偏转距离解析模型的适用条件,同时提出一种基于近地点时刻预估的偏转距离近似模型; 考虑运载约束,将化学推进变轨简化为脉冲推力变轨,建立了直接转移(两脉冲及三脉冲)和行星借力飞行转移(单次及两次借力)的动能撞击轨道优化模型,利用遗传算法求解了优化问题. 以偏转小行星Apophis为例, 相比于解析模型,验证了本文提出的近似模型可以同时提升最优性、降低求解复杂性. 优化结果表明,三脉冲直接转移方案与两脉冲直接转移方案的最优偏转效果基本一致,借力飞行转移方案相比于直接转移方案对偏转距离的提升效果并不明显.在动能撞击任务的前期设计中, 可以基于二体模型进行防御效果的快速评估,虽然对计算偏转距离存在一定误差, 但对防御窗口的优化结果影响不大. 进一步,数值求解偏转距离时, 可通过引入主要引力摄动项(金星、地球、木星)修正二体模型,使其与高精度模型之间的求解误差在1%以下.     

The Simplest Resonance Capture Problem,Using Harmonic Balance Based Averaging

We study the dynamics of capture into, or escape from, resonance in a strongly nonlinear oscillator with weak damping and forcing, using harmonic balance based averaging (HBBA). This system provides the simplest example of resonance capture that we know of. The HBBA technique, here adapted to tackle nonlinear resonances, provides a harmonic balance assisted approximation to the underlying, asymptotically correct, averaged dynamics. Allowing the harmonic balance approximation makes a variety of systems analytically tractable which might otherwise be intractable. The evolution equations for amplitude and phase of oscillations are derived first. Restricting attention near the primary resonance, the slow flow equations are approximately averaged. The resulting flow transparently shows the stable and unstable primary resonant solutions, as well as the trajectories that get captured into resonance and the ones that escape. Good agreement with numerics is obtained, showing the utility of HBBA near resonance manifolds.     

平动点轨道演化性质分析和应用研究

三体问题中, 轨道的受力和运动规律非常复杂. 对于特定的任务, 如何选择轨道的初始解是一大难题.针对平面三体问题, 利 用近拱点庞加莱映射, 对平动点顺行轨道和逆行轨道的长期和短期演化性质进行分析.根据轨道的初始状态将其分为逃逸轨道和捕获轨道.对于逃逸轨道, 给出了同宿轨道和异宿轨道的设计方法, 并利用两级微分修正法消除了拼接点处的位置不连续问题.对于捕获轨道, 得到了几类典型的周期和准周期轨道.对逆行轨道的演化性质进行分析时发现, 逆行轨道通常为准周期轨道, 比顺行轨道更加稳定.利用近拱点庞加莱映射可以快速确定不同类型轨道对应的初始状态, 为特定任务需求下的轨道设计提供了一种快速而有效的选择方案.     

On optimization of many-revolution low-thrust orbit transfers: Part 1

The paper proposes a numerical approach to the problem of optimal control of low-thrust spacecraft in a strong central gravity field. The approach employs the solution of the averaged equations of optimal motion. For an optimal variable-thrust maneuver, it is shown that quasioptimal trajectories are close to the averaged ones. It is established that in the case of constant thrust, the averaged solutions can be used as a satisfactory first approximation for finding a quasioptimal solution by minimizing the discrepancy at the right end of the trajectory __________ Translated from Prikladnaya Mekhanika, Vol. 44, No. 7, pp. 110–119, July 2008.     

火星引力捕获动力学与动态误差分析

火星探测的制动捕获机会唯一,是影响任务成败的关键. 从限制性三体问题出发,推导了火星引力球、作用球与希尔球半径的计算公式,比较了三者的特点与适用范围,并结合作用球的定义与物理意义,给出了一种火星探测制动捕获段的工程定义. 在作用球范围内建立了火星制动捕获段动力学模型,给出了对捕获轨道精度产生影响的各项误差源. 通过蒙特卡洛仿真,定量分析了导航初始误差、发动机推力误差、制动点火时间误差等对捕获轨道近火点与远火点高度的影响,并对不同误差源可能导致的超差概率进行了分析,指出了影响捕获精度的主导误差源,可为我国未来火星探测制动捕获段的任务实施提供参考.      

Constructing dynamical systems having homoclinic bifurcation points of codimension two

A procedure is derived which allows for a systematic construction of three-dimensional ordinary differential equations having homoclinic solutions. The equations are proved to exhibit codimension-two homoclinic bifurcation points. Examples include the non-orientable resonant bifurcation, the inclination-flip, and the orbit-flip. In addition, an equation is constructed which has a homoclinic orbit converging to a saddle-focus satisfying Shilnikov's condition. The vector fields are polynomial and non-stiff in that the eigenvalues are of moderate size.     

柯伊伯带小行星平运动共振研究

研究柯伊伯带小行星对理解太阳系的起源和演化有着重要的意义。由于距离海王星较近,柯伊伯带小行星受其影响较大。这其中,又以共振小行星和离散小行星两族受影响最为明显。本文主要讨论了这两族小行星与海王星的共振现象。共振小行星处在共振轨道中,可以避免与海王星的近距离接触,轨道相对稳定,可以长时间保持。离散小行星的演化过程是共振黏滞与引力离散共同作用的结果。本文除了综述共振小行星和离散小行星的研究进展,还进一步分析了相应共振比下共振在大偏心率时的宽度,解释了离散小行星在离散盘大量分布的原因。     

逆行小行星的未解之谜

首颗与木星成逆行$1:1$共振的小行星——2015 BZ509的发现,点燃了公众对于逆行小行星的好奇心。本文简要介绍太阳系内鲜为人知的逆行小行星及其起源问题,并对与2015 BZ509相关的逆行共振问题提供通俗易懂的讲解。     

Low-thrust trajectory optimization for multiple target bodies tour mission

Spacecraft science missions to planets or asteroids have historically visited only one or several celestial bodies per mission. The research goal of this paper is to create a trajectory design algorithm that generates trajectory allowing a spacecraft to visit a significant number of asteroids during a single mission. For the problem of global trajectory optimization, even with recent advances in low-thrust trajectory optimization, a full enumeration of this problem is not possible. This work presents an algorithm to traverse the searching space in a practical fashion and generate solutions. The flight sequence is determined in ballistic scenario, and a differential evolution method is used with constructing a three-impulse transfer problem, then the local optimization is implemented with low-thrust propulsion on the basis of the solutions of impulsive trajectories. The proposed method enables trajectory design for multiple asteroids tour by using available low thrust propulsion technology within fuel and time duration constraints.     

Dirac reduction of binary asteroid systems with symmetry and stability of relative equilibria

In this paper, we study symmetry reduction for a binary asteroid system modeled by a rigid body and a particle. In particular, we demonstrate how translational and rotational symmetry reduction appeared in the binary asteroid system can be carried out in the context of Dirac reduction by stages and with the associated reduction of implicit Hamiltonian systems. Then we investigate stability of relative equilibria of the asteroid pair and show stability regions by using the energy-momentum method. Lastly, we illustrate some numerical simulations for stable and unstable orbits near from relative equilibria of the Collinear and T configurations.     

Periodic Solutions for Some Systems of Delay Differential Equations

In this paper, we give sufficient conditions for the existence of periodic orbits of some systems of delay differential equations with a unique delay having 3, 4 or n equations. Moreover, we provide examples of delay systems satisfying the different sets of sufficient conditions.