THRUST-AMPLITUDE CONTINUATION DESIGN APPROACH FOR SOLVING SPACECRAFT OPTIMAL CONTROLLED FLY-AROUND TRAJECTORY

针对航天器燃料最优可变周期绕飞轨迹的求解问题, 提出了一种以推力幅值为延拓参数的延拓方法. 问题求解从最为简单的双脉冲绕飞轨迹出发, 首先利用有限推力替代脉冲推力, 设定推力序列为“开— 关— 开”,然后逐步减小推力幅值, 最终得到最小推力绕飞轨迹; 此后, 再逐步增加推力幅值, 结合主矢量曲线判断最优推力开关序列, 将最小推力解延拓至有限推力以及脉冲推力燃料最优解. 该方法通过对推力幅值的延拓, 实现了有限推力bang-bang 控制与脉冲推力燃料最优绕飞轨迹优化问题的一并求解, 同时避免了最优控制问题中协态变量的随机猜测. 慢速与快速绕飞算例的优化结果验证了所提出方法的有效性.     

多星编队构型重构全局优化策略1）--第七届全国空间轨道设计竞赛乙题解法

第七届全国空间轨道设计竞赛乙组题目以近地轨道卫星编队的燃料最优构型重构问题为背景,要求合理设计从星的相对飞行轨迹,构建尽可能多的目标构型,并考虑燃料消耗均衡分配问题.本文介绍了该题目的解法,包括问题分析、求解方案以及相关计算结果.由于燃料最优控制问题可用能量最优控制问题近似,文中采用能量最优连续推力优化模型近似计算燃料最优控制律.首先通过优化分析两两构型之间的燃料消耗,确定了构建4种目标构型的次序;然后综合考虑构型保持时间约束以及相位约束,采用混合PSO（particle swarm optimization）算法进行全局优化;最后将影响燃料消耗指标的从星相对飞行轨迹的连续推力段转化为bang-bang控制.     

第六届全国空间轨道设计竞赛冠军团队解法

第六届全国空间轨道设计竞赛题目乙是一个利用行星引力辅助最快飞出太阳系的轨迹优化问题,本文介绍了国防科学技术大学团队的求解方法. 该方法先基于构建的推力方向固定的小推力引力辅助优化模型得到最优的引力辅助行星序列,再通过对优化模型的改进和推力方向的优化得到更进一步的解. 求解结果表明该方法可以有效地优化出一条最快逃逸的轨道.     

基于星历匹配法的载人小行星探测轨迹优化问题求解

对基于星历匹配法的载人小行星探测轨迹优化问题解法进行了研究. 提出星历匹配法的概念,利用其求出最优发射窗口初值与候选最优探测序列,然后利用遗传算法对特定探测序列的时间节点等参数进行优化,最后利用基于庞德里亚金极大值原理的同伦法进行小推力转化以求得最终探测轨道及其推力控制律. 结果显示星历匹配法可以快速准确地求出最优发射窗口初值与候选探测序列,这大大提高了载人小行星探测等多目标交会探测问题的求解效率.     

多星编队构型重构全局优化策略——第七届全国空间轨道设计竞赛乙题解法

第七届全国空间轨道设计竞赛乙组题目以近地轨道卫星编队的燃料最优构型重构问题为背景,要求合理设计从星的相对飞行轨迹,构建尽可能多的目标构型,并考虑燃料消耗均衡分配问题.本文介绍了该题目的解法,包括问题分析、求解方案以及相关计算结果.由于燃料最优控制问题可用能量最优控制问题近似,文中采用能量最优连续推力优化模型近似计算燃料最优控制律.首先通过优化分析两两构型之间的燃料消耗,确定了构建4种目标构型的次序;然后综合考虑构型保持时间约束以及相位约束,采用混合PSO(particle swarm optimization)算法进行全局优化;最后将影响燃料消耗指标的从星相对飞行轨迹的连续推力段转化为bang-bang控制.     

基于强化学习的冲压发动机飞行器爬升段轨迹优化控制

冲压发动机飞行器爬升过程中发动机性能随飞行状态时变,且易受动力性能偏差、气动偏差和风干扰的耦合影响,传统的方法难以给出能量最优的爬升段轨迹解.针对该问题,提出了一种基于强化学习的轨迹优化控制方法.首先构建了基于近端策略优化(PPO)的强化学习任务模型,将轨迹优化问题转化为基于状态给出最优动作策略的强化学习问题,提出了对...     

连续小推力航天器的深空探测轨道优化方法综述

连续小推力作用下航天器的深空探测轨道的优化设计是一个存在大量局部最优解的全局优化问题. 轨道设计流程总体上分为全局优化和局部优化. 全局优化为粗略设计, 通常在对航天器受连续推力作用下的轨道作近似处理的前提下大致确定探测序列和时间节点. 局部优化方法可分为直接法、间接法和混合法. 直接法是将连续的问题离散成一个参数优化问题. 间接法是求解由变分法和极大值原理推导的满足一阶最优必要条件的两点或多点边值问题. 混合法利用间接法推导的方程, 再离散后优化求解. 本文综述当前轨道优化设计领域最新和最常用的方法, 分析各种方法的优缺点.     

有限推力多小行星探测轨迹优化

针对任务时长与燃料存在限制的多颗小行星之间顺序探测轨迹优化问题,利用极小值原理,建立了整个探测区间的最优控制问题并使用同伦算法进行求解. 其中将目标飞越、交会等约束作为内点约束,特别地对交会后停留一定时间的约束进行了转换处理,使其成为与交会约束类似的形式;并给出了考虑起始时间可滑动的情形的最优条件. 结果表明,该算法可快速得到整体最优的探测轨迹,可应用于小行星多目标探测的任务设计与轨迹规划中.     

两自由度可调非线性减振器

研究了可调非线性减振器的优化设计.基于哈密尔顿最小势能原理建立非线性动力学模型,系统局域参数内,实现非线性系统幅值优化.利用平均法求解可调非线性减振器频响方程.分析系统解的稳定性,优化系统参数,降低系统幅值响应.     

第四届全国空间轨道设计竞赛冠军团队解法

 介绍第四届全国空间轨道设计竞赛的解法,主要包括问题分析、求解方案规划、飞行序列选择和计算结果. 本文的求解思路特点是,着重探测目标的特性分析,通过目标之间的排列组合来确定飞行序列,计算表明该方法能够有效降低计算量和保留最优解.     

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.     

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.     

Low-thrust trajectory optimization in a full ephemeris model

The low-thrust trajectory optimization with complicated constraints must be considered in practical engineering. In most literature, this problem is simplified into a two-body model in which the spacecraft is subject to the gravitational force at the center of mass and the spacecraft＇s own electric propulsion only, and the gravity assist （GA） is modeled as an instantaneous velocity increment. This paper presents a method to solve the fuel-optimal problem of low-thrust trajectory with complicated constraints in a full ephemeris model, which is closer to practical engineering conditions. First, it introduces various perturbations, including a third body＇s gravity, the nonspherical perturbation and the solar radiation pressure in a dynamic equation. Second, it builds two types of equivalent inner constraints to describe the GA. At the same time, the present paper applies a series of techniques, such as a homotopic approach, to enhance the possibility of convergence of the global optimal solution.     

冲击荷载作用下有限元方法求解波动过程的精度研究

研究了用动力有限元求解瞬态波动过程中产生的高频振荡和波形畸变的原因，提出了提高计算精度的有效方法及相应的确定单元尺寸及时间步长的方法。计算结果表明，作者提出的方法能有效地提高冲击荷载下波动问题求解精度。     

Near-Earth asteroid flyby trajectories from the Sun-Earth L2 for Chang’e-2’s extended flight

Driven by curiosity about possible flight options for the Chang'e-2 spacecraft after it remains at the Sun-Earth L2 point, effective approaches were developed for designing preliminary fuel-optimal near-Earth asteroid flyby trajectories. The approaches include the use of modified unstable manifolds, grid search of the manifolds' parameters, and a two-impulse maneuver for orbital phase matching and z-axis bias change, and are demonstrated to be effective in asteroid target screening and trajectory optimization. Asteroid flybys are expected to be within a distance of 2×107 km from the Earth owing to the constrained Earth-spacecraft communication range. In this case, the spacecraft's orbital motion is significantly affected by the gravities of both the Sun and the Earth, and therefore, the concept of the "heliocentric oscillating-Kepler orbit" is proposed, because the classical orbital elements of the flyby trajectories referenced in the heliocentric inertial frame oscillate significantly with respect to time. The analysis and results presented in this study show that, among the asteroids whose orbits are the most accurately predicted, "Toutatis", "2005 NZ6", or "2010 CL19" might be encountered by Chang'e-2 in late 2012 or 2013 with total impulses less than 100m/s.     

Tailoring of pinched hysteresis for nonlinear vibration absorption via asymptotic analysis

The method of multiple scales is adopted to investigate the dynamic response of a nonlinear Vibration Absorber (VA) whose constitutive behavior is governed by hysteresis with pinching. The asymptotic analysis is first devoted to study the response of the absorber to harmonic excitations and to evaluate its sensitivity to the main constitutive parameters. The frequency response obtained in closed form allows to carry out the stability analysis together with a parametric study leading to behavior charts characterizing multi-valued softening/hardening responses or single-valued, quasi-linear responses. A two-degree-of-freedom model of a primary nonlinear structure endowed with the hysteretic vibration absorber is investigated to explore transfers of energy from the structure to the absorber resulting into optimal vibration amplitude reduction. The asymptotic solution is proved to be in good agreement with the numerical solution obtained via continuation. The asymptotic approach is embedded into a differential evolutionary algorithm to obtain a multi-parameter optimization procedure by which the optimal hysteresis parameters are found.     

A new method for predicting the maximum vibration amplitude of periodic solution of non-linear system

An original method based on the proposed framework for calculating the maximum vibration amplitude of periodic solution of non-linear system is presented. The problem of determining the worst maximum vibration is transformed into a non-linear optimization problem. The harmonic balance method and the Hill method are selected to construct the general non-linear equality and inequality constraints. The resulting constrained maximization problem is then solved by using the MultiStart algorithm. Finally, the effectiveness of the proposed approach is illustrated through two numerical examples. Numerical examples show that the proposed method can, at much lower cost, give results with higher accuracy as compared with numerical results obtained by a parameter continuation method.     

Dynamics of an inshore–offshore fishery model with impulsive pollutant input in inshore area

Concerning the polluted environment in inshore areas and the effects of unbalanced impulsive diffusion between inshore and offshore areas on the size of fish population, based on optimal harvesting policy, a logistic offshore fishery system with impulsive pollutant input in inshore areas and impulsive diffusion at different fixed time is formulated, and we investigate the dynamics of such system. The sufficient conditions are obtained for the existence of the positive periodic solution and the global asymptotic stability of both the trivial periodic solution and the positive periodic solution. Moreover, the maximum sustainable yield and the corresponding harvesting effort are obtained.     

On the motion of a mass point on a surface

The motion of a mass point (particle) on a smooth surface in a potential force field is considered. To determine the particle trajectories, Zhukovskii’s geometric approach[1] is elaborated. It is shown that the trajectory equations obtained by this method are equivalent to the trajectory equations which can be derived from the Lagrange equations by the isoenergetic reduction (Whittaker’s method [2]). The geometric approach enables one to prove that if the external forces are tangent to the particle trajectory (e.g., “dry friction” forces), then the trajectories coincide with the geodesics. This research extends the results obtained in [3].