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Optimal maneuver strategy to improve the observability of angles-only rendezvous 被引量:1
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作者 DU Ronghua LIAO Wenhe ZHANG Xiang 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2023年第4期1020-1032,共13页
This paper proposes an optimal maneuver strategy to improve the observability of angles-only rendezvous from the perspective of relative navigation.A set of dimensionless relative orbital elements(ROEs)is used to para... This paper proposes an optimal maneuver strategy to improve the observability of angles-only rendezvous from the perspective of relative navigation.A set of dimensionless relative orbital elements(ROEs)is used to parameterize the relative motion,and the objective function of the observability of anglesonly navigation is established.An analytical solution of the optimal maneuver strategy to improve the observability of anglesonly navigation is obtained by means of numerical analysis.A set of dedicated semi-physical simulation system is built to test the performances of the proposed optimal maneuver strategy.Finally,the effectiveness of the method proposed in this paper is verified through the comparative analysis of the objective function of the observability of angles-only navigation and the performances of the angles-only navigation filter under different maneuver schemes.Compared with the cases without orbital maneuver,it is concluded that the tangential filtering accuracy with the optimal orbital maneuver at the terminal time is increased by 35%on average,and the radial and normal filtering accuracy is increased by 30%on average. 展开更多
关键词 angles-only navigation OBSERVABILITY optimal maneuver orbital rendezvous
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Time-optimal rendezvous transfer trajectory for restricted cone-angle range solar sails 被引量:1
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作者 Jing He Sheng-Ping Gong +1 位作者 Fang-Hua Jiang Jun-Feng Li 《Acta Mechanica Sinica》 SCIE EI CAS CSCD 2014年第5期628-635,共8页
The advantage of solar sails in deep space exploration is that no fuel consumption is required. The heliocentric distance is one factor influencing the solar radiation pressure force exerted on solar sails. In additio... The advantage of solar sails in deep space exploration is that no fuel consumption is required. The heliocentric distance is one factor influencing the solar radiation pressure force exerted on solar sails. In addition, the solar radiation pressure force is also related to the solar sail orientation with respect to the sunlight direction. For an ideal flat solar sail, the cone angle between the sail normal and the sunlight direction determines the magnitude and direction of solar radiation pressure force. In general, the cone angle can change from 0° to 90°. However, in practical applications, a large cone angle may reduce the efficiency of solar radiation pressure force and there is a strict requirement on the attitude control. Usually, the cone angle range is restricted less more than an acute angle (for example, not more than 40°) in engineering practice. In this paper, the time-optimal transfer trajectory is designed over a restricted range of the cone angle, and an indirect method is used to solve the two point boundary value problem associated to the optimal control problem. Relevant numerical examples are provided to compare with the case of an unrestricted case, and the effects of different maximum restricted cone angles are discussed. The results indicate that (1) for the condition of a restricted cone-angle range the transfer time is longer than that for the unrestricted case and (2) the optimal transfer time increases as the maximum restricted cone angle decreases. 展开更多
关键词 Solar sail - Time-optimal rendezvous Indirect method Restricted cone-angle range
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Optimal Rendezvous Sequence for LEO Debris Capture 被引量:1
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作者 Ciro Bordello Lorenzo Casalino 《Journal of Aerospace Science and Technology》 2015年第1期27-35,共9页
The primary purpose of this study is to exploit the effect of Earth's non-sphericity perturbation, particularly due to the J2 term, in order to optimize the capture sequence of potential orbital debris, that is the c... The primary purpose of this study is to exploit the effect of Earth's non-sphericity perturbation, particularly due to the J2 term, in order to optimize the capture sequence of potential orbital debris, that is the cumulative AV associated to the transfers between one object and the others. As results of several researches and model predictions, many international agencies agree that the growing population of objects and debris in LEO (low earth orbits), will follow a diverging trend in the future. This, in turn, would constitute a serious threat to circum-terrestrial space safety and sustainability. In LEO, the ,J disturbance is prevailing over the others, and it acts by affecting the longitude of the ascending node (Ω), the argument of perigee (ω) and, accordingly, the true anomaly (v). Therefore, the goal of optimizing the AV is achieved by taking advantage of the rate of variation of Ω and ω, thereby compensating for the △Ω and △ω, present between the orbital transfer vehicle (chaser) and the debris to be captured (target). Obviously, the perturbation will lead to favourable variations of the orbital parameters only for some combinations of Ω and ω. Yet the presence of a debris population with random distribution of Ω and ω, makes this application particularly suited to the problem. The single maneuver has been modelled with a 4-impulse time fixed rendezvous and the optimization problem has been addressed by implementing a hybrid evolutionary algorithm, which adopts, in parallel, three different strategies, namely, genetic algorithm, differential evolution and particle swarm optimization. 展开更多
关键词 Trajectory optimization hybrid evolutionary algorithms debris removal multi-target rendezvous J2 perturbation assist.
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Practical Optimization of Low-Thrust Minimum-Time Orbital Rendezvous in Sun-Synchronous Orbits 被引量:1
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作者 Jian Ma ChangxuanWen Chen Zhang 《Computer Modeling in Engineering & Sciences》 SCIE EI 2021年第2期617-644,共28页
High-specific-impulse electric propulsion technology is promising for future space robotic debris removal in sun-synchronous orbits.Such a prospect involves solving a class of challenging problems of low-thrust orbita... High-specific-impulse electric propulsion technology is promising for future space robotic debris removal in sun-synchronous orbits.Such a prospect involves solving a class of challenging problems of low-thrust orbital rendezvous between an active spacecraft and a free-flying debris.This study focuses on computing optimal low-thrust minimum-time many-revolution trajectories,considering the effects of the Earth oblateness perturbations and null thrust in Earth shadow.Firstly,a set of mean-element orbital dynamic equations of a chaser(spacecraft)and a target(debris)are derived by using the orbital averaging technique,and specifically a slow-changing state of the mean longitude difference is proposed to accommodate to the rendezvous problem.Subsequently,the corresponding optimal control problem is formulated based on the mean elements and their associated costate variables in terms of Pontryagin’s maximum principle,and a practical optimization procedure is adopted to find the specific initial costate variables,wherein the necessary conditions of the optimal solutions are all satisfied.Afterwards,the optimal control profile obtained in mean elements is then mapped into the counterpart that is employed by the osculating orbital dynamics.A simple correction strategy about the initialization of the mean elements,specifically the differential mean true longitude,is suggested,which is capable of minimizing the terminal orbital rendezvous errors for propagating orbital dynamics expressed by both mean and osculating elements.Finally,numerical examples are presented,and specifically,the terminal orbital rendezvous accuracy is verified by solving hundreds of rendezvous problems,demonstrating the effectiveness of the optimization method proposed in this article. 展开更多
关键词 Trajectory optimization low thrust many revolutions orbital rendezvous sun-synchronous orbits
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Optimizing Inter Cluster Ant Colony Optimization Data Aggregation Algorithm with Rendezvous Nodes and Mobile Sink
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作者 Annu Ghotra 《Wireless Sensor Network》 2017年第1期16-24,共9页
Energy conservation is becoming the main critical issue in wireless sensor network and also the main research area for most of the researchers. For improving the energy efficiency, sink mobility is used with constrain... Energy conservation is becoming the main critical issue in wireless sensor network and also the main research area for most of the researchers. For improving the energy efficiency, sink mobility is used with constrain path in wireless sensor network. In order to solve these optimization problems, inter cluster Ant Colony Optimization Algorithm (ACO) is used with mobile sink (MS) and rendezvous nodes (RN). The proposed algorithm will improve 30% more network lifetime than the existing algorithm and prompts high accurate delivery of packets in highly dense network. 展开更多
关键词 WSN Clustering ACO Ant COLONY optimization MS Mobile SINK RP rendezvous Point
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Regularizing fuel-optimal multi-impulse trajectories 被引量:1
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作者 Kenta Oshima 《Astrodynamics》 EI CSCD 2024年第1期97-119,共23页
The regularization theory has successfully enabled the removal of gravitational singularities associated with celestial bodies.In this study,regularizing techniques are merged into a multi-impulse trajectory design fr... The regularization theory has successfully enabled the removal of gravitational singularities associated with celestial bodies.In this study,regularizing techniques are merged into a multi-impulse trajectory design framework that requires delicate computations,particularly for a fuel minimization problem.Regularized variables based on the Levi–Civita or Kustaanheimo–Stiefel transformations express instantaneous velocity changes in a gradient-based direct optimization method.The formulation removes the adverse singularities associated with the null thrust impulses from the derivatives of an objective function in the fuel minimization problem.The favorite singularity-free property enables the accurate reduction of unnecessary impulses and the generation of necessary impulses for local optimal solutions in an automatic manner.Examples of fuel-optimal multi-impulse trajectories are presented,including novel transfer solutions between a near-rectilinear halo orbit and a distant retrograde orbit. 展开更多
关键词 REGULARIZATION trajectory optimization fuel minimization multi-impulse trajectory
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Optimal impulsive ellipse-to-circle coplanar rendezvous 被引量:2
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作者 CHEN ChangQing XIE YongChun 《Science China(Technological Sciences)》 SCIE EI CAS 2009年第5期1435-1445,共11页
The problem of ellipse-to-circle coplanar rendezvous with chaser spacecraft in low eccentricity was investigated in this paper.With reference frame established in the centroid of the target spacecraft,the process of e... The problem of ellipse-to-circle coplanar rendezvous with chaser spacecraft in low eccentricity was investigated in this paper.With reference frame established in the centroid of the target spacecraft,the process of ellipse-to-circle coplanar rendezvous was described by the relative equations based on cy-lindrical reference frame,and then the solutions and distributions of optimal rendezvous models of a kind of close ellipse-to-circle coplanar rendezvous were provided.The simulation results showed that the guidance law based on the optimal rendezvous model in this research has good performance,and that the distributions of optimal rendezvous models of ellipse-to-circle coplanar rendezvous with the chaser spacecraft in low eccentricity are similar,albeit with slight difference,to those of rendezvous between close circular orbits.The work in this paper is a useful extension to Prussing's optimal ren-dezvous theory between close circular orbits. 展开更多
关键词 ellipse-to-circle rendezvous optimal IMPULSIVE rendezvous rendezvous MODEL
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Low Thrust Minimum Time Orbit Transfer Nonlinear Optimization Using Impulse Discretization via the Modified Picard–Chebyshev Method 被引量:4
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作者 Darin Koblick Shujing Xu +1 位作者 Joshua Fogel Praveen Shankar 《Computer Modeling in Engineering & Sciences》 SCIE EI 2016年第1期1-27,共27页
The Modified Picard-Chebyshev Method(MPCM)is implemented as an orbit propagation solver for a numerical optimization method that determines minimum time orbit transfer trajectory of a satellite using a series of multi... The Modified Picard-Chebyshev Method(MPCM)is implemented as an orbit propagation solver for a numerical optimization method that determines minimum time orbit transfer trajectory of a satellite using a series of multiple impulses at intermediate waypoints.The waypoints correspond to instantaneous impulses that are determined using a nonlinear constrained optimization routine,SNOPT with numerical force models for both Two-Body and J2 perturbations.It is found that using the MPCM increases run-time performance of the discretized lowthrust optimization method when compared to other sequential numerical solvers,such as Adams-Bashforth-Moulton and Gauss-Jackson 8th order methods. 展开更多
关键词 Low THRUST Picard–Chebyshev optimization multi-impulse Boundary Value Problem.
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Optimal four-impulse rendezvous between coplanar elliptical orbits 被引量:6
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作者 WANG JianXia BAOYIN HeXi +1 位作者 LI JunFeng SUN FuChun 《Science China(Physics,Mechanics & Astronomy)》 SCIE EI CAS 2011年第4期792-802,共11页
Rendezvous in circular or near circular orbits has been investigated in great detail, while rendezvous in arbitrary eccentricity elliptical orbits is not sufficiently explored. Among the various optimization methods p... Rendezvous in circular or near circular orbits has been investigated in great detail, while rendezvous in arbitrary eccentricity elliptical orbits is not sufficiently explored. Among the various optimization methods proposed for fuel optimal orbital rendezvous, Lawden's primer vector theory is favored by many researchers with its clear physical concept and simplicity in solu- tion. Prussing has applied the primer vector optimization theory to minimum-fuel, multiple-impulse, time-fixed orbital ren- dezvous in a near circular orbit and achieved great success. Extending Prussing's work, this paper will employ the primer vec- tor theory to study trajectory optimization problems of arbitrary eccentricity elliptical orbit rendezvous. Based on linearized equations of relative motion on elliptical reference orbit (referred to as T-H equations), the primer vector theory is used to deal with time-fixed multiple-impulse optimal rendezvous between two coplanar, coaxial elliptical orbits with arbitrary large ec- centricity. A parameter adjustment method is developed for the prime vector to satisfy the Lawden's necessary condition for the optimal solution. Finally, the optimal multiple-impulse rendezvous solution including the time, direction and magnitudes of the impulse is obtained by solving the two-point boundary value problem. The rendezvous error of the linearized equation is also analyzed. The simulation results confirmed the analyzed results that the rendezvous error is small for the small eccentric- ity case and is large for the higher eccentricity. For better rendezvous accuracy of high eccentricity orbits, a combined method of multiplier penalty function with the simplex search method is used for local optimization. The simplex search method is sensitive to the initial values of optimization variables, but the simulation results show that initial values with the primer vector theory, and the local optimization algorithm can improve the rendezvous accuracy effectively with fast convergence, because the optimal results obtained by the primer vector theory are already very close to the actual optimal solution. 展开更多
关键词 If the initial values are taken randomly it is difficult to converge to the optimal solution. elliptical orbit rendezvous primer vector fuel optimal
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Target sequence optimization for multiple debris rendezvous using low thrust based on characteristics of SSO 被引量:7
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作者 Shuge Zhao Jingrui Zhang +1 位作者 Kaiheng Xiang Rui Qi 《Astrodynamics》 2017年第1期85-99,共15页
A method is proposed to select the target sequence for a J 2-perturbed multiple debris rendezvous mission aimed at removing dozens of debris from several thousand debris candidates running on sun-synchronous orbits(SS... A method is proposed to select the target sequence for a J 2-perturbed multiple debris rendezvous mission aimed at removing dozens of debris from several thousand debris candidates running on sun-synchronous orbits(SSO).The solving methodology proceeds in two steps:Firstly,the variance of the right ascension of ascending node(RAAN)of the debris group is used for narrowing down the potential debris candidate;secondly,the debris of the candidate group that has closest RAAN to the current debris is chosen as the next debris.The low thrust near-minimum-fuel trajectories of each rendezvous leg are obtained by the indirect optimization method.The proposed approach is demonstrated for the problem of the 8th China Trajectory Optimization Competition(CTOC).The radar cross section(RCS)of the debris is also considered in the first step since the primary performance index of the competition is to maximize the total RCS of the debris visited.The results show that the proposed approach achieves better performance within a competition period.Of the many rendezvous sequences found,the best one submitted for the competition obtained a total RCS of 184 by accomplishing rendezvous with 70 debris within a transfer duration of one year. 展开更多
关键词 multiple debris rendezvous sun-synchronous orbits(SSO) low thrust optimal control
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Robust optimization of nonlinear impulsive rendezvous with uncertainty 被引量:2
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作者 LUO YaZhong YANG Zhen LI HengNian 《Science China(Physics,Mechanics & Astronomy)》 SCIE EI CAS 2014年第4期731-740,共10页
The optimal rendezvous trajectory designs in many current research efforts do not incorporate the practical uncertainties into the closed loop of the design.A robust optimization design method for a nonlinear rendezvo... The optimal rendezvous trajectory designs in many current research efforts do not incorporate the practical uncertainties into the closed loop of the design.A robust optimization design method for a nonlinear rendezvous trajectory with uncertainty is proposed in this paper.One performance index related to the variances of the terminal state error is termed the robustness performance index,and a two-objective optimization model(including the minimum characteristic velocity and the minimum robustness performance index)is formulated on the basis of the Lambert algorithm.A multi-objective,non-dominated sorting genetic algorithm is employed to obtain the Pareto optimal solution set.It is shown that the proposed approach can be used to quickly obtain several inherent principles of the rendezvous trajectory by taking practical errors into account.Furthermore,this approach can identify the most preferable design space in which a specific solution for the actual application of the rendezvous control should be chosen. 展开更多
关键词 rendezvous and docking UNCERTAINTY robust optimization multi-objective evolutionary algorithm
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Fast optimization of impulsive perturbed orbit rendezvous using simplified parametric model
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作者 An-Yi Huang Ya-Zhong Luo Heng-Nian Li 《Astrodynamics》 EI CSCD 2021年第4期391-402,共12页
A novel simplified parametric model for long-duration impulsive orbit rendezvous is proposed.Based on an existing fast estimation method,the optimal impulses and trajectory can be expressed by only ten parameters whos... A novel simplified parametric model for long-duration impulsive orbit rendezvous is proposed.Based on an existing fast estimation method,the optimal impulses and trajectory can be expressed by only ten parameters whose initial values can be easily determined.Then,these parameters are used to predict orbital deviations with a target orbit.A simple correction process is designed to sequentially update the parameters based on the J_(2) perturbed analytical dynamic equations of circular orbits.Finally,an iteration loop is formed to obtain the precise parameters and optimal trajectory.The simulation results confirm that the simplified parametric optimization method can be applied to elliptical orbits of small eccentricity and adapts well to both analytical and high-precision dynamics.The deviations could always converge within five iterations and the calculation was more efficient than the existing methods. 展开更多
关键词 impulsive trajectory optimization long-duration perturbed rendezvous parametric model
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空间交会寻的最优轨道机动 被引量:23
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作者 荆武兴 耿云海 +1 位作者 杨旭 吴瑶华 《中国空间科学技术》 EI CSCD 北大核心 1998年第2期22-27,共6页
研究了交会寻的阶段的燃料优化问题。在经典C-W方法基础上,导出了考虑第一次脉冲位置的双脉冲寻的燃料优化方法。当寻的时间给定时,优化变量为第一次脉冲启动的时刻;当寻的时间不定时,优化变量为第一次脉冲启动的时刻和寻的时间... 研究了交会寻的阶段的燃料优化问题。在经典C-W方法基础上,导出了考虑第一次脉冲位置的双脉冲寻的燃料优化方法。当寻的时间给定时,优化变量为第一次脉冲启动的时刻;当寻的时间不定时,优化变量为第一次脉冲启动的时刻和寻的时间。仿真结果表明,考虑和不考虑第一次脉冲位置,燃料消耗差别悬殊。对于地面站较少、要求寻的时间比较长的情况,该方法有重要意义。 展开更多
关键词 航天器 交会 轨道机动 燃料消耗量 优化 对接
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用弹性绳系系统进行空间捕捉的最优控制 被引量:10
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作者 陈辉 文浩 +1 位作者 金栋平 胡海岩 《宇航学报》 EI CAS CSCD 北大核心 2009年第2期550-555,612,共7页
研究如何从空间平台上释放绳系捕捉系统与被捕捉负载相交会,给出了交会机动可行点的求解过程。计入系绳弹性,采用高斯伪谱算法计算交会机动涉及的非线性最优控制问题。结果表明,在满足相关约束的条件下,通过调节系绳张力和捕捉系统上的... 研究如何从空间平台上释放绳系捕捉系统与被捕捉负载相交会,给出了交会机动可行点的求解过程。计入系绳弹性,采用高斯伪谱算法计算交会机动涉及的非线性最优控制问题。结果表明,在满足相关约束的条件下,通过调节系绳张力和捕捉系统上的推进力即可实现精确的交会控制。 展开更多
关键词 弹性系绳 捕捉 交会机动 最优控制
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多冲量最优交会的动态规划方法 被引量:15
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作者 谌颖 黄文虎 +2 位作者 倪茂林 王旭东 白拜尔 《宇航学报》 EI CAS CSCD 北大核心 1993年第2期1-7,共7页
本文利用动态规划技术,研究了多冲量推力作用下燃料最优、固定点交会控制问题。与现有一些结果相比,这里提出的方法计算简单,而且适用于一般共面椭圆轨道情况,并保证全局最优性。
关键词 交会 对接 动态规划 轨道 控制
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环月远程快速交会任务规划 被引量:4
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作者 陈欢 张洪礼 +3 位作者 韩潮 彭坤 马晓兵 胡雯婷 《载人航天》 CSCD 2016年第4期417-422,共6页
针对载人登月返回任务中月面上升舱与指挥服务舱的环月远程快速交会问题,以共椭圆快速交会策略为标称策略,并给出摄动模型下的修正方法。给出考虑总交会时间约束、机动时间间隔约束和燃料优化效率的燃料最优共椭圆快速交会策略,以及考... 针对载人登月返回任务中月面上升舱与指挥服务舱的环月远程快速交会问题,以共椭圆快速交会策略为标称策略,并给出摄动模型下的修正方法。给出考虑总交会时间约束、机动时间间隔约束和燃料优化效率的燃料最优共椭圆快速交会策略,以及考虑总速度增量约束、机动时间间隔约束和时间优化效率的时间最优共椭圆快速交会策略。通过算例仿真验证了共椭圆快速交会策略的可行性以及摄动模型下的交会精度,对共椭圆快速交会策略的总速度增量与交会时间的关系进行分析,并对比燃料最优和时间最优共椭圆快速交会对接策略,证明了优化策略的有效性。 展开更多
关键词 环月远程交会 快速交会 共椭圆交会 燃料最优 时间最优
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常推力作用下飞行器固定时间最优交会 被引量:6
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作者 谌颖 陈祖贵 刘良栋 《中国空间科学技术》 EI CSCD 北大核心 1998年第2期1-7,共7页
研究了在常推力作用下,两个空间飞行器的固定时间最省燃料交会问题。通过对飞行器交会过程中最优推力弧段的研究,给出了关于飞行器的最优推力弧段的几个性质。这些结果为空间飞行器交会对接的工程设计提供了理论依据。
关键词 常推力 航天器 最佳控制 交会 对接 相对运动
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交会对接远距离接近段制导研究 被引量:7
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作者 许伦辉 徐建闽 +1 位作者 周其节 任萱 《飞行力学》 CSCD 北大核心 1998年第2期90-96,共7页
基于飞行器相对目标空间站的线性化运动方程,研究了交会对接中远距离接近段最优冲量解的必要条件,推导了确定最优解特征矢量曲线方程中待定参数的计算公式,给出了在特定初始状态和末状态下实现远距离接近的四次、三次、二次最优冲量... 基于飞行器相对目标空间站的线性化运动方程,研究了交会对接中远距离接近段最优冲量解的必要条件,推导了确定最优解特征矢量曲线方程中待定参数的计算公式,给出了在特定初始状态和末状态下实现远距离接近的四次、三次、二次最优冲量解的作用时刻和大小的算法。通过一个交会实例的数字仿真分析,得到了有关远距离接近段制导方法的有指导价值的结果,验证了该方法是正确的、合理的。 展开更多
关键词 交会 对接 制导方法 特征矢量 最优冲量 航天器
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最优双冲量交会问题的数学建模与数值求解 被引量:15
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作者 佘志坤 薛白 +2 位作者 丛源良 刘铁钢 郑志明 《宇航学报》 EI CAS CSCD 北大核心 2010年第1期155-161,共7页
基于普适变量法研究了两个共面轨道的最优双冲量交会问题。具体地,基于求解Lambert问题的普适变量法,在将给定时间段划分初始飘移阶段、轨道转移阶段与终端停泊阶段的前提下,对两圆轨道及两拱线相同的椭圆轨道的最优双冲量交会问题分别... 基于普适变量法研究了两个共面轨道的最优双冲量交会问题。具体地,基于求解Lambert问题的普适变量法,在将给定时间段划分初始飘移阶段、轨道转移阶段与终端停泊阶段的前提下,对两圆轨道及两拱线相同的椭圆轨道的最优双冲量交会问题分别进行了优化数学建模,并利用数学软件Lingo进行了数值求解。数值结果表明,划分给定时间段可以得到更优解。 展开更多
关键词 双冲量交会 普适变量法 优化数学建模 数值求解
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多脉冲C-W交会的优化方法 被引量:30
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作者 李晨光 肖业伦 《宇航学报》 EI CAS CSCD 北大核心 2006年第2期172-176,186,共6页
在航天器的近距离交会中,常采用C-W交会的方法。本文发展了多脉冲C-W交会。建立了一般情况下的优化模型,并进行了分析。为了减少优化变量,提出了三种速度脉冲施加模式:切向、径向、变径向。提出了一种简单的误差修正方法:通过修正计算... 在航天器的近距离交会中,常采用C-W交会的方法。本文发展了多脉冲C-W交会。建立了一般情况下的优化模型,并进行了分析。为了减少优化变量,提出了三种速度脉冲施加模式:切向、径向、变径向。提出了一种简单的误差修正方法:通过修正计算的目标位置而减小仿真误差。在实际算例中采用了遗传算法。针对多个初始状态,不同的脉冲次数进行了仿真计算,并与文献中的算法进行了对比,精度有了进一步的提高,结果证明优化模型是可行的,可以应用于多种情况。 展开更多
关键词 航天器 交会 轨道动力学 遗传算法 优化
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