多变点检测问题的Shape-based BS算法

BS算法是时间序列多变点检测中最经典的算法之一,但是基于全局CUSUM统计量的识别过程会带来过多误判和较高的时间复杂度.BS算法是一种离线的序贯方法,因此没有充分利用数据的时序信息;另一方面,BS算法识别变点的原则是CUSUM统计量最大化,也没有考虑统计量构成序列的形态特性.鉴于此,提出一种基于局部形态识别的BS改进算法,命名为Shape-based BS算法.基于局部形态识别统计量,不仅大大降低计算复杂度,且降低了因变点间的互相干扰而带来的误判率,进而提升变点识别的稳健性.最后,将此算法应用到了电力系统的"场景压缩"问题上,具有满意的实用效果.

Satellite observed shape-based overall rotation—A new aspect in eddy kinematics

With the development of satellite altimetry technology,the resolution of sea-level anomaly(SLA)datasets is constantly improving.Current spatial resolution levels can reach a grid size of(1/4)°×(1/4)°,with daily measurements that span from 1993 to 2018,allowing for the precise identification and tracking of individual eddies.In the current study,in addition to the internal circulation and migration of eddies,a new aspect in eddy kinematics is revealed and investigated for the first time:shape-based overall eddy rotation(SOER),based on the intrinsic elliptical shape of eddies identified from a high-resolution SLA dataset.We found that eddies can maintain an elliptical shape and a slow and stable SOER during their migration process.The SOER speed was observed to be negatively correlated to eddy lifetime,and exhibited a dependence on latitude,decreasing from low-and high-to mid-latitudes.The SOER direction tended to be consistent with the direction of internal circulation,particularly for long-lived eddies.In addition,we identified a negative relationship between internal circulation speed and SOER speed while the migration speed was positively related to SOER speed.These findings further expand and improve eddy kinematics,which is of great significance for the future study of eddy dynamics.

Modified shape-based method for three-dimensional trajectory design

Although the shape-based method has been proven to be useful for low-thrust trajectory design,and be capable to provide near-optimal solution for a more accurate trajectory optimization method,it is slightly non-effective when used in some 3D cases.In this paper,a modified 3D shape-based method is proposed for earth trajectory design.In this approach,in consideration of the sinusoidal periodic variation in z direction of actual trajectory,a new exponential sinusoid model is chosen for the out-of-plane motion,with four coefficients such that four scalar out-of-plane boundary conditions can be satisfied.After deriving the 3D shape-based procedure,low-thrust trajectory design example with modest inclination change is given.The results demonstrate that this modified approach is feasible for the transfer trajectory design,and comparing to the former shape-based method,the z direction solution is more coincident with the actual situation,furthermore,the solution may be used for further mission planning,trajectory evaluation and optimization.

星际小推力转移任务发射机会的快速搜索方法

结合小推力与借力飞行技术可为星际探测任务提供更多行之有效的转移方案。现针对此类探测任务的发射机会搜索问题,基于Shape-Based理论,提出了一种新的快速搜索算法。该算法通过引入目标星体的状态约束,建立起初始飞行角与转移时间之间单调映射关系,从而实现了可行性轨道的快速解算;然后,综合考虑任务及轨道动力学约束条件,给出了搜索参数的合理搜索域。与传统搜索算法相比,该算法有效降低了搜索维数,减少了搜索空间,提高了计算效率。最后,以近地小行星1627Ivar为例,搜索了其在2010~2016年采用火星借力进行探测的发射机会,验证了本文方法的有效性。

Fast cooperative trajectory optimization and test verification for close-range satellite formation using Finite Fourier Series method

The process of formation reconfiguration for close-range satellite formation should take into account the risk of collisions between satellites.To this end,this paper presents a method to rapidly generate low-thrust collision-avoidance trajectories in the formation reconfiguration using Finite Fourier Series(FFS).The FFS method can rapidly generate the collision-avoidance threedimensional trajectory.The results obtained by the FFS method are used as an initial guess in the Gauss Pseudospectral Method(GPM)solver to verify the applicability of the results.Compared with the GPM method,the FFS method needs very little computing time to obtain the results with very little difference in performance index.To verify the effectiveness,the proposed method is tested and validated by a formation control testbed.Three satellite simulators in the testbed are used to simulate two-dimensional satellite formation reconfiguration.The simulation and experimental results show that the FFS method can rapidly generate trajectories and effectively reduce the risk of collision between satellites.This fast trajectory generation method has great significance for on-line,constantly satellite formation reconfiguration.

Spiral trajectories induced by radial thrust with applications to generalized sails

In this study,new analytical solutions to the equations of motion of a propelled spacecraft are investigated using a shape-based approach.There is an assumption that the spacecraft travels a two-dimensional spiral trajectory in which the orbital radius is proportional to an assigned power of the spacecraft angular coordinate.The exact solution to the equations of motion is obtained as a function of time in the case of a purely radial thrust,and the propulsive acceleration magnitude necessary for the spacecraft to track the prescribed spiral trajectory is found in a closed form.The analytical results are then specialized to the case of a generalized sail,that is,a propulsion system capable of providing an outward radial propulsive acceleration,the magnitude of which depends on a given power of the Sun-spacecraft distance.In particular,the conditions for an outward radial thrust and the required sail performance are quantified and thoroughly discussed.It is worth noting that these propulsion systems provide a purely radial thrust when their orientation is Sun-facing.This is an important advantage from an engineering point of view because,depending on the particular propulsion system,a Sun-facing attitude can be stable or obtainable in a passive way.A case study is finally presented,where the generalized sail is assumed to start the spiral trajectory from the Earth’s heliocentric orbit.The main outcome is that the required sail performance is in principle achievable on the basis of many results available in the literature.