基于内模原理的椭圆轨道编队最优维持控制

 基于内模原理,针对椭圆轨道编队维持控制过程中存在的周期扰动问题,结合动力学方程的时变周期系数特性,设计具有干扰抑制功能的线性周期时变最优二次调节器。干扰内模的加入,使得系统响应在稳态时具有良好的控制精度,同时基于最优性原理的设计使得系统的瞬态响应过程满足某种最优性能指标要求。仿真结果表明,在椭圆轨道的编队维持控制器中引入部分干扰内模可大幅度提高维持精度。     

基于Hill方程的编队初始化误差分析

Hill方程具有形式简单、方便编队队形设计和队形保持控制律的设计等优点.然而,由于Hill方程自身模型误差的存在,导致基于Hill方程初始化所建立的队形具有一定的误差.针对这个问题,基于保留二阶非线性项的、改进形式的Hill方程和考虑偏心率的Lawden方程,分别在非线性和偏心率的影响下,分析了初始化队形的长期漂移和相对运动误差问题,分别给出了针对非线性和偏心率影响的修正初始化相对速度,从而消除队形的长期漂移,修正或减小相对运动误差.最后通过数值仿真进行了验证.     

近距编队飞行气动影响建模与分析

针对近距编队飞行面临的相互气动影响问题,采用等效气动效应法建立了尾流气动影响的等效模型.该模型可引入编队飞行六自由度方程.通过仿真验证表明,由等效模型计算出的诱导力与诱导力矩和风洞数据具有较好的符合度,等效模型可直接用于编队飞行建模及控制器的设计与仿真.     

无人机紧密编队队形构成控制

针对无人机编队飞行问题,通过借鉴Agent体系结构确定无人机编队的控制结构.建立了以航迹坐标系为参考坐标系的长机与僚机的相对运动模型,根据僚机距离长机最优位置的误差,利用李亚普诺夫稳定性理论设计队形构成中僚机的控制律.最后通过建立的六自由度非线性飞行仿真平台进行仿真验证,结果表明所设计的控制律能稳定引导无人机完成编队的队形构成.     

编队攻击集群目标时的反舰导弹弹道规划

以海上编队对集群目标实施导弹攻击为背景,分析了多发射平台对多目标进行导弹射击时反舰导弹弹道规划的重点和难点,探索了编队对集群目标射击时的弹道规划的基本原则与思路方法。     

Fixed-time position coordinated tracking control for spacecraft formation flying with collision avoidance

In this paper, the fixed-time stability of spacecraft formation reconfiguration (position tracking) is studied. Firstly, a novel nonsingular terminal sliding mode surface is designed and based on which a fixed-time coordinated controller is designed to keep the closed-loop system states have a finite settling time bounded by some predefined constants. Secondly, another nonsingular terminal sliding mode surface is designed by combining the artificial potential function and the aforementioned sliding surface, which meets the mutual distance constraint during transition process among spacecraft when it is bounded. Then another coordinated controller with fixed-time observer considering mutual distance constraint is presented, which guarantees the closed-loop system states stable also in bounded settling time. Finally, simulation results are shown to validate the correctness of the proposed theorems. It is worth mentioning that the control schemes also work even though there is a properly limit on the control input.     

多约束下备件多层多级库存优化模型

备件库存优化是提高装备保障效率和战备完好性的有效途径之一,针对目前部队现有多约束多层多级备件供应模式及工程实践要求的问题,以舰艇编队索马里护航任务准备阶段备件携带方案优化为研究背景,以舰艇保障经费、载荷和仓库体积为约束条件,以舰艇编队期望短缺数最小和可用度最大为目标函数,运用拉格朗日乘子法和边际效应法求出舰艇编队最优多层多级备件携带方案。通过实例将优化前后基地和后方仓库备件总的质量、体积及费用与对应约束指标上限进行对比分析,结果表明:本文模型和方法可以有效解决编队备件携带问题,同时也可为其他领域解决此类问题提供借鉴。      

基于卫星自旋的纯引力轨道万有引力干扰抑制

一个称为“内卫星”的验证质量块位于外卫星的内部空腔中,不与外卫星接触而自由飞行,由于外卫星的屏蔽,其不受大气阻力、太阳光压等干扰作用,沿着纯引力轨道飞行。外卫星会对内卫星产生万有引力作用,是内卫星纯引力轨道的主要残余干扰。根据卫星相对运动动力学方程,建立了万有引力干扰对内卫星纯引力轨道影响的分析模型;基于将外卫星绕轨道面法向旋转以调制万有引力的策略,建立了外卫星自旋对万有引力干扰影响的抑制模型。以内编队纯引力飞行系统为例,对比计算了外卫星有无自旋时万有引力干扰对内卫星纯引力轨道的影响。基于模型的分析表明,外卫星自旋能够显著抑制万有引力干扰对内卫星纯引力轨道的长期影响;实例计算表明,万有引力干扰的天长期影响能够降低5~7个数量级。     

The role of ultraviolet imaging in studies of resolved and unresolved young stellar populations. M31 and M33

We discuss the relevance of UV data in the detection and characterization of hot massive stars and young stellar populations in galaxies. We show results from recent extensive surveys in M31 and M33 with Hubble Space Telescope (HST) multi-wavelength data including UV filters, which imaged several regions at a linear resolution (projected) of less than half a pc in these galaxies, and from GALEX far-UV and near-UV wide-field, low-resolution imaging of the entire galaxies. Both datasets allow us to study the hierarchical structure of star formation: the youngest stellar groups are the most compact, and are often arranged within broader, sparser structures. The derived recent star-formation rates are rather similar for the two galaxies, when scaled for the respective areas. We show how uncertainties in metallicity and type of selective extinction for the internal reddening may affect the results, and how an appropriate complement of UV filters could reduce such uncertainties, and significantly alleviate some parameter degeneracies.     

Optimal H∞ robust output feedback control for satellite formation in arbitrary elliptical reference orbits

A two degree-of-freedom signal-based optimal H_∞ robust output feedback controller is designed for satellite formation in an arbitrary elliptical reference orbit. Based on high-fidelity linearized dynamics of relative motion, uncertainties introduced by non-zero eccentricity and gravitational J2 perturbation are separated to construct a robust control model. Furthermore, a distributed robust control model is derived by modifying the perturbed robust control model of each satellite with the eigenvalues of the Laplacian matrix of the communication graph, which represent uncertainty in the communication topology. A signal-based optimal H_∞ robust controller is then designed primarily. Considering that the uncertainties involved in the distributed robust control model have a completely diagonal structure, the corresponding analyses are made through structured singular value theory to reduce the conservativeness. Based on simulation results, further designs including increasing the degrees of freedom of the controller, modifying the performance and control weighted functions, adding a post high-pass filter according to the dynamic characteristics, and reducing the control model are made to improve the control performance. Nonlinear simulations demonstrate that the resultant optimal H_∞ robust output feedback controller satisfies the robust performance requirements under uncertainties caused by non-zero eccentricity, J2 perturbation, and varying communication topology, and that 5 m accuracy in terms of stable desired formation configuration can be achieved by the presented optimal H_∞ robust controller. In addition to considering the widely discussed uncertainties caused by the orbit of each satellite in a formation, the optimal H_∞ robust output feedback control model presented in the current work considers the uncertainties caused by varying communication topology in the satellite formation that works in a cooperative way. Other new improvements include adopting a new method to more accurately describe and analyze the effects of the higher-order J2 perturbation, combining all the uncertainties into a diagonal structure, and utilizing a structured singular value to synthesize and analyze the controller.