舰载直升机的研究现状与发展趋势

从舰载直升机的发展历史出发,首先给出了舰载直升机的主要使命和任务,并对国外先进舰载直升机主要机型进行梳理和分析,总结了国外舰载直升机的特点;然后,从舰载直升机使用特殊性考虑,详细阐述了其使用环境特点,提出了舰载直升机应具有的特殊要求,即良好的环境适应性和舰机适配性,同时分析给出了舰载直升机的指标要求;最后,通过对舰载直升机发展趋势的探究,提出了国内舰载直升机的发展建议.     

Formation tracking control for time-delayed multi-agent systems with second-order dynamics

In this paper, formation tracking control problems for second-order multi-agent systems (MASs) with time-varying delays are studied, specifically those where the position and velocity of followers are designed to form a time-varying formation while tracking those of the leader. A neigh-boring relative state information based formation tracking protocol with an unknown gain matrix and time-varying delays is presented. The formation tracking problems are then transformed into asymptotically stable problems. Based on the Lyapunov-Krasovskii functional approach, condi-tions sufficient for second-order MASs with time-varying delays to realize formation tracking are examined. An approach to obtain the unknown gain matrix is given and, since neighboring relative velocity information is difficult to measure in practical applications, a formation tracking protocol with time-varying delays using only neighboring relative position information is introduced. The proposed results can be used on target enclosing problems for MASs with second-order dynamics and time-varying delays. An application for target enclosing by multiple unmanned aerial vehicles (UAVs) is given to demonstrate the feasibility of theoretical results.     

Influence of processing and external storage conditions on the performance of envelope materials for stratospheric airships

Envelope materials are extremely vital for stratospheric airships, which are widely used in numerous applications. The influence of processing as well as the storage and utilization conditions on the performance of envelope materials has been studied systematically for the first time. Results show that the performance of envelope materials depends largely on the hot-pressing temperature and the flexing during processing. The tensile strength of samples dropped to 289.1 ± 8.0 MPa from 346.6 ± 9.3 MPa when pressed at temperature above 180 °C and helium leakage appeared. The outer layers would be worn off when flexed no matter by manual or machine, resulting in dramatic increase of helium permeability and even leakage as well as varying decrease of mechanical properties. Hence, suitable hot-pressing temperature and limitation of flexing as little as possible during processing are essential to obtain products with suitable properties. Besides, the storage and utilization conditions are also critical to the properties of envelope materials. Both naturally aged samples in outdoor storage on ground and samples recovered from actual flight on stratospheric airship exhibited reduced mechanical properties and even helium leakage due to excess solar irradiation, ozone concentration and energetic particles interaction compared with those stored indoors. The weatherability of envelope materials should be further strengthened in the next few years. This research could provide a theoretical guidance for actual practice.     

多航天器反步滑模SO(3)协同控制

针对多航天器系统的姿态协同控制问题,基于特殊正交群(Special Orthogonal Group, SO(3))提出了滑模协同控制设计方法。结合有向通信拓扑,建立了多航天器SO(3)姿态模型。在此基础上研究了SO(3)上协同误差形式,提出了适用于协同控制器构造的SO(3)指令设计方法。为了解决姿态奇异问题,根据SO(3)姿态特性引入补偿项并设计了相应的滑模面,进一步采用反步法完成了SO(3)协同控制器设计,同时给出稳定性分析过程。提出的反步滑模方法保证了协同控制器在整个姿态空间内的适用性,使得多航天器系统能够实现稳定的姿态协同。文中采用两组多航天器系统仿真校验了所提协同方法的有效性。     

一种多约束条件下的三维变结构制导律

针对现代空地导弹多约束、高精度制导的基本需求，从末段精确制导问题的三维数学模型出发，利用虚位移概念构建弹目相对运动关系，结合滑模变结构理论的基本特点，推导出一种满足制导精度、落角和入射角多约束条件的三维变结构制导律。并利用滑模理论构建非线性观测器，对未知量进行估计和预测。最后通过典型弹道的仿真，验证了本文提出的制导律的良好性能和较强的通用性。结果显示该制导律具有较强的鲁棒性和自适应能力，能较灵活地解决各约束量间的平衡关系。     

Oscillatory thermocapillary flows in simulated floating-zones with time-dependent temperature boundary conditions

This study deals with numerical simulations of the Maxus sounding rocket experiment on oscillatory Marangoni convection in liquid bridges. The problem is investigated through direct numerical solution of the non-linear, time-dependent, three-dimensional Navier-Stokes equations. In particular, a liquid bridge of silicon oil 2[cs] with a length L = 20 [mm] and a diameter D = 20 (mm) is considered. A temperature difference ΔT = 30 [K] is imposed between the supporting disks, by heating the top disk and cooling the bottom one with different rates of ramping. The results show that the oscillatory flow starts as an ‘axially running wave’, but after a transient time the instability is described by the dynamic model of a ‘standing wave’, with an azimuthal spatial distribution corresponding to m = 1 (where m is the critical wave number). After the transition, the disturbances become larger and the azimuthal velocity plays a more important role and the oscillatory field is characterized by a travelling wave. The characteristic times for the onset of the different flow regimes are computed for different rates of ramping.     

弹性薄圆板混合边界问题的解析解法：分区联合解法

板的混合边界问题的解析解法长期未能满意解决，对这方面所做的工作很少。近年来我国力学工作者做出了不少成绩，但都是有效的近似解法。设弹性薄圆析周边支承与板内受载周期性地改变，可将板假想地分成若干以圆心为顶点的扇形，每一块扇形内只有一种支承方式，再设载荷对称于各该扇形的中线，在以上条件下，根据天津大学严送教授首先系统地提出的“加补充项的广义Ｆｏｕｒｉｅｒ－Ｂｅｓｓｅｌ双重级数法”提出了“分区联合解法”即     

基于Lyapunov方法的非线性系统自适应观测器设计

针对一类满足L ipsch itz条件的具有未知参数的非线性系统,利用Lyapunov方法对L ipsch itz非线性系统自适应观测器的设计问题进行了研究。基于分析求解代数R iccati方程给出求解问题的不完善性、特征结构配置理论给出设计方法的重特征值限制性、对不同形式的观测器增益矩阵求解方法进行比较,最终选用线性矩阵不等式来改进观测器增益矩阵的选取方法。在观测误差稳定的条件下,得出了基于线性矩阵不等式方程设计状态观测器的增益矩阵,保证系统的状态估计误差收敛到零,并对其进行了仿真研究。结果证明,本文所构造的非线性观测器增益矩阵方法明显优越于其他方法,增强了系统的鲁棒性。     

Proposal for a multiple-asteroid-flyby mission with sample return

Asteroid exploration provides a new approach to study the formation of the solar system and the planetary evolution. Choosing a suitable target and designing of feasible profile for asteroid mission are challenging due to constraints such as scientific value and technical feasibility. This paper investigates a feasible mission scenario among the potential candidates of multiple flybys and sample return missions. First, a group of potential candidates are selected by considering the physical properties and accessibility of asteroids, for the sample return missions. Second, the feasible mission scenarios for multiple flybys and sample return missions to various spectral-type asteroids are investigated. We present the optimized design of preliminary interplanetary transfer trajectory for two kinds of missions. One is the single sample return mission to asteroids with various spectral types. The other is the multiple flybys and sample return mission to several asteroids. In order to find the optimal profiles, the planetary swing-by technique and Differential Evolution algorithm are used.     

An improved multiple model GM-PHD filter for maneuvering target tracking

In this paper, an improved implementation of multiple model Gaussian mixture probability hypothesis density (MM-GM-PHD) filter is proposed. For maneuvering target tracking, based on joint distribution, the existing MM-GM-PHD filter is relatively complex. To simplify the filter, model conditioned distribution and model probability are used in the improved MM-GM-PHD filter. In the algorithm, every Gaussian components describing existing, birth and spawned targets are estimated by multiple model method. The final results of the Gaussian components are the fusion of multiple model estimations. The algorithm does not need to compute the joint PHD distribution and has a simpler computation procedure. Compared with single model GM-PHD, the algorithm gives more accurate estimation on the number and state of the targets. Compared with the existing MM-GM-PHD algorithm, it saves computation time by more than 30%. Moreover, it also outperforms the interacting multiple model joint probabilistic data association (IMMJPDA) filter in a relatively dense clutter environment.