典型海上热发射动力学效应及影响因素分析

考虑海上发射环境特殊性,分析了发射船承受的典型海浪以及风环境,针对陆基发射时运载火箭直接坐落在发射台上的裸箭热发射方式,分析了该支撑形式在海上动态环境下的射前稳定性,获得海上裸箭热发射方式的承受晃动极限。为解决陆基热发射支撑方式不满足三级海况发射稳定性的问题,提出运载火箭的框架式扶稳措施,通过框架内的柔性支撑保证运载火箭的射前稳定性。构建由火箭、等效甲板、导向框架、导轨、柔性支撑、发射台等组成的发射系统动力学仿真模型,开展复杂海况条件下的发射动力学分析,获得了框架式热发射方式在典型海况条件下,不同因素对火箭出框过程飞行姿态、安全间隙等影响规律,可为运载火箭框架式热发射的海上动基座发射动力学安全性评估提供技术支撑,并用于框架式热发射方式的海上动基座环境适应性的综合评价。     

Reachable set modeling and engagement analysis of exoatmospheric interceptor

A novel reachable set(RS) model is developed within a framework of exoatmospheric interceptor engagement analysis. The boost phase steering scheme and trajectory distortion mechanism of the interceptor are firstly explored. A mathematical model of the distorted RS is then formulated through a dimension–reduction analysis. By treating the outer boundary of the RS on sphere surface as a spherical convex hull, two relevant theorems are proposed and the RS envelope is depicted by the computational geometry theory. Based on RS model, the algorithms of intercept window analysis and launch parameters determination are proposed, and numerical simulations are carried out for interceptors with different energy or launch points. Results show that the proposed method can avoid intensive on-line computation and provide an accurate and effective approach for interceptor engagement analysis. The suggested RS model also serves as a ready reference to other related problems such as interceptor effectiveness evaluation and platform disposition.     

飞机备件供应费用动力学仿真研究

以飞机维修保障中备件供应费用为研究对象,首先分析了费用产生的因果关系,然后绘制存量流量图,建立存量、流量、辅助变量、常量之间的关联方程：在确定模型合理的基础上,对备件供应费用随时间的变化情况进行仿真分析。     

基于SD模型的政府航空管制影响分析

随着经济的快速发展,中国航空运输业取得了显著的发展,开始从民航大国向民航强国迈进.同时,航空运输业的发展趋势是自由化,即政府对航空运输企业经营活动从详尽管理过渡到更多地依靠市场力量予以调节,给予航空运输企业更多的经营权和灵活性.借鉴了国外放松管制的经验,以系统动力学方法为基础,对政府航线管制进行分析研究.建立SD模型,分析不同的航空运输发展水平下政府放松航线管制对航空运输系统带来的影响.研究结果表明,当航空运输市场越发达、越完善,政府放松航线管制对航空运输系统的促进作用越大.最后,对中国下一阶段政府航空管制的思路提出相应的建议和措施.     

中性浮力和失重环境人体运动仿真比较研究

为了模拟失重状态,航天技术发达的国家都建立了用于航天员出舱活动训练的中性浮力水槽。但与太空失重环境相比,水中存在的水动阻力会导致两种环境下人体运动反馈的差异性。基于ADAMS多体动力学仿真软件,按照“飞天”舱外航天服的质量分布,建立了着舱外服人体动力学模型。利用此模型仿真比较了水下和失重环境中肘关节屈伸、肩内收外展、肩矢状面内运动时人体躯干的动力学反馈,发现水下环境中模型躯干的转动速度峰值和平均值均较大。研究结果已应用于神舟七号载人飞行任务出舱活动航天员训练,建立的航天员人体动力学模型可应用于我国未来空间站任务出舱活动仿真分析。     

直升机在风切变气流场中的响应特性

为了研究直升机在风切变气流场中的响应特性,基于相关文献,建立了风切变工程化模型。根据旋翼的非均匀入流模型,建立了直升机非线性动力学模型,并利用四阶龙格—库塔法,对某型直升机在风切变场中的飞行特性进行了数值仿真。研究结果表明:样机进入风切变场后,飞行姿态立即出现俯仰震荡、左右摇摆的现象,10 s内,侧倾角的峰值差最大达到了73.14°,直升机下坠的高度为53.19 m,偏航距离为93.79 m。     

Tumbling object deorbiting using spaceborne laser engagement – A CubeSat case study

This paper demonstrates active space debris removal using spaceborne laser systems. The laser beam and the surface of the target are discretised into multiple rays and finite elements, respectively, for laser-target interaction modelling, in which the laser ablation process is investigated. A high-fidelity attitude/orbit propagator tool is developed to account for both the linear impulse and angular impulse induced by the laser engagement and other perturbations. The laser system is activated only when three switch criteria are satisfied. In numerical simulations, laser pulses from international space station are generated to deorbit a 3U CubeSat with initially tumbling modes. The results validate the effectiveness of deorbiting tumbling CubeSats using spaceborne laser engagement, with the perigee height lowered by approximately $2.4\mathrm{km}$ in around $30\min$ after $2\mathrm{h}$ propagation. It is also found that the laser engagement becomes more effective for an initially faster rotating object.     

The YORP effect on the GOES 8 and GOES 10 satellites: A case study

The Yarkovsky-O’Keefe-Radzievskii-Paddack (YORP) effect is a proposed explanation for the observed rotation behavior of inactive satellites in Earth orbit. This paper further explores the YORP effect for highly asymmetric inactive satellites. Satellite models are developed to represent the GOES 8 and GOES 10 satellites, both of which are currently inactive in geosynchronous Earth orbit (GEO). A simple satellite model for the GOES 8 satellite is used to analyze the short period variations of the angular velocity and obliquity as a result of the YORP effect. A more complex model for the rotational dynamics of the GOES 8 and GOES 10 satellites are developed to probe their sensitivity and to match observed spin periods and states of these satellites. The simulated rotation periods are compared to observations for both satellites. The comparison between YORP theory and observed rotation rates for both satellites show that the YORP effect could be the cause for the observed rotational behavior. The YORP model also predicts a novel state for the GOES 8 satellite, namely that it could periodically fall into a tumbling rotation state. Recent observations of this satellite are consistent with this prediction.     

喷雾液滴撞击液膜影响参数及流动机理分析

液滴撞击壁面是喷雾冷却中最常见的现象。使用计算流体力学软件中的Volume of Fluid （VOF）模型对液滴撞击壁面过程进行了数值模拟研究，研究了不同参数的液滴撞击壁面液膜过程的水花形态特点，针对水花高度和直径等参数进行了分析，通过运动间断理论和无量纲参数Re和We的变化分析了不同参数对液膜的流动特征和水花形态的影响及水花产生机理。结果表明：大液滴撞击液膜时能够改善液膜的流动状态；过大的液滴速度会产生大量飞溅及表面干涸；液滴撞击薄液膜时，液膜的流动性较好，当0.6<h*<1.2时，液膜的流动性不随液膜厚度改变。     

Simulation of long-term rotational dynamics of large space debris: A TOPEX/Poseidon case study

Accurate knowledge of the rotational dynamics of a large space debris is crucial for space situational awareness (SSA), whether it be for accurate orbital predictions needed for satellite conjunction analyses or for the success of an eventual active debris removal mission charged with stabilization, capture and removal of debris from orbit. In this light, the attitude dynamics of an inoperative satellite of great interest to the space debris community, the joint French and American spacecraft TOPEX/Poseidon, is explored. A comparison of simulation results with observations obtained from high-frequency satellite range measurements is made, showing that the spacecraft is currently spinning about its minor principal axis in a stable manner. Predictions of the evolution of its attitude motion to 2030 are presented, emphasizing the uncertainty on those estimates due to internal energy dissipation, which could cause a change of its spin state in the future. The effect of solar radiation pressure and the eddy-current torque are investigated in detail, and insights into some of the satellite’s missing properties are provided. These results are obtained using a novel, open-source, coupled orbit-attitude propagation software, the Debris SPin/Orbit Simulation Environment (D-SPOSE), whose primary goal is the study of the long-term evolution of the attitude dynamics of large space debris.