航天器展开机构阻尼器技术概述

航天器上的一些展开机构采用了弹性元件为动力源。当其展开到位时,通常会对与之相连的部件产生冲击。加装阻尼器是抑制这种冲击的有效措施之一。文章介绍了航天器展开机构常用转动型阻尼器的类型、工作原理及特点,并对相关技术的发展和应用作了分析和评述,提出了开展黏滞阻尼器研究的建议,并指出了研究中应考虑的问题。     

不同约束模型下降落伞-返回舱系统运动特性分析

建立了球铰链约束、单点吊挂约束、倒“Y”型约束三种约束模型,并对某型号舱-伞系统稳定下降过程的运动特性进行仿真计算,给出在三种约束模型下,系统运动参数随时间、高度变化的对比曲线图,并对仿真结果进行分析。计算所得结论可为降落伞-返回舱系统进行运动特性分析时简化约束模型提供重要参考。     

气动力对伞稳定下降阶段摆动的影响

为分析伞系统在稳定下降阶段运动稳定性,建立了5自由度的物伞模型,通过仿真发现具有不同气动力形式的物伞系统,其摆动情况有明显差异,并着重分析了气动力参数对物伞系统的摆动角度、频率的影响。     

航天器回收降落伞系统设计程序介绍

文章介绍了一种航天器回收降落伞系统的设计程序 ,重点介绍了回收控制方案和减速方案的设计。     

一种小型炮射子母弹装置的伞降系统

文章介绍了一种小型炮射子母弹装置伞降系统的功能及其组成。伞降系统由降落伞、伞舱、火工品等组成。     

Multi-objective optimization of parachute triggering algorithm for Mars exploration

A multi-objective optimization procedure to design parachute triggering algorithm, based on Monte Carlo analysis of flight uncertainties, has been developed in this paper. Most of Mars explorations missions utilize parachute for a safe descent through the lowest of the atmosphere. The parachute triggering algorithm is designed to accommodate the range of off-nominal entry trajectories, and is aimed to parachute opening in certain range of Mach numbers, dynamic pressure and altitude. Our novel algorithm takes the fight uncertainty into the account through Monte Carlo analysis, selects maximization of altitude statistical mean and minimization of Mach number statistical mean as two objectives, then employs multi-objective evolutionary algorithm based on decomposition (MOEA/D), to search the Pareto-front framework. Such a methodology can be implemented on the future design of entry, descent, and landing (EDL) mission.     

无人机前开伞式降落过程动力学建模与仿真

文章分析了某型无人机降落伞回收阶段的动力学过程,对各工作阶段的无人机和降落伞的组合体进行了数学建模,使用Matlab软件中的Simulink组件搭建了无人机伞降过程的仿真模型,按照真实飞行和回收工况进行了计算,通过仿真结果与试验数据的比较,验证了模型的正确性.     

Wireless sensor networks for planetary exploration: Experimental assessment of communication and deployment

Planetary surface exploration is an appealing application of wireless sensor networks that has been investigated in recent years by the space community, including the European Space Agency. The idea is to deploy a number of self-organizing sensor nodes forming a wireless networked architecture to provide a distributed instrument for the study and exploration of a planetary body. To explore this concept, ESA has funded the research project RF Wireless for Planetary Exploration (RF-WIPE), carried out by GMV, SUPSI and UPM. The purpose of RF-WIPE was to simulate and prototype a wireless sensor network in order to assess the potential and limitations of the technology for the purposes of planetary exploration.     

集成火星进入弹道的开伞过程动力学特性研究

针对火星探测任务设计阶段的需求,提出集成再入弹道、开伞过程仿真一体化设计方法。首先,利用质点动力学模型,计算质点弹道,进行探测器进入过程的飞行轨迹仿真,获得开伞初始状态。其次,基于任意拉格朗日-欧拉（ALE）方法,建立开伞过程的流固耦合（FSI）动力学模型,进行典型工况开伞过程数值模拟,分析开伞动压和马赫数对降落伞充气过程的影响。数值模拟开伞过程伞衣几何外形变化和降落伞的流固耦合动力学行为,得到开伞过载变化曲线、伞衣阻力面积变化等典型特征参数。计算结果表明,降落伞开伞动力学的数值仿真方法为火星再入、减速和着陆（EDL）过程的概念设计提供了一定的参考依据。     

基于LS—DYNA的降落伞伞衣织物透气性参数仿真验证

利用已知的伞衣织物透气量与压差曲线计算得到了表征伞衣织物透气性能的两个主要参数一粘性系数和惯性系数,并运用LS—DYNA软件的流固耦合算法对其进行了验证,这对以后仿真降落伞充气过程有一定的参考作用。