宇航标准发展趋势

介绍美国和欧洲宇航标准的发展状况,在分析我国宇航标准现状的基础上,提出我们的宇航标准应具有继承与发展、开放、先进等特性,同时指出我国宇航标准重点发展方向。     

宇航级电连接器的材料质量控制研究

阐述宇航级电连接器为经受住不同轨道空间飞行器所经受的真空、温度交变、辐照和原子氧等复杂苛严的环境条件,对设计选材和材料筛选提出的质量控制要求。分析研究为验证宇航级电连接器材料能否满足这些特殊的空间环境条件要求j必须开展的热真空释气、温度交变、臭氧暴露、抗辐照、可燃性、气味和毒性（废气）等材料筛选试验方法。并对我国宇航级电连接器材料质量控制提出了意见和建议。     

宇航电连接器材料选用和可靠性试验

阐述了宇航用电连接器,为经受真空,辐照,原子氧和温度交变等十分复杂的空间环境,对设计选料提出的质量要求。介绍了为验证设计所选材料能否经受住这些复杂苛严的空间环境条件,宇航用电连接器产品鉴定试验或周期试验时,需进行的高真空,臭氧暴露,抗辐照,水解稳定性,撞击,可燃性,气味和毒性（废气）等可靠性筛选试验要求。并对宇航电接连器发展提出了意见和建议。     

宇航软件标准体系框架探析

随着航天事业的发展,宇航软件已经成为宇航事业至关重要的一部分。国际化的发展趋势,国际合作与交流的不断增多,宇航软件从质量、管理、产品保证等方面亟待跟上发展的步伐。本文在分析了国內外软件标准现状的基础上,根据我国航天软件标准化特点给出了宇航软件标准体系框架的建议。     

国外宇航产品AIT相关标准综合分析

概述NASA宇航项目系统工程过程中的AIT(总装、测试和试验),从总装、测试、试验以及技术保证等方面对NASA、MIL等与AIT相关的标准进行了综合分析,得到几点启示.     

宇航用微矩形电连接器评估方法

为验证宇航用微矩形电连接器研制的成熟度和在宇航工程中应用的适用度,提出了一种应用验证的新方法。其核心在于以微矩形电连接器鉴定试验为基础,结合宇航应用的实际背景及其自身特性制定评估试验方案,对其耐受力裕度、实际性能指标进行评价。该方法成功应用于宇航用微矩形电连接器的评估,得出了在不同应用条件下其电性能参数的变化趋势以及与进口样品间电参数比对结果,并对其结构与航天型号要求的符合性以及极限性能指标等进行了评估验证,为微矩形电连接器的研制和应用提供参考依据。     

我国宇航元器件标准发展方向与趋势的探讨

介绍美国航天局和欧洲空间局宇航元器件标准体系的构成,回顾我国宇航元器件标准的发展历程,探讨我国宇航元器件标准的发展方向与趋势。     

宇航电连接器材料选用和可靠性试验（续）

3宇航电连接器材料的可靠性试验 为验证设计所选材料能否经受得住真空,辐照等苛严特殊的环境条件,宇航电连接器技术标准中通常都规定：     

宇航级电连接器的材料质量控制研究（续）

3宇航级电连接器材料的筛选试验为验证设计所选材料能否经受得往真空、辐照等苛严特殊的环境条件．宇航电连接器技术标准中通常都规定：宇航用电连接器的全部材料,在产品鉴定试验时需进行热真空释气、温度循环、臭氧暴露、原子氧和抗辐照等筛选试验;所有非金属外壳的超小型、微型和印制板矩形连接器材料需进行可燃性、气味和毒性（废气）等筛选试验。     

航天用电连接器的解体失效分析

航天用电连接器在使用过程中由于结构不可靠造成解体,是危及整个系统工程成败的致命失效。总结并分析了近年来出现的多起解体失效案例,在阐明解体失效模式和失效机理的基础上,提出针对性的检验和防止解体失效的措施。     

国外航天元器件发展现状与思考

以航天元器件供应与采购问题为中心,分析国外航天元器件发展现状和国外宇航机构在航天元器件发展方面的主要做法与成功经验,并在借鉴吸收的基础上,结合我国的实际,对我国航天元器件的发展提出建议.     

关于空间辐射环境标准的探讨

在分析国外现行的空间辐射环境标准的基础上,提出制定和实施空间辐射环境数据标准、环境分析与效应标准、设计标准以及试验标准是保证航天型号能够承受空间辐射环境的有效手段.     

影响航天行业标准实施因素的分析

根据问卷调查的对航天行业标准的认识、需求、可操作性和实用性等情况.简要分析航天产品研制、生产过程中参与各方对航天行业标准实施的影响因素与程度,并结合工作实际得出了各方对实施其标准重要影响的结论.     

关于航天产品研制与生产中标准选用的几点思考

概述标准选用的定义,分析航天产品研制与生产中标准选用的现状及存在的问题,提出正确选用标准的方法、标准选用范围的编制和动态管理方法以及超范围选用等相关做法.     

Assessment of nanosystems for space applications

This paper first gives an overview of the applications of micro-electro-mechanical systems (MEMS) in space. Microsystems are advertised for their extremely low size and mass, along with their low power consumption and in some case their improved performances. Examples of actual flown MEMS and future missions relying on MEMS are given. Microsystems are now enjoying a dynamic and expanding interest in the space community. This paper intends to give an idea about the next step in miniaturization, since the microelectronic industry is already looking at nano-electro-mechanical systems (NEMS) driven by the more-than-Moore philosophy. We show that the impact of nanosystems should not be reduced at a homothecy in size, weight and power consumption. New forces appear at this scale (Casimir force…) which have to be considered in the system design. The example of a nano-mechanical memory is developed. We also show that performances of nanosystems are not systematically better than their microscopic counterparts through the study of the impact of dimension reduction on an accelerometer resolution and sensitivity. We conclude with the idea that nanosystems will find their greatest applications in distributed intelligent networks that will allow new mission concepts for space exploration.     

Potential of laser-induced ablation for future space applications

This paper surveys recent and current advancements of laser-induced ablation technology for space-based applications and discusses ways of bringing such applications to fruition. Laser ablation is achieved by illuminating a given material with a laser light source. The high surface power densities provided by the laser enable the illuminated material to sublimate and ablate. Possible applications include the deflection of Near Earth Objects – asteroids and comets – from an Earth-impacting event, the vaporisation of space structures and debris, the mineral and material extraction of asteroids and/or as an energy source for future propulsion systems. This paper will discuss each application and the technological advancements that are required to make laser-induced ablation a practical process for use within the space arena. Particular improvements include the efficiency of high power lasers, the collimation of the laser beam (including beam quality) and the power conversion process. These key technological improvements are seen as strategic and merit greater political and commercial support.     

航天型号产品多余物及其预防和控制标准的实施检查

分析了航天型号产品研制中产生多余物的主要环节,介绍了三江航天集团公司在现行标准的基础上补充了预防和控制多余物的有关内容,并提出了对标准进行监督检查的要点和方法。     

General background and approach to multibody dynamics for space applications

Multibody dynamics for space applications is dictated by space environment such as space-varying gravity forces, orbital and attitude perturbations, control forces if any. Several methods and formulations devoted to the modeling of flexible bodies undergoing large overall motions were developed in recent years.Most of these different formulations were aimed to face one of the main problems concerning the analysis of spacecraft dynamics namely the reduction of computer simulation time. By virtue of this, the use of symbolic manipulation, recursive formulation and parallel processing algorithms were proposed. All these approaches fall into two categories, the one based on Newton/Euler methods and the one based on Lagrangian methods; both of them have their advantages and disadvantages although in general, Newtonian approaches lend to a better understanding of the physics of problems and in particular of the magnitude of the reactions and of the corresponding structural stresses. Another important issue which must be addressed carefully in multibody space dynamics is relevant to a correct choice of kinematics variables. In fact, when dealing with flexible multibody system the resulting equations include two different types of state variables, the ones associated with large (rigid) displacements and the ones associated with elastic deformations. These two sets of variables have generally two different time scales if we think of the attitude motion of a satellite whose period of oscillation, due to the gravity gradient effects, is of the same order of magnitude as the orbital period, which is much bigger than the one associated with the structural vibration of the satellite itself. Therefore, the numerical integration of the equations of the system represents a challenging problem.This was the abstract and some of the arguments that Professor Paolo Santini intended to present for the Breakwell Lecture; unfortunately a deadly disease attacked him and shortly took him to death, leaving his work unfinished. In agreement with Astrodynamics Committee it was decided to prepare a paper based on some research activities that Paolo Santini performed during almost 50 years in the aerospace field. His researches spanned many arguments, encompassing flexible space structures, to optimization, stability analysis, thermal analysis, smart structure, etc. just to mention the ones more related to the space field (Paolo Santini was also one the pioneers of the studies of composite wing structures, aeroelasticity and unsteady aerodynamics for aeronautical applications). Following notes have been prepared by Paolo Gasbarri who was one of Paolo Santini collaborators for almost 15 years, they will attempt to offer a sketch of Professor Santini's activity by focusing on three main topics: the stability of flexible spacecrafts, the dynamics of multibody systems and the use of the smart structure technology for the space applications.