航天飞机再入大气层三维机动飞行的最大过载和热流峰值

本文研究了航天飞机再入大气层三维机动飞行时所产生的最大过载及驻点的热流峰值,提出了一种计算最大过载及热流峰值的解析方法。在一阶近似运动方程的基础上,建立了最大过载、热流峰值与航天飞机的升阻比、再入角、滚转角等参数之间的解析关系式,由之可简便地确定最大过载与热流峰值。文中分析了升阻比、再入角等参数对过载和热流的影响,并与再入三维轨道精确解的相应值作了对比,表明此种解法具有一定的精度,可供再入三维轨道特性的分析及航天飞机的初步设计阶段使用。     

载人航天的发展

简述了国外主要载人航天器的种类、技术参数和发展过程。介绍了我国载人航天工程的发展概况和主要技术指标,并分析了我国发展载人航天在科学、经济和政治等方面的重要意义。     

深空探测器推进系统

以技术较成效的月球探测器、火星探测器推进系统为重点，介绍了国外深空探测活动的情况。简述了深空探测对推进系统的需求、我国航天器液体推进技术的现状。认为我国的推进技术经一些适应性发展，即可满足深空探测的需求，并且设想了我国近期较为可行的深空探测器推进系统方案。     

Future spacelift projections

In 1996 the NASA Advisory Council asked for a comprehensive look at future launch projections out to the year 2030 and beyond. In response to this request NASA sponsored a study at The Aerospace Corporation to develop long-range space transportation models for future commercial and government applications, and to analyze the design considerations and desired characteristics for future space transportation systems. Follow-ons to present space missions as well as a wide array of potential new space applications are considered in the study. This paper summarizes the space transportation system characteristics required to enable various classes of future missions. High reliability and the ability to achieve high flight rates per vehicle are shown to be key attributes for achieving more economical launch systems. Technical, economic and policy implications are also discussed.     

组网数据处理探讨

讨论了测向定位中双站交会定位及定位误差分析、三站交会定位、多站交会定位若干问题，首次尝试将最小二乘法和递推最小二乘法用于多站测向定位，减少了大量的矩阵求逆，数据利用效率高，可以提高测向定位的精度和简化运算。特别是在存在多径效应的情况下，有利于发现和去除野值。在测向站组网数据的处理和应用上有较强的实用性和推广价值。     

有限空间轴对称射流流场的数值模拟

本文在к－ε紊流模型下，采用罚有限元法对有限空间轴对称射流流场进行数值模拟。引用罚函数优化迎风格式和退化积分，建立有限元解法的数值矩阵，在不同截面上求得工，压力和紊流参数分布，计算结果与实验数据十分接近。本文研究结果可应用于火箭发动机的喷射设计和射流量论的研究。     

跨大气层和空间区域飞行器的液体推进剂管理

根据大气层飞行环境与机动飞行特点,以及空间飞行环境与液体推进剂特点,分析了跨大气层和空间区域飞行器的保证重力场和失重状态下均无夹气液体输送、控制液体推进剂质心位移、剩余推进剂空间排放和重复使用等液体推进剂管理技术要求。阐述了相应的关键技术,如包括无夹气输送、液体质心位移控制、失重状态下的流体动力、参数确定和结构设计等管理模式确定,以及包括模型参数确定、模型、状态模拟和验证等的管理模式试验。     

A Geosynchronous Orbit Search Strategy

Since more than 10 years there is evidence that small-size space debris is accumulating in the geosynchronous orbit (GEO), probably as the result of breakups. Two break-ups have been reported in GEO. The 1978 break-up of an EKRAN 2 satellite, SSN 10365, was identified in 1992, and in 1992 a Titan 3C Transtage, SSN 3432, break-up produced at least twenty observable pieces. Subsequently several nations performed optical surveys of the GEO region in the form of independent observation campaigns. Such surveys suffer from the fact that the field of view of optical telescopes is small compared with the total area covered by the GEO ring. As a consequence only a small volume of the orbital element-magnitude-space is covered by each individual survey. Results from these surveys are thus affected by observational biases and therefore difficult to compare. This paper describes the development of a common search strategy to overcome these limitations. The strategy optimizes the sampling for objects in orbits similar to the orbits of the known GEO population but does not exclude the detection of objects with other orbital planes. A properly designed common search strategy clearly eases the comparison of results from different groups and the extrapolation from the sparse (biased) samples to the entire GEO environment.     

Tether Satellite System Collision Study

A study was performed to determine the probability of collision with resident space objects and untrackable debris for the tether component of the Tethered Satellite System (TSS) after it broke away from the Space Shuttle orbiter (mission STS-75) in February 1996. Both an analytical and a numerical approach were used in this study, and the results obtained with these two methods were found to be in good agreement. These results show that the deployed tether is expected to have been impacted by several particles 0.1mm or larger in size. The probability of collision with objects 10cm in size or larger was on the order of 10^–3 per month. Since the severed tether reentered within one month after deployment, the collision hazard to other objects while in orbit was small. The analytical methods used in this study are useful for tether collision evaluations in general.     

再入机动飞行器数学仿真研究

本文讨论了再入机动飞行器三自由度和六自由度仿真和分析。三自由度仿真研究了再入机动飞行器的导引规律和减速控制规律，证明了其合理性，且精度是满足要求的。而六自由度仿真说明了飞行器再入过程中虽然有静稳定和静不稳定交替出现的飞行状态，且动压变化大，如控制系统和制导方法设计良好，其精度仍可满足要求