转变财政投资观念，促进经济发展

财政投资是政府运用国家财力调节宏观经济运行的重要手段，就如何重新确定财政投资范围，财政投资方式和财政投资产业的配置等方面进行了阐述。     

EUV emission from normal galaxies

Using data from the Wide Field Camera EUV all-sky survey, we have established upper limits to the EUV flux from a sample of 30 bright, nearby, non-active spiral galaxies. These galaxies were chosen to be those most likely to be detected in the EUV on the basis of (i) low interstellar absorption within our own galaxy, (ii) brightness in other wavebands, (iii) high star formation activity, and (iv) proximity. The derived EUV upper limits are restrictive, and establish for the first time that the EUV flux escaping from galaxies does not constitute a major component of their bolometric luminosity, and in particular that it cannot be the sink for the energy injected into the interstellar medium by supernova explosions, as had been suggested following the failure to detect this power in the X-ray band.     

密集编队气动耦合效应分析

简要介绍密集编队飞行时长机旋涡对僚机产生的气动耦合效应，以比奥特－萨瓦尔特定律为基础，初步分析由上洗及侧洗引起的升力、阻力和侧力变化，导出了编队稳定性导数的计算公式，计算及应用举例表明：模型化编队飞行时的气动耦合效应是有实际应用价值的。     

备件配置方法研究

针对电路板件故障数据记录的实际,运用可靠性理论,提出了没有故障数据板件的备件数量计算方法;对有故障统计数据的板件引用了经验模型来确定备件配置。     

A bistatic SAR mission for earth observation based on a small satellite

The authors present a new scientific space mission consisting of a satellite carrying a receiving- only SAR which receives the signal transmitted by the ENVISAT-1 SAR. The integration of ENVISAT-1 SAR and bistatic radar data offers an improved potentiality of surface classification, three-dimensional observation, and the opportunity of advanced scientific experiments in the field of bistatic scattering. The small satellite nominal orbit and the attitude manoeuvres are designed in order to maintain an adequate overlap between the two radar swaths along the whole orbit, taking into account the ENVISAT-1 attitude and pointing. A preliminary satellite design (2-year lifetime) is then performed to evaluate the orbit decay and to determine the appropriate orbit manoeuvres (every 4 days) to control the satellites relative phase. The numerical simulation shows that a spacecraft of about 584kg is able to meet the mission requirements.     

The China Multimode Microwave Remote Sensor (CMMRS) Onboard the SZ-4 Spaceship

In this report, the specifications and some results of the China multimode microwave remote sensor (CMMRS) onboard China's SZ-4 spaceship are described. Technical details and initial processing results of the CMMRS measurement data are reported.     

卫星VLBI观测时延和相位条纹旋转模型研究

空间卫星在绕地球或月球等星体运行时，为了跟踪和控制卫星就要时刻掌握其在空间的位置和运动状态．但由于地球的自转和公转使得卫星和地球之间的相对运动描述关系变得复杂，目标卫星相对地球任意两个观测站的时间差(时延)和多普勒频移(相关条纹旋转)时刻都在改变．VLBI相关处理机是卫星观测和空间探测极为重要的技术手段，其原理以FX和XF两种相关模型处理观测数据．以FX相关模型为基础修正VLBI观测数据的时延补偿和相关条纹旋转的模型，提出对称“1／n Multiplier”时延补偿模型和条纹旋转模型，并且对实际观测数据进行操作和详细分析，对相关相位谱的剩余时延变化趋势和方差分布进行分析，从中找出优选时延补偿和条纹旋转模型．对于精确描述卫星轨道运动状态提供更准确的方法．     

GPS based onboard and onground orbit operations for small satellites

In extension to common applications such as groundtrack displays and antenna steering, the SGP4 orbit model is proposed for operational orbit determination in small satellite missions. SGP4 is an analytical orbit model for Low-Earth orbiting satellites that is widely used for the propagation of NORAD twoline elements. Twoline elements may hence be generated completely independent of NORAD. Their use as exclusive source of orbital information simplifies the operations concept and reduces mission costs through the extensive use of existing low-cost mission support software. Due to small computer resource requirements of 8–10kByte, the SGP4 model may also be applied for onboard orbit computations making use of e.g. a 80186 processor, thus ensuring full compatibility of ground-based and onboard operations. The proposed approach is particularly suited in combination with a space-borne GPS receiver, were the C/A-code navigation solutions are treated as measurements that are adjusted in a least-squares sense using the SGP4 model. As consequence, inherent drawbacks of the pure navigation solutions such as data gaps and scatter as well as limited velocity accuracy are avoided, while the operational navigation activities are kept at a minimum. The feasibility of the concept is illustrated based on real GPS navigation data from the TOPEX/Poseidon and the MIR space station with an inherent data quality of 50–100 m. It is shown that 3 hours of data within a 4 day period are sufficient to keep the position error within 4 km, that is considered sufficient for most applications.     

飞行末区目标可攻击性算法研究

分析了飞行器飞行末区存在的各种约束条件及其对飞行器飞行的影响，用最大爬升（下滑）半径约束法来代替过载约束进行飞行器纵向机动飞行的高度控制，并给出了在诸多约束条件下目标可攻击性的算法。最后利用等高线地形图进行了仿真验证，结果表明，该算法满足诸多约束要求，可用于工程应用。     

k-ε-g紊流燃烧模型数值研究

本文对k-ε-g紊流燃烧模型中模型系数C_R,C_(g1),C_(g2)的选定和计算浓度脉动均方值g的不同方法进行数值研究。计算结果表明模型系数值的选定直接与化学反应速率有关,而其中C_R影响最大。g的计算虽然可有不同方法,而其中微分方程求解最佳。并用实验数据来验证计算结果。