航天飞行器防热部件烧蚀行为的数值模拟

对航天飞行器防热部件在氧－煤油发动机火焰喷吹下的烧蚀行为进行了有限元数值模拟。利用“杀死”单元的方法建立防热部件瞬态温度场的有限元模型，实现了烧蚀边界的退缩，从而完成了对烧蚀尺寸变化的定量描述。烧蚀开始于4．59s，到12s时线烧蚀量为1．47mm。计算结果与试验的实测结果一致。     

LISA — a study of the ESA cornerstone mission for observing gravitational waves

The primary objective of the Laser Interferometer Space Antenna (LISA) mission is to detect and observe gravitational waves from massive black holes and galactic binaries in the frequency range 10⁻⁴ to 10⁻¹ Hz. This low-frequency range is inaccessible to ground-based interferometers because of the unshieldable background of local gravitational noise and because ground-based interferometers are limited in length to a few km. LISA is an ESA cornerstone mission and recently had a system study (Ref. 1) carried out by a consortium led by Astrium, which confirmed the basic configuration for the payload with only minor changes, and provided detailed concepts for the spacecraft and mission design. The study confirmed the need for a drag-free technology demonstration mission to develop the inertial sensors for LISA, before embarking on the build of the flight sensors. With a technology demonstration flight in 2005, it would be possible to carry out LISA as a joint ESA-NASA mission with a launch by 2010 subject to the funding programmatics. The baseline for LISA is three disc-like spacecraft each of which consist of a science module which carries the laser interferometer payload (two in each science module) and a propulsion module containing an ion drive and the hydrazine thrusters of the AOCS. The propulsion module is used for the transfer from earth escape trajectory provided by the Delta II launch to the operational orbit. Once there the propulsion module is jettisoned to reduce disturbances on the payload. Detailed analysis of thermal and gravitational disturbances, a model of the drag-free control and of the interferometer operation confirm that the strain sensitivity of the interferometer will be achieved.     

按降低轨迹灵敏度综合最优设计飞行控制系统

本文提出了一个按降低轨迹灵敏度综合最优设计飞行控制系统的方法。它能使系统具有满意的动态品质,同时对系统参数的变化及非线性产生的影响具有较强的鲁棒性。该设计方法具有通用性和程序化,系统实现简单。     

航天飞行器交会对接段的姿态控制四元数法

本文研究利用四元数作为误差信号进行航天飞行器姿态控制的控制规律,应用Pontrgagin极小原理导出了喷咀最优控制开关曲线,所得结果不仅可用于交会对接段也适用于航天飞行器上升段和返回段的姿态控制。     

"微机原理及应用"课程教改浅谈

论文阐述了如何在“微机原理及应用”课程教学中，增强学生主体意识、激发学生创造思维、提高学生的动手实践能力。通过改进多媒体教学方式，进行网络教学来提高教学效果。     

中性浮力微重力环境模拟技术

我国载人试验飞船发射成功后,对载人航天用的大型中性浮力模拟器的需求越来越迫切。文章通过对国外中性浮力模拟试验和设备情况的介绍,归纳出该类设备主要的5类应用,并提出对我国大型中性浮力模拟器设备的总体设想。     

防雹火箭弹飞行弹道计算程序设计

结合防雹火箭实际，编制了无控火箭弹的外弹道计算程序，并利用１６种野战火箭弹，炮弹的实测数据以及防雹火箭弹的实测数据对程序进行修正。结果表明；该程序的阻力系数计算误差为２％，适用于各种无控火箭弹和炮弹的质心弹道计算。     

弹道式导弹的中段制导与控制

本文提出了一种中段制导的方案——“闭环路导引的中段制导方案”。该方案具有收敛快、节省推进剂能量、精度高等优点。文章较系统地进行了方案的推导,估计了其方法误差,提出了计算程序框图及计算结果,并与其他制导方案进行了比较。