卫星太阳电池阵的刚-柔耦合动力学

研究了卫星太阳电池阵在多点撞击过程中的刚-柔耦合动力学问题．基于Jourdain速度变分原理和单向递推组集方法，建立了柔性多体系统的动力学模型．用Hertz撞击法则建立了撞击力和撞击处的局部变形关系，分别用刚体模型和柔性体模型仿真计算了太阳电池阵的撞击力、撞击时间，揭示了变形运动和大范围运动的相互耦合作用．     

Hard X-Ray Modulation Telescope(HXMT) Mission

The HXMT mission concept consists of a slat-collimated hard X-ray detector assembly sensitive in 20～250 keV with a collection area of about 5000 cm2. Based on the reconstruction technique by direct demodulation developed in recent years, HXMT is mainly devoted to performing a hard X-ray all-sky imaging survey with both high sensitivity and high spatial resolution. It can also be used to make pointed observations of X-ray sources to study their spectroscopic and temporal properties in details. The main detector of HXMT consists of 18 individual cylindrical NaI(T1)/CsI(Na) phoswich modules, each with anarea of 283.5 cm2 and a field of view of 5.7°× 1.1° (FWHM). Its spatial resolution and position accuracy are 5′ and 1′ by using the direct demodulation in 1994, and in 2000 its feasibility and technical demonstration study was selected as a project under the Major State Basic Research Program of China. In October 2005, this project entered the full design phase and was listed as a candidate for the first dedicated astronomy satellite around 2010. We are now also considering secondary low energy instruments for this satellite.     

卫星成本预测的一种动态建模结构

首先从卫星成本预测的决策对象分析入手，研究了卫星工程和卫星成本的结构，同时进一步分析阐述了卫星成本预测的发展状况，在此基础之上，把在其它领域应用较为广泛而且成熟的动态建模的思想及技术引入到了卫星成本预测模型之中，并结合卫星自身特点，对适合于卫星领域成本预测的动态模结构进行了研究与分析，获得了一种动态建模结构。     

卫星磁试验设备和磁试验技术

文章全面、系统地介绍了国内外卫星磁试验设备和磁试验方法,反映了当前磁试验技术的发展水平。     

卫星瞬变热流红外模拟技术研究

文章对卫星瞬变热流红外灯模拟的基本要求、系统组成及各个分系统的研究作了扼要地叙述,并给出了5路不同瞬变热流红外灯模拟试验结果。     

DQ—1气球卫星热设计

文章介绍了中国气球卫星的热设计与热试验。根据气球卫星的特性,讨论了无源热控制方法在热设计中的应用。说明热试验数据同热计算数据基本一致,气球卫星的温度满足设计要求。     

Singularity problem of control moment gyro cluster with vibration isolators

As powerful torque amplification actuators, control moment gyros (CMGs) are often used in the attitude control of many state-of-the-art high resolution satellites. However, the distur-bance generated by the CMGs can not only reduce the attitude stability of a satellite but also dete-riorate the performance of optic payloads. Currently, CMG vibration isolators are widely used to target this problem. The isolators can affect the singularity of the CMG system as they are placed between the CMGs and the satellite bus and provide additional freedoms to the CMG system due to their flexibility. The formulation of the output torque of a CMG is studied first considering the dynamic imbalance of its spin rotor and then the deformation angle as a result of the isolator’s flex-ibility is calculated. With the additional freedoms, the influence of isolator on the singularity problem is studied and a new steering logic to escape from the singular states is proposed.     

基于1553B总线星时精确产生硬件秒脉冲的方法

本设计在整星不能提供硬件秒脉冲的情况下,利用单片机对1553B总线协议芯片进行配置,使其只对星时数据产生中断.该中断触发外围电路自主产生硬件秒脉冲信号,进而实现校时.由于该方法为纯硬件的触发控制环节,在不考虑卫星平台发送星时数据随机误差的情况下,其误差仅取决于硬件的延时误差,通过标定可达到与整星提供秒脉冲相同的校时精度,而大大优于不采用校时的情况.此外,该成果通过对触发电路外围进行配置,可以实现任意脉宽及方向的秒脉冲信号输出,可满足不同型号对不同类型秒脉冲信号的需求,具有很大的灵活性及广泛的适用性.     

霍尔推进系统扭矩特性分析及应用设计

为降低霍尔推进系统产生的扭矩长期作用于航天器对姿态控制造成的干扰,对其扭矩特性进行分析和优化设计,通过对扭矩的产生机理进行模型化分析,得到了放电参数对扭矩大小及方向的影响关系。分析表明,1kW～5kW功率级霍尔推力器工作时,会产生量级为10-4N?m的扭矩,通过控制励磁电流方向可改变扭矩方向。针对典型的全电推进飞行任务,通过提出霍尔推进系统扭矩主动控制设计,实现了对系统产生的扭矩进行相互抵消或者叠加利用,降低了系统的应用风险。