现代民机新型灭火剂性能研究

对新型灭火剂研究背景和种类进行了简要介绍,对具有开发潜力的新型灭火剂的理化性能、毒性、腐蚀性、灭火性能、环保性能进行深入分析与研究。通过对新型灭火剂性能的研究,得出每种灭火剂的优缺点,筛选出适用于现代民机灭火系统的灭火剂。     

Development of in-situ Space Debris Detector

Due to high relative velocities, collisions of spacecraft in orbit with Space Debris (SD) or Micrometeoroids (MM) can lead to payload degradation, anomalies as well as failures in spacecraft operation, or even loss of mission. Flux models and impact risk assessment tools, such as MASTER (Meteoroid and Space Debris Terrestrial Environment Reference) or ORDEM (Orbital Debris Engineering Model), and ESABASE2 or BUMPER II are used to analyse mission risk associated with these hazards. Validation of flux models is based on measured data. Currently, as most of the SD and MM objects are too small (millimeter down to micron sized) for ground-based observations (e.g. radar, optical), the only available data for model validation is based upon retrieved hardware investigations e.g. Long Duration Exposure Facility (LDEF), Hubble Space Telescope (HST), European Retrievable Carrier (EURECA). Since existing data sets are insufficient, further in-situ experimental investigation of the SD and MM populations are required. This paper provides an overview and assessment of existing and planned SD and MM impact detectors. The detection area of the described detectors is too small to adequately provide the missing data sets. Therefore an innovative detection concept is proposed that utilises existing spacecraft components for detection purposes. In general, solar panels of a spacecraft provide a large area that can be utilised for in-situ impact detection. By using this method on several spacecraft in different orbits the detection area can be increased significantly and allow the detection of SD and MM objects with diameters as low as 100 μm. The design of the detector is based on damage equations from HST and EURECA solar panels. An extensive investigation of those panels was performed by ESA and is summarized within this paper. Furthermore, an estimate of the expected sensitivity of the patented detector concept as well as examples for its implementation into large and small spacecraft are presented.     

空间拦截防御的射击诸元快速解算算法

针对空间平台发射非制导毁伤单元对近程高速非合作目标进行拦截防御的射击诸元快速解算问题,建立了命中方程,并基于命中方程的一阶解,给出了2种解析算法确定发射时刻、发射速度矢量与提前点坐标之间的函数关系.提出了计算命中时刻、发射速度矢量与发射时刻间函数关系的二分数值方法.最后通过仿真分析了算法的方法误差及适用范围.     

基于感应传感的位置增量编码器设计

为解决传统编码器的易损坏、可靠性不高、更换价格昂贵的问题,提出采用非接触式、电感感应传感设计位置编码器的方案。用LDC1312数字电感传感器作为感应探头,检测涂有金属物的旋转圆盘,将其感应测量到的数据通过IIC接口送入MSP430F5529处理数据,实现对旋转圆盘位置的检测。该设计与机械编码器相比,具有寿命长、可靠性高,适用于在油渍、潮湿、灰尘等恶劣环境工作的优点。     

消火栓消防系统工程验收常见问题及对策

针对消火栓系统验收时发现的问题，通过分析问题产生的原因，并就一些问题提出了改进办法，同时阐述了编制消火栓系统专项验收规范的建议。     

快速模拟算法在多目标超视距攻击火控系统中的应用

多目标超视距空战将是今后空战的主要形式和发展趋势。本文将快速模拟算法应用于多目标攻击火控系统设计, 提出了一种多目标超视距攻击火控系统的设计方案。仿真结果表明: 该设计方案精度高, 计算速度快, 完全可以满足机载武器系统的快速性和实时性要求     

角速率轰炸原理应用研究

介绍了角速率轰炸原理及其在某型飞机上的应用。并建立角速率轰炸的工作式，同时进行了火控轰炸的精度分析和仿真计算，为轰炸机装备角速率轰炸系统提供了依据。     

家用火灾自动报警装置的设计

城市家庭安装火灾自动报警装置非常必要。使用单片机,选用数字化温度传感器和烟雾检测器作为敏感元件,利用多传感器信息融合技术,设计适用于家庭的火灾报警装置,可使整个系统硬件电路设计合理,性能安全可靠。     

Solar X-ray Monitor (XSM) on-board Chandrayaan-2 orbiter

The remote X-ray fluorescence spectroscopy is a powerful technique to investigate the elemental abundances in the atmosphere-less planetary bodies. The experiment involves measuring spectra of fluorescent X-rays from lunar surface using a low energy X-ray detector onboard an orbiting satellite. Since the flux of fluorescent X-ray lines critically depend on the flux and spectrum of the incident solar X-rays, it is essential to have simultaneous and accurate measurement of X-ray from both Moon and Sun. In the context of Moon, this technique has been employed since early days of space exploration to determine elemental composition of lunar surface. However, so far it has not been possible to exploit it to its full potential due to various reasons. Therefore it is planned to continue the remote X-ray fluorescence spectroscopy experiment on-board Chandrayaan-2 which includes both lunar X-ray observations and solar X-ray observations as two separate payloads. The lunar X-ray observations will be carried out by Chandra Large Area Soft x-ray Spectrometer (CLASS) experiment; whereas the solar X-ray observations will be carried out by a separate payload, Solar X-ray Monitor (XSM). Here we present the overall design of the XSM instrument, the present development status as well as preliminary results of the laboratory model testing. XSM instrument will have two packages namely – XSM sensor package and XSM electronics package. XSM will accurately measure spectrum of Solar X-rays in the energy range of 1–15 keV with energy resolution ∼200 eV @ 5.9 keV. This will be achieved by using state-of-the-art Silicon Drift Detector (SDD), which has a unique capability of maintaining high energy resolution at very high incident count rate expected from Solar X-rays. XSM onboard Chandrayaan-2 will be the first experiment to use such detector for Solar X-ray monitoring.     

等离子体对空间飞行器表面充电效应探测研究

为确保空间飞行器在轨安全，有必要搭载探测器对轨道空间环境进行实时监测，获取表面充电效应数据。在对轨道空间充电环境分析的基础上，确定探测器的任务目标并完成基于电位探头和电流探头的探测器方案设计，包括探头设计和电路设计。探测器设计方案在空间环境特殊效应测量领域迈出的关键一步，为更多空间效应参数的测量奠定了坚实基础。