Using high-energy proton fluence to improve risk prediction for consequences of solar particle events

The potential for exposure to large solar particle events (SPEs) with high energy levels is a major concern during interplanetary transfer and extra-vehicular activities (EVAs) on the lunar and Mars surface. Previously, we have used data from the last 5 solar cycles to estimate percentiles of dose to a typical blood-forming organ (BFO) for a hypothetical astronaut in a nominally shielded spacecraft during a 120-d lunar mission. As part of this process, we made use of complete energy spectra for 34 large historical SPEs to calculate what the BFO mGy-Eq dose would have been in the above lunar scenario for each SPE. From these calculated doses, we then developed a prediction model for BFO dose based solely on an assumed value of integrated fluence above 30 MeV (Φ₃₀) for an otherwise unspecified future SPE. In this study, we reasoned that since BFO dose is determined more by protons with higher energies than by those with lower energies, more accurate BFO dose prediction models could be developed using integrated fluence above 60 (Φ₆₀) and above 100 MeV (Φ₁₀₀) as predictors instead of Φ₃₀. However to calculate the unconditional probability of a BFO dose exceeding a pre-specified limit (“BFO dose risk”), one must also take into account the distribution of the predictor (Φ_30,Φ₆₀, or Φ₁₀₀), as estimated from historical SPEs. But Φ₆₀ and Φ₁₀₀ have more variability, and less available historical information on which to estimate their distributions over many SPE occurrences, than does Φ₃₀. Therefore, when estimating BFO dose risk there is a tradeoff between increased BFO dose prediction at a given energy threshold and decreased accuracy of models for describing the distribution of that threshold over future SPEs as the threshold increases. Even when taking the second of these two factors into account, we still arrived at the conclusion that overall prediction improves as the energy level threshold increases from 30 to 60 to 100 MeV. These results can be applied to the development of approaches to improve radiation protection of astronauts and the optimization of mission planning for future space missions.     

红外检测在老龄飞机蒙皮搭接结构腐蚀检测中的应用分析

随着服役时间的增加,老龄飞机的腐蚀问题不断积累,严重影响了飞机的使用寿命和飞行安全。在对退役飞机进行检测时发现,在蒙皮搭接结构中经常发生腐蚀产生的蚀坑。这种蚀坑由于隐蔽性强,目视检查无法发现,使用常规的无损检测技术,检测效果不好。根据红外检测技术的原理,模拟检测环境,对蒙皮搭接结构进行有限元建模,分析了在表面划伤情况下的模型表面温度场变化,验证了红外检测技术对于老龄飞机蒙皮搭接结构腐蚀问题的可行性,为红外检测技术的应用提供了理论基础。     

嵌入式红外视频数字录像机的设计与实现

设计并实现了嵌入式红外视频数字录像机.它基于PC/104Plus体系结构,实现了PCI数据传输,在FPGA(Field-Programmable Gate Array)的控制下、使用2个存储单元轮换存储方式硬件化地实现了红外视频采集与数据传输、红外视频播放与数据传输的并行操作.该录像机人机界面友好,文件管理完善.      

基于SRAM型FPGA单粒子效应综合防护技术

为解决基于SRAM(Static Random Access Memory,静态随机存储器)型FPGA(Field Programmable Gate Array,现场可编程门阵列)的扩频应答机在空间环境中时常发生功能故障的难题,提出了一种低轨卫星基于SRAM型FPGA的应答机的单粒子综合防护方案。该方案在代码级、器件级、单机级、整星级综合采用器件优选、结构屏蔽设计、巡检自愈、自主复位等多种方法,有效杜绝了单粒子事件带来的种种危害,已成功应用于某在轨卫星。在轨测试结果表明:遥测、遥控、跟踪测量等功能、性能指标满足任务要求,且未发生需要地面干预的问题或现象。该技术还可推广应用于其他采用低等级器件及其他类型FPGA、DSP(Digital Signal Processing,数字信号处理)等大规模集成电路的星载单机防护。     

Type II Solar Radio Bursts: Theory and Space Weather Implications

Recent data and theory for type II solar radio bursts are reviewed, focusing on a recent analytic quantitative theory for interplanetary type II bursts. The theory addresses electron reflection and acceleration at the type II shock, formation of electron beams in the foreshock, and generation of Langmuir waves and the type II radiation there. The theory's predictions as functions of the shock and plasma parameters are summarized and discussed in terms of space weather events. The theory is consistent with available data, has explanations for radio-loud/quiet coronal mass ejections (CMEs) and why type IIs are bursty, and can account for empirical correlations between type IIs, CMEs, and interplanetary disturbances. This revised version was published online in August 2006 with corrections to the Cover Date.     

高速飞行条件下CMC材料细观热响应特性

耐高温防热结构性能评估与设计是保障高速飞行器热安全的重要前提;精确预测真实飞行条件下防热结构非稳态热响应特性至关重要。以典型陶瓷基复合防热结构（CMC）为研究对象;分别基于有限体积法（FVM）和有限差分法（FDM）开展了飞行器前缘外流场计算以及对流辐射耦合条件下CMC材料代表单元体（REV）模型与等效模型热响应过程模拟;对比分析了瞬时气动热载荷条件下CMC材料非稳态热响应特性。研究表明:REV模型的热响应在流热耦合条件下反映出更为复杂的时空分布特性;在给定的高速飞行条件下;气动热载荷条件为150.34 kW/m²;相较于等效模型;其壁面最大温差可达21.78 K;且热流差极值延后温差极值2.39 s出现;结构内部温度分布与基体和纱线的空间分布及热物性强相关;沿厚度方向温度梯度呈逐渐衰减的“振荡”波形。相关研究结论可为飞行器热防护系统低冗余设计及热环境精确预测提供重要理论参考。     

高空飞行环境中液体运载火箭底部热环境研究

采用数值模拟和飞行测试验证相结合的方法对液体运载火箭高空对流/辐射耦合换热问题开展系统深入研究。基于燃气多组分输运Navier-Stokes方程、热辐射方程、Realizable k-ε两方程湍流模型,建立了高空含自由流的运载火箭燃气喷流流动模型。辐射模型采用离散坐标法(DOM),空间离散采用二阶迎风TVD格式,对多个典型飞行高度火箭底部热流进行大型并行计算,将数值结果与试验数据进行广泛对比,验证了计算模型的精度和有效性。数值研究表明,火箭底部辐射热流在刚起飞阶段达到最大值,随着飞行高度上升,辐射热流逐渐降低,火箭底部对流热流表现为先升高后降低的趋势,并在20 km高空达到峰值。本文的预测分析方法对液体运载火箭底部热防护设计具有重要的理论意义和工程应用价值。     

基于 DS算法的混胺燃料近红外光谱分析模型传递

对混胺燃料的近红外光谱分析模型的传递方法进行研究。采用 K/S(Kennard/Stone)算法选择转换集样品,采摘用直接校正(Direct Standardization,DS)算法对从仪器采集的光谱进行校正。通过光谱平均差异(ARMS)比较奇异值分解(Singular Value Decomposition,SVD)算法和偏最小二乘法(Partial Least Squares,PLS)对光谱校正的效果。当 PLS算法的最佳主因子数为 3时,DS-PLS算法的光谱校正率可达到 97.5%,优于 DS-SVD算法。混胺样品的分析模型经过 DS-PLS算法传递后,对从仪器的混胺样品各项指标的预测标准偏差(SEP)明显好于传递前,与主仪器预测效果接近,说明采用 K/S算法选择合适的转换集样品后,通过 DS-PLS模型传递算法可有效降低仪器间的光谱差异,实现近红外光谱分析模型在各台光谱仪之间共享。     

Cd1-xZnxS体系红外光谱及发射率特性

制备了Cd1-xZnxS三元系半导体材料。利用X射线衍射(XRD)对其结构进行了表征,结果表明实验所得样品均为纤锌矿结构。建立了Cd1-xZnxS混晶替位模型,根据所建模型和晶格振动理论,对Cd1-xZnxS红外光谱特性进行探讨。研究了Cd1-xZnxS三元系半导体材料红外发射率特性,Cd1-xZnxS在3~5μm波段的发射率远远低于8~14μm波段的发射率,这与材料的红外吸收机制和光谱特性有关;Cd1-xZnxS半导体材料的红外发射率随着烧结温度的提高而降低,这是由于温度升高,晶格畸变减小并逐渐趋近于完整晶格。     

基于蒙特卡罗法辐射传递系数的统计分析

文章基于蒙特卡罗方法定义了表面热辐射换热辐射传递系数的表达式,确定其概率分布和置信度水平并进行统计分析.推导封闭腔内辐射传递系数的相对和绝对误差公式,为求解辐射传递系数所需追踪射线数量提供参考依据.