辐射变色薄膜剂量计性能测试及加速器应用

本课题的目的是建立用于辐射加工高剂量水平吸收剂量测量的辐射变色薄膜剂量计。通过系统研究,批量制备了以尼龙为基材,副品红氰化物为染料的辐射变色薄膜剂量计。为了验证批制辐射变色薄膜剂量测量的可靠性,选择了国际上应用较广的FWT-60膜及丙氨酸薄膜剂量计与本实验室批制的辐射变色薄膜开展实验室内剂量比对,比对结果均在±4%内符合,归一化偏差En绝对值均小于1。通过在加速器上进一步应用实验表明批制辐射变色薄膜可用于电子束辐照参数测量。     

Relativistic electron fluxes and dose rate variations during April–May 2010 geomagnetic disturbances in the R3DR data on ISS

Space radiation has been monitored successfully using the Radiation Risks Radiometer-Dosimeter (R3D) installed at the ESA EXPOSE-R (R3DR) facility outside of the Russian Zvezda module of the International Space Station (ISS) between March 2009 and January 2011. R3DR is a Liulin type spectrometer–dosimeter with a single Si PIN detector 2 cm² of area and 0.3 mm thick. The R3DR instrument accumulated about 2 million measurements of the absorbed dose rate and flux of 10 s resolution. The total external and internal shielding before the detector of R3DR device is 0.41 g cm⁻². The calculated stopping energy of normally incident particles to the detector is 0.78 MeV for electrons and 15.8 MeV for protons. After the Coronal Mass Ejection (CME) at 09:54 UTC on 3 April 2010, a shock was observed at the ACE spacecraft at 0756 UTC on 5 April, which led to a sudden impulse on Earth at 08:26 UTC. Nevertheless, while the magnetic substorms on 5 and 6 of April were moderate; the second largest in history of GOES fluence of electrons with energy >2 MeV was measured. The R3DR data show a relatively small amount of relativistic electrons on 5 April. The maximum dose rate of 2323 μGy day⁻¹ was reached on 7 April; by 9 April, a dose of 6600 μGy was accumulated. By the end of the period on 7 May 2010 a total dose of 11,587 μGy was absorbed. Our data were compared with AE-8 MIN, CRESS and ESA-SEE1 models using SPENVIS and with similar observations on American, Japanese and Russian satellites.     

现场校准试验用便携式γ射线照射装置研制

固定式环境γ辐射剂量率监测仪表是承担环境连续监测任务的主要设备,这类仪表通常不便于拆卸和安装,而且送检周期较长（一周左右）,影响了连续监测点数据的连续性。为了固定式仪表的按期校准,结合蒙卡方法研制了便携式γ射线照射装置,利用PTW剂量计对辐射场进行标定,最后利用便携式照射装置对固定式环境γ辐射剂量率监测仪表进行现场校准实验。     

一种新颖的RFID多标签防碰撞算法

在标签运动较规律的无线射频识别(RFID, Radio Frequency Identification)系统中,读写器按照一般的算法不会优先读取即将离开可读范围的标签,而使系统出现较高的漏读率.针对这种场景,提出一种新的防碰撞算法——先到先服务 (FCFS, First Come First Served) 算法.读写器首先按照到达顺序对标签进行分组,先识别紧迫性高的时间分组标签;其次,算法通过新增一个参数有效避免了一些可预测的碰撞时隙.在识别时间分组的过程中设置了总时隙的上限,从而避免系统阻塞.仿真结果表明,在保持漏读率小于0.01的情况下,系统所能承受的标签运动速度比前缀随机化算法提高了50%.当标签到达率为0.45时,系统的通过率改善最明显,比前缀随机化算法提高了13%左右.      

The dose rate observed on 19-21 October 1989 and its modulation by geophysical effects.

The Liulin dosimeter-radiometer on the MIR space station detected the 19 October 1989 high energy solar proton event. These results show that the main particle increase contains protons with energies up to about 9 GeV. After the main particle onset the Liulin dosimeter observed a typical geomagnetic cutoff modulation of the dose rate from the solar particles as the MIR space station traversed magnetic latitudes. When the interplanetary shock and associated solar plasma enveloped the earth on 20 October between 14 and 17 UT the radiation exposure increased significantly due to the lowering of the geomagnetic cutoff. The analysis of this event shows how various geophysical phenomena can significantly modulate the dose rate encountered by earth-orbiting spacecraft.     

Repair of DNA double-strand breaks and cell killing by charged particles.

It has been suggested that it is not simple double-strand breaks (dsb) but the non-reparable breaks which correlate well with the high biological effectiveness of high LET radiations for cell killing (Kelland et al., 1988; Radford, 1986). We have compared the effects of charged particles on cell death in 3 pairs of cell lines which are normal or defective in the repair of DNA dsbs. For the cell lines SL3-147, M10, and SX10 which are deficient in DNA dsb repair, RBE values were close to unity for cell killing induced by charged particles with linear energy transfer (LET) up to 200 keV/micrometer and were even smaller than unity for the LET region greater than 300 keV/micrometer. The inactivation cross section (ICS) increased with LET for all 3 pairs. The ICS of dsb repair deficient mutants was always larger than that of their parents for all the LET ranges, but with increasing LET the difference in ICS between the mutant and its parent became smaller. Since a small difference in ICS remained at LET of about 300 keV/micrometer, dsb repair may still take place at this high LET, even if its role is apparently small. These results suggest that the DNA repair system does not play a major role in protection against the attack of high LET radiations and that a main muse of cell death is non-reparable dsb which are produced at a higher yield compared with low LET radiations. No correlation was observed between DNA content or nuclear area and ICS.     

Peculiarities of the solar proton events of 19 October 1989 and 23 March 1991 according to the measurements onboard the Mir space station.

Flux and dose rate dynamics of solar cosmic rays were measured by the Lyulin dosimeter during the events 19 October 1989 and 23 March 1991. The maximum dose rate registered was 0.4, 0.12 and 0.01 cGy/hour, respectively. Based on the latitude distribution of particle flux a power law form for the energy spectra of solar protons in the anisotropic phase of the events on 19 October 1989 and 23 March 1991 was determined. It was obtained that after the development of geomagnetic storm protons with energies more than 1 GeV were registered.     

China's Deep-space Exploration to 2030

Focusing on the key scientific questions of deep space exploration which include the origin and evolution of the solar system and its planets, disastrous impact on the Earth by the solar activities and small bodies, extraterrestrial life, this paper put forward a propose about the roadmap and scientific objectives of China's Deep-space Exploration before 2030.     

The magnetic fields of Jupiter and Saturn

Jupiter and Saturn are two of the more “exotic” planets in our solar system. The former possesses its own system with 15 satellites in orbit about the parent planet. Saturn has a uniquely well developed and distinctive ring system of particulate matter and also at least 11 satellites, including the largest one amongst all the planets, Titan, with a radius of 2900 km ± 100 km. In the decade of the 70's, the USA launched 4 unmanned spacecraft to probe these giant planets in-situ with a suite of highly advanced instrumentation. Four separate encounters have occurred at Jupiter: 1. Pioneer 10 in December 1973 2. Pioner 11 in December 1974 3. Voyager 1 in March 1979 4. Voyager 2 in July 1979 The characteristics of these trajectories is shown in Table I. Thus far, only a single encounter of Saturn has occurred, that by Pioneer 11 in September 1979. Future encounters of Saturn by Voyager spacecraft will occur in mid-November 1980 and late-August 1981. It is the purpose of this talk to summarize what is presently known about the magnetic fields of these planets and the characteristics of their magnetospheres, which are formed by interaction with the solar wind.     

Landforms of Europa and selection of landing sites

Three major features make Europa a unique scientific target for a lander-oriented interplanetary mission: (1) the knowledge of the composition of the surface of Europa is limited to interpretations of the spectral data, (2) a lander could provide unique new information about outer parts of the solar system, and (3) Europa may have a subsurface ocean that potentially may harbor life, the traces of which may occur on the surface and could be sampled directly by a lander. These characteristics of Europa bring the requirement of safe landing to the highest priority level because any successful landing on the surface of this moon will yield scientific results of fundamental importance. The safety requirements include four major components. (1) A landing site should preferentially be on the anti-Jovian hemisphere of Europa in order to facilitate the orbital maneuvers of the spacecraft. (2) A landing site should be on the leading hemisphere of Europa in order to extend the lifetime of a lander and sample pristine material of the planet. (3) Images with the highest possible resolution must be available for the selection of landing sites. (4) The terrain for landing must have morphology (relief) that minimizes the risk of landing and represents a target that is important from a scientific point of view. These components severely restrict the selection of regions for landing on the surface of Europa. After the photogeologic analysis of all Galileo images with a resolution of better than about 70 m/pixel taken for the leading hemisphere of Europa, we propose one primary and two secondary (backup) landing sites. The primary site (51.8°S, 177.2°W) is within a pull-apart zone affected by a small chaos. The first backup site (68.1°S, 196.7°W) is also inside of a pull-apart zone and is covered by images of the lower resolution (51.4 m/pixel). The second backup site (2.4°N, 181.1°W) is imaged by relatively low-resolution images (∼70 m/pixel) and corresponds to a cluster of small patches of dark and probably smooth plains that may represent landing targets of the highest scientific priority from the scientific point of view. The lack of the high-resolution images for this region prevents, however, its selection as the primary landing target.     

Initial accuracy and reliability of current BDS-3 precise positioning,velocity estimation,and time transfer (PVT)

The primary system of Chinese global BeiDou satellite system (BDS-3) was completed to provide global services on December 27, 2018; this was a key milestone in the development process for BDS in terms of its provision of global services. Therefore, this study analyzed the current performance of BDS-3, including its precise positioning, velocity estimation, and time transfer (PVT). The datasets were derived from international GNSS monitoring and assessment system (iGMAS) tracking networks and the two international time laboratories in collaboration with the International Bureau of Weights and Measures (BIPM). With respect to the positioning, the focus is on the real-time kinematic (RTK) positioning and precise point positioning (PPP) modes with static and kinematic scenarios. The results show that the mean available satellite number is 4.8 for current BDS-3 system at short baseline XIA1–XIA3. The RTK accuracy for three components is generally within cm level; the 3D mean accuracy is 8.9 mm for BDS-3 solutions. For the PPP scenarios, the convergence time is about 4 h for TP01 and BRCH stations in two scenarios. After the convergence, the horizontal positioning accuracy is better than cm level and the vertical accuracy nearly reaches the 1 dm level. With respect to kinematic scenarios, the accuracy stays at the cm level for horizontal components and dm level for the vertical component at two stations. In terms of velocity estimation, the horizontal accuracy stays at a sub-mm level, and the vertical accuracy is better than 2 mm/s in the BDS-3 scenario, even in the Arctic. In terms of time and frequency transfer, the noise level of BDS-3 time links can reach 0.096 ns for long-distances link NT01–TP02 and 0.016 ns for short-distance links TP01–TP02. Frequency stability reaches 5E–14 accuracy when the averaging time is within 10,000 s for NT01–TP02 and 1E–15 for TP01–TP02.     

基于注意力机制和改进YOLOv3的红外弱小目标检测

红外弱小目标检测技术是红外探测系统的核心技术之一。针对远距离复杂场景下红外弱小目标对比度低、信噪比低和纹理特征稀疏分散导致目标检测率低的问题,提出一种融合注意力机制和改进YOLOv3的红外弱小目标检测算法。首先,在YOLOv3的基础上,用更大尺度的检测头替换最小尺度的检测头,在保证推理速度的基础上有效提升了红外图像中小目标的检测概率。然后,在检测头之前设计了Infrared Attention模块,通过通道间的信息交互,抽取出更加关键重要的信息供网络学习。最后,用完全交并比损失(Complete IoU Loss)替代交并比损失(Intersection over Union Loss)来衡量预测框的检测能力,通过梯度回传实现更好的模型训练。实验结果表明,提出的YOLOv3-DCA能完成多种场景下红外弱小目标的检测任务,且检测准确率、召回率、F1和平均准确率分别达到91.8%、88.8%、93.0%和88.8%,平均准确率比YOLOv3基线提升约7%,与主流的SSD、CenterNet和YOLOv4模型对比平均准确率也取得了目前最优。     

The VESTA project: Combined studies of Mars and small bodies of the solar system

A mission to Mars and small solar system bodies is presently studied as a possible collaboration between INTERCOSMOS, CNES, ESA and eventually other participants. The VESTA concept, based on the same strategy as the successful VEGA mission, is more ambitious, as two spacecrafts separate soon after launch: a soviet spacecraft, dedicated to the study of Mars, and a spacecraft dedicated to the study of small bodies, under the responsibility of CNES and ESA. This spacecraft would use Mars gravity assists to visit up to 4 small bodies in less than 5 years. The mission is duplicated, which means that up to 8 small bodies could be studied (e.g. 6 main belt asteroids, 1 apollo-amor asteroid and 1 short period comet). Low relative velocities (< 3.5 km/s) should allow to drop a penetrator on two large main belt asteroids, such as 4 Vesta and 1 Ceres (1994 launch).     

ALTEA: anomalous long term effects in astronauts. A probe on the influence of cosmic radiation and microgravity on the central nervous system during long flights.

The ALTEA project participates to the quest for increasing the safety of manned space flights. It addresses the problems related to possible functional damage to neural cells and circuits due to particle radiation in space environment. Specifically it aims at studying the functionality of the astronauts' Central Nervous Systems (CNS) during long space flights and relating it to the peculiar environments in space, with a particular focus on the particle flux impinging in the head. The project is a large international and multidisciplinary collaboration. Competences in particle physics, neurophysiology, psychophysiology, electronics, space environment, data analyses will work together to construct the fully integrated vision electrophysiology and particle analyser system which is the core device of the project: an helmet-shaped multi-sensor device that will measure concurrently the dynamics of the functional status of the visual system and passage of each particle through the brain within a pre-determined energy window. ALTEA is scheduled to fly in the International Space Station in late 2002. One part of the multi-sensor device, one of the advanced silicon telescopes, will be launched in the ISS in early 2002 and serve as test for the final device and as discriminating dosimeter for the particle fluences within the ISS.     

Determining CME parameters by fitting heliospheric observations: Numerical investigation of the accuracy of the methods

Transients in the heliosphere, including coronal mass ejections (CMEs) and corotating interaction regions can be imaged to large heliocentric distances by heliospheric imagers (HIs), such as the HIs onboard STEREO and SMEI onboard Coriolis. These observations can be analyzed using different techniques to derive the CME speed and direction. In this paper, we use a three-dimensional (3-D) magneto-hydrodynamic (MHD) numerical simulation to investigate one of these methods, the fitting method of  and . Because we use a 3-D simulation, we can determine with great accuracy the CME initial speed, its speed at 1 AU and its average transit speed as well as its size and direction of propagation. We are able to compare the results of the fitting method with the values from the simulation for different viewing angles between the CME direction of propagation and the Sun-spacecraft line. We focus on one simulation of a wide (120–140°) CME, whose initial speed is about 800 km s⁻¹. For this case, we find that the best-fit speed is in good agreement with the speed of the CME at 1 AU, and this, independently of the viewing angle. The fitted direction of propagation is not in good agreement with the viewing angle in the simulation, although smaller viewing angles result in smaller fitted directions. This is due to the extremely wide nature of the ejection. A new fitting method, proposed to take into account the CME width, results in better agreement between fitted and actual directions for directions close to the Sun–Earth line. For other directions, it gives results comparable to the fitting method of Sheeley et al. (1999). The CME deceleration has only a small effect on the fitted direction, resulting in fitted values about 1–4° higher than the actual values.     

振动状态下频率源特性测试技术研究

阐述了频率稳定性时频域表征的理论和测试方法,以及在振动条件下测量频率稳定性的意义,详细介绍了测量系统的组建方案及工作原理.最后提供了部分测试数据及测试曲线,并对测试系统的经济效益和社会效益进行了简单分析.该测试系统具有噪底低,体积小,便于携带,操作简便等特点,其综合技术指标达到国内领先水平,不仅适用于振动状态下的频率源特性测试,而且完全可以作为通用测试系统用于实验室、工厂等.     

大气中子感生的γ射线本底

大气中子同探测器物质相互作用产生的γ射线,往往成为一些X、γ射线探测器本底计数的重要组成部分。如何减少这部分本底的强度以增加探测器的观测灵敏度,是空间天文实测工作中一个重要课题。本文介绍一个附有中子屏蔽物质的小型背附探测器系统及其在气球上的飞行观测结果。结果表明,3cm厚的纯石蜡屏蔽层不仅不能减少本底,而且可能有相反的效果。      

一种三维激光扫描系统的设计及参数标定

基于三维激光扫描系统的移动机器人动态环境地图构建技术是机器人智能感知技术的重要组成部分,而三维激光扫描系统的设计及标定技术对于地图构建的精度有决定性的影响。针对应用于小型移动机器人的三维激光扫描系统低成本、小型化的需求,设计了一套由高精度旋转云台和小型二维激光测距传感器组成的三维激光扫描系统,并提出了一种新的系统参数标定方法以提高三维扫描测量的准确度。该方法使用镂空圆孔标定板作为标定对象以完成对三维扫描特征自动准确获取,并根据非线性最小二乘法对三维激光扫描系统的参数进行优化计算。实验结果表明,所设计的三维激光扫描系统能够准确地测量周围环境的三维信息,实现了以低成本获得高质量环境建模的三维扫描数据技术。      

Biologically weighted measurement of UV radiation in space and on Earth with the biofilm technique.

Biological dosimetry has provided experimental proof of the high sensitivity of the biologically effective UVB doses to changes in atmospheric ozone and has thereby confirmed the predictions from model calculations. The biological UV dosimeter 'biofilm' whose sensitivity is based on dried spores of B. subtilis as UV target weights the incident UV radiation according to its DNA damaging potential. Biofilm dosimetry was applicated in space experiments as well as in use in remote areas on Earth. Examples are long-term UV measurements in Antarctica, measurements of diurnal UV profiles parallel in time at different locations in Europe, continuous UV measurements in the frame of the German UV measurement network and personal UV dosimetry. In space biofilms were used to determine the biological efficiency of the extraterrestrial solar UV, to simulate the effects of decreasing ozone concentrations and to determine the interaction of UVB and vitamin D production of cosmonauts in the MIR station.